N821BX

Part: SWITCH — OUT OF ADJUST (MLG DOOR) · airframe 91,169 hrs · 39,309 cycles

DURING CLIMBOUT,THE GEAR DOOR NOT LATCH LIGHT CAME ON. THE CREW CYCLED THE GEARS AND THE LIGHT REMAINED ON. THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX ADJUSTED THE STRIKER SWITCH AND LUBED BOTH DOOR UPLATCH MECHANISMS. OPS CHECK GOOD IAW UAL MM 32-31-15 STEP 22-25 AND 32-60-02. ACFT WAS RETURNED TO SERVICE.

Part: UPLOCK — OUT OF ADJUST (MLG) · airframe 91,169 hrs · 39,310 cycles

DURING CLIMBOUT, WHILE THE CREW PERFORMING CLIMB CHECK LIST, THE UP LATCH CHECK FAILED WITH RED DOOR LIGHT ON. THEY CYCLED THE GEARS WITH NO HELP. THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX DEFERRED THE UPLATCH SYS IAW MEL 32-14-01 TO BE ACCOMPLISHED IN DESTINATION. MX ADJUSTED THE LT UPLATCH MECHANISM. OPS CHECK GOOD IAW MM 32-31-4, 32-30-0.

Part: PIN — BROKEN (MLG RETRACT) · airframe 90,879 hrs · 39,120 cycles

AFTER TAKEOFF LANDING GEAR UNSAFE LIGHT CAME ON, THE CREW CYCLED GEAR LIGHT WENT OUT. ONE HR INTO FLIGHT DOOR NOT LATCH LIGHT CAME ON THEN WENT OUT, THE LANDING GEAR UNSAFE LIGHT REMAINED ON DURING FLIGHT. UPON GEAR EXTENSION, A LOUD BANG WAS HEARD, GOT (3) GREEN LIGHTS. THE CREW LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED LANDING GEARS AND FOUND LEFT MAIN LANDING GEAR RETRACT PIN BROKEN. THEY REPLACED THE LEFT MAIN LANDING GEAR STRUT ASSY. OPERATIONAL CHECK GOOD IAW UAL MAINTENANCE MANUAL 32-11-03. AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATOR — DEFECTIVE (AIRSPEED) · airframe 90,289 hrs · 38,796 cycles

DURING TAKEOFF, THE CAPT'S AIRSPEED INDICATOR HAD NO INDICATION. CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS. MX REPLACED CAPT'S AIRSPEED INDICATOR. OPS CHECK GOOD IAW UAL MM 30-30-04. ACFT WAS RETURNED TO SERVICE.

Part: TRANSDUCER — DEFECTIVE (ZONE 300) · airframe 89,924 hrs · 38,560 cycles

DURING CRUISE, AN UNCOMMANDED RUDDER KICK WITH NO MOVEMENT OF PEDALS. THE CREW DIVERTED TO KDFW AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE DEFERRED THE AUTOPILOT SYSTEM. MAINTENANCE IN KTOL REPLACED THE LINEAR POSITION TRANSDUCER. OPERATIONAL CHECK GOOD IAW UAL 27-24-24. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ACCESS PANEL — MISINSTALLED (COCKPIT) · airframe 89,259 hrs · 38,252 cycles

DURING CLIMB-OUT FROM KBDL, THE CREW HEARD LOUD NOISE OF AIR FROM CAPT'S SIDE. THE CREW RETURNED TO KBDL WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND EMERGENCY ACCESS PANEL TO CAPT CLEARVIEW WINDOW HAD COME OUT AND FELL DOWN INTO FUSELAGE. MAINTENANCE REINSTALLED PANEL IAW DACO DC8 MAINTENANCE MANUAL 6-11-1.

Part: ENGINE — FLAMED OUT (NR 3) · airframe 89,254 hrs · 38,245 cycles

AFTER LEVEL OFF AT 37,000 FT DURING THROTTLE REDUCTION NUMBER THREE ENGINE FLAMED OUT. THE CREW PERFORMED INFLIGHT START AT 22,000 FT, RESTART NORMAL. THE CREW LANDED IN KTOL WITHOUT FURTHER INCIDENT. MAINTENANCE PERFORMED CFM FAULT 51, TROUBLESHOT TREE, CLEANED WEEP HOLE ON CDP TUBE, CHECKED CHIP DETECTOR, SPECIFIC GRAVITY .82, FLIGHT IDLE 74 N2-FF 6000PPH AT 75 PERCENT N1. EGT 683, FUEL PRESSURE 31PSI PUMP OFF. OPERATIONAL CHECK GOOD IAW CFM MAINTENANCE MANUAL 71-00-00. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONNECTOR — CONTAMINATED (FIRE DETECTION) · airframe 89,014 hrs · 38,110 cycles

FLT NR: ATN 807/KBRI TO KMSP. DURING CRUISE FROM KBFI THE NR 1 ENGINE FIRE WARNING LIGHT AND BELL CAME ON. THE FIRE WARNING LIGHT WENT OUT AND THE BELL STOPPED RINGING. THE CREW SUCCESSFULLY TESTED THE SYSTEM AND PERFORMED A PRECAUTIONARY ENGINE SHUTDOWN, AFTER AN ADDITIONAL HOUR OF FLT TIME THE FIRE WARNING LIGHT ILLUMINATED AND THE BELL SOUNDED, THE CREW DISCHARGED BOTH FIRE BOTTLES. THE ACFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED NR 1 ENGINE FIRE WARNING SYSTEM AND FOUND A WET ELEMENT CONNECTOR, MAINTENANCE CLEANED AND DRIED CONNECTOR AND REPLACED BOTH BOTTLES. OPERATIONAL CHECK GOOD IAW W/D 26-01-01, MM 26-21-09. AIRCRAFT WAS RETURNED TO SERVICE. (A)

Part: FIRE WARNING — FALSE ACTIVATION

DURING CRUISE, THE NR 1 ENGINE FIRE WARNING LIGHT AND BELL CAME ON. THE FIRE WARNING LIGHT WENT OUT AND THE BELL STOPPED RINGING. THE CREW TESTED THE SUCCESSFULLY TESTED THE SYSTEM AND PERFORMED A PRECAUTIONARY ENGINE SHUTDOWN, AFTER ONE HOUR MORE OF FLIGHT TIME THE FIRE WARNING LIGHT ILLUMINATED AND THE BELL SOUNDED, THE CREW DISCHARGED BOTH FIRE BOTTLES. THE AIRCRAFT LANDED WITHOUT INCIDENT. (K)

Part: TRANSDUCER — DEFECTIVE (SPEED COMMAND)

DURING CLIMB OUT, AT 240 KIAS WITH A 9 DEGREE PITCH NOSE UP STICK SHAKER CAME ON STEADY. IT CYCLED ON AND OFF RANDOMLY FOR 15 MINUTES UNTIL LANDING. STALL WARNING TEST SWITCH WAS TOGGLED WITH NO EFFECT. THE CREW LANDED WITH NO FURTHER INCIDENT. MAINTENANCE REPLACED LIFT SPEED COMMAND TRANSDUCER. OPS CHECK GOOD IAW MM 34-16-0. AC WAS RETURNED TO SERVICE. (K)

Part: SKIN — DENTED (ZONE 500) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HAND INBOARD FLAP UPPER SKIN HAS DENTS BETWEEN STATION XW 104.000 TO STATION XW 115.000.REMOVED FASTNERS AS NEEDED TO PERFORM REPAIR.REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, AND BONDED DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTNERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 ITEM "A" AND "L", DC8 SRM 57-1-0 PAGE 1, 51-1-21, DC8 SRM 51-1-9 TR NUMBER 51-142, 51-1-9A TR NUMBER 51-141, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.

Part: FITTING — CRACKED (BS 798 L20R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT CUSP EXTRUSION UPPER SURFACE AFT FITTING WITH CRACK AT STATION 798.000 LONGERON 20 RIGHT. REMOVED AFT CRACKED FITTING. FABRICATED FITIING. PERFORMED NDT INSPECTION. CLEANED TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-3-1, SRM 51-1-20D, DACO DPS 4.707, DC8 SRM 51-1-8B, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779874.

Part: FITTING — CRACKED (ZONE 200) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT CUSP EXTRUSION UPPER SURFACE FORWARD FITTING CRACKED AT STATION 742.250 LONGERON 19 LEFT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, AND DC8 SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXTERIOR FUSELAGE SKIN HAS CORROSION AT STATION FS 505.000 LONGERON 33 RIGHT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS, SRM 51-1-8B. ORIGINALS DOCUMENTS ENTERED ON N/R NR100296 IAW FAA FORM 8100-9 DATED 05-22-08, AD 2005-18-0-7, S/B DC8-53-078, DRAWING SR08530019 AND 5750776, MESSAGE 1-821382564-7 DATED 05-09-08, ND 1-842846685-2 DATED 05-22-08, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 51-3-0, 51-1-21, 51-1-20D, REPAIR SKETCH 1-821382564, ED-SEMAN 4757, NDT SPM PART 06-10-01-001, AND SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD AILERON UPPER SKIN HAS IMPROPER REPAIR AT STATION XA 542.000 - 603.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, BONDED DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. PERFORMED WEIGHT AND BALANCE. FOUND WITHIN TOLERANCE MOMENT= 3320 INCH-POUNDS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-8-1 FIGURE 1 ITEM "B" AND "K", DRAWING 5705334, SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, SRM 51-1-8B, AND SRM 51-4-1 PAGES 1-3.

Part: CARGO TRACK — DETERIORATED (CARGO BAY) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT NUMBER 5 TRACK LUGS DETERIORATED BETWEEN STATION 70.000 AND STATION 210.000. REMOVED DAMAGED SEGMENT OF TRACK AND EXISTING SPLICES. CLEANED, TREATED AND PRIMED AREA AND EXISTING SPLICES. INSTALLED NEW SEGMENT OF TRACK AND REINSTALLED SPLICES IAW DC8 SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, DC8 SRM 51-3-0, DC8 SRM 51-1-8B, 51-1-20D, AND 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1731 LONGERON 35.5 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, FILLER, FINGER DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08197 DATED 04/25/08, SEMAN DRAWING ED-4775 DATED 04/22/08, SRM 51-1-21, 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, AND 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1694 LONGERON 27 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION FOUND. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8100-9 DATED 05-09-08, AD 2007-02-02, SB DC8-53A080 DATED 06-22-04, DRAWING SR08530032, MESSAGE 1-819144906-11 DATED 05/07/08, 1-819144906-13 DATED 05-05-08, AND DRAWING ED-4754 DATED 05-10-08.

Part: FITTING — CRACKED (BS 940 L20L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT CUSP EXTRUSION UPPER SURFACE FORWARD FITTING CRACKED AT STATION 940.000 LONGERON 20 LEFT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DPS 4.707, DC8 SRM 51-1-8B, 51-3-1, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779874.

Part: FITTING — CRACKED (BS 717 L19L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT CUSP EXTRUSION UPPER SURFACE AFT FITTING CRACKED AT STATION 717.750 LONGERON 19 LEFT. REMOVED CRACKED FITTING. FABRICATED FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED TREATED AND PRIMED FITTING AND AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DACO DPS 4.707, DC8 SRM 51-1-8B, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779978.

Part: FITTING — CRACKED (BS 940 L20L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT CUSP EXTRUSION UPPER SURFACE AFT FITTING CRACKED AT STATION 940.000 LONGERON 20 LEFT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DPS 4.707, DC8 SRM 51-1-8B, 51-3-1, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779874.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT OUTBOARD FLAP TRAILING EDGE LOWER SKIN IMPROPER REPAIR AT STATION XF 370.000 - 404.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, AND DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-02, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIGURE 4 TR 57-94 ITEM U AND Q, SRM 51-1-9 TR 51-1-42, SRM 51-1-9A TR 51-1-41, SRM 51-1-8B, AND SRM 51-1-11.

Part: CARGO TRACK — DETERIORATED (BS 70-340) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT NUMBER 4 TRACK LUGS DETERIORATED AT STATION 70.000 TO 340.000. REMOVED SEGMENT OF DAMAGED TRACK AND EXISTING SPLICES. CLEANED, TREATED AND PRIMED AREA AND EXISTING SPLICES. INSTALLED NEW SEGMENT OF TRACK AND REINSTALLED SPLICES IAW DC8 SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, DC8 SRM 53-1-0 PAGE 1, 51-3-0, DC8 SRM 51-1-8B, 51-3-0, AND 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING CENTER LOWER LEADING EDGE HAS IMPROPER REPAIR AT STATION XFS 360.250. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, 51-3-1, DC8 SRM 51-1-21, 51-1-20D, 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, FAA FORM 8110-3 NUMBER 08198 DATED 04-25-08, AND SEMAN DRAWING NUMBER ED-4773 DATED 04-22-08.

Part: SKIN — MISREPAIRED (LT WING) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING NR 1 LOWER PART STUB WING HAS IMPROPER REPAIR REMOVED FASTENERS AS NEEDED TP PERFORM REPAIR. REMOVED EXITING REPAIR. FABRICATED EXTERNAL DOUBLER, AND INTERNAL DOUBLER. PERFORMED HEAT TREATMENT. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-2-1A FIGURE 1, DC8 SRM 51-1-20D, DC8 SRM 51-1-1 PAGES 1 13 AND 17, DC8 SRM 51-1-8B, 51-1-11, 51-1-21, AND 51-3-1.

Part: FITTING — CRACKED (BS 290 L19R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT UPPER SURFACE OF CUSP EXTRUSION FWD FITTING CRACKED AT STATION 920.000 LONGERON 19 RIGHT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DPS 4.707, DC8 SRM 51-1-8B, 51-3-1, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779874.

Part: FITTING — CRACKED (BS 960 L19R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT UPPER SURFACE OF CUSP EXTRUSION FT FITTING WITH CRACK AT STATION 960.000 LONGERON 19 RIGHT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-3-1 DC8 SRM 51-1-20D, DPS 4.707, DC8 SRM 51-1-8B, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779874.

Part: SKIN — MISREPAIRED (LT WING) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT AND RIGHT INNER WING TRAILING EDGE STRUCTURE HAS IMPROPER REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. INSTALLED REPAIR PART KIT ON LT AND RT INNER WING TRAILING EDGE STRUCTURE. CLOSED MLG DOORS AND RAISED FLAPS IAW AD 90-16-05, DACO SB 57-58 DATED 01-19-08, DOUGLAS DRAWING 5758978, 5643410, DC8 SRM 51-1-21, 51-1-20D, DACO SRM 51-1-11, 51-1-21, 51-1-20D, AND 51-3-1, DC8 MM 27-27-1, AND 32-1-4.

Part: FITTING — CRACKED (BS 798 L20L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION; FOUND LEFT CUSP EXTRUSION UPPER SURFACE FORWARD FITTING CRACKED AT STATION 798.000 LONGERON 20 LEFT. REMOVED CRACKED FITTING. FABRICATED FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED TREATED AND PRIMED FITTING AND AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DACO DPS 4.707, DC8 SRM 51-1-8B, ATI REPAIR SPECIFICATION NUMBER 2003-05, DOUGLAS DRAWING 3779970.

Part: FRAME — CRACKED (BS 1580) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FRAME FLANGE CRACKED AT STATION 1580.000 LONGERON 20 LEFT TO LONGERON 21 LEFT. REMOVED DAMAGED SEGMENT OF FRAME. FABRICATED SEGMENT OF FRAME, ANGLES. PERFORMED HEAT TREATMENT TO REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-0 FIGURE 2 SHEETS 1, 4 AND 6, SRM 53-4-1 FIGURE 51 ITEM "A", 53-2-0 FIGURE 2 SHEET 7, 8 TR NUMBER 53-110 DATED 11-10-00, 53-2-0 FIGURE 2 SHEET 5 TR NUMBER 53-125 DATED 08-31-01, SRM 51-1-1 PAGES 1, 13 AND 17, SRM 51-1-8B, SRM 51-1-20, AND 51-3-1.

Part: FITTING — CRACKED (BS 781 L18L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION; FOUND LEFT HAND CUSP EXTRUSION UPPER SURFACE FORWARD FITTING CRACKED AT STATION 781.500 LONGERON 18LEFT.REMOVED CRACKED FITTING.FABRICATED FITTING.PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND.CLEANED TREATED AND PRIMED FITTING AND AREA.INSTALLED NEW FITTING IAW DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DACO DPS 4.707, DC8 SRM 51-1-8B, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND DOUGLAS DRAWING 3779978.

Part: FITTING — CRACKED (ZONE 200) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT UPPER SURFACE OF CUSP EXTRUSION AFT FITTING CRACKED AT STATION 702.875 LONGERON 19 RIGHT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED TREATED AND PRIMED FITTING AND AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, REPAIR SPECIFICATION NUMBER 2003-05 DRAWING 3779874, DPS 4.707, SRM 51-1-8B, AND 51-3-1.

Part: SKIN — CRACKED (ZONE 500) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP LOWER SKIN CRACKED BETWEEN STATION XF 375.000 - 404.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN FABRICATED NEW SKIN, DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-2002, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIGURE 4 TR 57-94 ITEM "U" AND "Q", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, SRM 51-1-8B, AND SRM 51-1-11.

Part: SKIN — CANNING (ZONE 300) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT RUDDER SKIN OIL CANNING AT STATION ZR 168.656. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, BONDED DOUBLER. BONDED BOTH PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. PERFORMED BALANCE. FOUND WITHIN TOLERANCE, MOMENT=2549.7 INCH/POUNDS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 55-6-1 FIGURE 1, SRM 55-1-0 PAGE 1 AND 51-1-21, SRM 55-6-1 FIGURE 1 ITEM "A", SRM 51-1-9 T/R NUMBER 51-142, 51-1-9A T/R NUMBER 51-141, 51-1-8B, SRM 51-1-11, 51-1-21, AND SRM 51-4-5 PAGES 1-5.

Part: FITTING — CRACKED (ZONE 500) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT WING TRAILING EDGE FITTING CRACKED BETWEEN STATION XRS 337.000 TO XRS 351.000. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION. NO CRACK AND NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, ATI REPAIR SPECIFICATION NUMBER 2003-05, ED-SEMAN 4785, DACO DPS 4.707, DC8 SRM 51-1-8B, AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (BS 940 L24R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT MAIN LANDING GEAR WHEEL WELL FITTING CRACKED AT STATION 940.000 LONGERON 24. REMOVED CRACKED FRAME FITTING. FABRICATED SPLICES, DOUBLER, FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FITTING AND REPAIR PARTS IAW DC8 SRM 53-2-0 FIGURE 8 SHEETS 1, 2, 5 AND 6, DC8 SRM 53-1-0 PAGE 1, 51-1-20D, DC8 AND SRM 51-1-8B.

Part: SKIN — CRACKED (ZONE 600) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING UPPER SKIN CRACKED AT STATION XRS 74.000, STRINGER 7. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED NEW SKIN, AND FILLER. TAPERED BOTH SIDE OF DOUBLER. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08188 DATED 04-23-08, SEMAN DRAWING NUMBER ED-4769 DATE 04-22-08, DC8 SRM 51-1-20D, 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-10-0, FIGURE 1 PAGE 20, DC8 SRM 51-1-12, DC8 SRM 51-1-11, 51-1-21, AND 51-3-1.

Part: SKIN — WORN (LT WING TE FLAP) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION; FOUND LEFT INBOARD FLAP UPPER SKIN WORN AT STATION XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 ITEM "D", DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.

Part: SKIN — MISREPAIRED (BS 118 L27R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR LOCATED AT STATION FS 118 LONGERON 27 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1 AND 4, DC8 SRM 51-9-0 FIGURE 68A, DC8 SRM 53-4-1 FIGURE 1 ITEM D, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 45.000 LONGERON 29LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-0 FIGURE 13 SHEET 1 TR NUMBER 53-169 SHEET 5 DATED 09-20-03, SRM 51-1-20D, SRM 53-2-0 FIGURE 13 SHEET 1 VIEW A (7001) ITEM 1, SRM 53-3-1 FIGURE 1 ITEM C, SRM 51-1-8B, SRM 51-1-11, 51-1-21, 51-1-20D AND 51-3-1.

Part: SKIN — MISREPAIRED (BS 400 L29R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR LOCATED AT STATION FS 400 LONGERON 29 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED EXTERNAL REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIRS PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEETS 1 AND 4, 51-9-0 FIGURE 68A, 53-4-1 FIGURE 1 ITEM "B", 51-1-11, 51-3-1, DC8 SRM 51-1-21, 51-1-20D, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT OUTBOARD FLAP LOWER SKIN IMPROPER REPAIR AT STATION XF 375.000 - STATION XF 404.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10-01-2002, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIGURE 4 TR 57-94 ITEM "U" AND "Q", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-1-41, SRM 51-1-8B, AND SRM 51-1-11.

Part: SKIN — MISREPAIRED (BS 260 L22R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR LOCATED AT STATION FS 260 LONGERON 22.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEETS 1, 4 AND 5, 51-9-0 FIGURE 68A, 53-4-1 FIGURE 1 ITEM B, 51-1-11, 51-3-1, DC8 SRM 51-1-21, 51-1-20D, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (BS 310 L22L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR LOCATED AT STATION FS 310 LONGERON 22 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXITING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEETS 1 AND 5, 51-9-0 FIGURE 68A, 53-4-1 FIGURE ITEM "B", 51-1-11, 51-3-1, DC8 SRM 51-1-21, 51-1-20D, AND DC8 SRM 51-1-8B.

Part: DOOR FRAME — WORN (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND "B" CARGO DOOR FORWARD LOWER JAMB CORNER SKIN WORN AT STATION 520.000 LONGERON 30 RIGHT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, FILLERS, CLEANED. TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8100-9 DATED 05-22-08, AD 2005-18-0-7 S/B DC8-53-078, DRAWING SR08530019, 5750776, MESSAGE 1-821382564-7 DATED 05-09-08 ND 1-842846685-2 DATED 05-22-08, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 51-3-0, 51-1-21, 51-1-20D, REPAIR SKETCH 1-821382564, NDT SPM PART 06-10-01-001, AND SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1755 LONGERON 35.5 RT. 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, FILLER, FINGER DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08197 DATED 04/25/08, SEMAN DRAWING ED-4775 DATED 04/22/08, SRM 51-1-21, 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, AND 51-3-1.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING INBOARD FLAP UPPER SKIN DENTED AT STATION XW 104.000 TO 115.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN, 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 51-1-11, 51-1-21, DC8 SRM 57-7-1 FIGURE 1 ITEM "A" AND "L", DC8 SRM 57-1-0 PAGE 1, 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-9 TR NUMBER 51-142, AND 51-1-9A TR NUMBER 51-141.

Part: SKIN — CRACKED (ZONE 500) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING CENTER LEADING EDGE LOWER SKIN CRACKED AT STATION XFS 335.000 - XFS 341.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08244 DATED 05/08/08, SEMAN DRAWING NUMBER ED-4767 DATED 04/25/08, SRM 51-1-21, 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, 51-3-0, AND 51-3-1.

Part: STRUCTURE — MISREPAIRED (ZONE 700) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT XRS 74 EXTERNAL DOUBLER LEFT WHEEL WELL AFT OF MAIN LANDING GEAR TRUNNION. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED EXTERNAL DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PART IAW AD 90-16-05, DACO SB 57-58 DATED 01-19-08, DOUGLAS DRAWING 5758978 AND 5643410, DACO SRM 51-1-11, 51-1-21, 51-1-20D AND 51-3-1, DC8 SRM 51-1-21 AND 51-1-20D.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 670 LONGERON 35.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER. INSTALLED NEW FASTENERS AND REPAIR DOUBLER IAW DC8 SRM 51-1-11, 51-1-21, 51-3-0, 51-3-1, FAA FORM 8110-3 NUMBER 08197 DATED 04/25/08, SEMAN DRAWING ED-3863 REVISION 1 DATED 04/21/08, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1384 LONGERON 35.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING INTERNAL FINGER DOUBLER. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED INTERNAL FINGER DOUBLER. CLEANED, TREATED AND PRIMED AREA AND INTERNAL FINGER DOUBLERS. INSTALLED NEW FASTENERS AND INTERNAL FINGER DOUBLERS 51-1-20D, 51-3-1 FAA FORM 8110-3 NUMBER 08197 DATED 04/25/08, SEMAN DRAWING ED-3865 REVISION1 DATED 04/21/08, DC8 SRM 51-1-21, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 404 LONGERON 35.5 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, INTERNAL FINGER DOUBLER, SKIN FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, 51-3-1, FAA FORM 8110-3 NUMBER 08244 DATED 05/08/08 SEMAN DRAWING ED-3861 REVISION1 DATED 04/26/08, DC8 SRM 51-1-21, 51-3-0, 51-1-20D, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 35 LONGERON 25.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING SPLICE DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED SKIN SEGMENT, SPLICE DOUBLERS, INTERNAL FINGER DOUBLER, INTERNAL DOUBLER, AND INTERNAL DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS DC8 SRM 51-1-11, 51-1-20D, 51-3-1, FAA FORM 8110-3 NUMBER 08188 DATED 04/23/08, SEMAN DRAWING ED-4755 DATED 04/21/08, DC8 SRM 51-1-21, SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 545 LONGERON 35.75 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLER, AND FINGER DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08188 DATED 04/23/08, SEMAN DRAWING ED-4758 DATED 04/19/08, DC8 SRM 51-1-21, 51-1-20D, 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1350 LONGERON 36. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLER, FINGER DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08198 DATED 04/25/08, DRAWING ED-4760 DATED 04/24/08, SRM 51-1-21, 51-1-20D, 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, AND 51-3-1.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C-CHECK INSPECT, FOUND FUSELAGE SKIN FORWARD OF FLAT AFT PRESSURE BULKHEAD HAS IMPROPER REPAIR AT STATION FS 1690.000 LONGERON 28. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. PERFORMED DETAILED VISUAL INSPECTION AND EDDY CURRENT INSPECTION. NO CRACK FOUND. FABRICATED NEW SKIN, INTERNIAL, AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA, AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW S/B 53A080, AD 2008-06-23, BOEING SB DC853A080 DATED 06/22/04 ACCOMPLISHMENT INSTRUCTION B WORK INSTRUCTION PARAGRAPH 4 APPENDIX "A" INSPECTION SEQUENCE 02, AND ATI EO 53-DC8-3729 DATED 02/05/07.

Part: SKIN — MISREPAIRED (BS 167 L21R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIRS LOCATED AT STATION FS 167 LONGERON 21.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, INTERNAL DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEETS 1 AND 5, DC8 SRM 51-1-21, 51-1-20D, DC8 SRM 53-4-1 FIGURE 1 ITEM "D", DC8 SRM 51-1-8B, 51-1-11, AND 51-3-1.

Part: SKIN — MISREPAIRED (BS 653 L26L) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIRS LOCATED AT STATION FS 653 LONGERON 26.5 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER, TRIPLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08198 DATED 04/25/08, SEMAN DRAWING NUMBER ED-4761 DATED 04/24/08, DC8 SRM 51-1-21, 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 290 L35R) · airframe 88,878 hrs · 38,040 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIRS LOCATED AT STATION FS 290 LONGERON 35.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR.REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER, TRIPLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08188 DATED 04/23/08, SEMAN DRAWING NUMBER ED-4756 DATED 04/21/08, DC8 SRM 51-1-21, 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, 51-1-21, AND 51-3-1.

Part: CONTROL BOX — DEFECTIVE (ANTI SKID SYS) · airframe 88,742 hrs · 37,899 cycles

DURING TAXI OUT FROM KFLL, THE CREW NOTICE THAT WITH THE ANTI-SKID SYSTEM ON THE AIRCRAFT HAD NO BRAKE'S, WHEN THE CREW TURNED THE ANTI-SKID SYSTEM OFF THE AIRCRAFT HAD BRAKE'S. THE CREW RETURNED TO BLOCK'S AT KFLL. MAINTENANCE AT KFLL DEFERRED ANTI-SKID SYSTEM IAW MRL -32-1. THE CREW FLEW THE AIRCRAFT TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE AT KTOL REMOVED AND REPLACED THE ANTI-SKID CONTROL BOX, TAXI THE AIRCRAFT AND PERFORMED OPERATIONAL CHECK ON THE BRAKES WITH THE ANTI-SKID ON AND OFF BRAKES CHECKED GOOD ALL TIMES IAW DACO DC8 MAINTENANCE MANUAL 32-43-6 AND ATI ERH 09.01. AIRCRAFT WAS RETURNED TO SERVICE.

Part: STRUCTURE — DAMAGED (MLG DOOR) · airframe 88,182 hrs · 37,650 cycles

DURING CLIMB-OUT FROM KIAH, THE CREW NOTICED WHEN THE GEARS ARE UP RED LANDING GEAR UNSAFE LIGHT REMAINED ON, THE CREW RECYCLED THE GEAR AND NO CHANGE, DURING UPLATCH CHECK GEAR UNSAFE LIGHT REMAINED ON, BUT DOOR LIGHT DID NOT ILLUMINATE. THE CREW FELT MOVEMENT AND VIBRATION DURING UPLATCH CHECK, PRESSURE AND QUANTITY OK. THE CREW RETURNED TO KIAH, AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE MAIN LANDING GEAR DOORS AND FOUND LEFT DOOR OUTER SECTION DAMAGED. MAINTENANCE REMOVED THE DAMAGED SECTION OF THE DOOR, AND FOUND TO BE IN SAFE CONDITION TO FERRY FLIGHT TO KTOL. IN KTOL, MAINTENANCE REPLACED MAIN LANDING GEAR DOOR, AND MAIN LANDING GEAR DOOR CONTROL VALVE. MAINTENANCE ACCOMPLISHED OPERATIO

Part: COMPUTER — MALFUNCTIONED · airframe 88,101 hrs · 37,610 cycles

DURING CLIMB-OUT FROM KSJC STALL WARNING ACTIVATED AT START OF ROTATION AND REMAINED ON. THE CREW PULLED CIRCUIT BREAKER AND RETURNED TO KSJC AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE LIFT COMPUTER, PERFORMED OPERATIONAL CHECK WAS GOOD IAW UAL 41-10-2. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (ZONE 600) · airframe 87,731 hrs · 37,432 cycles

DURING ROUTINE CPCP INSPECTION, FOUND RIGHT WING UPPER SKIN CRACKED AT STATION XRS 74 STRINGER 16. REMOVED DAMAGE AREA, NO CRACK'S OR CORROSION FOUND AFTER DAMAGE REMOVED. MANUFACTURED REPAIR PARTS. TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DACO DC8 SRM57-2-1 FIGURE 10.

Part: SKIN — CRACKED (ZONE 600) · airframe 87,731 hrs · 37,432 cycles

DURING ROUTINE CPCP INSPECTION, FOUND RIGHT WING UPPER SKIN CRACKED AT STATION XRS 74 STRINGER 9. REMOVED DAMAGE AREA, NO CRACK'S OR CORROSION FOUND AFTER DAMAGE REMOVED. MANUFACTURED REPAIR PARTS. TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DACO DC8 SRM 57-2-1 FIGURE 10.

Part: SKIN — CRACKED (ZONE 500) · airframe 87,097 hrs · 37,016 cycles

DURING PREFLIGHT INSPECTION, FOUND RUNNING FUEL LEAK INBOARD OF NR 1 PYLON COMING FROM NUMBER ONE ALTERNATE FUEL TANK. THE DAMAGE WAS REMOVED AND REPAIRED PER BOEING ROD SKETCH 06-04-18-001 REF TIMCO GOODYEAR S/O 216006. OPS 27846 REPAIR APPROVED AS TEMPORARY REPAIR UNTIL DAMAGE TOLERANCE ASSESSMENT APPROVED FOR THE NEXT 24 MONTHS. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SPAR CAP — CRACKED (RT WING) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING UPPER FRONT SPAR CAP STRUCTURE CRACKED BETWEEN STA XFS-6 CAP. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND CORROSION FROM SLANT PANEL UPPER CAP. FOUND OUT OF LIMITS. CLEANED, TREATED AND PRIMED AREA. INSTALLED DOUBLER AND REMOVED UPPER SPAR CAP. REMOVED STIFFENER PERFORMED NDT INSPECTION. APPLIED SEALANT TO FAYING SURFACES. INSTALLED DOUBLER AND ANGLE DOUBLER IAW S/B DC8-57-072 RO3, DWG DACO 5892075, CN1, DC8 SRM 51-1-8, 51-1-11, 51-1-15, 51-1-20D, 51-1-22, 51-1-26, 51-3-1, 57-2-0, 57-2-1, 57-3-1, 57-3-2 DPS 1.05-8, 3.67-3, 2.50.

Part: SPAR CAP — CRACKED (RT WING) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT WING UPPER FRONT SPAR CAP STRUCTURE HAS CRACK DAMAGE BETWEEN STA XFS -6 CAP. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS. REMOVED CORROSION FROM SLANT PANEL UPPER CAP AND FOUND OUT OF LIMITS. CLEANED, TREATED AND PRIMED AREA. INSTALLED DOUBLER AND REMOVED UPPER SPAR CAP DAMAGE. REMOVED STIFFENER AND PERFORMED NDT INSPECTION. APPLIED SEALING TO ALL FAYING SURFACES AND INSTALLED DOUBLER, ANGLE DOUBLER AND INSTALLED KIT (S/N 0570072-3). TORQUED IAW S/B DC8 57-072 RO3, DWG, DACO 5892075, CN1, DC8 SRM 51-1-8, 51-1-11, 51-1-15, 51-1-20D, 51-1-22, 51-1-26, 51-3-30, 51-3-1, 57-2-0, 57-2-1, 57-3-1, 57-3-2, DPS 1.05-8, 3.67-3, 2.50.

Part: DOUBLER — CORRODED (BS335 STR35R-35L) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND FUSELAGES CENTER SECTION FORWARD CARGO COMPARTMENT FORWARD DOOR AFT JAMB INTERNAL DOUBLER CORROSION DAMAGE STA 335.000 L-35R 35L. MAJOR REPAIR ACCOMPLISHED REMOVAL OF CORROSION AND FOUND OUT OF LIMITS. REMOVED EXISTING DOUBLER AND FASTENERS FROM REPAIR DOUBLER. REMOVED THE DAMAGED AREA. PERFORMED NDT INSPECTION TO AREA, FABRICATED EXTERNAL REPAIR, DOUBLER + FILLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SEMAN DRAWING ED-3879 AND FAA FORM 8110-3 NR 05083, DC8 SRM 51-1-11, 51-1-15, 51-1-20D, 51-1-26, 51-3-1, 51-3-2.

Part: FRAME — CRACKED (FS 55.00 L-24L) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT FUSELAGE FORWARD ACCESSORY COMPARTMENT STRUCTURE FRAME CRACK DAMAGE AT STA FS 55.00, L-24L. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND CRACKED FRAME SEGMENT. PERFORMED AN NDT INSPECTION. FABRICATED FRAME SEGMENT AND SPLICES. PERFORMED HEAT TREATMENT, CLEANED, TREATED AND PRIMED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED FRAME SEGMENT AND SPLICES IAW DC8 SRM 53-2- FIG 2 SH 1, 6 TR NR 53-125, 53-3-1 FIG 3 SH 2, 2S, 51-1-1, 51-1-4, 51-1-11, 51-1-15, 1-1-20D, 51-3-2, DPS 3.69-7 REV "AM" R-1, 7.00-1 REV "BK".

Part: FRAME — CRACKED (FS55.00 L-24R) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT FUSELAGE FORWARD ACCESSORY COMPARTMENT STRUCTURE FRAME CRACK DAMAGE STA FS 55.00 L-24R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS. REMOVAL OF DAMAGED AREA FRAME SEGMENT. PERFORMED NDT INSPECTION, FABRICATED FRAME SEGMENT AND SPLICE DOUBLER. PERFORMED HEAT TREATMENT. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED FRAME SEGMENT AND SPLICES IAW DC8 SRM 53-2-0 FIG 2 SHEET 1, 6 TR NR 53-110, TR NR 53-125, 53-3-1 FIG 3 SH 2, 2A, 51-1-1, 51-1-4, 51-1-11, 51-1-15, 51-1-20D, 51-3-1, 51-3-2,DPS 3.69-4 REV "AM" R-1, 7.00-1 REV "BK" EO 2005220.

Part: RIB — CRACKED (WS 67.750) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT OUTBOARD PYLON STUB WING N 4 RIB EXTENDED LEADING EDGE CRACK DAMAGE AT STA XOLDO 67.750. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGE. FABRICATED NEW RIB. PERFORMED NDT INSPECTION, CLEANED, TREATED AND PRIMED AREA+ NEW RIB. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED NEW RIB IAW DWG DACO 9753297, REPAIR SPEC NR 2003-05, DC8 SRM 54-1-0 PG 1, 54-3-0 FIG 14B, 51-1-1, 51-1-4, 51-1-20D, 51-3-1, 51-3-2, DPS 3.69-4 REV"AM" R-1, DPS 7.00-REV "BK".

Part: PANEL — DENTED (T/E FLAP) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP AFT PANEL DENT DAMAGE BETWEEN STA XF 304.000-XF 333.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGED PLATING. FABRICATED NEW PLATING, CLEANED, TREATED AND PRIMED AREA + INNER FACE ON NEW PLATING. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW PLATING IAW DC8 SRSM 57-7-0 PG 1, 57-7-1 FIG 4 TR # 57-94, 51-1-21, 51-3-0, 51-3-1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT FUSELAGE FORWARD ACCESSORY COMPARTMENT STRUCTURE FRAME CRACK DAMAGE AT STA FS 55.00,L-24R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS FROM REPAIR AREA. REMOVED DAMAGED FRAME SEGMENT. PERFORMED NDT INSPECTION. FABRICATED FRAME SEGMENT AND SPLICE DOUBLER. PERFORMED HEAT TREATMENT, CLEANED, TREATED AND PRIMED AREA AND REPAIRED PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED FRAME SEGMENT AND SPLICES IAW DC8 SRSM 53-2-0 FGI2 SH 1, 6 TR NR 53-125, 53-3-1 FIG 3 SH 2, 2A, 51-1-1, 51-1-4, 51-1-11, 51-1-15, 51-1-20D, 51-3-1, 51-3-2 DPS 3.69-4 REV "AM" R-1,7.00-1 REFV."BK".

Part: REPAIR — IMPROPER (XF 385.00) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, LT WING OUTBOARD FLAP LOWER AFT PLATING INTERIM REPAIR AROUND STA XF 385.00. MAJOR REPAIR ACCOMPLISHED BY REMOVING EXISTING REPAIR IAW DC8 SRM 51-1-11 PG1, DC8 SRM 51-3-0 PG1. REMOVED DAMAGED AREA IAW DC8 SRM 57-2-5N FIG 2 SHEET 3,4 PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001. FABRICATED EXTERNAL REPAIR DOUBLER IAW DC8 SRM 57-2-5 FIG 2 SHEET 3,4. CLEANED, TREATED AND PRIMED AREA IAW DC8 SSRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 PAGE 9. INSTALLED DOUBLER IAW DC8 SRM 57-2-5 F1G 2 SHEET 3, 4 DC9 SR, 51-1-9, DC8 SRM 51-1-21 PG 1.

Part: PANEL — CRACKED (XRS 71.000 S7-S8) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT INNER WING AFT TOP PANEL PLATING CRACK DAMAGE AROUND STA XRS 71.000, S-7 TO S-8. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS FROM REPAIR AREA AND PERFORMED NDT INSPECTION. FABRICATED REPAIR DOUBLER AND FILLER PLUG. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED REPAIRED PARTS IN ACCORDANCE WITH SEMON DRAWING ED-3830 AND FAA FORM 8110-3 NR 05030, DC8 SRM 51-1-11, 51-1-15, 51-1-20D, 51-3-1, 51-3-2.

Part: ACCESS DOOR — CRACKED (FS -12.00L-27R) · airframe 85,985 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT FUSELAGE NOSE SECTION ACS MODIFICATION DOUBLER LOWER AFT JAMB CORNER RAM AIR EXHAUST ACCESS DOOR COMPARTMENT CRACK DAMAGE AT STA FS -12.00, L-27R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING FILLER AND DAMAGED SECTION. PERFORMED AN NDT INSPECTION. FABRICATED REPAIR DOUBLER AND REPAIR TRIPLER + FILLER. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED REPAIRED PARTS IAW ALL APPLICABLE MANUALS, DRAWINGS AND FORMS.

Part: SPAR CAP — CRACKED (RT WING) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING UPPER FRONT SPAR CAP STRUCTURE CRACK DAMAGE BETWEEN STA XFS-6 CAP. MAJOR REPAIR ACCOMPLISHED BY REMOVING FASTENERS. REMOVING CORROSION FROM SLANT PANEL UPPER CAP AND FOUND OUT OF LIMITS. CLEANED, TREATED AND PRIMED AREA. INSTALLED DOUBLER, REMOVED UPPER SPAR CAP (DAMAGED). REMOVED STIFFENER AND PERFORMED NDT INSPECTION. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED DOUBLER, ANGLE DOUBLER. INSTALLED KIT, TORQUE AND LEAK CHECKED IAW S/B DC8-57-072 R03 DWG DACO 5892075, CN1, DC8 SRM 51-1-8, 51-1-11, 51-1-15, 51-1-20D, 51-1-26, 51-3-0, 51-3-1, 51-3-2, DPS 1.05-8, 3.67-3, 2.5.

Part: REPAIR — MISSING (STA 180L-35RH-36) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND FUSELAGE AFT CENTER SECTION LOWER PLATING DRAIN HOLE REPAIR DOUBLER MISSING ONE ROW FASTENERS AT STA 180.000, L-35 RT TO L-36. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR DOUBLER. FABRICATED EXTERNAL REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER. APPLIED SEALANT TO FAYING SUFACES. INSTALLED REPAIR DOUBLER IAW ALL APPLICABLE MANUALS AND DRAWINGS.

Part: FASTENER — MISSING (BS 1380) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND AFT CENTER SECTION LOWER PLATING DRAIN HOLE REPAIR ONE ROW FASTENERS MISSING STA 1380.000 L-35 RT L-36. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR. REMOVED DAMAGED SECTION AND PERFORMED NDT INSPECTION. FABRICATED EXTERNAL REPAIR DOUBLER AND INTERNAL FINGER DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED REPAIR PARTS IAW ALL APPLICABLE MANUALS, DRAWINGS AND REVISIONS.

Part: PLATE — CRACKED (XRS 74.869 S-14) · airframe 85,985 hrs · 36,255 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RT INNER WING FWD TOP PANEL PLATING WITH CRACK DAMAGE AT STA XRS 74.869, S-14. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND DAMAGED AREA. PERFORMED NDT INSPECTION. FABRICATED REPAIR DOUBLER AND FILLER PLUG. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED REPAIRED PARTS IAW ALL APPLICABLE MANUALS, DRAWINGS AND FORMS.

Part: FASTENER — MISSING (FS 620 L35R-36) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND WING TO FUSELAGE LOWER PLATING DRAIN HOLE REPAIR MISSING ONE ROW OF FASTENERS AT STA FS 620.000, L-35R TO L-35R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING DOUBLER AND FASTENERS WITHIN REPAIR AREA AND REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, SKIN FILLER AND INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER, TRIPLER, SKIN FILLER AND INTERNAL DOUBLER FILLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED ALL REPAIRED PARTS IAW ALL APPLICABLE MANUALS, DRAWINGS AND FORMS.

Part: SKIN — CRACKED (XRS 144.00) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING FORWARD TOP PANEL PLATING CRACK DAMAGE AT STA XRS 144.00 FRONT SPAR. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND DAMAGED AREA. PERFORMED NDT INSPECTION. FABRICATED EXTERNAL DOUBLER AND FILLER PLUG. CLEANED, TREATED AND PRIMED AREA AND REPAIRED PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIRED PARTS IAW SEMAN DWG ED-3833 AND FAA FORM 8110-3 NR 05020, DC8 SRM 51-1-11, 51-1-15, 51-120D, 51-1-22, 51-1-26, 51-3-0, 51-3-1, 51-3-2, 51-6-0.

Part: REPAIR — IMPROPER (XW 87.000) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD FLAP FORWARD UPPER PLATING INTERIM REPAIR AT STA XW 87.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR AND THE DAMAGED AREA. FABRICATED NEW PLATING SEGMENT + INTERNAL SPLICE, EXTERNAL DOUBLERS. CLEANED TREATED AND PRIMED DOUBLERS AND AREA. INSTALLED REPAIR PART IAW SEMAN DWG ED-3841 AND FAA FORM 8110-3 NR 05019, DC8 SRM 51-1-11, 51-1-15, 51-1-20D, 51-1-22, D51-1-26, 51-3-0, 51-3-1, 51-3-2.

Part: LONGERON — CRACKED (BS 1770 L17R) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT FUSELAGE TAIL SECTION STRUCTURE LONGERON 17 RT HAS CRACK DAMAGE STA 1770.00. MAJOR REPAIR ACCOMPLISHED REMOVAL OF CRACKED LONGERON. FABRICATED NEW LONGERON, CLEANED, TREATED AND PRIMED AREA. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW LONGERON IAW DC8 SRM 53-1-0 PG 1, 53-5-1 FIG 7 SH 1, 51-2-0 FIG 50 SH 37, 51-1-20D, 51-1-21, 51-3-1.

Part: PLATE — DENTED (XW 110.000) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD FLAP UPPER AFT PLATING DENT DAMAGE AT STA XW 110.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGED PLATING. FABRICATED NEW PLATING AND FINGER DOUBLER. CLEANED, TREATED AND PRIMED NEW PLATING INTERNAL PART. BONDED FINGER DOUBLERS AND APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIRED PARTS IAW DC8 SRM 57-1-0 PG 1, 57-7-1 FIG 1 SH 1, 51-1-9A, 51-1-11, 51-1-21, 51-1-3, 51-3-0, 51-3-1.

Part: PLATE — CRACKED (XRS 74.869 S-5) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND RT INNER WING AFT TOP PANEL PLATING CRACK DAMAGED AT STA XRS 74.869, S-5. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND DAMAGED SECTION. PERFORMED NDT INSPECTION AND FABRICATED EXTERNAL DOUBLER + FILLER PLUG. CLEANED, TREATED AND PRIMED AREA + FILLER PLUG + REPAIR DOUBLER SIDE. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED REPAIR PARTS IAW SEMAN DWG ED-3832 AND FAA FORM 8110-3 NR 05020, DC8 SRM 51-1-11, 51-1-15, 51-1-20D, 51-1-22, 51-1-26, 51-3-1, 51-3-2.

Part: REPAIR — IMPROPER (XW 34.000) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING INBOARD FLAP AFT LOWER PANEL INTERIM REPARI AT STA XW 34.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR. REMOVAL OF DAMAGED SECTION. PERFORMED NDT INSPECTION, FABRICATED NEW PLATING SEGMENT, INTERNAL SPLICES, EXTERNAL REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS AND INNER PART OF NEW PLATING SEGMENT. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS + NEW PLATING SEGMENT IAW SEMAN DWG ED-3855 AND FAA FORM 8110-3 NR 0551, DC8 SRM 51-1-11, 51-1-15, 51-1-20D, 51-1-21, 51-1-22, 51-3-0, 51-3-1, 51-1-3 AN EO 2005085

Part: PANEL — CRACKED (WS 74.869) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT INNER WING AFT TOP PANEL PLATING CRACK DAMAGE AT STA XRS 74.869, S-2. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND DAMAGED SECTION. FABRICATED EXTERNAL DOUBLER + FILLER PLUG. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER + FILLER PLUG. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SEMAN DRAWING ED-3831 AND FAA FORM 8110-3 05020, DC8 SRM 51-1-11, 51-1-20D, 51-1-22, 51-1-26, 51-3-1, 51-3-2.

Part: SKIN — CORRODED (FS 1540.00) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT FUSELAGE AFT CENTER SECTION LOWER PLATING INTERNAL CORROSION DAMAGE AROUND STA FS 1540.00, L-25R TO L-26R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF CORROSION AND FOUND OUT OF LIMITS. REMOVED FASTENERS FROM REPAIR AREA AND REMOVED THE DAMAGED AREA. PERFORMED AN NDT INSPECTION. FABRICATED EXTERNAL REPAIR DOUBLER, INTERNAL FINGER DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIRED PARTS. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED REPAIRED PARTS IAW ALL APPLICABLE MANUALS, DRAWINGS AND REVISIONS.

Part: REPAIR — IMPROPER (XW87.00-XW 91.) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK, INSPECTION FOUND LT WING INBOARD FLAP UPPER FORWARD PLATING INTERIM REPAIRS BETWEEN STA XW 87.000 AND XW 91.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR, AND REMOVED PLATING SEGMENT. PERFORMED NDT INSPECTION AND FABRICATED NEW PLATING SEGMENT + INTERNAL SPLICE + EXTERNAL DOUBLER. CLEANED, TREATED AND PRIMED AREA AND NEW REPAIRED PARTS INTERNAL PART. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-3845 AND FAA FORM 8110-3 NR 05019, DC8 SRM CHAPTERS 51-1-11, 51-1-20D, 51-1-21, 51-1-22, 51-1-26, 51-3-1, 51-3-2.

Part: REPAIR — UNKNOWN (RT WING TE FLAP) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP UPPER FORWARD PLATING INTERIM REPAIR STA XF 417.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND DAMAGE FROM AREA. PERFORMED A NDT INSPECTION TO AREA AND FABRICATED A REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA, FILLER AND DOUBLER. APPLIED SEALANT TO FAYING SURFACES AN INSTALLED THE REPAIRED PARTS IAW ALL APPLICABLE MANUALS, DRAWINGS AND REVISIONS.

Part: PLATE — DAMAGED (XFS 710.00) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT OUTER WING INBOARD EXTENDED LEADING EDGE ELONGATED HOLE AROUND STA XFS 710.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF PLATING WITH IMPROPER REPAIR. FABRICATED NEW PLATING, CLEANED, TREATED AND PRIMED AREA AND NEW PLATING INTERNAL PART. APPLIED SEALANT TO ALL FAYING SURFACES AND INSTALLED NEW PLATING IAW ALL APPLICABLE MANUALS, DRAWINGS AND FORMS.

Part: PLATE — DENTED (XF 415.-XW 408.0) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP LOWER AFT PLATING DENTS DAMAGE BETWEEN STA XF 415.000 AND XW 408.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGED SKIN. FABRICATED NEW SKIN, CLEANED, TREATED AND PRIMED AREA + NEW SKIN INTERNAL PART. APPLIED SEALANT TO FAYING SEURFACES AND INSTALLED NEW SKIN IAW ALL APPLICABLE MANUALS, DRAWNINGS AND FORMS.

Part: DOOR FRAME — WORN (FS 1440.00) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, RT FUSELAGE AFT CENTER SECTION AFT CARGO COMPARTMENT AFT DOOR AFT JAMB WEAR DAMAGE AT STA FS 1440.00, L-30R TO L-31R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND DAMAGED AREA. PERFORMED AN NDT INSPECTION, FABRICATED EXTERNAL REPAIR DOUBLER + FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED FILLER AND REPAIR DOUBLER IAW ALL APPLICABLE MANUALS, DRAWINGS AND FORMS.

Part: SKIN — DAMAGED (FS 25.000 L-21R) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, RT FUSELAGE FORWARD PASSENGER ENTRANCE DOOR UPPER AFT JAMB PLATING WEAR DAMAGE AT STA FS 25.000, L-21R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGE. FABRICATED NEW SKIN, CLEANED, TREATED AND PRIMED AREA + NEW SKIN. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 52-1-0 PG 1, 52-3-1 FIG 1, 52-1-11, 51-1-21, 51-1-22.

Part: FASTENER — MISSING (BS 1322.00 L35.5) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT FUSELAGE AFT CENTER SECTION LOWER PLATING OLD OMEGA ANTENNA DOUBLER MISSING ON ROW FASTENERS AND MAX PITCH EXCEEDS LIMITS AT STA FS 1322.00L, 35.5R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION TO AREA. FABRICATED REPAIR DOUBLER AND INTERNAL FINGER DOUBLERS AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIRED PARTS IAW DC8 SRM 3-2-1 FIG 7, FIG 1 AND 3, 53-2-0, 53-4-1 FIG 16 SH 1, 51-10-1 FIG 2 SH 5, 51-3-1, 51-3-5, 51-1-4, 51-1-20D, 51-1-21.

Part: SKIN — DAMAGED (T/E FLAP) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT WING OUTBOARD FLAP UPPER FORWARD PLATING INTERIM REPAIR STA XF 227.00. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGED PLATING AREA. PERFORMED AN NDT INSPECTION. FABRICATED NEW PLATING SEGMENT, INTERNAL SPLICE AND EXTERNAL DOUBLER CLEANED. TREATED AND PRIMED AREA AND REPAIRED PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIRED PARTS IAW SEMAN DRAWING ED-3848 AND FAA FORM 8110-3 NR 05056, DC8 SRM 51-1-11, 51-1-20D, 51-1-21, 51-1-22, 51-1-26, 51-3-0, 51-3-1, 51-3-2.

Part: SKIN — WORN (BS1400 30R-31R) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, RT FUSELAGE AFT CENTER SECTION AFT CARGO COMPARTMENT AFT DOOR FWD JAMB WEAR DAMAGE AT STA FS 1400.00, L-30R TO L-31R. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FASTENERS. REMOVED DAMAGED SECTION. PERFORMED NDT INSPECTION. FABRICATED EXTERNAL REPAIR DOUBLER + FILLER. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES INSTALLED REPAIR PARTS IAW SEMAN DRAWING ED-3827 AND FAA FORM 8110-3 NR 05055, DC8 SRM 51-1-411, 51-1-21, 51-1-22, 51-1-26, 51-3-1.

Part: REPAIR — DAMAGED (XW2.00 &XW91.00) · airframe 85,895 hrs · 36,255 cycles

DURING A ROUTINE C CHECK INSPECTION, RT WING INBOARD FLAP AFT UPPER PLATING INTERIM REPAIRS AND DENT DAMAGE BETWEEN STA XW 2.00 CANT AND XW 91.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGED PLATING. FABRICATED NEW PLATING. CLEANED, TREATED AND PRIMED AREA AND NEW PLATING INTERNAL PART. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED NEW PLATING IAW SEMAN DRAWING E.

Part: LANDING GEAR — MALFUNCTIONED · airframe 85,766 hrs · 36,180 cycles

AFTER TAKEOFF FROM KHRL TO KTOL, LANDING GEAR UNSAFE LIGHT ILLUMINATED WITH GEAR UP. UPLOCK CHECK UNSATISFACTORY, NOSE GEAR FALLS FREE. CREW LANDED IN KTOL WITHOUT INCIDENT. AN INSPECTION IS ON GOING. WHEN MORE INFORMATION IS AVAILABLE IT WILL BE PROVIDED.

Part: UPLOCK — CORRODED (MLG) · airframe 84,790 hrs · 35,734 cycles

DURING UPLATCH CHECK AFTER TAKE OFF, GEAR DOORS AND GEAR UNSAFE LIGHTS CAME ON. CREW PERFORMED UNSATISFACTORY UPLATCH CHECK (WARNING LIGHTS ON) CHECK WAS STILL UNSATISFACTORY. CREW RETURNED AIRCRAFT AND LANDED WITHOUT INCIDENT. AN INVESTIGATION IS ON GOING. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE TROUBLESHOT LANDING GEAR EXTENSION/ RETRACTION IN ENTIRETY. FOUND RT MAIN LANDING GEAR UPLATCH MECHANISM CORRODED. MAINTENANCE CLEANED THE MECHANISM ALONG WITH THE ATTACHING PARTS AND JACKED THE AIRCRAFT IAW ALL APPLICABLE MANUALS. OPERATIONAL CHECK GOOD AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: CYLINDER — LEAKING (LT MLG) · airframe 84,789 hrs · 35,733 cycles

AFTER DEPARTURE FROM VTBU TO RJTY NOTED HYD FLUID AND PRESSURE LOSS. CREW FOLLOWED ABNORMAL CHECKLIST, PROCEEDED TO RJTY FOR AN UNEVENTFUL LANDING. MX DISCOVERED LEFT MLG BOGIE TRIM CYLINDER LEAKING AND REPLACED THIS COMPONENT. SYSTEM LEAKS AND OPS CHECKS GOOD AIRCRAFT RETURNED TO SERVICE.

Part: WINDOW — DELAMINATED (COCKPIT) · airframe 84,651 hrs · 35,693 cycles

DURING TAKEOFF FROM KMCO F/O'S WINDOW STARTED DELAMINATION. CREW SHUTOFF WINDOW HEAT AND DELAMINATING STOPPED. CREW RETURNED AIRCRAFT TO KMCO AND LANDED WITHOUT INCIDENT. AN INSPECTION IS ON GOING. WHEN MORE INFORMATION IS AVAILABLE IT WILL BE PROVIDED. AFTER INSPECTION OF F/O'S WINDOW FOUND IT TO BE THE INNER WINDOW WITH THE DELAMINATION. FOUND IT WITHIN LIMITS PER ALL APPLICABLE MANUELS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATOR — INOPERATIVE (NR 2 OIL PRESS) · airframe 84,434 hrs · 35,576 cycles

ON CRUISE FROM KTOL TO KLRD NR 2 ENGINE OIL PRESSURE INDICATOR WENT TO 2 PSI. OIL PRESSURE LIGHT PRESS TO TEST OKAY. COMPLIED WITH ABNORMAL CHECKLIST. ALL OTHER ENGINE INDICATIONS NORMAL. CREW RETURNED AIRCRAFT TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 2 OIL PRESSURE GAGE. OPERATIONAL CHECK GOOD ON GROUND IAW ALL APPLICABLE MANUALS. NO OTHER DEFECTS NOTED AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — CRACKED (I/B T/R SUP.RING) · airframe 83,897 hrs · 34,853 cycles

DURING ROUTINE C CHECK INSPECTION, A CRACK WAS DISCOVERED IN THE # 3 ENGINE INBOARD THRUST REVERSER HALF BLOCKER DOOR SUPPORT RING AT THE 11 O'CLOCK POSITION. REPAIR ACCOMPLISHED REMOVAL STOP DRILLED CRACK FABRICATION AND INSTALLATION OF REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND DRAWING R74-R03.

Part: DOOR ACTUATOR — DAMAGED (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C-CHECK INSPECTION, A TEMPORARY REPAIR WAS DISCOVERED ON THE UPPER FORWARD L-1 DOOR JAMB STATION 25. REPAIR ACCOMPLISHED REMOVAL OF TEMPORARY REPAIR AND DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER AND TRIPLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C-CHECK INSPECTION, A TEMPORARY REPAIR WAS DISCOVERED IN THE LOWER FORWARD L-2 DOOR JAMB STATION 1620. REPAIR ACCOMPLISHED REMOVAL OF TEMPORARY REPAIR AND DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER AND TRIPLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SUPPORT — CORRODED (RT WING) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE INBOARD AND OUTBOARD LOWER AREA OF THE NR 2 FLAP HINGE UPPER SUPPORT ON THE RIGHT WING. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND BOEING'S LETTER TIN-MIA-02-00017H.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 82,897 hrs · 34,853 cycles

DURING A ROUTINE C-CHECK INSPECTION, A TEMPORARY REPAIR WAS DISCOVERED OF THE RIGHT AFT CORNER OF THE CARGO DOOR. REPAIR ACCOMPLISHED REMOVAL OF TEMPORARY REPAIR AND DAMAGED AREA. FABRICATION AND INSTALLATION OF DOUBLER AND TRIPLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL.

Part: SKIN — CRACKED (SERVICE DOOR) · airframe 82,897 hrs · 34,853 cycles

DURING A ROUTINE C-CHECK INSPECTION, A CRACK WAS DISCOVERED ON THE LOWER FORWARD CORNER OF THE AFT RIGHT SERVICE DOOR STATION 1620. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION REPAIR OF DOUBLER AND TRIPLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING A ROUTINE C-CHECK INSPECTION, EVIDENCE OF LIGHTNING STRIKES WERE DETECTED ON FUSELAGE STATION 280 LONGERON 10R AND FUSELAGE STATION 340 LONGERON 9R. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL AND DRAWING R74-R01.

Part: WING — CRACKED (LEFT UPPER LE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C CHECK INSPECTION, CRACKS WERE DETECTED JUST OUTBOARD OF THE INBOARD STUB WING AREA ON THE LEFT WING UPPER LEADING EDGE. REPAIRED ACCOMPLISHED REMOVAL OF DAMAGED AREA FABRICATION AND INSTALLATION REPAIR OF DOULBER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C-CHECK INSPECTION EVIDENCE OF LIGHTNING STRIKES WERE DETECTED ON FUSELAGE STATION 600 LONGERON 7R. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA FABRICATION AND INSTALLATION OF INTERNAL FINGER DOUBLERS IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL AND ENGINEERING ORDER R74-R01.

Part: SKIN — DAMAGED (SERVICE DOOR) · airframe 82,897 hrs · 34,853 cycles

DURING A ROUTINE C-CHECK INSPECTION, A TEMPORARY REPAIR WAS DISCOVERED ON THE FORWARD SERVICE DOOR AT STATION 400. REPAIR ACCOMPLISHED REMOVAL OF TEMPORARY REPAIR AND DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C-CHECK INSPECTION, EVIDENCE OF LIGHTNING STRIKES WERE DETECTED ON FUSELAGE STATION 460, 480 & 520 LONGERONS 7R-8R. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL AND DRAWING R74-R01.

Part: WING — CRACKED (LT WING LOWER LE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C CHECK INSPECTION A CRACK WAS DETECTED ADJACENT TO THE INBOARD FIRE BOTTLE VIEWING DOOR ON LEFT WING LOWER LEADING EDGE. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER R74-R02-IR

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING ROUTINE C-CHECK INSPECTION EVIDENCE OF LIGHTNING STRIKES WERE DETECTED ON FUSELAGE STATION 180 LONGERONS 9R. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL AND DRAWING R-74-R01.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 82,897 hrs · 34,853 cycles

DURING A ROUTINE C-CHECK INSPECTION, EVIDENCE OF LIGHTNING STRIKES WERE DETECTED ON FUSELAGE STATION 120 LONGERON 9R. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL AND DRAWING R74-R01.

Part: OIL CAP — LOOSE (NR 1 ENGINE) · airframe 82,657 hrs · 34,696 cycles

EN ROUTE FROM PDX TO BFI, THE FLIGHT CREW NOTICED THE NUMBER ONE ENGINE OIL QUANTITY DECLINING. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND SECURED THE ENGINE AND CONTINUED TO BFI FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE LOCATING THE STARTER OIL SERVICING CAP OFF. MAINTENANCE SERVICED THE ENGINE STARTER AND SECURED THE SERVICING CAP. MAINTENANCE PERFORMED LEAK CHECK AND OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: UPLOCK — STICKS (LT MLG) · airframe 82,570 hrs · 34,644 cycles

EN ROUTE FROM RFD TO TOL, THE LANDING GEAR UPLATCH CHECK FAILED AND THE LANDING GEAR UNSAFE LIGHT ILLUMINATED. THE CREW CYCLED THE GEAR SEVERAL TIMES BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE LEFT MAIN LANDING GEAR UP LATCH MECHANISM STICKING. MAINTENANCE CLEANED AND LUBED THE MECHANISM AND PERFORMED SUCCESSFUL OPERATIONAL CHECKS IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FILTER — DIRTY (NR 3 ENGINE) · airframe 81,275 hrs · 34,009 cycles

EN ROUTE FROM LAX TO PDX, THE NUMBER THREE ENGINE FLAMED OUT DURING CLIMB. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURE AND PERFORMED A SUCCESSFUL RESTART AFTER TRANSFERRING TO AN ALTERNATE FUEL SOURCE. THE FLIGHT CONTINUED TO PDX FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE IN ACCORDANCE WITH THE CFMI MAINTENANCE MANUAL WITH NO DISCREPANCY NOTED. MAINTENANCE REPLACED THE MAIN ENGINE FUEL FILTER AS PRECAUTIONARY, PERFORMED POWER ASSURANCE CHECKS IN ACCORDANCE WITH THE COMPANY ENGINE RUN HANDBOOK WITH NO DISCREPANCIES NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING LIGHT — FALSE ACTIVATION (COCKPIT) · airframe 80,884 hrs · 33,860 cycles

EN ROUTE FROM BDL TO IND, THE LOWER FORWARD CARGO COMPARTMENT FIRE WARNING LIGHT ILLUMINATED. THE FORWARD LOWER CARGO COMPARTMENT FIRE DETECTION SYSTEM WAS PREVIOUSLY ON DEFERRAL IN ACCORDANCE WITH THE COMPANY APPROVED MEL 26-10. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND RETURNED TO BDL FOR AN UNEVENTFUL LANDING. AIRPORT EMERGENCY CREWS MEET THE AIRCRAFT AND VERIFIED NO FIRE WAS PRESENT. THE AIRCRAFT RETURNED TO THE RAMP. MAINTENANCE DEACTIVATED THE LOWER CARGO FIRE DETECTION SYSTEM IN ACCORDANCE WITH THE COMPANY ENGINEERING ORDER 26-DC8-1249. THE AIRCRAFT WAS RETURNED TO SERVICE. UPON ACCOMPLISHMENT OF REPAIRS A FOLLOW UP WILL BE SUBMITTED.

Part: PLATING — CRACKED (WS 323)

DURING A SCHEDULED HEAVY MAINTENANCE VISIT, A CRACK WAS DETECTED ON THE RIGHT WING LOWER EXTERNAL PLATING AT WING STATION XRS323, BETWEEN STRINGER 62 AND 63. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION AN INTERNAL REPAIR FILLER, EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING SK99526 AND DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: BALLAST — DEFECTIVE (COCKPIT)

EN ROUTE, A BURNING ODOR WAS SENSED IN THE COCKPIT WHEN THE GLARESHIELD FLUORESCENT LIGHTING WAS ILLUMINATED. THE LIGHTING SYSTEM WAS TURNED OFF AND THE ODOR SUBSIDED AND THE FLIGHT CONTINUED TO TOL. MAINTENANCE INSPECTED AND FOUND THE GLARESHIELD LIGHT BALLAST DEFECTIVE. THE GLARESHIELD LIGHTING WAS PLACED ON DEFERRAL AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: RETRACT PIN — CRACKED (LT MLG)

AFTER TAKEOFF AND GEAR RETRACTION, THE GEAR UNSAFE AND DOORS WARNING LIGHTS REMAINED ILLUMINATED AND WOULD NOT EXTINGUISH AFTER CYCLING. FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. GROUND INSPECTION FOUND THE LEFT MAIN LANDING GEAR RETRACT PIN BROKEN. MAINTENANCE REPLACED THE LEFT MAIN LANDING GEAR RETRACT PIN AND ACCOMPLISHED THE GEAR SWING IN ACCORDANCE WITH THE DOUGLAS OVERHAUL AND MAINTENANCE MANUALS 32-1-1 AND 32-60-0.

Part: CONTAINER — DAMAGED (CARGO COMPT)

ON TAKEOFF ROLL, DEPARTING LRD, POSITION 6 CONTAINER SHIFTED AFT, DUE TO ITS BASE BEING DISTORTED, JUMPING OVER THE FULLY ERECTED LOCKS TO POSITION 8. CREW ACCOMPLISHED REJECTED TAKEOFF PROCEDURE AND RETURNED TO THE BLOCKS. THE CONTAINER WAS DOWNLOADED AND REPLACED. MAINTENANCE PERFORMED A REJECTED TAKEOFF INSPECTION AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: CARGO CONTAINER — FUMES (CARGO COMPT)

ON CLIMB-OUT FROM TOL, FUMES ENTERED THE FLIGHT DECK, THE AIRCRAFT RETURNED TO TOL. THE EMERGENCY RESPONSE TEAM LOCATED THE SOURCE OF THE FUMES. THE FUMES WERE GENERATED BY NON-HAZARDOUS MATERIAL, AUTOMOTIVE PARTS, IN THE POSITION 4, UPPER DECK CONTAINER. THE PARTS WERE REMOVED AND THE AIRCRAFT RELOADED AND DEPARTED. THE MANUFACTURER INDICATED DURING THE MANUFACTURE PROCESS OF THE PARTS, THEY ARE CLEANED AND COATED WITH A CHEMICAL WHICH IS SPUN DRY, BAKED, AND THEN AIR DRIED FOR 24 HOURS TO DISSIPATE THE FUMES. THE ORIGINATING SHIPPING POINT HUMIDITY HAS BEEN EXTREMELY HIGH WHICH POSSIBLY HAMPERED THE AIR DRY FUME DISSIPATION. (M)

Part: SKIN — CRACKED (LT WING)

DURING FUEL LEAK TROUBLESHOOTING, TWO SMALL CRACKS WERE IDENTIFIED RADIATING OUT OF ONE RIVET HOLE ON LT WING LOWER EXTERIOR PLATING, JUST OUTBOARD OF NR 1 PYLON. CRACK LOCATION BETWEEN STRINGERS 60 AND 61. TOTAL CRACK LENGTH APPROXIMATELY ONE INCH. ACTION CLASSIFIED AS A MAJOR REPAIR, AND REQUIRES FAA APPROVAL. REPAIR IS ACCOMPLISHED IAW AAR OKLA REPAIR SKETCH. CRACK REPAIR TO LOWER WING SKIN BETWEEN STR 60 AND 61, OUTBOARD OF NR 1 PYLON. REV IR DATED 7-23-96. WHICH WAS FAA APPROVED ON FAA FORM 8110-3. BY DER SO-443. (M)

Part: CONTROL — NOT EFFECTIVE (ELEVATOR)

TAKEOFF OUT OF OAK WAS ABORTED AT 80 KT DUE TO AN ABNORMAL ELEVATOR EFFECTIVENESS CHECK. (M)

Part: FITTING — CRACKED (LT WING SPAR CAP)

DURING REPLACEMENT OF LT MLG TRUNNION FITTING, INSPECTION FOUND LT SPAR CAP FITTING CRACKED. THE SPAR CAP FITTING WAS REPLACED IAW DOUGLAS INSTALLATION GUIDE, THE AIRCRAFT SRM, AND MM. (X)

Part: ANGLE — CRACKED (SERVICE DOOR)

DURING ROUTINE C-CHECK INSPECTION, A CRACKED ANGLE ON THE RT AFT SERVICE DOOR WAS NOTED. THE ANGLE WAS REMOVED AND LOCALLY MANUFACTURED IAW DRAWING N821BX-04 WHICH WAS FAA DER APPROVED. THE NEW ANGLE WAS INSTALLED IAW AIRCRAFT SRM AND MM. (X)

Part: SKIN — CRACKED (BS 280)

DURING ROUTINE C-CHECK INSPECTION, A 1 INCH CRACK WAS FOUND AT FS 280, AND LONGERON 36. REPAIR OF THE CRACK WAS ACCOMPLISHED IAW AIRCRAFT SRM. (X)

Part: BULKHEAD WEB — CRACKED (BS 1766)

DURING ROUTINE C-CHECK, A 1 INCH CRACK WAS LOCATED IN THE AFT PRESSURE BULKHEAD, FS 1766, AT LONGERON 11 LEFT. REPAIR WAS ACCOMPLISHED IAW AIRCRAFT SRM AND SB 53-73. (X)

Part: SKIN — CRACKED (NLG WW)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS LOCATED AT THE NOSE WHEELWELL DOOR CUT-OUT. THE EXTERNAL PLATING WAS CRACKED AT THE RIGHT AFT CORNER. REPAIR OF THE CRACK WAS ACCOMPLISHED IAW AIRCRAFT SRM 53-2-1 WHICH INSTALLED AN EXTERNAL REPAIR DOUBLER. (X)

Part: FITTING — CRACKED (SERVICE DOOR)

DURING ROUTINE C-CHECK INSPECTION, A CRACKED FITTING ON THE LT AFT SERVICE DOOR WAS FOUND. THE FORWARD UPPER FITTING EXHIBITED A .250 INCH CRACK. THE FITTING WAS REMOVED AND REPLACED IAW THE AIRCRAFT SRM. (X)

Part: SKIN — CRACKED (WS 585)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND IN THE RIGHT LEADING EDGE. THE CRACK MEASURED 6 INCHES AND WAS LOCATED AT XFS 585. THE REPAIR WAS ACCOMPLISHED IAW AIRCRAFT SRM. SRM REFERENCE 57-2-1. (X)

Part: LONGERON — CORRODED (FS 980/1060)

DURING ROUTINE C-CHECK AND CORROSION PREVENTION AND CORROSION CONTROL INSPECTION, LEVEL 2 CORROSION WAS FOUND BETWEEN FS 980 AND FS 1060, LONGERON 31 LEFT. THE LONGERON WAS REMOVED AND REPLACED IAW AIRCRAFT SRM. CORROSION DAMAGE WAS CONFINED TO THE LONGERON. (X)

Part: FITTING — CRACKED (BS 857)

DURING ROUTINE C-CHECK INSPECTION, A 1.25 INCH CRACK WAS FOUND ON THE STA 857 FITTING OF LONGERON 24. REPAIR ON THE LONGERON FITTING WAS ACCOMPLISHED IAW THE AIRCRAFT SRM. SRM REFERENCE 53-2-2. (X)

Part: SKIN — CRACKED (PASSENGER DOOR)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND IN THE PLATING OF THE LT FORWARD ENTRY DOOR. THE CRACK WAS LOCATED AT THE UPPER AFT CORNER. REPAIR TO THE EXTERNAL PLATING WAS ACCOMPLISHED IAW AIRCRAFT SRM. (X)

Part: TRUNNION — CRACKED (LT MLG)

DURING ROUTINE C-CHECK INSPECTION, THE LT MLG TRUNNION FITTING WAS FOUND CRACKED. INSPECTION WAS ACCOMPLISHED IAW SB 57-94. THE CRACK WAS LOCATED, 8 INCHES, IN THE FORWARD LANDING GEAR ATTACH LUG. THE FITTING WAS REMOVED AND REPLACED IAW DOUGLAS INSTALLATION GUIDE, SRM, AND MM. THE BRAKE PLUMBING WAS CONFIRMED TO BE PROPERLY CONNECTED IAW DOUGLAS AOL 8-1091, JOB CARD 74201. (X)

Part: LONGERON — CRACKED (RT FUSELAGE)

DURING ROUTINE C-CHECK INSPECTION. LONGERON 24 WAS FOUND WITH 2 CRACKS. THE RT LONGERON 24 HAD BOTH A 7 INCH AND 1 INCH CRACK AT SEPARATE LOCATIONS. THE LONGERON WAS REMOVED AND REPLACED IAW THE AIRCRAFT SRM, DOUGLAS INSTALLATION GUIDE, AND THE MM. (X)

Part: FITTING — CRACKED (FS 260)

DURING ROUTINE C-CHECK INSPECTION. LONGERON AND FITTINGS AT SEVERAL LOCATIONS WERE FOUND CRACKED. END FITTINGS AT FS 260, AND LONGERONS 34 AND 35 LEFT AS WELL AS LONGERON 36. ALL FITTINGS WERE REPLACED WITH NEW IAW AIRCRAFT SRM. (X)