N820BX

Part: FITTING — CRACKED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STA 902.000 LONGERON 5 LT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA.INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, AND SRM 51-3-1.

Part: SKIN — DENTED (RT WING TE FLAP)

( SPUY) DURING ROUTINE C-CHECK INSPECTION, RT WING INBD FLAP - FWD UPPER SURFACE SKIN PANEL SHOWS DENTS ( STA XW 104.000-122.000)

Part: SKIN — DENTED (RT WING TE FLAP)

( SPUY) DURING ROUTINE C-CHECK INSPECTION, RT WING OTBD FLAP - AFT LOWER SURFACE SKIN PANEL SHOWS INTERM REPAIR AND DENT ( STA XF375.00-415.00).

Part: ANGLE — CRACKED (BS 1690)

(SPUY) DURING ROUTINE C-CHECK INSPECTION, AFT FUSELAGE INTERNAL SECTION- RING ANGLE CRACKED AT STA FS 1690.000 BETWEEN 30L AND L36.

Part: DOUBLER — WORN (FUSELAGE)

(SPUY) DURING ROUTINE C-CHECK INSP, FUSELAGE NOSE SECTION, INTERNAL DOUBLER WORN AND BROKEN AT STA FS-156.00 (THRU NR 2 ACCESS DOOR. GROUND PNEU CONNECTION).

Part: SKIN — DAMAGED (LT WING TE FLAP)

( SPUY) DURING ROUTINE C-CHECK INSPECTION, LT WING INBD FLAP - AFT UPPER SURFACE SKIN PANEL SHOWS SCRATCHES AND (05EA) DENTS (STA XW 1.000 - 91.000).

Part: HOOK — CRACKED (DOOR HOLD OPEN)

( SPUY) DURING ROUTINE C-CHECK INSPECTION, FUSELAGE NOSE SECTION SKIN - FWD PASSENGER DOOR HOLD OPEN HOOK CRACKED .5" AT STA FS 15,000, L-16.

Part: STRUCTURE — CRACKED (LT WING)

(SPUY) DURING ROUTINE C-CHECK INSPECTION, LT OTBD WING L/E INNER SECTION. LOWER PLATING CRACKED AT STA XFS 597.500.

Part: FINGER DOUBLER — CORRODED (FLOOR WEB)

(SPUY) DURING ROUTINE C-CHECK INSP, FLIGHT COMPARTMENT - HORIZ PRESS PANEL (SUB FLOOR) FINGER DOUBLER CORRODED AT STA 58.000 AND LBL 19.

Part: SKIN — CRACKED (ZONE 500) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND FWD CARGO COMPARTMENT INTERNAL SKIN CORRODED AT STA FS 285.000 LONGERON 35 RT- LONGERON 36. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS, FILLERS, REPAIR PLUGS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 04/15/10, DWG ED-5114 DATED 04/08/10, SRM 51-1-8 PAGES 17-18, SRM 53-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, DPS 7.00-5 REV 6, SRM 51-1-21, SRM 51-1-20D, SRM 51-1-14, AND SRM 51-3-1.

Part: FINGER DOUBLER — CORRODED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND FLIGHT COMPARTMENT HORIZONTAL PRESS PANEL (SUB FLOOR) FINGER DOUBLER CORRODED AT STA 58.000 LT BOTTOM LINE 19. REMOVED CORRODED DOUBLER. REMOVED DAMAGED AREA. FABRICATED DOUBLERS, SEGMENT PANEL, SPLICE. CLEANED, TREATED PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DWG SR08530026 IPI NR 2010277, SRM 51-1-21, SRM 51-1-8B, SRM 53-3-1, FIGURE 7 SHEET 1,2, ITEM "A"; DPS 4.710 REV. "L", 51-1-20D, 51-1-11, 51-3-0, AND 51-3-1.

Part: FITTING — CRACKED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

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

Part: SEAT TRACK — CRACKED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND MAIN CARGO COMPARTMENT NR 5 SEAT TRACK LUG BROKEN AT STA 148.00-1570.000. REMOVED DAMAGED SEGMENT OF TRACK. REMOVED EXISTING FWD SPLICE HAT AND SPLICE PLATE. FABRICATED SPLICE HAT, AND SPLICE PLATE. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED TRACK SEGMENT, AFT SPLICE HAT AND SPLICE PLATE AND REINSTALLED FWD SPLICE HAT AND SPLICE PLATE. IAW DC8 SRM CHAPTER 53-2-3 FIGURE 8A PAGE 36A, SRM 53-2-3, SRM 53-2-3, SRM 51-1-8B, SRM 51-1-20D, SRM 53-2-3, AND SRM 51-3-1.

Part: ANGLE — CRACKED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND AFT FUSELAGE INTERNAL SECTION RING ANGLE CRACKED AT STA FS 1690.000 LONGERON 30, LT LONGERON 36. REMOVED CRACKED RING ANGLE. FABRICATED SPLICES. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAPTER 53-2-5 FIGURE 8C-1 SHEET 2, SRM 51-3-0, SRM 51-1-21, SRM 51-1-8B, SRM 53-2-5, SRM 51-1-1 PAGES 1, 13, 17, AND SRM 51-3-1.

Part: SEAT TRACK — CRACKED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C CHECK INSP FOUND MAIN CARGO COMPARTMENT NR 4 SEAT TRACK LUG BROKEN AT STA 590.000. REMOVED DAMAGED SEGMENT OF TRACK. REMOVED EXISTING FWD SPLICE HAT AND SPLICE PLATE. FABRICATED SPLICE HAT, AND SPLICE PLATE. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED TRACK SEGMENT, AFT SPLICE HAT AND SPLICE PLATE AND REINSTALLED FWD SPLICE HAT AND SPLICE PLATE. IAW SRM CHAPTER 53-2-3 FIGURE 8A PAGE 36A, SRM 53-2-3, SRM 53-2-3, SRM 51-1-8B, SRM 51-1-20D, SRM 53-2-3, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 92,081 hrs · 38,426 cycles

DURING C-CHECK INSP, FOUND RT WING OTBD FLAP AFT LOWER HAS IMPROPER REPAIR AT STA XF 375.000 - 415.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIG 4, T/R NR 57-94, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 51-1-9 TR NR 51-142, SRM 51-1-9A TR NR 51-141, DPS 1.950 REV "AR" R-1, AND SRM 51-1-21.

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING OTBD FLAP FWD UPPER SKIN HAS IMPROPER REPAIR AT STA XF 432.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 1, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9 TR NR 51-142, SRM 51-1-9A TR NR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: SKIN — DENTED (ZONE 600) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND RT WING INBD FLAP FWD UPPER SURFACE SKIN HAS DENTS AT STA XW 104.000 - 122.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 1, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 51-1-21, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (RT WING TE FLAP) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND RT WING OTBD FLAP FWD LOWER SKIN IMPROPER REPAIR AT STA XF 227.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN AND INNER STRAP. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS.INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 04/07/10, DWG ED-5087 DATED 03/19/10, SRM 51-1-21, NDT SPM PART 06-10-01-001, DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-5 REV "U", SRM 51-1-8B, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C CHECK INSP FOUND LT WING OTBD FLAP AFT LOWER SKIN PANEL HAS IMPROPER REPAIR AT STA XF 304.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 4 T/R 57-94, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 57-7-1 FIGURE 4 TR 57-94 ITEM "A", DPS 4.710, AND SRM 51-1-21.

Part: SKIN — DENTED (LT WING) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING INBD FLAP AFT UPPER SURFACE SKIN HAS SCRATCHES AND DENTS AT STA XW 2.000 - 91.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 1, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9 TR NR 51-142, SRM 51-1-9A TR NR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C CHECK INSP, FOUND LT WING OTBD FLAP FWD LOWER SKIN HAS IMPROPER REPAIR AT STA XF 193.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-7-1 FIGURE 1, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9 TR NR 51-142, SRM 51-1-9A TR NR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: FITTING — CRACKED (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND MAIN CARGO COMPARTMENT CTR WING FITTING CRACKED AT STA FS 702.000 LONGERON 21 RT AND LONGERON 20 RT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-3-1, AND SRM 51-1-8B.

Part: HOOK — CRACKED (DOOR HOLD OPEN) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND FWD PASSENGER DOOR HOLD OPEN HOOK CRACKED AT STA FS 15.000 LONGERON 16 LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO CRACKS OR CORROSION NOTED. FABRICATED REPAIR DOUBLERS, FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 04/09/10, DWG ED-5086 DATED 03/12/10, SRM 51-1-21, SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — BROKEN (ZONE 100) · airframe 92,081 hrs · 38,426 cycles

DURING ROUTINE C-CHECK INSP FOUND FUSELAGE NOSE SECTION INTERNAL DOUBLER WORN AND BROKEN AT STA FS -156.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO CRACKS OR CORROSION NOTED. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS, INNER SPLICE DOUBLERS CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 04/07/10, DWG ED-5096 DATED 03/18/10, SRM 51-1-21, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: ENGINE — POWER LOSS (NR 2) · airframe 91,761 hrs · 38,263 cycles

DURING CRUISE, SHUT DOWN NR 2 ENGINE DUE TO POWER LOSS AND VIBRATION. CREW LANDED WITHOUT FUTHER INCIDENT. MAINTENANCE REPLACED NR 2 ENGINE. OPERATIONAL CHECK GOOD IAW ATI ERH 70.01. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 31 LONGERON 30.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 5, DER DRAWING 53-09133-3 DATED 4/8/09.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS160 LONGERON 22 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 5, DER DRAWING 53-09133-3 DATED 4/8/09.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 349. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 8 SHEET 2.

Part: SKIN — MISREPAIRED (BS 1204) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS1204 LONGERON 16.25. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIGURE 22A SHEET 11.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1718 LONGERON 17.5. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIGURE 22A SHEET 11.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 143 LONGERON 28.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 5, DER DRAWING 53-09133-3 DATED 4/8/09.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS287 LONGERON 35.5 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 5, DER DRAWING 53-09133-3 DATED 4/8/09.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS363 LONGERON 36. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 8 SHEET 2.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 91,196 hrs · 38,031 cycles

DURING ROUTINE CPCP INSPECTION, FOUND IMPROPER REPAIR AT STATION FS 1348 LONGERON 35.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. NO CRACK’S OR CORROSION NOTED. MANUFACTURED REPAIR PARTS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 2 SHEET 2.

Part: INDICATION SYS — MALFUNCTIONED (OIL SYSTEM) · airframe 91,026 hrs · 37,932 cycles

DURING CRUISE NR 2 ENG OIL QUANTITY INDICATED 0, OIL PRESSURE 25 PSI, OIL TEMP FLUCTUATING 70C. THE CREW SHUTDOWN NR 2 ENG. OIL QUANTITY RETURNED NORMAL, OIL PRESSURE INDICATED 0-3 PSI. ON APPROACH N2 INDICATED 0 RPM, N1 INDICATED 10 RPM, AIRSPEED 170 KNOTS OR LESS. THE CREW RETURNED TO DEPARTURE, LANDED WITHOUT FURTHER INCIDENT. MX COMPLETED CFM FAULT CODE 60, BOROSCOPED BLADES AND SUMP SEAL. NO DEFECTS NOTED. REMOVED NR 1 SUMP SCAVENGE TUBE. NO OBSTRUCTION NOTED. RAN NR 2 ENGINE AT MAX POWER FOR 20 MINUTE. OPS CHECK GOOD IAW MM 71-00-0, 79-21-10, 72-21-00, AND ERH 70.01. ACFT WAS RETURNED TO SERVICE.

Part: PRESSURE SWITCH — DEFECTIVE (ENGINE OIL) · airframe 90,945 hrs · 37,894 cycles

DURING TAKEOFF FROM KTOL AT APPROXIMATELY NINTY KNOTS THE CREW HAD A NUMBER TWO LOW OIL PRESSURE LIGHT FLICKER FOR ABOUT 1/2 SECOND WHILE SETTING MAX POWER OF EIGHTY-SEVEN PERCENT N1. POWER WAS AT ABOUT EIGHTY-SIX PERCENT AT THE TIME THEN LIGHT CAME ON STEADY FOR ABOUT 1 SECOND AND THE CAPTAIN ABORTED THE TAKEOFF. AS POWER WAS RETARDED LOW OIL PRESSURE LIGHT WENT OUT IMMEDIATELY. MAINTENANCE REPLACED THE LOW OIL PRESSURE SWITCH. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE WARNING — ILLUMINATED

DURING CRUISE, THE NR (3) FIRE WARNING CAME ON. THE CREW ACCOMPLISHED THE APPROPRIATE CHECK LIST AND DISCHARGED BOTH FIRE BOTTLES, AND CONTINUED TO DESTINATION AND LANDED WITHOUT INCIDENT. CORRECTIVE ACTION IN PROGRESS (K)

Part: FIRE DETECTOR — MALFUNCTIONED (NR 3 NACELLE) · airframe 90,597 hrs · 37,649 cycles

FLT NR: ATN 820/KDFW TO KIAH. DURING CRUISE FROM KDFW TO KIAH THE NR 3 FIRE WARNING CAME ON. THE CREW ACCOMPLISHED THE APPROPRIATE CHECK LIST AND DISCHARGED BOTH FIRE BOTTLES, AND CONTINUED TO KIAH AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED LT FAN, RT CORE, PYLON FIRE SENSING ELEMENT, LT CORE CONNECTOR, AND BOTH FIRE BOTTLES. OPERATIONAL CHECK GOOD IAW MM 26-11-16, 26-11-15 AND 26-21-09. AIRCRAFT WAS RETURNED TO SERVICE. (A)

Part: FIRE WARNING — ILLUMINATED (NR 2)

DURING CRUISE, NR 2 FIRE WARNING CAME ON, THE CREW DISCHARGED BOTH FIRE BOTTLES AND SHUTDOWN NR (2) ENGINE. CREW LANDED WITHOUT INCIDENT. IN WORK. (K)

Part: INDICATOR — INOPERATIVE (AIRSPEED)

ON TAKEOFF ROLL, CAPTAIN AIRSPEED DID NOT REGISTER 80 KNOTS (ANALOG NEEDLE AT ZERO, DIGITAL READOUT ERROR). CREW REJECTED TAKEOFF AT 80 KNOTS, THE CREW RETURNED TO BLOCKS WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED CAPTAIN MACH AIRSPEED INDICATOR OPERATIONAL AND LEAK CHECK GOOD IAW MM 34-12-1. MAINTENANCE ALSO ACCOMPLISHED REJECTED TAKEOFF INSPECTION IAW , NO DEFECTS NOTED. AC WAS RETURNED TO SERVICE. (K)

Part: CONTROL VALVE — LEAKING (HYD SYSTEM)

ON CLIMBOUT FROM KPHL HYDRAULIC PRESSURE WENT TO ZERO, HYDRAULIC FLUID LEVEL TO STANDPIPE, THE CREW DECLARED EMERGENCY AND LANDED INTO KTOL WITHOUT INCIDENT. MAINTENANCE INSPECTED HYDRAULIC SYSTEM AND FOUND SLOT CONTROL VALVE LEAKING, MAINTENANCE REPLACED SLOT CONTROL VALVE AND SERVICED HYDRAULIC SYSTEM. OPERATIONAL CHECK GOOD IAW DACO DC-8 MM 27-80-4. AIRCRAFT RETURNED TO SERVICE. (B)

Part: TERMINAL — DEFECTIVE (FIRE LOOP) · airframe 90,488 hrs · 37,576 cycles

DURING CLIMB FROM KSJC TO KRFD NUMBER ONE ENGINE FIRE WARNING LIGHT AND BELL CAME ON INTERMITTENTLY. ALL ENGINE INSTRUMENT INDICATIONS WERE NORMAL. WHEN THROTTLE WAS REDUCED TO IDLE FIRE INDICATION CAME BACK AND SILENCED ON IT'S OWN. THE CREW RAN THE QRH CHECKLIST WITH NO OTHER INDICATION. THE CREW RETURNED TO KSJC AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE FIRE WARNING SYSTEM AND FOUND THE FORWARD LEFT HAND LOWER FIRE LOOP GROUND CONNECTION BAD. MAINTENANCE SPLICED ON A NEW GROUND TERMINAL AND CLEANED THE FIRE LOOP CONNECTOR. MAINTENANCE PERFORMED A SHAKEDOWN TEST OF ALL FIRE LOOPS AND CONNECTORS, NO FURTHER DEFECTS WERE NOTED IAW UAL MAINTENANCE MANUAL 26-11-02 AND 26-11-07. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE LOOP — INTERMITTENT (NR ENGINE) · airframe 90,489 hrs · 37,577 cycles

DURING CRUISE FROM KSJC TO KRFD NUMBER ONE ENGINE FIRE INDICATION AT FL 350 WITH FIRE WARNING LIGHT ON. AFTER SILENCING THE BELL THE CREW DISCHARGED THE FIRE AGENT, AFTER THIRTY SECONDS THE FIRE LIGHT REMAINED ON AND THE CREW DISCHARGED THE SECOND BOTTLE AND THE FIRE LIGHT WENT OUT. THE FIRE LIGHT CAME BACK ON AT FL 096 AND REMAINED ILLUMINATED. THE CREW LANDED AT KRNO WITHOUT INCIDENT. MAINTENANCE INSPECTED NUMBER ONE ENGINE AND FOUND NO EVIDENCE OF FIRE, MAINTENANCE DID FIND RIGHT FAN CASE LOOP WOULD DROP FROM 2.M OHMS INTO K OHMS INTERMITTENTLY CENTER PIN TO GROUND. MAINTENANCE REPLACED RIGHT FAN CASE LOOP, LEFT FAN CASE LOOP, UPPER PYLON LOOP, AND NUMBER ONE ENGINE FIRE DETECTOR. OPERATIONAL CHECK GOOD IAW W/D 26-01-01, ERH 70.1. AIRCRAFT RETURNED TO SERVICE.

Part: CONTROLLER — MALFUNCTIONED (WINDSHIELD HEAT) · airframe 90,411 hrs · 37,539 cycles

DURING CLIMB-OUT FROM KTOL, FIRST OFFICERS WINDSHIELD SHATTERED IN FLIGHT CLIMBING THROUGH 25000 FT. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED FIRST OFFICERS WINDOW AND WINDOW TEMP CONTROLLER. OPERATIONAL CHECK WAS GOOD IAW DACO MAINTENANCE MANUAL 56-10-2. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONNECTOR — DAMAGED (FIRE LOOP) · airframe 90,391 hrs · 37,518 cycles

DURING CRUISE FROM KLAX TO KTOL THE CREW HAD A FIRE WARNING INDICATION ON NUMBER ONE ENGINE, ALL PARAMETERS WERE WITHIN NORMAL LIMITS. NUMBER ONE ENGINE WAS SHUTDOWN IAW THE QRH AND THE INBOARD FIRE BOTTLE WAS DISCHARGED. THE FIRE WARNING INDICATION EXTINGUISHED AND THE CREW CONTINUED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE FIRE WARNING SYSTEM AND FOUND A BAD CONNECTOR AT NR 1 ENG PYLON FIRE LOOP. MAINTENANCE REPLACED THE CONNECTOR AND REPLACED NR 1 ENG PYLON FIRE LOOP IAW MM 26-10-1. ALSO IAW MM 20-50-1. MAINTENANCE RAN NR 1 ENG AND TESTED FIRE WARNING, NO DEFECTS NOTED IAW ATI ERH 70.01. C/W ATI GMM 3.116 NR 1 ENG FIRE WARNING OP'S NORMAL AT THIS TIME. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATOR — FAILED (AIRSPEED) · airframe 90,374 hrs · 37,511 cycles

DURING CLIMB-OUT FROM KTOL, THE CREW NOTICE V1=134 NOTICE HESITATION IN AIR SPEED INCREASE AT VR AT 151 AIRSPEED FAILED TO INCREASE IN EXTERNAL MODE. WHEN SWITCH TO STANDBY AIRSPEED INDICATE 220KTS WHICH MATCHED TO FMS SPEEDS. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND FOUND PITOT STATIC LINE AT DRAIN BROKEN. REPLACED PITOT LINE OPERATIONAL CHECK GOOD IAW DACO DC-8 MAINTENANCE MANUAL 34-12-0, AND ATI JOB CARD 34.12.1. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE LOOP — SHORTED (NR 1 NACELLE) · airframe 90,332 hrs · 37,496 cycles

DURING CRUISE FROM KBFI TO KPDX AT FL160 NUMBER ONE ENGINE FIRE WARNING BELL AND LIGHT CAME ON. THE MASTER FIRE WARNING WOULD NOT SILENCE BELL. THE FIRE LIGHT AND BELL BECAME INTERMITTENT WHILE THE CREW RAN THE APPROPRIATE CHECKLIST. THE CREW SHUTDOWN NUMBER ONE ENGINE AND THE LIGHT STAYED ON. THE CREW FIRED ONE AGENT AND AFTER 30 SECONDS THE LIGHT AND BELL WERE STILL ON, THE CREW FIRED THE SECOND AGENT AND THE LIGHT AND BELL EXTINGUISHED. THE CREW LANDED THE AIRCRAFT WITHOUT INCIDENT. MAINTENANCE INSPECTED NUMBER ONE ENGINE INTERNALLY AND EXTERNALLY AND FOUND NO EVIDENCE OF FIRE. MAINTENANCE CHECKED ALL FIRE LOOP AND FOUND TOP LOOP AT HOT SECTION SHORTED. MAINTENANCE REPLACED LOOP AND NUMBER ONE AND NUMBER TWO FIRE BOTTLES. OPERATIONAL CHECK GOOD IAW DACO DC8-MAINTENANCE MANUAL 26-10-1, DACO DC8-MAINTENANCE MANUAL 26-20-1, ERH 70.01.1. AIRCRAFT WAS RETURNED TO SERVICE.

Part: TRANSFER VALVE — DEFECTIVE (FUEL SYSTEM) · airframe 90,232 hrs · 37,444 cycles

AFTER ROTATION FROM KLRD AIRCRAFT DID A UNCOMMANDED YAW TO THE LEFT AND RIGHT, THE CREW TURNED YAW DAMPER OFF AND OSCILLATION DAMPENED OUT. THE CREW RETURNED TO KLRD AND LANDED WITH OUT INCIDENT. MAINTENANCE DEFERRED THE AUTO PILOT SYSTEM IAW ATI MEL 22-01-00 TO KTOL. MAINTENANCE IN KTOL INSPECTED THE AUTO PILOT SYSTEM AND REPLACED YAW DAMPER TRANSFER VALVE, OPERATIONAL CHECK GOOD IAW UAL DC8 MAINTENANCE MANUAL 22-10-37. AIRCRAFT WAS RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (ZONE 700) · airframe 89,797 hrs · 37,245 cycles

DURING TAKEOFF FROM KLRD, THE NOSE WHEEL STEERING WAS VERY SLOW TO RESPOND TO TILLER. THE CREW REJECTED TAKEOFF DUE TO UNABLE TO HOLD AIRCRAFT TO CENTER LINE OF RUNWAY ON INITIAL TAKEOFF ROLL. THE CREW RETURNED TO BLOCKS AT KLRD WITHOUT INCIDENT. MAINTENANCE INSPECTED NOSE WHEEL STEERING SYSTEM ACCUMULATOR SERVICED AS REQUIRED. INSPECTED AND LUBED ALL CABLES FOR STEERING, CHECKED TIRE PRESSURE, ACCOMPLISHED OPERATIONAL CHECK GOOD IAW DC8 MAINTENANCE MANUAL 32-52-6, N/R J/C NUMBER 13.01-5, AND ATI ERH 09.01-1. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — LEAKING · airframe 89,400 hrs · 37,062 cycles

DURING CRUISE FROM KRFD TO KLRD, THE CREW OBSERVED THE NUMBER THREE ENGINE OIL QUANTITY DECREASING. THE ENGINE WAS SHUTDOWN FOR LOSS OF OIL QUANTITY. THE CREW LANDED AT KLRD WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT THE SYSTEM AND FOUND THE LEAK WAS FROM THE DRAIN MAST. MAINTENANCE ISOLATED THE LEAK TO THE TRANSFER GEARBOX MANUAL HAND CRANKING DRIVE PAD. MAINTENANCE CAPPED THE DRAIN LINE PER UAL DC-8 M/M 71-70-02. MAINTENANCE RAN THE ENGINE AFTER CAPPING THE LINE AT IDLE AND HIGH POWER SETTINGS, NO LEAK NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PROXIMITY SENSOR — DEFECTIVE (ZONE 700) · airframe 89,111 hrs · 36,954 cycles

DURING CLIMB OUT OF KTOL AFTER GEAR WAS RETRACTED THE DOOR LIGHT REMAINED ON AFTER UPLATCH CHECK. THE CREW DID ALL NECESSARY PROCEDURES AND RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND PROXIMITY CONTROL SWITCH FAILED BITE TEST. MAINTENANCE REPLACED PROXIMITY CONTROL SWITCH AND OPERATIONAL CHECK WAS GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: SKIN — DAMAGED (ZONE 300) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER HAS ELONGATED HOLES AT LEADING EDGE STATION XFS 285.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PASTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0 DC8 NDT PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SEMAN DRAWING NUMBER ED 4443 DATED 01-24-07 AND COMPLETED FAA FORM 8110-3 NUMBER 07031 DATED 01-26-07.

Part: SKIN — CRACKED (LT WING) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING-EXTERNAL UPPER SKIN CRACKED AT STATION XRS74.000 STRINGER 14. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 57-2-1 FIGURE 10 SHEET 3, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 57-3-1 FIGURE 10 PAGE 17 ITEM "A", DC8 SRM 51-10-0, FIGURE 1 SHEET 6, DC8 SRM 51-1-8B, DC8 SRM 51-1-12 AND DC8 SRM 51-3-1.

Part: SKIN — CRACKED (LT WING) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING-EXTERNAL UPPER SKIN CRACKED AT STATION XRS74.000 STRINGER 12. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 57-2-1 FIGURE 10 SHEET 3, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 57-3-1 FIGURE 10 PAGE 17 ITEM "A", DC8 SRM 51-10-0, FIGURE 1 SHEET 6, DC8 SRM 51-1-8B, DC8 SRM 51-1-12 AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 200) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS680.000, LONGERON 2 LEFT. REMOVED CRACKED FITTING CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-21 SRM 51-1-20D, DC8 SRM 51-3-1 PAGE 2A AND DC8 SRM 51-1-8B.

Part: VANE — MISREPAIRED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LEADING EDGE SLOT VANE HAS A NON STANDARD REPAIR FROM STATION XFS521.000 TO STATION XFS527.000. REMOVED EXISTING NON STANDARD REPAIRS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVAL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4437 DATED 01-17-07. COMPLETED FAA FORM 8110-3 NUMBER 07019 DATED 01-18-07.

Part: DOUBLER — CORRODED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING INTERNAL DOUBLER CORRODED FROM STATION FS 1640.000 TO STATION FS 1660.000 AND FROM LONGERON 29 RIGHT TO LONGERON 33 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 51-1-21, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, SEMAN DRAWING NUMBER ED-4431 DATED 01-23-07 AND COMPLETED FAA FORM 8110-3 NR 07

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS367, LONGERON 20 LEFT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1, 4 AND 5, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 53-4-1 FIGURE 6 ITEM "B", DC8 SRM 51-9-0 FIGURE 68A, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 300) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR LOWER SKIN PANEL HAS A NON STANDARD REPAIR FROM STATION XE79.531 TO STATION XE89.718. REMOVED EXISTING SKIN PANEL WITH NON STANDARD REPAIR. FABRICATED NEW SKIN PANEL AND FINGER DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL FROM STATION XAR0.00 TO STATION XE132.000. PERFORMED BALANCE, FOUND WITHIN TOLERANCE, MOMENT 1454.8 INCH POUNDS. IAW DC8 SRM 51-4-4 PAGES 1-4, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2, ITEMS "E" AND "F", DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: FITTING — CRACKED (BS 980 L22R) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS 980.000 LONGERON 22 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: FASTENER — WRONG PART (ZONE 300) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR LOWER SKIN PANEL HAS IMPROPER FASTENERS FROM STATION XE306.062 TO STATION XE273.875. REMOVED EXISTING SKIN PANEL WITH IMPROPER FASTENERS. FABRICATED NEW SKIN PANEL AND FINGER DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL INNER SURFACE. INSTALLED NEW SKIN PANEL FROM STATION XE246.000 TO STATION XH285.000. PERFORMED BALANCE, FOUND WITHIN TOLERANCE MOMENT 1454.8 INCH POUNDS IAW DC8 SRM 51-4-4 PAGES 1-4, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2 ITEMS E AND F, DC8 SRM 55-1-0 PG 1, DC8 SRM 51-1-21, DC8 SRM 51-1-9 AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD FLAP UPPER SKIN PANEL HAS A NON STANDARD REPAIR FROM STATION XF169.000 TO STATION XF172.000. REMOVED EXISTING SKIN PANEL WITH NON STANDARD REPAIR. FABRICATED NEW SKIN PANEL AND REPAIR PARTS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA, NEW SKIN PANEL AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 PAGE 2 TR NR 57-94 DATED 10-01-02, ITEM "P" AND "Q", DC8 SRM 51-1-9, DC8 SRM 51-1-8B AND DC8 SRM 51-1-11.

Part: SKIN — DAMAGED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LOWER FUSELAGE SKIN HAS SCRATCHES AND SMALL DENT AT STATION FS1870 LONGERON 36. REMOVED DAMAGED SKIN PANEL. CLEANED TREATED AND PRIMED AREA AND NEW SKIN PANEL. APPLIED SEALANT TO FAYING SURFACES INSTALLED NEW SKIN PANEL FROM STATION FS 1696 TO STATION 1890, LONGERON 28 RIGHT TO LONGERON 28 LEFT IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 53-5-1 FIGURE 1 ITEM "E", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, BOEING MESSAGE NUMBER 1-271850875-2 DATED 01-10-07.

Part: SKIN — CRACKED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT UPPER OUTBOARD FLAP CRACKED AT STATION XF442.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND REPAIR PARTS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA, NEW SKIN AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIGURE 4 ITEMS "U" AND "Q", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LEADING EDGE HAS A NON STANDARD REPAIR FROM STATION XFS416.000 TO STATION XOLDI6.220. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51.3.1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SEMAN DRAWING ED-4436 DATED 01-18-07, COMPLETED FAA FORM 8110-3 NUMBER 07026 DATED 01-22-07.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LEADING EDGE HAS A NON STANDARD REPAIR FROM STATION XFS304.000 TO STATION XFS310.000. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001,DC8 SRM 51-18B, DC8 SRM 51-1-11. SEMAN DRAWING NUMBER ED-4435 DATED 01-20-07 AND COMPLETED FAA FORM 8110-3 NUMBER 07026 DATED 01-22-07.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING LOWER CENTRAL LEADING EDGE HAS A NON STANDARD REPAIR FROM STATION XFS304.000 TO XFS316.000. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SEMAN DRAWING NUMBER ED-4433 DATED 01-22-07 AND COMPLETED FAA FORM 8110-3 NUMBER 07031 DATED 01-26-07.

Part: LONGERON — CORRODED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LONGERON 25 RIGHT CORRODED AT STATION 1620.000. REMOVED FASTENERS. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED LONGERON SECTION AND FABRICATED NEW LONGERON SECTION. PERFORMED HEAT TREATMENT. PERFORMED NDT INSPECTION. FABRICATED SPLICES. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-2 FIGURE 4A, DC8 SRM 51-1-8 PAGES 17 AND 18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 53-2-2 FIGURE 4A, DC8 SRM 53-4-1 FIGURE 42 SHEET 2 ITEM "E", DC8 SRM 51-2-0 FIGURE 50, DC8 SRM 51-1-1 PAGES 1, 13 AND 17, DC8 NDT SPM PART 08-00-02, DC8 SRM 53-2-2 FIGURE 10 SHEET 1 AND 3, TR NUMBER 53-153, DATED 12-10-02, DC8 SRM 53-2-2 FIG 10 SHEET 4

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LEADING EDGE HAS A NON STANDARD REPAIR FROM STATION XFS422.000 TO STATION XOLDI6.220. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51.3.1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11,SEMAN DRAWING ED-4436 DATED 01-18-07, COMPLETED FAA FORM 8110-3 NUMBER 07026 DATED 01-22-07.

Part: FITTING — CRACKED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION FOUND A CRACKED FITTING AT STATION FS 824.000 LONGERON 14 RIGHT. REMOVED CRACKED FITTING. FABRICATED FITTING. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED FITTING IAW DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DC8 NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-8B AND DOUGLAS DRAWING NUMBER 4751643.

Part: SKIN — CORRODED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING UPPER LEADING EDGE CORRODED, BETWEEN STATIONS XFS341.500 AND XFS304.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 51-1-20D, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-1 FIGURE 2G, DC8 SRM 57-2-1, FIGURE 44 DC8 SRM 57-3-1 PAGE 8 FIGURE 4 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-0 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A NON STANDARD REPAIR AT STATION FS12.000 LONGERON 27 RIGHT. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION FOUND. AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW UNITED AIRLINES DC8 MM 53-30-09 PAGES 201-209, DC8 SRM 51-1-21, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT OUTBOARD FLAP HAS A NON STANDARD REPAIR AT STATION XF240.000. REMOVED EXISTING REPAIR. REMOVED DAMAGED SKIN. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED NEW SKIN AND REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA, NEW SKIN AND REPAIR PARTS. INSTALLED NEW SKIN AND REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-3-1, AND SEMAN DRAWING NUMBER ED-4430 DATED 01-13-07. COMPLETED FAA FORM 8110-3 NUMBER 07021 DATED 01-19-07

Part: SKIN — MISREPAIRED (ZONE 300) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR LOWER PANEL HAS A NON STANDARD REPAIR FROM STATION XE55.062 TO STATION XE65.156. REMOVED SKIN PANEL WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN PANEL AND REPAIR PARTS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL INNER SURFACE. APPLIED SEALANT TO FAYING SURFACE. INSTALLED NEW SKIN PANEL AND REPAIR PARTS. PERFORMED RIGHT ELEVATOR BALANCING. FOUND WITHIN TOLERANCE, MOMENT 1471.4 IN-LBS IAW DC8 SRM 51-4-4 PAGE 1-4, DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1-2 ITEM "E” AND "F", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT HAND UPPER OUTBOARD FLAP HAS A NON STANDARD REPAIR AT STATION XF210.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. IAW DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIGURE 4 ITEM "C", DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: SKIN — CORRODED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING UPPER FORWARD SKIN CORRODED AT STATION XFS410.250. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND DAMAGE OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 57-2-1 FIGURES 16 AND 38 PAGE 2 TR NUMBER57-85 DATED 11-22-2000, DC8 SRM 51-1-8 PAGES 17 AND 18, DC8 SRM 57-2-1 FIGURE 2G, DC8 SRM 57-2-1 FIGURE 38, DC8 SRM 57-3-1 FIG 4 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 57-2-1 FIG 38 DC8 SRM 51-1-21, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION FOUND A IMPROPER REPAIR AT STATION FS1762, LONGERON 34 LEFT. REMOVED DAMAGED SKIN PANEL CLEANED TREATED AND PRIMED AREA AND NEW SKIN PANEL. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL FROM STATION 1696 TO STATION 1890, FROM LONGERON 28 RIGHT TO LONGERON 28 LEFT IAW DC8 SRM 51-1-21 SRM 51-1-20D, SRM 51-3-1, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-8B, DC8 SRM 53-5-1 FIG 1 ITEM "E", DC8 SRM 51-1-8B, DC8 SRM DC8 51-1-11. BOEING MESSAGE NUMBER 1-271850875-2 DATED 01-10-07.

Part: SKIN — CRACKED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXTERNAL FUSELAGE SKIN CRACKED AT STATION FS1400.00 LONGERON 33 RIGHT. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 51-1-20B, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DOUGLAS DRAWING NUMBER SR08530019, AD-2005-18-07,S.B DC8-53-078 AND DOUGLAS DRAWING NUMBER 5750776.

Part: LONGERON — CRACKED (ZONE 200) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED LONGERON AT STATION 1776.000 LONGERON 17 RIGHT. REMOVED DAMAGED LONGERON. FABRICATED NEW LONGERON. CLEANED, TREATED AND PRIMED AREA AND NEW LONGERON. INSTALLED NEW LONGERON IAW DC8 SRM 53-5-1 FIG 7 SHEET 1 PAGE 22, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-8B, DC8 SRM 51-2-0 FIG 50, DC8 SRM 51-1-21, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS 240.000, LONGERON 33 RIGHT. REPLACED CRACKED FITTING IAW DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (BS 824 L19L) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS824.000 LONGERON 19 LEFT. REPLACED CRACKED FITTING IAW DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 300) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR.-LOWER SKIN HAS A NON STANDARD REPAIR FROM STATION XE55.062 TO STATION XE65.156. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND REPAIR PARTS. BONDED REPAIR PARTS WITH HYSOL AS NEEDED. CLEANED, TREATED AND PRIMED AREA, NEW SKIN AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN FROM STATION XAR0.00 TO XE132.000. BALANCED LEFT ELEVATOR. MOMENT 1454.8 INCH POUNDS, FOUND WITHIN TOLERANCE IAW DC8 SRM 55-4-1 FIGURE 1 SHEET 1 AND 2, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 55-4-1 FIGURE 1 SHEET 1 AND 2. ITEM "E" AND "F", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21 AND DC8 SRM 51-4-4 PAGES

Part: SKIN — CRACKED (ACCESSORY DOOR) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD ACCESSORY COMPARTMENT DOOR SKIN CRACKED. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. INSTALLED NEW SKIN IAW DC8 SRM 52-8-1 FIG 1 SHEET 1, DC8 SRM 52-1-0 PAGE 1, DC8 SRM 52-8-1 FIG 1 SHEET 1 ITEM "E", DC8 SRM 51-9-0 FIG 68A, DC8 SRM 51-1-8B AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT UPPER OUTBOARD FLAP HAS A NON STANDARD REPAIR AT STATION XF350.000. REMOVED EXISTING SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED TREATED AND PRIMED AREA AND NEW SKIN AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 57-7-1 FIG 4 PAGE 2 TR NR 57-94 DATE 10-01-2002, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 4 PAGE 2 ITEM "B", DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: LONGERON — CRACKED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LONGERON 17 LEFT CRACKED AT STATION 1776.000. REMOVED DAMAGED LONGERON. CLEANED TREATED AND PRIMED AREA AND NEW LONGERON. INSTALLED NEW LONGERON IAW DC8 SRM 53-5-1 FIGURE 7, SHEET 1, PAGE 22, DC8 SRM 53-1-0 PAGE 1 DC8 SRM 51-1-8B, DC8 SRM 51-2-0, FIGURE 50, DC8 SRM 51-1-21, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: FITTING — CORRODED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CORRODED FITTING AT STATION FS450.000, LONGERON 26 LEFT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 51-1-8B, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 200) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS702.000 LONGERON 14 RIGHT. REMOVED CRACKED FITTING. FABRICATED FITTING. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 NDT SPM PART 08-00-02-07, DC8 SRM 51-1-8B, DOUGLAS DRAWING NUMBER 3779978.

Part: FITTING — CRACKED (BS 1690 S24L) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS 1690.000, LONGERON 24 LEFT. 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: SKIN PANEL — DELAMINATED (ZONE 300) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR UPPER SKIN PANEL IS DELAMINATED AT STATION XE50.000. REMOVED DAMAGED SKIN PANEL. FABRICATED NEW SKIN PANEL AND REPAIR PARTS. BONDED REPAIR PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL AND REPAIR PARTS FROM STATION XAR0.00 TO STATION XE132.000. PERFORMED RIGHT ELEVATOR BALANCING FOUND WITHIN TOLERANCE, MOMENT 1471.4 IN-LBS IAW DC8 SRM 51-4-4 PAGE 1-4, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2, ITEMS "E" AND "F".DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: FITTING — CRACKED (ZONE 200) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED FITTING AT STATION FS 702.000, LONGERON 19 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: SKIN — MISREPAIRED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING FLAP UPPER SKIN HAS A NON STANDARD REPAIR BETWEEN STATIONS XF415.000 AND XF420.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0.PAGE 1, DC8 SRM 57-7-1 FIG 4 ITEM "P", DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: SKIN — CORRODED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING-UPPER LEADING EDGE CORRODED AT STATION 472.099. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 57-3-1 FIGURE 5 PAGE 10, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-0 PAGE 16, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-8B, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-11, DC8 SRM 51-3-0 AND DC8 SRM 51-3-1.

Part: VANE — ELONGATED (RT WING) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD SLOT VANE HOLES ELONGATED AT STATION XS520.168. REMOVED EXISTING INTERNAL DOUBLER. REMOVED OUT DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW, DC8 SRM 51-3-0, DC8 SRM 51-3-1, 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, SEMAN DRAWING NUMBER ED-4424 DATED 01-16-07. COMPLETED FAA FORM 8110-3 NUMBER 07019 DATED 01-18-07.

Part: PLATE — CORRODED (BS 902) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT MAIN LANDING GEAR WHEEL WELL PLATE UPPER SIDE CORRODED AT STATION FS902.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED PLATE. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW PLAT. IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 53-2-0 PAGE 2P AND DC8 SRM 51-1-8B.

Part: SKIN — DAMAGED (RT WING) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD LEADING EDGE HOLES ELONGATED AT STATION XFS 710.000. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS, CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4426 DATED 01-20-07.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP UPPER SKIN HAS A NON STANDARD REPAIR FROM STATION XW132.000 TO STATION XW135.000. REMOVED EXISTING SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 57-1-0, PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 1 PAGE 2 ITEM "F" DC8 SRM 51-1-8B DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS1710, LONGERON 34 LEFT. REMOVED DAMAGED SKIN PANEL. CLEANED TREATED AND PRIMED AREA AND NEW SKIN PANEL. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL FROM STATION 1696 TO STATION 1890 FROM LONGERON 28 RIGHT TO LONGERON 28 LEFT IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 53-5-1 FIGURE 1 ITEM "E", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, BOEING MESSAGE NUMBER 1-271850875-2 DATED 01-10-07.

Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP UPPER SKIN HAS A NON STANDARD REPAIR FROM STATION XF326.000 TO STATION XF333.000. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11SEMAN DRAWING NUMBER ED-4410 DATED 01-13-07. COMPLETED FAA FORM 8110-3 NUMBER 07021 DATED 01-19-07.

Part: SKIN — DAMAGED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HAND WING OUTBOARD SLOT VANE HOLES ELONGATED AT STATION XOLDI6.225. REMOVED EXISTING INTERNAL DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10.01.001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, SEMAN DRAWING NUMBER ED-4425 DATED 01-17-07 AND COMPLETED FAA FORM 8110-3 NUMBER 07019 DATED 01-18-07.

Part: SKIN — CORRODED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING UPPER LEADING EDGE CORRODED AT STATION XFS304.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS FROM STATION XFS304.000 TO STATION XFS341.000 IAW DC8 SRM 57-2-1, FIG 44, TR NR 57-102 DATED 10/15/2003, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-0, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-1 FIG 2G, DC8 SRM 57-2-1 FIG 44, DC8 SRM 57-3-1 PAGE 8, FIG 4 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 57-2-1, FIG. 44, DC8 SRM 5

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP UPPER SKIN HAS A NON STANDARD REPAIR FROM STATION XW104.000 TO STATION XW110.000. REMOVED EXISTING SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED PLATING IAW DC8 SRM 57-7-1 FIG 1 PAGE 2, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 1 PAGE 2 ITEM "D", DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS 1696, LONGERON 36. REMOVED EXISTING SKIN WITH IMPROPER REPAIR. CLEANED TREATED AND PRIMED AREA. TREATED AND PRIMED NEW SKIN PLATING. APPLIED SEALANT TO FAYING SURFACE. INSTALLED NEW SKIN PLATING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 53-5-1 FIGURE 1 ITEM "E", DC8 SRM DC8 51-1-11 AND BOEING MESSAGE NUMBER 1-271850875-2 DATED 01-10-07.

Part: SKIN PANEL — MISREPAIRED (T/E FLAP) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP SKIN PANEL HAS A NON STANDARD REPAIR FROM STATION XW104.000 TO STATION XW108.000. REMOVED SKIN PANEL WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN PANEL AND INTERNAL BONDED DOUBLERS. BONDED REPAIR PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED PANEL IAW DC8 SRM 57-7-1 FIGURE 1 PAGE 2, DC8 SRM 57-1-0, PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 1 PAGE 2 ITEM "A", "L" AND "R" DC8 SRM 51-1-9, DC8 SRM 51-1-8B AND DC8 SRM 51-1-11.

Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A NON STANDARD REPAIR ON THE LEFT OUTBOARD FLAP FROM STATION XF169.000 TO STATION XF174.000. REMOVED EXISTING SKIN PANEL WITH NON STANDARD REPAIR. FABRICATED NEW SKIN PANEL AND BONDED DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL IAW DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIGURE 4 ITEMS "P" AND "Q", DC8 SRM 51-1-9, DC8 SRM 51-1-8B AND DC8 SRM 51-1-11.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS 1692, LONGERON 36. REMOVED EXISTING REPAIR DOUBLER. FABRICATED REPAIR PARTS. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 53-2-1 FIGURE 7 SHEETS 1, 4 AND, 5DC8 SRM 51-1-21, DC8 SRM 53-5-1 FIGURE 1 PAGE 2 ITEM "E" AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD AILERON FITTING CRACKED BETWEEN STATION XA494.000 AND XA504.000. REPLACED AILERON HINGE FITTING IAW DC8 SRM 51-1-21, 51-1-20D AND 51-3-0, 51-3-1.

Part: SUPPORT FITTING — CRACKED (ZONE 600) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A CRACKED OUTBOARD FLAP HINGE SUPPORT FITTING ON THE RIGHT WING AT STATION XF213.000. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8, SRM 51-3-1, DC8 SRM 51-1-21,DC8 SRM 51-3-0 AND DC8 SRM 51-1-8B.

Part: SKIN — CRACKED (ZONE 500) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING-EXTERNAL UPPER SKIN CRACKED AT STATION XRS74.000 STRINGER 11. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 57-2-1 FIGURE 10 SHEET 3, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 57-3-1 FIGURE 10 PAGE 17 ITEM "A", DC8 SRM 51-10-0, FIGURE 1 SHEET 6, DC8 SRM 51-1-8B, DC8 SRM 51-1-12 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS 1693, LONGERON 27 LEFT. REMOVED EXISTING REPAIR REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DOUGLAS DRAWING SR08530032 WITH APPROVED DEVIATIONS, SEMAN DRAWING ED-4469 DATED 02-16-07, BOEING MESSAGE NUMBER 1-288540577-7 DATED 02-15-07, ATI ENGINEERING ORDER NUMBERDC8-3729 DATED 02-05-07, AD-DC8-2007-02-02,SB-DC8-53A080, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001 AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT FS 1282, LONGERON 35 RIGHT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS FROM STATION FS1265.000 TO STATION FS1282.000 IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4418 DATED 01-12-07. FAA FORM 8110-3 NUMBER 07012 DATED 01-15-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS1290, LONGERON 15 RIGHT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED4423 DATED 01-26-07. COMPLETED FAA FORM 8110-3 NUMBER 07077 DATED 02-13-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK, FOUND EXISTING REPAIR IS IMPROPER AT STATION FS 403, LONGERON 35 LEFT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 51-1-20D, DC8 NDT SPM PART 06-10-01-001,DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4416 DATED 01-15-07, FAA FORM 8110-3 NUMBER 07012 DATED 01-15-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT FS 330, LONGERON 30 RIGHT. REMOVED EXISTING REPAIR. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVAL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW 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, DC8 SRM 51-3-1. AD 2005-18-07, BOEING MESSAGE NR 1-274569452-5 DATED 01-17-07 BOEING MESSAGE NR 1-290998891-2 AND SEMAN DRAWING ED-4414-1 DATED 01-17-07. COMPLETED FAA FORM 8100-9 DATED 02-17-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR AT STATION FS 1384, LONGERON 35 RIGHT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1 AND 3, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 53-4-1 FIGURE 16 SHEET 2 ITEM "B", DC8 SRM 51-9-0 FIGURE 68A, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING OUTBOARD FLAP HAS A NON STANDARD REPAIR ON UPPER SURFACE FROM STATION XF216.000 TO STATION XF220.000. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED NEW SKIN AND REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN AND REPAIR PARTS IAW DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 AND SEMAN DRAWING, NUMBER ED-4409 DATED 01-13-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS 280 LONGERON 30 REMOVED EXISTING REPAIR. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAWDC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-3-1, AD 2005-18-07, BOEING MESSAGE NUMBER 1-274569452-5 DATED 01-17-07, BOEING MESSAGE NUMBER 1-290998891-2 DATED 01-17-07, SEMAN DRAWING NUMBER ED-4414 DATED 01-17-07 AND ATI ENGINEERING ORDER 53-DC8-2452. COMPLETED FAA FORM 8110-9 DATED 02-17-07.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND INTERIM REPAIR AT FS 1542, LONGERON 35 LEFT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVAL. FABRICATED EXTERNAL REPAIR DOUBLER AND INTERNAL FINGER DOUBLER. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4419 DATED 01-19-07. COMPLETED FAA FORM 8110-3 NUMBER 07026 DATED 01-22-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS1265, LONGERON 35 RIGHT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS FROM STATION FS1265.000 TO STATION FS1282.000, LONGERON 35 RIGHT IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4418 DATED 01-12-07. COMPLETED FAA FORM 8110-3 NUMBER 07012 DATED 01-15-07.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK, FOUND EXISTING REPAIR AT STATION FS174, LONGERON 34 RIGHT, DOES NOT MEET DTA REQUIREMENTS OF MDC 91K0262 REPORT. REMOVED EXISTING REPAIR REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. AFTER DAMAGE REMOVAL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-3-0, 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, DC8 SRM 51-3-0, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4412 DATED 01-17-07. COMPLETED FAA FORM 8110-3 NUMBER 07019 DATED 01-18-07.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND INTERIM REPAIR AT STATION FS 518, LONGERON 31 RIGHT. REMOVED EXISTING REPAIR PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. FABRICATED REPAIR PARTS CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-0, DC8 SRM 51-3-1, SERVICE BULLETIN DC8-53-078, AD-2005-18-07 BOEING MESSAGES NUMBER 1-274569706-5, 1-274569706-7 DATED 01-17-07 AND SEMAN DRAWING ED-4422-1 DATED 02-05-07. COMPLETED FAA FORM 8110-9 DATED 02-05-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR REPAIR AT STATION FS 222.000, LONGERON 35 RIGHT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1 AND 3, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 53-4-1 FIGURE 1 ITEM "B", DC8 SRM 51-9-0 FIGURE 68A, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR AT STATION FS 1143, LONGERON 35 RIGHT, DOES NOT MEET THE DTA REQUIREMENTS OF MDC 91K0262 REPORT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-3-1, DC8 SRM 53-2-1 FIGURE 7 SHEET 1 AND 3,DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 53-4-1 FIGURE 16 ITEM D, DC8 SRM 51-1-8B AND DC8 SRM 51-1-11.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS 1682, LONGERON 35 RIGHT. REMOVED EXISTING IMPROPER REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4442 DATED 01-25-07. COMPLETED FAA FORM 8110-3 NUMBER 07031 DATED 01-26-07.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR AT STATION FS104, LONGERON 35 LEFT DOES NOT MEET DTA REQUIREMENTS OF MDC91K0262 REPORT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1 AND 2, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 53-4-1 FIGURE 1 ITEM "C", DC8 SRM 51-9-0 FIGURE 68A, DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR AT STATION FS1694, LONGERON 27 RIGHT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS DC8. INSTALLED REPAIR PARTS IAW DOUGLAS DRAWING SR08530032, BOEING MESSAGE NUMBER 1-288540577-7, SEMAN DRAWING ED-4469 DATED 02-16-07, BOEING MESSAGE NUMBER 1-288540577-5 DATED 02-15-07, ATI ENGINEERING ORDER NUMBER 53-DC8-3729 DATED 02-05-07, AD-DC8-2007-02-02, SB-DC8-53A080, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001 AND SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AN IMPROPER REPAIR FROM STATION FS 290 TO STATION FS 330 LONGERON 30, REMOVED EXISTING REPAIR. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS. IAWDC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-3-1, AD 2005-18-07, BOEING MESSAGE NUMBER 1-274569452-5 DATED 01-17-07, BOEING MESSAGE NUMBER 1-290998891-2 DATED 01-17-07, SEMAN DRAWING NUMBER ED-4414 DATED 01-17-07 AND ATI ENGINEERING ORDER 53-DC8-2452. COMPLETED FAA FORM 8110-9 DATED 02-17-07.

Part: SKIN — CRACKED (RT WING) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT HAND WING UPPER SKIN CRACKED AT STATION XRS105.000, STRINGER 14.REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-12, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4408. COMPLETED FAA FORM 8110-3 NUMBER 07021 DATED 01/19/07.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT HAND OUTBOARD FLAP HAS A NON STANDARD REPAIR FROM STATION XF384.000 TO STATION XF390.000. REMOVED EXISTING SKIN PANEL WITH NON STANDARD REPAIR. FABRICATED NEW SKIN PANEL. BONDED BOTH PARTS. WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN PANEL INTERIOR SURFACE. APPLIED SEALANT TO FAYING SURFACES. DC8 INSTALLED NEW SKIN PANEL IAW DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIGURE 4 ITEMS "A" AND "Q", DC8 SRM 51-1-9, DC8 SRM 51-1-8B AND SRM 51-1-11.

Part: SUPPORT FITTING — CRACKED (RT WING) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING TRAPEZOIDAL FITTING CRACKED AT STATION 902.000. REMOVED DAMAGED TRAPEZOIDAL SUPPORT FITTING. INSTALLED NEW TRAPEZOIDAL SUPPORT FITTING IAW DOUGLAS DRAWINGS, NUMBER 5750127 AND NUMBER 5750092, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT STATION FS172, LONGERON 35 RIGHT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-3-1, DC8 SRM 51-3-0, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-11, SEMAN DRAWING NUMBER ED-4412 DATE 01-17-07 AND COMPLETED FAA FORM 8110-3 NUMBER 07019 DATED 01-18-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR AT STATION FS 76, LONGERON 35 RIGHT, DOES NOT MEET THE DTA REQUIREMENTS OF MDC 91K0262 REPORT. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVAL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW 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 DC8 SRM 51-3-1. SEMAN DRAWING NUMBER ED-4411 DATED 01-11-07. COMPLETED FAA FORM 8110-3, NUMBER 07012, DATED 01-15-07.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 89,079 hrs · 36,944 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR AT STATION FS 545, LONGERON 35 RIGHT. REMOVED EXISTING REPAIR. TRIMMED OUT DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-21, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-1 AND SEMAN DRAWING NUMBER ED-4417 DATED 01-11-07. COMPLETED FAA FORM 8110-3 NUMBER 07012 DATED 01-15-07.

Part: HYDRAULIC SYSTEM — LEAKING (MAIN) · airframe 87,257 hrs · 36,203 cycles

DURING FLIGHT 828 FROM KRFD TO KIAH MAIN SYSTEM HYDRAULIC FLUID LOST TO STANDPIPE AFTER GEAR RETRACTION BEFORE FLAPS WERE RETRACTED. AIR BRAKE WAS NOT USED. THE CREW ELECTED TO LAND AT KTOL AND LANDED WITHOUT INCIDENT. INSPECTION IS ON GOING AND MORE INFORMATION WILL BE ADDED AS SOON AS IT IS AVAILABLE.

Part: ENGINE — FLAMED OUT (NR 1) · airframe 87,207 hrs · 36,187 cycles

DURING FLIGHT FROM KLRD TO KLRD LEVELING AT 17000 FT NR 1 ENGINE FLAMED OUT. ACCOMPLISHED FLAMEOUT CHECK LIST ENGINE STARTED NORMALLY. AFTER WARM UP PERIOD THROTTLE WAS ADVANCED WITH NO RESPONSE FROM ENGINE. THE ENGINE SHUTDOWN. OIL PRESSURE WENT TO 0 AT THAT TIME. MAINTENANCE REMOVED AND REPLACED THE NR 1 ENGINE AND NR 1 ENGINE NOSE COWL. AFTER ENGINE INSTALLATION AN IDLE CHECK AT PARTIAL POWER AND AT MAX POWER WERE PERFORMED AS WELL AS A VISUAL INSPECTION OF FORWARD AND REAR MOUNTS. WORK WAS PERFORMED PER ALL APPLICABLE MANUALS. THERE WERE NO DEFECTS AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: MEC — INOPERATIVE (NR 1 ENGINE) · airframe 87,197 hrs · 36,180 cycles

DURING CLIMB FROM KTOL TO KPHL NR 1 THROTTLE HAS TO BE RETARDED APPROX 4 KNOTS WIDTH TO MAINTAIN CLIMB THRUST, AT CRUISE POWER THROTTLE IS JUST ABOVE IDLE. CREW SHUT DOWN ENGINE PRIOR TO LANDING BECAUSE UNABLE TO RETARD POWER, POSITIVE OIL PRESSURE AND QUANTITY NOTED PRIOR TO SHUTDOWN. MAINTENANCE REMOVED AND REPLACED CIT SENSOR AND MEC. PERFORMED FLIGHT IDLE, 75% AND MAXPOWER RUNS. THE NR 1 ENGINE OPS CHECK WAS NORMAL. THE ENGINE RUN WAS ACCOMPLISHED WITHIN 24 HOURS OF ENGINE SHUTDOWN. OPS CHECKS WERE GOOD PER ALL APPLICABLE MANUALS AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: HSI — MALFUNCTIONED (COCKPIT) · airframe 86,455 hrs · 35,946 cycles

ON TAKEOFF, NR 1 COMPASS FAILED WITH OFF FLAG IN CAPTAIN HSI. CREW RETURNED AND LANDED WITHOUT INCIDENT. MX REMOVED AND REPLACED CAPTAIN HSI PER ALL APPLICABLE MAINTENANCE MANUALS. OPS CHECK GOOD. ACFT RETURNED TO SERVICE.

Part: VANE — DELAMINATED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT HAND OUTBOARD FLAP INBOARD FLAP VANE DELAMINATED. REMOVED AND REPLACED FLAP VANE, RIG CHECK GOOD IAW DC8 MM 27-51-14.

Part: VANE — DELAMINATED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT HAND FLAP STATION 219 FLAP VANE DELAMINATED. REMOVED AND REPLACED FLAP VANE, RIG CHECK GOOD IAW DC8 MM 27-51-14.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FLIGHT DECK COUIER SEAT TRACK AFT TRACK CRACKED ON END. REMOVED DAMAGE, MANUFACTURED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-21.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND MAIN CABIN SEAT TRACK GOUGED AT STATION 235 LEFT BUTT LINE 45.5. GOUGE IS OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 53-2-3, 51-1-21, 51-1-8, 51-3-0, AND 51-3-1.

Part: BUSHING — MIGRATED (THRUST REVERSER) · airframe 86,085 hrs · 35,775 cycles

DURING A ROUTINE C- CHECK FOUND NUMBER 3 ENGINE OUTBOARD THRUST REVERSER TRANSITION COWL BUSHING MIGRATED AT FRICTION PAD. REPAIRED MIGRATING BUSHING BY REMOVING FASTENERS, REMOVING DAMAGED EDGE ANGLE, FABRICATING NEW ANGLE AND BONDING INTO PLACE. ALODINED, PRIMED, INSTALLED FASTENERS AND SEALED REPAIR AREA IAW TIMCO REO G10300, CFM MM 78-31-20, 78-30-00, 78-31-40 SERVICE BULLETIN CFM56 78-022, DC8 SRM 51-2-21 AND 51-3-1.

Part: ANGLE — CRACKED (BS 790) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND SUPPORT ANGLE CRACKED AT THE RIGHT WHEEL WELL STATION 790 LONGERON 23 RIGHT SWING DOWN PANEL. MANUFACTURED REPAIR ANGLES. LOCATED, DRILLED, TRIMMED, ALODINED, PRIMED, AND INSTALLED REPAIR ANGLES IAW DC8 DRAWING 5643404, DC8 SRM 53-2-0, 51-1-8, AND 51-1-20D.

Part: WEB — CRACKED (ZONE 800) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT HAND PASSENGER DOOR FORWARD WEB JUST ABOVE OPENING MECHANISM CRACKED. STOP DRILLED CRACK AND FABRICATED DOUBLER. LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED DOUBLER AND FASTENERS IAW DC8 SRM 52-3-2, 52-2-0 51-1-21, AND 51-1-8.

Part: FLOORBOARD — DELAMINATED (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND CABIN FLOORBOARD DELAMINATED AT STATION 1120 TO STATION 1260 RIGHT BUTT LINE 54. REMOVED DAMAGED FLOORBOARD, MANUFACTURED NEW FLOORBOARD, LOCATED, DRILLED AND INSTALLED NEW FLOORBOARD IAW DC8 SRM 51-3-0, 51-1-11 AND DOUGLAS SPEC 3932193.

Part: FRAME — CRACKED · airframe 86,085 hrs · 35,775 cycles

DURING A ROUTINE C-CHECK FOUND FRAME JUST AFT OF AIRSTART COMPARTMENT CRACKED AT 2 LOCATIONS. REMOVED FASTENERS, AND DAMAGED AREA. FABRICATED REPAIR PARTS. LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED REPAIR PARTS, IAW DC8 SRM 53-2-0, 51-1-20D, 51-3-0, 51-1-8, AND 51-1-21.

Part: RIB — CRACKED (ZONE 800) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FORWARD RIGHT HAND SERVICE DOOR UPPER INTERNAL RIB CRACKED. STOP DRILLED CRACK. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0, 52-3-0, 51-9-0 AND 51-1-8.

Part: SKIN — CORRODED (STA 680 - 780) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK, FOUND CORROSION ON EXTERIOR FUSELAGE SKIN FROM STATION 680 TO STATION 780 BETWEEN LONGERON 32 LEFT AND LONGERON 32 RIGHT. REMOVED FASTENERS, AND ANTENNA TO GAIN ACCESS. REMOVED CORROSION. ORIGINAL SKIN THICKNESS .125 AFTER CORROSION REMOVED SKIN THICKNESS WAS .056, OUT OF LIMITS. MANUFACTURED, ALODINED, PRIMED AND INSTALLED REPAIR DOUBLERS IAW DC8 SRM 51-3-8, 51-1-20D, 51-1-8, 53-2-0, AND 53-2-1.

Part: ANGLE — CRACKED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT WING OUTBOARD FLAP INBOARD CENTER AFT INSIDE PANEL NUMBER 551 AREA ANGLE CRACKED AND 3 FASTENERS MISSING. REMOVED FASTENERS, AND ANGLE. FABRICATED NEW ANGLE, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED NEW ANGLE AND INSTALLED MISSING FASTENERS IAW DC8 SRM 51-1-21, 57-7-0, AND 51-1-8.

Part: SHROUD — WORN (NR 3 INLET) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND, NR 3 ENGINE INLET FAN ABRADABLE SHROUD WORN, APPROXIMATELY 40 PERCENT MATERIAL MISSING. REMOVED 2 ACOUSTICAL PANELS, AND DAMAGE. CLEANED AREA AND APPLIED FIBERGLASS REPAIR IAW CFM56 MM 72-33-00.

Part: DOUBLER — GOUGED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT OUTBOARD TRAILING EDGE FLAP UPPER SKIN REPAIR PATCH GOUGED AT CENTER HINGE. REMOVED FASTENERS AND DAMAGED DOUBLER. FABRICATED NEW DOUBLER, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED NEW DOUBLER, AND FASTENERS IAW DC8 SRM 51-1-21A, 57-2-0, AND 51-1-8.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND MAIN CABIN SEAT TRACK AT STATION 1220 -F- WORN. REMOVED DAMAGE FOUND TO BE OUT OF LIMITS. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-3, AND 51-1-8.

Part: SKIN — CRACKED (ZONE 100) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND EXTERNAL FUSELAGE SKIN CRACKED AT STATION 45 LONGERON 28 LEFT IN AREA OF EXISTING REPAIR. PERFORMED HFEC TO VERIFY CRACK. VERIFIED, GAINED ACCESS, REMOVED FASTENERS, EXISTING DOUBLER, AND REMOVED DAMAGE. FABRICATED FILLER AND DOUBLER. TREATED, PRIMED, INSTALLED REPAIR PARTS AND FASTENERS IAW MD NDT SM 06-10-001-001, DC8 SRM 51-3-1, 51-1-21, 53-2-0, 51-1-8, AND 51-1-20D.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FLIGHT DECK FIRST OFFICER SEAT TRACKS AFT SET HOLES ELONGATED. REMOVED SEAT TRACKS. ORIGINAL THICKNESS WAS .125, REMOVED .040 MATERIAL, .080 REMAINING, OUT OF LIMITS. FABRICATED STRAPS FROM .040 THICK 301 STAINLESS STEEL. LOCATED, DRILLED AND INSTALLED REPAIR STRAPS WET WITH SEALANT AND FASTENERS. REINSTALLED SEAT TRACKS AND FUNCTIONAL CHECKED GOOD IAW DC8 SRM 51-1-20-D, 53-2-3, 25-11-1 AND 51-1-11.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FLIGHT DECK COURIER SEAT TRACKS FORWARD AND AFT WORN. REMOVED FASTENERS, AND DAMAGED SEAT TRACKS. RECEIVED NEW SEAT TRACKS, LOCATED, DRILLED AND INSTALLED NEW SEAT TRACKS IAW DC8 SRM 51-1-24 AND 51-3-1.

Part: HINGE — GOUGED (ZONE 600) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND RIGHT HAND INBOARD FLAP, INBOARD HINGE, OUTBOARD ARM GOUGED AND CHAFED. REMOVED DAMAGE, ORIGINAL THICKNESS WAS .250, REMOVED .081 MATERIAL, REMAINING THICKNESS .169, OUT OF LIMITS. FABRICATED REPAIR PARTS, LOCATED, DRILLED, PRIMED, AND INSTALLED REPAIR PARTS IAW DC8 SRM 57-7-0, 51-1-8, 51-9-0, DC8 DRAWING SR0827008, AND DC8 SERVICE BULLETIN 27-279.

Part: SUPPORT ANGLE — CRACKED (ZONE 600) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND RIGHT WING OUTBOARD FLAP INBOARD EDGE AT STATION XW 129 TRAILING EDGE SUPPORT ANGLE CRACKED. REMOVED FASTENERS, AND DAMAGED SUPPORT ANGLE. FABRICATED NEW SUPPORT ANGLE. LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED NEW SUPPORT ANGLE AND FASTENERS IAW DC8 SRM 51-1-8, 51-7-1, AND 51-1-20D.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FLIGHT DECK FLIGHT ENGINEER FORWARD AND AFT SEAT TRACKS WORN. REMOVED FASTENERS AND DAMAGED SEAT TRACKS. RECEIVED NEW SEAT TRACKS, LOCATED, DRILLED AND INSTALLED NEW SEAT TRACKS IAW DC8 SRM 51-3-0, 51-3-1, AND 51-1-21.

Part: BRACKET — CRACKED (ZONE 100) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND AIRSTART NOZZLE BRACKET CRACKED AT 3 LOCATIONS. STOP DRILLED CRACKS, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND FASTENERS IAW DC8 SRM 53-2-0, 51-9-0, AND 51-1-8.

Part: DOUBLER — TORN (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT WING INBOARD FLAP OUTBOARD FORWARD HINGE FAIRING PANEL DOUBLER TORN. REMOVED FASTENERS AND DAMAGED DOUBLER. FABRICATED NEW DOUBLER, LOCATED, DRILLED, TREATED, PRIMED, INSTALLED NEW DOUBLER WET WITH SEALANT, AND INSTALLED FASTENERS IAW DC8 SRM, 51-1-21, 57-2-0, 51-1-8, 51-1-11, AND 51-1-21.

Part: SKIN — GOUGED (ZONE 600) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND RIGHT HAND OUTBOARD FLAP UPPER SKIN IS GOUGED AT PREVIOUS REPAIR. REMOVED DAMAGED REPAIR, FABRICATED, NEW REPAIR PART, ALODINED, PRIMED AND INSTALLED NEW REPAIR PART IAW DC8 SRM 57-2-0, 51-1-20D, AND 51-1-8.

Part: TRIM TAB — DELAMINATED (ZONE 300) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT ELEVATOR TAB DELAMINATED. REMOVED TAB, DISASSEMBLED, CLEANED INSPECTED, AND REPLACED TRAILING EDGE WEDGE. REINSTALLED TAB ON LEFT ELEVATOR IAW DC8 SRM 51-1-21, 51-1-22, 51-1-8B, 51-4-5, 51-3-0, DC8 DRAWING 5702579 AND DC8 OHM 27-16-1.

Part: TRIM TAB — DENTED (ZONE 300) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT ELEVATOR TAB DENTED AT MID SKIN. REMOVED TAB, DISASSEMBLED, CLEANED INSPECTED, AND REPLACED TRAILING EDGE WEDGE. REINSTALLED TAB ON LEFT ELEVATOR IAW DC8 SRM 51-1-21, 51-1-22, 51-1-8B, 51-4-5, 51-3-0, DC8 DRAWING 5702579 AND DC8 OHM 27-16-1.

Part: BRACKET — WORN (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT WING OUTBOARD FLAP AT OUTBOARD FLAP TRACK UPPER SURFACE HAS BRACKET WORN / CHAFED THROUGH AND BAD FASTENERS. REMOVED BAD FASTENERS, FABRICATED NEW BRACKET, TREATED, PRIMED, INSTALLED NEW BRACKET AND FASTENERS IAW DC8 DRAWING 5763200, DC8 SRM 51-1-8, AND 51-3-1.

Part: SKIN — DENTED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT WING INBOARD FLAP LOWER SKIN DENTED SEVERAL PLACES. BLENDED TWO DENTS WITHIN LIMITS ONE DENT OUT OF LIMITS. REPAIRED OUT OF LIMIT DENT IAW DC8 SRM 57-2-0. TREATED AND PRIMED ALL DENTS IAW DC8 SRM 51-1-8.

Part: HEAT SHIELD — DAMAGED (THRUST REVERSER) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND NUMBER 1 ENGINE THRUST REVERSER INBOARD INNER HEAT SHIELD HAS A HOLE WORN THROUGH. RECEIVED NEW HEAT SHIELD, LOCATED, DRILLED AND INSTALLED HEAT SHIELD IAW CFM56 MM 78-31-10.

Part: FRAME — CHAFED (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FLIGHT DECK AT STATION 12.00 TO STATION 20.00 LEFT BUTT LINE 10 FRAME CHAFED THROUGH. REMOVED LOWER L-ANGLE WIRE BUNDLE ATTACH ANGLE, STIFFENERS, AND INTERCOSTAL. FABRICATED INTERCOSTAL AND DOUBLER. LOCATED INTERCOSTAL AND DOUBLER, DRILLED, ALODINED AND PRIMED. INSTALLED INTERCOSTAL AND DOUBLER. REINSTALLED L-ANGLE WIRE BUNDLE ATTACH ANGLE AND STIFFENERS IAW DC8 DRAWING 5641543, DC8 SRM 51-1-21, 53-7-0, 51-9-0, 51-1-8, 53-2-0, AND 51-1-20D.

Part: CLIP — CRACKED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK, FOUND LEFT WING OUTBOARD FLAP INBOARD SUPPORT HINGE TRAILING EDGE UPPER WING SUPPORT CLIP CRACKED. REMOVED FASTENERS, FABRICATED NEW CLIP, TREATED, PRIMED, AND INSTALLED NEW CLIP AND FASTENERS IAW DC8 SRM 57-2-0, 51-1-21, AND 51-1-8.

Part: STRUCTURE — GOUGED (THRUST REVERSER) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND NUMBER 2 ENGINE THRUST REVERSER INBOARD SHELL HAS GOUGES. REMOVED DAMAGE, RECEIVED REPAIR DOUBLER, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED DOUBLER IAW CFM MM 78-31-10.

Part: FRAME — CRACKED (STA 1120) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FRAME CRACKED IN THE AFT PIT STATION 1120 AT LONGERON 30 RIGHT. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-20D.

Part: SHROUD — WORN (NR 1 ENGINE) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND NUMBER 1 ENGINE FAN ABRADABLE SHROUD WORN BEYOND LIMITS AT 12:00, AND 1:00 POSITIONS. REMOVED ACCOUSTICAL PANELS, POTTED REPAIR AREAS, APPLIED FIBERGLASS OVERLAYS, CLEANED AND SEALED AREAS. REINSTALLED ACCOUSTICAL PANELS IAW CFM MM 72-23-02.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND FLOORING IN COURIER AREA CORRODED. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REMOVED FASTENERS, FABRICATED NEW FLOOR PANEL, ALODINED, PRIMED, INSTALLED NEW FLOOR PANEL AND FASTENERS IAW DC8 DRAWING 564827, DC8 SRM 51-1-8, 53-2-0, 51-3-0, 51-1-21, AND 53-7-1.

Part: COWLING — CRACKED (NR 1 NACELLE) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND NUMBER 1 ENGINE NOSE COWL EXTERNAL SKIN CRACKED BEYOUND STOP DRILL AT INBOARD ANTI-ICE CUTOUT LOWER FORWARD CORNER. REMOVED FASTENERS. PERFORMED HFEC TO VERIFY CRACK STOPS AT FASTENER HOLE. FABRICATED DOUBLER, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED DOUBLER IAW DC8 SRM 71-2-0, 51-1-8, AND 51-1-21.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND AIR START ENCLOSURE GOUGED AND CRACKED. REMOVED FASTENERS, INNER AND OUTER DOUBLER. FABRICATED INNER AND OUTER DOUBLER. LOCATED, DRILLED, TREATED PRIMED, AND INSTALLED NEW INNER AND OUTER DOUBLER IAW DAC DRAWING 5614438, DC8 SRM 53-3-1, AND 51-1-8

Part: SKIN — GOUGED (ZONE 100) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND EXTERNAL FUSELAGE GOUGED AT STATION 280 LONGERON 30 RIGHT. REMOVED GOUGE. ORIGINAL MATERIAL THICKNESS IS .071 AFTER DAMAGED REMOVED MATERIAL THICKNESS IS .051 OUT OF LIMITS. FABRICATED DOUBLER, LOCATED, DRILLED, ALODINED, PRIMED, AND INSTALLED DOUBLER IAW DC8 SRM 51-1-8, 53-4-1, 53-2-1, AND 51-1-20D.

Part: ANGLE — CRACKED (785 LONGERON) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND SUPPORT ANGLE CRACKED AT THE RIGHT WHEEL WELL STATION 785 LONGERON 23 RIGHT SWING DOWN PANEL. MANUFACTURED REPAIR ANGLES. LOCATED, DRILLED, TRIMMED, ALODINED, PRIMED, AND INSTALLED REPAIR ANGLES IAW DC8 DRAWING 5643404, DC8 SRM 53-2-0, 51-1-8, AND 51-1-20D.

Part: ATTACH FITTING — CORRODED (STA 870) · airframe 86,085 hrs · 35,775 cycles

DURING A ROUTINE C-CHECK FOUND LONGERON ATTACH FITTING AT STATION 870 LONGERON 24 LEFT CORRODED. ORIGINAL THICKNESS .125 REMOVED .025 MATERIAL, FITTING OUT OF LIMITS. DURING CORROSION REMOVAL FOUND LONGERON 24 LEFT CRACKED AT STATIION 870. REMOVED FASTENERS, DAMAGED FITTING, AND CRACKED LONGERON SECTION. FABRICATED REPAIR PARTS, RECEIVED NEW FITTING, DRILLED, CLEANED, TREATED, PRIMED AND INSTALLED REPAIR PARTS IAW DAC DRAWING 3641004, DC8 SRM 53-2-0, 51-1-20D, 51-1-24, 51-1-8 MD NDT SPM 06-10-01.001.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND ATTACH FITTING CORRODED AT RIGHT WHEEL WELL STATION XCW44.00 LONGERON 24 RIGHT. CLEANED AREA, UPON FURTHER INSPECTION SEVERAL CRACKS NOTED VERIFIED BY INSPECTION. REMOVED FASTENERS AND DAMAGED FITTING. RECEIVED NEW ATTACH FITTING AND REPAIR PARTS, LOCATED DRILLED, TRIMMED, ALODINED, PRIMED AND INSTALLED REPAIR PARTS IAW DC8 MM 53-2-0, 51-1-24, 51-1-8, 51-1-20D, AND 51-3-1.

Part: SKIN — CRACKED (ZONE 400) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND LEFT WING JUST ABOVE NUMBER 2 PYLON UPPER SKIN CRACKED. REPLACED UPPER SLOT DOOR WITH NEW, IAW DC8MM 20-12-0, AND 27-81-02.

Part: STIFFENER — CRACKED (ZONE 100) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND THREE CRACKED STIFFENERS IN THE FORWARD PIT RIGHT HAND FORWARD BULKHEAD. REMOVED FASTENERS, AND DAMAGED PARTS. MANUFACTURED REPLACEMENT PARTS. LOCATED, DRILLED, ALODINED, PRIMED, AND INSTALLED REPLACEMENT PARTS IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-21.

Part: SPAR — CRACKED (WING) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK COMPLY WITH AD 2001-06-02, INSPECT LOWER FRONT SPAR CAPS. REMOVED FASTENERS AND PHENOLIC FAIRINGS AS REQUIRED TO FACILITATE INSPECTION OF FRONT LOWER SPAR CAPS. PERFORMED HFEC ON LEFT WING NO CRACKS INDICATED. PERFORMED HFEC ON RIGHT WING, RIGHT WING HOLE NUMBER 3 GOING OUTBOARD HAS CRACK INDICATION. REAMED HOLE TO .500 AND PERFORMED HFEC, NO CRACK INDICATED. STRESS COINED HOLES IN LEFT WING, AND FABRICATED REPAIR BUSHINGS AND PARTS, INSTALLED BUSHINGS, REPAIR PARTS, PHENOLIC FAIRINGS, AND FASTENERS IAW AD2001-06-02, NDT SPM 06-10-01.003, DAC DRAWING J060232, DC8 SERVICE BULLETIN 57-090 DPS 3.67-56, DPS 2.70-2, DC8 SRM 51-1-20D, 51-3-1, 51-1-11, 51-3-0, AND 51-1-16.

Part: CLOSEOUT PANEL — CORRODED (ZONE 700) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK FOUND RIGHT HAND GEAR OVERHEAD TRUNNION PANEL CORRODED, DELAMINATED. REMOVED FASTENER AND DAMAGED PANEL. RECEIVED OVERHAULED TRUNNION PANEL. LOCATED, DRILLED AND INSTALLED TRUNNION PANEL IAW DC8 SRM 51-1-24, 51-3-0, AND 51-3-1.

Part: ATTACH FITTING — CRACKED (ZONE 500) · airframe 86,085 hrs · 35,775 cycles

DURING ROUTINE C-CHECK, FOUND LEFT WING INBOARD FLAP OUTBOARD SUPPORT HINGE UPPER TRAILING EDGE ATTACH FITTING CRACKED. REMOVED FASTENERS AND DAMAGED BRACKET. RECEIVED NEW BRACKET, LOCATED, DRILLED, PRIMED AND INSTALLED NEW STEEL BRACKET IAW DC8 SRM 51-3-0, 57-1-24, AND 51-1-8.

Part: COMPUTER — MALFUNCTIONED (STALL WARNING) · airframe 85,080 hrs · 35,201 cycles

AT V1, 121 KNOTS STALL WARING (SHAKER STICK) WENT OFF. HIGH SPEED ABORT 122 KNOTS BRAKE CHART 28 MILLION FT. LBS. 2.5 HOURS COOLING TIME REQUIRED. CREW RETURNED TO BLOCKS. AN INSPECTION IS ON GOING. AS SOON INFORMATION IS AVAILABLE IT WILL BE PROVIDED. MAINTENANCE REMOVED AND REPLACED LIFT COMPUTER. SYSTEM OPERATIONAL CHECK GOOD PER ALL APPLICABLE MANUALS. MAINTENANCE ALSO PERFORMED ATI JOB CARD 13.01-5 REJECTED TAKE OFF INSTPECTION. NO DEFECTS WERE NOTED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATOR — MALFUNCTIONED (MLG) · airframe 84,421 hrs · 35,003 cycles

ON LANDING GEAR EXTENSION INTO FJDG GEAR CAME DOWN WITH NORMAL INDICATIONS, AT APPROXIMATELY 200 FT BOTH LEFT AND RIGHT MAIN GEAR INDICATIONS WENT OUT. CREW EXECUTED A GO-AROUND, CYCLED GEAR AND LANDED WITH A NORMAL GEAR DOWN INDICATION. MAINTENANCE CYCLED GEAR HANDLE, DIMMING SWITCH BRIGHT TO DIM SEVERAL TIMES. CHECKED GEAR SWITCHES PER APPLICABLE MANUALS AND OPERATES NORMAL ON GROUND. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE HARNESS — BROKEN (NR 1 ENGINE) · airframe 83,768 hrs · 34,873 cycles

DURING CLIMB FROM FJDG NR 1 ENGINE EGT WENT TO ZERO. CREW RETURNED AIRCRAFT TO FJDG AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED EGT PIGTAIL FROM THERMOCOUPLE JUNCTION TO PYLON. OPERATIONAL CHECK OKAY PER ALL APPLICABLE MANUALS. ACCOMPLISHED ENGINE RUN IN ACCORDANCE WITH ATI ENGINE RUN HANDBOOK. ALL PARAMETERS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.

Part: MEC — FAULTY (NR 4 ENGINE) · airframe 83,542 hrs · 34,790 cycles

IN CRUISE AT 17,000 FT NR 4 ENGINE FLAMED OUT, 7,000 LBS INDICATED ON FUEL GAUGE. ALL CROSSFEEDS CLOSED. ENGINE RE-LIT AFTER COMPLETION OF CFM56 FLAMEOUT/INFLIGHT RESTART CHECK LIST. AN INSPECTION IS ON GOING. AS THE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE PERFORMED TROUBLESHOOTING PER CFM MM 71-00-00 FAULT 51 LEAD TO MEC CHANGE. MAINTENANCE REMOVED AND REPLACED MEC PER CFM 73-21-10. OPERATIONAL AND CHECK LEAK GOOD IN ACCORDANCE WITH ALL APPLICABLE MANUALS. ALL ENGINE PARAMETERS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 82,691 hrs · 34,424 cycles

AFTER DEPARTURE FROM GSO DURING CLIMB OUT TO TOL. WHEN POWER REDUCED FROM CLIMB TO CRUISE, CREW NOTED NR 1 ENGINE COMPRESSOR STALL. PRECAUTIONARY ACTION WAS TAKEN AND ENGINE SHUTDOWN FOR REMAINDER OF FLIGHT. CREW MADE AN UNEVENTFUL LANDING IN TOL.

Part: CONTROL CABLE — OUT OF RIG (NR 1 ENGINE) · airframe 82,687 hrs · 34,421 cycles

AFTER DEPARTURE FROM GSO WHILE PERFORMING POST HEAVY MAINTENANCE CHECK FLIGHT. COMPRESSOR STALL ON NR 1 ENGINE WAS NOTED WHILE REDUCING POWER SETTING FROM CLIMB TO CRUISE. AS PRECAUTIONARY ACTION NR 1 ENGINE WAS SHUTDOWN. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE INSPECTED FAN EXHAUST AND BOROSCOPED ENGINE IN ACCORDANCE WITH CFM56 MAINTENANCE MANUAL AND ATI JOB CARD 30.07. MAINTENANCE FOUND VARIABLE STATOR VALVE AND VARIABLE BLEED VALVE FEEDBACK CABLE OUT OF RIG. MAINTENANCE RIGGED CABLES IN ACCORDANCE WITH CFM56 MAINTENANCE MANUAL.

Part: PANEL — CRACKED (ZONE 500) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND LEFT FLAP ICE BREAKER PANEL CRACKED AT STATION XF219. REPAIRED PER TIMCO EO REO609034 AND DC8 SRM 51-3-0.

Part: PLATE — DAMAGED (ZONE 500) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK FOUND LEFT WING NUMBER FOUR FLAP VANE HAVE AN ELONGATED HOLE. REMOVED DAMAGED PLATE, FABRICATED NEW PLATE, LOCATED DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW PLATE IAW DOUGLAS DRAWING 5655752, DC8 SRM 51-1-8, 51-1-20D, AND 51-1-3.

Part: RIB — CRACKED (ZONE 600) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE RIB AT STATION 341 CRACKED. STOP DRILLED CRACK, FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED DOUBLER IAW DC8 SRM 57-2-0, 51-1-8, AND 51-1-20D.

Part: FRAME — DAMAGED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND FRAME DAMAGED AT STATION 1903 LEFT SIDE ABOVE HINGE CUT OUT. REMOVED DAMAGE, FABRICATED REPAIR ANGLE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR IAW DC8 SRM 51-1-8, 53-2-0, AND 51-1-21.

Part: PANEL — CHAFED (ZONE 500) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING UPPER TRAILING EDGE PANEL AFT OF TRUNNION PANEL CHAFED ON INBOARD UPPER SKIN. REMOVED DAMAGED AREA, FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED DOUBLER. IAW 57-2-0, 57-2-1, 57-3-1, 51-1-22, 57-2-21 AND 51-1-8.

Part: LONGERON — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 11 RIGHT CRACKED AT AFT SERVICE DOOR JAMB UPPER AFT CORNER. FABRICATED NEW LONGERON AND NEW SPLICES, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED NEW LONGERON AND SPLICES IAW DOUGLAS DRAWING 3773512, DC8 SRM 51-1-24, 51-1-21, 51-1-20D, 51-3-0, AND 51-1-21A.

Part: INTERCOSTAL — CRACKED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND INTERCOSTAL CRACKED FROM STATION 1140 TO STATION 1160, AT LONGERON 33 LEFT. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS. IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-21.

Part: PLATE — GOUGED (ZONE 500) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND THE LEFT NR 4 FLAP VANE CENTER OUTBOARD FLAP ATTACH PLATE GOUGED. REMOVED DAMAGED PLATE, FABRICATED NEW PLATE, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED NEW PLATE IAW DOUGLAS DRAWING 565-37552 DC8 SRM 51-3-0, AND 51-1-8.

Part: STRINGER — CORRODED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND THE CENTER WING LOWER STRINGER 76 LEFT CORRODED AT STATION XCW50.0. REMOVED CORROSION. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW TIMCO REPAIR ENGINEERING ORDER REO-G09014 DATED 1/31/2003.

Part: FRAME — CRACKED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND A CRACKED FRAME AT STATION 280 LONGERON 29 RIGHT. REMOVED DAMAGED FRAME, FABRICATED NEW FRAME, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW FRAME IAW DOUGLAS DRAWING 9779487, DC8 SRM 51-1-8, AND 51-1-20D.

Part: PLATE — WORN (ZONE 600) · airframe 82,687 hrs · 3,440 cycles

DURING ROUTINE C CHECK, FOUND RIGHT OUTBOARD FLAP BOILER PLATE KNIFE EDGED AT STATION 410. REMOVED DAMAGED BOILER PLATE, FABRICATED REPAIR PARTS, LOCATED, DRILED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW DOUGLAS DRAWINGS 5719443, 5719445, DC8 SRM 51-1-8, AND 51-1-21.

Part: BEAM — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND L-1 DOOR FORWARD INTERNAL TOP SIDE CORNER ON FIRST HORIZONTAL BEAM FROM TOP FORWARD SIDE CRACKED IN RADIUS. STOP DRILLED CRACKED, FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR DOUBLER IAW DC8 SRM 52-2-0, 51-1-8 AND 51-1-21.

Part: STRUCTURE — CRACKED (SERVICE DOOR) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND RIGHT AFT SERVICE DOOR AFT CORNER CRACKED, EXTENDING PAST STOP DRILL AT LIGHTNING HOLE. REMOVED DAMAGE, FABRICATED, REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0, 52-2-0, 51-1-8, AND 51-1-21.

Part: SKIN — CRACKED (ZONE 600) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE SKIN CRACKED AT STATION XW291. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED, REPAIR PARTS. IAW DC8 SRM 51-1-8, 51-2-1, 51-1-20D, AND 51-3-0.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND COCKPIT FLOOR PANEL 674A ATTACH ANGLE CORRODED. REMOVED DAMAGED ATTACH ANGLE. FABRICATED NEW ATTACH ANGLE, LOCATED, DRILLED TRIMMED, TREATED, PRIMED AND INSTALLED NEW ATTACH ANGLE IAW DC8 SRM 51-1-8, 53-2-0, 53-7-3 51-9-0, AND 51-3-0.

Part: SKIN — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK FOUND RIGHT AFT SERVICE DOOR CUTOUT UPPER AFT CORNER CRACKED AT FASTENER HOLE. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS WITH NEW FASTENERS IAW DC8 SRM 53-2-0, 51-1-8, 51-1-21, 51-1-20D, AND 51-3-0.

Part: INTERCOSTAL — CRACKED (SERVICE DOOR) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C-CHECK, FOUND RIGHT AFT SERVICE DOOR MID INTERCOSTAL CRACKED. REMOVED DAMAGED INTERCOSTAL. FABRICATED NEW INTERCOSTAL, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW INTERCOSTAL IAW DC8 SRM 51-1-20, 51-1-8, 51-1-21, AND DOUGLAS DRAWING 5772639.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND SEAT TRACK GOUGED AT STATION 250 BL-0. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS, IAW DC8 SRM 53-2-3, AND 53-2-3.

Part: ANGLE — CORRODED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND ANGLE CORRODED AT STATION FS 70 LONGERON 32 LEFT. REMOVED DAMAGE, FABRICATED, REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8, 51-2-0, AND 53-2-5.

Part: SKIN — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND AFT PASSENGER DOOR CUTOUT UPPER AFT CORNER CRACKED. REMOVED FASTENERS AS NEEDED TO REMOVE DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-20D.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND SEAT TRACK WORN AND GOUGED AT STATION 240 BL-0. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS, IAW,DC8 SRM 53-2-3, AND 51-1-8.

Part: DOUBLER — DAMAGED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND FORWARD LOWER AIR CONDITIONER ACCESS DOOR INTERNAL DOUBLER REQUIRES REPLACEMENT DUE TO MANY PREVIOUS REPAIRS. REMOVED EXISTING DOUBLER. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8, DOUGLAS DRAWING 5613836, AND TIMCO REPAIR ENGINEERING ORDER REO-G09011 DATED 1/28/2003.

Part: FITTING — CRACKED (BS 1767-1770) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND A CRACKED END FITTING FROM STATION 1767 TO 1770 AT LONGERON 17 RIGHT. REMOVED CRACKED END FITTING. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW END FITTING IAW DC8 SRM 51-1-20D, 51-1-21, AND 51-3-0.

Part: FRAME — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND EMPENNAGE FRAME CRACKED AT STATION 1960 LEFT SIDE WHERE HORIZONTAL STIFFENER FASTENS TO FRAME. REMOVED DAMAGE. FABRICATED REPAIR DOUBLER, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR DOUBLER IAW DC8 SRM 53-2-0, 51-1-8, 51-1-20, AND 51-1-21.

Part: ANGLE — CRACKED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUITNE C CHECK FOUND RIGHT HAND ELEVATOR DRAIN PAN INSIDE OF TAIL CONE CRACKED. REMOVED DAMAGE, FABRICATED REPAIR ANGLE, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED REPAIR ANGLE. IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-21.

Part: FITTING — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND A CRACKED END FITTING FROM STATION 1767 TO 1772 AT LONGERON 10 LEFT. REMOVED CRACKED END FITTING. LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW END FITTING IAW DC8 SRM 51-1-20D, 51-1-21, 21-3-0, AND 51-1-24.

Part: SEAT TRACK — GOUGED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C-CHECK, FOUND SEAT TRACK "B" GOUGED AT STATION FS 400. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS, LOCATED, DRILLED TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-3, AND 51-1-8.

Part: WEB — CORRODED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND WEB CORRODED AT STATION FS 1165, LONGERON 35 RIGHT. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 1-1-8, 53-2-0, 51-1-21, 51-3-0, AND DOUGLAS DRAWING NUMBER 5750195.

Part: SKIN — BENT (ZONE 300) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR UPPER SKIN IS BENT AT OUTBOARD HINGE CUTOUT. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 51-1-8, 51-1-24, 51-1-21 AND DOUGLAS DRAWING J644400.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK FOUND A SEAT TRACK GOUGED AT STATION 275 RBL 45.5. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS.IAW DC8 SRM 53-2-3, 51-1-8, AND 53-2-3.

Part: SKIN — CRACKED (ZONE 600) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE OUT BOARD SKIN SPLICE REPAIR, OUTER SKIN CRACKED. REMOVED EXISTING REPAIR. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 57-2-1, 51-1-8, 51-1-20D, AND 51-3-0.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FORWARD ENTRY DOOR CUTOUT LOWER AFT EXISTING REPAIR DOES NOT MEET THE INTENT OF AD 2000-20-08. REMOVED EXISTING DOUBLER. REMOVED EXISTING DOUBLER. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-20D.

Part: COVER — WORN (ZONE 600) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING TRAILING EDGE FLAP SPRING COVER WORN AT STATION 255. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 51-3-0, DOUGLAS DRAWING NUMBER 5719443, AND TIMCO RE[AIR ENGINEERING ORDER REO-G09016 DATED 01/31/2003.

Part: SKIN — CRACKED (ZONE 600) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LOWER LEADING EDGE OUTBOARD OF PANEL 522A EXISTING REPAIR CRACKED. REMOVED EXISTING REPAIR. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 57-2-1, 51-1-8, AND 51-1-20D.

Part: WEB — DAMAGED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND LEFT AFT PASSENGER DOOR CUTOUT JAMB WEB HAS IMPACT DAMAGE. REMOVED DAMAGE, FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED AND INSTALLED REPAIR PARTS IAW DOUGLAS DRAWIMG 9751069, TIMCO REPAIR ENGENEERING ORDER REO-G09028 DATED 02/07/2003, DC8 SRM 51-1-8, 51-1-21, 51-1-20D, AND 51-3-0.

Part: STRUCTURE — CRACKED (ZONE 100) · airframe 82,687 hrs · 344,220 cycles

DURING ROUTINE C CHECK, FOUND AFT PIT BASKET DOOR ATTACHMENT HOLE CRACKED. REMOVED DAMAGE, FABRICATED DOUBLER AND FILLER, LOCATED, DRILLED TRIMMED, TREATED, PRIMED, AND INSTALLED DOUBLER AND FILLER, IAW DC8 SRM 53-2-0, 51-1-8, AND 51-1-21.

Part: DOUBLER — GOUGED (ZONE 100) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND AIR START DOOR CUTOUT DOUBLER GOUGED. REMOVED EXISTING DOUBLER. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 51-1-8, 51-1-21 AND DOUGLAS DRAWING NUMBER 5614438.

Part: WEB — GOUGED (ZONE 500) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND LEFT MAIN LANDING GREA STRUT CUTOUT AFT VERTICAL WEB GOUGED. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS IAW DC8 SRM 51-1-21, 51-1-8, AND DOUGLAS DRAWING 5651221.

Part: FITTING — CRACKED (ZONE 200) · airframe 82,687 hrs · 34,420 cycles

DURING ROUTINE C CHECK, FOUND FITTING CRACKED ON INSIDE OF L1 DOOR UPPER AFT EDGE, BACK SIDE OF DOOR STOP. REPLACED FITTING IAW DC8 SRM 51-1-21 AND 51-1-21D.

Part: TANK — UNCALIBRATED (#4 MAIN AND ALT) · airframe 82,065 hrs · 34,175 cycles

AFTER TAKE OFF FROM LRD, THE FLIGHT CREW NOTICED A SIGNIFICANT AIRCRAFT ROLL TO THE RIGHT WHICH REQUIRED HALF LEFT AILERON TO MAINTAIN LEVEL FLIGHT. THE FLIGHT RETURNED TO LRD FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE #4 MAIN AND #4 ALTERNATE TANKS READING LOW. MAINTENANCE RECALIBRATED THE TANKS AND PERFORMED SUCCESSFUL OPERATIONAL CHECKS IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: HARNESS — CRACKED (ENGINE) · airframe 81,502 hrs · 33,930 cycles

AFTER TAKEOFF FROM TOL, THE FLIGHT CREW NOTICED AN ABNORMALLY HIGH ENGINE GAS TEMPERATURE INDICATION ON THE NUMBER FOUR ENGING. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURE AND THE ENGINE WAS SECURED AS PERCAUTIONARY MEASURE AND DISCHARGED ONE FIRE AGENT BOTTLE. THE FLIGHT RETURNED TO TOL FOR AN UNVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGING WITH NO EVEIDENCE OF A FIRE. FURTHER INSPECTION REVEALED THE RIGHT EGT HARNESS CRACKED. MAINTENANCE REPLACED THE EGT HARNESS AND FIRE AGENT BOTTLE. MAINTENANCE PERFORM A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE COMPANY ENGINE RUN HAND BOOK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WEB — CRACKED (WHEEL WELL) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A CRACK WAS DETECTED ON THE VERTICAL WEB IN THE RIGHT WHEEL WELL AT FUSELAGE STATION 860, RIB LINE 14. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED WEB, FABRICATION AND INSTALLATION OA NEW WEB IN ACCORDANCE WITH DOUGLAS DRAWING 5654672 AND ENGINEERING ORDER 53-DC8-1786.

Part: FITTING — CORRODED (STA 8) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, CORROSION WAS DETECTED ON LONGERON 36 END FITTING BETWEEN FUSELAGE STATION 8 AND 10. REPAIR ACCOMPLISHED REMOVAL OF END FITTING, FABRICATION AND INSTALLATION NEW END FITTING IN ACCORDANCE WITH DOUGLAS DRAWING 9755865 AND ENGINEERING ORDER 53-DC8-1792.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE EXTERNAL PLATING AFT OF THE L-1 DOOR LOWER AFT CORNER.

Part: FITTING — CRACKED (STA 857) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A CRACK WAS DETECTED AT LONGERON END FITTING LOCATED AT FUSELAGE STATION 857, LONGERON 1. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED FITTING, FABRICATION AND ISTALLATION NEW END FITTING IN ACCORDANCE WITH DACO DRAWING 4750521 AND ENGINEERING ORDER 53-DC8-1784.

Part: DOUBLER — CRACKED (STABILIZSER) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT HORIZONTAL STABILIZER AFT SPAR WEB INTERNAL DOUBLER AT STATION XE 105. REPAIR ACCOMPLISHED REMOVAL OF DAMAGE AREA, FABRICATION AND INSTALLATION A NEW INTERNAL DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 53-DC8-1786.

Part: PAN — CRACKED (CARGO DOOR) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE LOWER C-PIT CARGO DOOR FORWARD DOOR PAN. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION A NEW DOOR PAN IN ACCORDANCE WITH DACO DRAWING 5704349 AND ENGINEERING ORDER 52-DC8-1781.

Part: CAP — GOUGED (STA 1703) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A GOUGED WAS DETECTED AT FUSELAGE STATION 1703, LONGERON 22 LEFT FUSELAGE FRAME CAP. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED CAP, FABRICATION AND INSTALLATION IN ACCORDANCE WITH DACO DRAWING 5612146 AND ENGINEERING ORDER 53-DC8-1783.

Part: FRAME — GOUGED (MAIN CABIN) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHEACK INSPECTION, A GOUGE WAS DETECTED ON FUSELAGE FRAME AT FUSELAGE STATION 1520, LONGERON 17 LEFT. REPAIR ACCOMPLISHED BLENDED GOUGE AND FABRICATED AND INSTALLED REPAIR DOUBLEERS IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 53-DC8-1768.

Part: PAN — CRACKED (CARGO DOOR) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE LOWER C-PIT DOOR CORNER PAN. REPAIRED ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION A NEW PAN AND SPLICE PLATES IN ACCORDANCE WITH DAC DRAWINGS 5707387-501, 5074349-7 AND DACO STRUCTURAL REPAIR MANUAL.

Part: INTERCOSTAL — CORRODED (NOSE) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, CORROSION WAS DETECTED ON INTERCOSTAL AT FUSELAGE STATION 8 LONGERON 35 RIGHT. REPAIR ACCOMPLISHED REMOVAL OF INTERCOSTAL, FABRICATION AND INSTALLATION AN NEW INTERCOSTAL IN ACCORDANCE WITH DOUGLAS DRAWING 5615530 AND ENINEERING ORDER 53-DC8-1779.

Part: FLANGE — CORRODED (F.S 1380) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, CORROSION WAS DETECTED ON FRAME FLANGE AT FUSELAGE STATION 1380, LONGERON 35 LEFT. REPAIR ACCOMPLISH CORROSION REMOVAL, FABRICATION AND INSTALLATION A REPAIR ANGLE IN ACCORDANCE WITH DACO STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 51-DC8-1782.

Part: STIFFENER — CRACKED (NOSE) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, CRACKS WERE DETECTED ON THE FORWARD BULKHEAD LOWER STIFFENER AT FUSELAGE STATION -156. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTUAL REPAIRE MANUAL AND ENGINEERING ORDER 53-DC8-1771.

Part: RIB — GOUGED (LEFT WING) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A GOUGE WAS DETECTED ON THE LEFT WING LEADING EDGE RIB AT STATION XFS 445. REPAIR ACCOMPLISHED FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 57-DC8-1767.

Part: RIB — CRACKED · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT WING LEADING EDGE LOWER RIB OUTBOARD ACCESS PANEL 518. REPAIR ACCOMPLISHED STOP DRILLING CRACK, FABRICATION AND INSTALLATION A REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL 57-2-0 AND ENGINEERING ORDER 57-DC8-1764.

Part: RIB — CRACKED (RIGHT WING) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT WING LEADING EDGE RIB BETWEEN ACCESS PANELS 519A AND 519B. REPAIR ACCOMPLISHED FABRICATION AND INSTALLATION OF REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 57-DC8-1765.

Part: PAN — CRACKED · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, THE "A" PIT BASKET DOOR AFT CENTER SECTION DOOR PAN WAS FOUND CRACKED. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED PAN, FABRICATION AN INSTALLATION A NEW SIDE PAN IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL, DACO DRAWING 5704349 AND ENGINEERING ORDER 52-DC8-1763.

Part: INTERCOSTAL — CRACKED (STA 520) · airframe 79,927 hrs · 33,374 cycles

DURING ROUTINE C CHECK INSPECTION, CORROSION AND CRACKS WERE DETECTED ON INTERCOSTALS BETWEEN FUSELAGE STATION 520 AND 560, LONGERON 33 RIGHT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGE AREA, FABRICATION AND INSTALLATION INTERCOSTALS IN ACCORDANCE WITH DOUGLAS DRAWING 5616520 AND ENGINEERING ORDER 53-DC8-1762.

Part: WIRE — DAMAGED (NOSE GEAR) · airframe 78,795 hrs · 32,840 cycles

EN ROUTE FROM LAX TO TOL, DURING DESCENT THE NOSE GEAR DOWN AND LOCK INDICATION LIGHT FAILED TO ILLUMINATE ACCOMPANIED BY A GEAR UNSAFE INDICATION DURING GEAR EXTENSION. THE FLIGHT CREW CYCLED THE LANDING GEAR AND NORMAL INDICATION WAS RESTORED. THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR INDICATION SYSTEM, A DAMAGED WIRE LOCATED ON THE NOSE GEAR DOWN AND LOCK SWITCH. THE WIRE WAS REPAIRED AND MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATION — MALFUNCTIONED (NLG)

ON DESCENT INTO TOL, WHEN THE CREW EXTENDED THE LANDING GEAR, THE NOSE GEAR DOWN AND LOCK INDICATION LIGHT FAILED TO ILLUMINATE, ACCOMPANIED BY A LANDING GEAR UNSAFE LIGHT. THE CREW CYCLED THE LANDING GEAR WITH THE WARNING INDICATIONS REMAINING THE SAME. MAINTENANCE INSPECTED THE NOSE GEAR AND THE INDICATION SYSTEM WIRING WITH NO DISCREPANCIES NOTED. MAINTENANCE PERFORMED A SUCCESSFUL GEAR SWING IN ACCORDANCE WITH THE MAINTENANCE MANUAL, ALL INDICATIONS WERE NORMAL, AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PIN — SHEARED (LT MLG)

EN ROUTE DFW TO TOL UPON GEAR RETRACTION, THE LEFT MAIN GEAR DOWN AND LOCK LIGHT REMAINED ILLUMINATED. THE CREW RECYCLED THE LANDING GEAR AND THE INDICATION REMAINED THE SAME. THE FLIGHT CONTINUED TO TOL WITH THE LANDING GEAR IN THE DOWN AND LOCKED POSITION AND MADE AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE LEFT MAIN GEAR RETRACT PIN SHEARED. MAINTENANCE REPLACED THE RETRACT PIN IN ACCORDANCE WITH DACO MAINTENANCE MANUAL PROCEDURES.

Part: RESISTOR — BURNT (EXTERNAL PWR SYS)

ON CREW PREFLIGHT, ODOR OF UNKNOWN ORIGIN WAS NOTED ON FLIGHT DECK WITH EXTERNAL POWER APPLIED. MAINTENANCE IDENTIFIED THE SOURCE OF ODOR TO BE AN EXTERNAL POWER CIRCUIT RESISTOR FOR THE INDICATION LIGHT. THE EXTERNAL POWER SYSTEM WAS DEFERRED IAW MEL 24-16, AND THE AIRCRAFT RETURNED TO SERVICE. S/D - REPLACED RESISTOR R4-19 IAW DACO M/M CHAPTER 20 AND CLEARED THE DEFERRED ITEM.

Part: TURBINE BLADES — DAMAGED (NR 2 ENGINE)

SHORTLY AFTER ROTATION DEPARTING FLL, THE NUMBER 2 ENGINE EXPERIENCED A HEAVY COMPRESSOR STALL. THE ENGINE REPORTILY FLAMED OUT. THE CREW SECURED THE ENGINE IAW COMPANY PROCEDURES AND RETURNED TO FLL. GROUND INSPECTION BY MAINTENANCE FOUND METAL IN THE TAILPIPE ACCOMPANIED BY DAMAGED TURBINE BLADES. THE ENGINE REQUIRED REPLACEMENT.

Part: ANGLE — CORROSION (FS 580)

DURING THE D-CHECK INSPECTION, FOUND CORROSION ON FLOOR SUPPORT ANGLE AT FS 580, L33R TO L33L, IN THE FWD CARGO COMPARTMENT. A REPAIR WAS ACCOMPLISHED PER DACO SRM 51-1-21, 51-1-8, AND 51-00. (X)

Part: FITTING — CRACKED (NR 1 PYLON)

DURING THE D-CHECK INSPECTION, FOUND A CRACK ON THE NR 1 PYLON SUPPORT FITTING AT FS YN 387 IN 2EA LOCATIONS. MANUFACTURED FITTING PER DACO DRAWING 5756790 AND INSTALL FITTING PER DACO DRAWINGS 5756791, 5756801, AND DACO SRM 51-00, 51-1-20, 51-3-0, AND 51-1-8. (X)

Part: ANGLE — CORROSION (FS 600)

DURING THE D-CHECK INSPECTION, FOUND CORROSION ON FLOOR SUPPORT ANGLE AT FS 600, L34R TO L34L, IN THE FWD CARGO COMPARTMENT. A REPAIR WAS ACCOMPLISHED PER DACO SRM 51-1-21, 51-1-8, AND 51-00. (X)

Part: COWLING — CRACKED (ENGINE)

DURING THE D-CHECK INSPECTION, FOUND CRACK ON THE INBOARD COWL ON ENGINE. REPAIR WAS ACCOMPLISHED PER DRAWING CF-N820BX, 10/96 DATED 1/18/96. REPAIR WAS APPROVED ON FAA FORM 8110-3 DATED 1/25/96. (M)

Part: SKIN — DENTED (FS 1420)

DURING THE D-CHECK INSPECTION, FOUND DENTS IN THE OUTER SKIN OF THE AFT LOWER CARGO DOOR. REPAIR WAS PERFORMED PER DACO SRM 52-4-1,52-2-0, 51-1-4, 51-1-8, AND 51-1-21A. (X)

Part: BLKHD COVER — CRACKED (FS 857.125)

DURING THE D-CHECK INSPECTION, FOUND CRACKS ON THE BULKHEAD COVER AT FS 857.125. REPAIR WAS PERFORMED PER DACO SRM 51-1-4, 51-1-8, 51-1-21, AND 53-2-0. (X)

Part: WEB — CRACKED (FS 781.500)

DURING THE D-CHECK INSPECTION, FOUND CRACKS ON RT WEB AT FS 781.500. REPAIR WAS ACCOMPLISHED PER DACO SRM 53-8-1, 51-1-4, 51-1-8, 53-2-0, AND 51-1-21. (X)

Part: SKIN — GOUGED (FS 505)

DURING D-CHECK INSPECTION, GOUGED AREA WAS FOUND AT 'B' PIT DOOR JAMB AT FS NR 505, L31 RT. REPAIR WAS ACCOMPLISHED BY INSTALLING FILLER AND DOUBLER PER DRAWING NR CF-N820BX, 11/96, DATED 1/27/96. THIS DRAWING IS APPROVED UNDER DACO SRM AND MAINTENANCE MANUAL AND GRANTED APPROVAL BY FAA FORM 8110-3. (M)

Part: SKIN — CRACKED (RT TE FLAP)

DURING THE D-CHECK INSPECTION, FOUND DAMAGE ON RIGHT LOWER FLAP AT FS NR 215. REPAIR WAS ACCOMPLISHED BY INSTALLING NEW SKIN PANEL PER DRAWING CF-N820BX, 2/96 DATED 1/6/96 AND WAS APPROVED BY FAA FORM 8110-3 DATED. (M)

Part: JAMB — DENTED (FS 250)

DURING THE D-CHECK INSPECTION, FOUND DENTS AND SCRATCHES AT FWD CARGO DOOR UPPER DOOR JAMB OF 'A' PIT AT FS NR 250. REPAIR WAS ACCOMPLISHED PER DRAWING CF-N820BX-11/96 DATED 1/27/96 AND APPROVED ON FAA FORM 8110-3 DATED 2/2/96. (M)

Part: LE FORMERS — CRACKED (LT WING)

DURING THE D-CHECK INSPECTION, FOUND TWO CRACKED FORMERS AT FS NR 422. REPAIR WAS ACCOMPLISHED PER DACO SRM 57-3-1 AND 57-0 CODE 5 AND DRAWING CF-N820, 7/96 DATED 1/18/96 WHICH HAS APPROVAL ON FAA FORM 8110-3 DATED 1/22/96. (M)

Part: SKIN — CRACKED (FS 360-380)

DURING THE D-CHECK INSPECTION, FOUND CRACK AT FS NR 360 TO 380, L30 RT. REPAIR WAS ACCOMPLISHED PER DRAWING CF-N820BX-3/96, DATED 1/9/96. THIS REPAIR WAS PERFORMED IAW DACO SRM AND MAINTENANCE MANUALS AND APPROVED ON FAA FORM 8110-3 DATED 1/31/96. (M)

Part: FRAME — CRACKED (FS 781.500)

DURING THE D-CHECK INSPECTION, FOUND CRACKS ON FRAME AT FS 781.500, L35R. REPAIR WAS PERFORMED PER DACO SRM 53-8-1,51-1-4, 51-1-8, AND 51-1-21. (X)

Part: FITTING — CRACKED (HORIZ STAB)

DURING THE D-CHECK INSPECTION, FOUND CRACKED FITTING ON THE RIGHT HORIZONTAL STABILIZER L/E AT FS XFS 47. FITTING WAS MANUFACTURED PER DRAWING CF-N820BX-15/96, DATED 2/9/96 AND WAS APPROVED BY FAA FORM 8110-3 DATED 2/20/96. (M)

Part: SUPPORT — CORROSION (FS 1460)

DURING THE D-CHECK INSPECTION, FOUND CORROSION ON STRUT SUPPORT LOWER LT SIDE AT FS 1460 IN THE AFT CARGO COMPARTMENT. A REPAIR WAS ACCOMPLISHED PER DACO SRM 51-1-21, 51-1-8, AND 51-00. (X)

Part: SKIN — CRACKED (AFT PAX DOOR)

DURING THE D-CHECK INSPECTION, FOUND A CRACK ON THE AFT PASSENGER DOOR ON THE LOWER AFT CORNER. A REPAIR WAS PERFORMED PER DACO SRM 53-2-0, 51-1-20D, 51-1-21A, 51-1-8, 51-00, AND DRAWING CF-N820BX-13/96. (X)

Part: ENGINE — FLAMED OUT (NR 1)

ON DESCENT INTO TOL, NR 1 ENGINE FLAMED OUT AT 31,000 FEET WHEN THE THROTTLE WAS RETARDED. THE ENGINE RE-LIT AND OPERATED NORMALLY AFTER COMPLETION OF POWER LOSS CHECKLIST. INSPECTION ON THE GROUND IN TOL IDENTIFIED NO DEFECTS. THE FUEL FILTER WAS CHECKED AND FOUND TO BE SERVICEABLE. IT WAS REPLACED AS A PRECAUTION. THE ENGINE WAS RUN AND FOUND TO OPERATE NORMALLY. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: ROD END — FRACTURED (RT MLG)

AFTER LANDING AT TOL, IT WAS NOTED THAT THE RT MLG ACTUATOR ROD END HAD FAILED DURING THE LAST LANDING GEAR EXTENSION. THE ROD END DID NOT, HOWEVER, FAIL IN THE THREADS. THE EYE ITSELF FRACTURED ADJACENT TO THE THREADED SHANK. A PREVIOUSLY EXISTING CRACK ORIGINATING IN THE TRANSITION AREA FROM THE EYE TO THE THREADED SHANK APPEARS TO HAVE BEEN THE ORIGIN OF THE FRACTURE. THE ROD END WAS REPLACED IAW THE DC-8 MM AND TR 32-121, AND THE AIRCRAFT RETURNED TO SERVICE.