N799AL

Part: OXYGEN MASK — TORN (EMERGENCY EQUIP) · airframe 87,026 hrs · 26,330 cycles

DURING POST FLIGHT INSP, FOUND F/A DEMO KIT O2 MASK TORN. MX REPLACED O2 MASK IN F/A DEMO KIT IAW MM 16.02.

Part: FAN — DEFECTIVE (ZONE 200) · airframe 86,341 hrs · 26,209 cycles

DURING CRUISE, THE LT RECIRCULATION FAN EMITTED A BURNED ODOR. THE CREW SHUT OFF THE LT RECIRCULATION FAN AND BURNED ODOR WENT AWAY. THEY LANDED WITHOUT FURTHER INCIDENT. MX REPLACED THE LT RECIRCULATION FAN. OPS CHECK GOOD IAW MM 21-21-1. ACFT WAS RETURNED TO SERVICE.

Part: FAN — ODOR (COCKPIT) · airframe 86,341 hrs · 26,209 cycles

DURING CRUISE, THE LT RECIRCULATION FAN EMITTED A BURNED ODOR IN COCKPIT. THE CREW SHUTOFF LT RECIRCULATION FAN AND ODOR WENT AWAY. OPEN

Part: FAN — DEFECTIVE (ZONE 200) · airframe 86,112 hrs · 26,169 cycles

DURING CRUISE, THE RT RECIRCULATION FAN EMMITTING A BURNING ODOR, TURNED OFF THE RT RECIRCULATION FAN AND ODOR WENT AWAY, LANDED WITHOUT FURTHER INCIDENT. MX REPLACED RT RECIRCULATION FAN. OPS CHECK GOOD IAW MM 21-21-1. ACFT WAS RETURNED TO SERVICE.

Part: GENERATOR — MALFUNCTIONED (NR 4) · airframe 85,925 hrs · 26,135 cycles

DURING CLIMB OUT, NR 4 GENERATOR BREAKER CYCLES OPEN AND CLOSED SEVERAL TIMES, GENERATOR WOULD NOT CARRY ITS OWN BUSS, VOLTS AND FREQUENCY OK. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. IN WORK.

Part: CSD — DEFECTIVE (NR 4 GENERATOR) · airframe 85,925 hrs · 26,135 cycles

DURING CLIMB OUT, NR 4 GENERATOR BREAKER CYCLED OPEN AND CLOSED SEVERAL TIMES, GENERATOR WOULD NOT CARRY ITS OWN BUSS, VOLTS AND FREQUENCYS OK. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. NR 4 GENERATOR WAS DEFERRED IAW MEL 24-10-01. MX REPLACED (CSD). OPS CHECK GOOD IAW MM 24-10-1. ACFT WAS RETURNED TO SERVICE.

Part: FITTING — CRACKED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING NR 1 STUB WING FITTING INTERNAL PART CRACKED AT STA XW 454.000. REMOVED CRACKED FITTING. CLEANED, TREATED, PRIMED AREA AND NEW FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-1-20D AND SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 300) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER SKIN CORRODED AT STATION XE 28.843. REMOVED CORROSION. FOUND OUT OF LIMITS. 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 DC8 SRM 51-1-8, DC8 SRM 55-2-0, DC8 SRM 51-1-21, SRM 51-3-0, SRM 55-1-0 PAGE 1, DC8 SRM 55-3-1 FIGURE 1 SHEETS 1-2 ITEM "L", DPS 4.710 REV "L", DC8 SRM 51-1-8B, DC8 SRM 55-3-1, SRM 51-1-21, SRM 51-3-0, AND SRM 51-3-1.

Part: ANGLE — CORRODED (ZONE 300) · airframe 85,843 hrs · 26,115 cycles

DUIRNG ROUTINE C CHECK INSPECTION FOUND RIGHT VERTICAL STABILIZER TO FUSELAGE JOINT ANGLE CORRODED AT STA 1590. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED ANGLE, SPLICE, FILLER AND SHIMS. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-5 FIGURE 16A SHEETS ½, SRM 51-1-8, SRM 53-2-0, SRM 53-2-2 FIGURE 16A SHEETS 1-2, DPS 4.710 REV "L", SRM 51-1-6, SRM 51-1-8B, SRM 53-2-2, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 200) · airframe 85,843 hrs · 26,115 cycles

DUIRNG ROUTINE C CHECK INSPECTION FOUND AFT FUSELAGE SKIN CRACKED AT STATION 1580.000 LONGERON 20RIGHT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/21/11, DRAWING ED-5307 DATED 01/20/11, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 100) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND FUSELAGE EXTERNAL SKIN CORRODED AT SEVERAL POINTS AT STATION 1530.000 LONGERON 23-28LEFT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL DOUBLER, EXTERNAL DOUBLER, FINGER DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/24/11, SMN DRAWING ED-5320 DATED 01/28/11, SRM 51-1-8, SRM 53-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING UPPER SKIN CORRODED AT STATION XRS 360.000 STRINGER 6. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/10/11, SEMAN DRAWING ED-5305 DATED 01/24/11, SRM 51-1-8, SWM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 600) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT WING UPPER SKIN CORRODED AT STATION XRS 795.000 STRINGER 3-5. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/10/11, SMN DRAWING ED-5301 DATED 01/26/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 600) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT WING UPPER SKIN CORRODED AT STATION XRS 763.000 STRINGER 2-4. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/10/11, SMN DRAWING ED-5301 DATED 01/26/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING UPPER SKIN CRACKED AND CORRODED AT STA XRS -17.000 STR-9. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAP 57-2-1, FIG 22, SRM 51-1-8, SRM 53-2-0, NDT SPM PART 06-10-01-001, SRM 57-3-2, FIG 13 ITEM "A", SRM 51-10-0, FIG 1, SHEET 20, DPS 4.710 REV "L", SRM 51-1-8B, SRM 57-2-1 FIGURE 22, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 600) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C-CHECK INSP, FOUND RT WING CTR L/E UPPER PANEL CORRODED AT STA XW 408.000. REMOVED CORRION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAP 57-3-2, FIG 5 SHEET 1, SRM 51-1-8, SRM 57-2-0, SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-3-2, FIG 5 SHEET 1 ITEMS "A", DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING CENTER LEADING EDGE LOWER SKIN CORRODED AT STATION XFS 347.750. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/21/11, SMN DRAWING ED-5313 DATED 01/25/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: DOUBLER — CORRODED (ZONE 600) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C-CHECK INSP, FOUND RT WING CTR L/E UPPER SURFACE DOUBLER CORRODED AT STA XFS 423.000 - XFS 400.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED DOUBLER. FABRICATED DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED DOUBLER IAW SRM CHAP 57-2-1, FIG 38, TR 57-85, SRM 51-1-8, SRM 57-2-0, SRM 51-1-21, DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING CENTER LEADING EDGE LOWER SKIN CORRODED AT STATION XFS 341.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/21/11, SMN DRAWING ED-5313 DATED 01/25/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING UPPER SKIN CORRODED AT STATION XRS 811.000 STRINGER 3 TO STRINGER 4. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/10/11, SMN DRAWING ED-5302 DATED 01/29/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING CENTER LEADING EDGE LOWER SKIN CORRODED AT STATION XFS 385.250. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/21/11, DRAWING ED-5315 DATED 01/28/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: FASTENER — IMPROPER PART (ZONE 100) · airframe 85,843 hrs · 26,115 cycles

DURING ROUTINE C-CHECK INSP, FOUND CHERRY MAX RIVETS USED IN REPAIR AT STATION ES 1360-1380. REMOVED FASTENERS FROM REPAIRED AREA. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, FINGER DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAP 53-2-1, FIGURE 7, TR 53-203, SRM 51-1-21, SRM 51-1-21A, SRM 53-4-1 FIG 18B, SHEET 2, ITEM "A", SRM 51-9-0, DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, SRM 51-1-11, AND SRM 51-3-1.

Part: SWITCH — SHORTED (ACM) · airframe 85,546 hrs · 26,041 cycles

FIFTEEN MINUTES INTO FLIGHT, BOTH AIR CYCLE MACHINES ON THE RT ENVIRONMENTAL CONTROL CIRCUIT BREAKER AND THE BATTERY DIRECT PACS OVERTEMP TRIPPED. NO CONTROL OF THE LOAD CONTROL VALVE WAS AVAILABLE. THE CREW RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT. MX TROUBLESHOT THE SYS AND FOUND THE COMPRESSOR OVERTEMP SWITCH PS 12-2-1, WIRING DIAGRAM 21-1-6 WIRE BROKEN OFF FROM THE TERMINAL AND GROUNDED TO THE DUCT. THE WIRE WAS REPAIRED AND REATTACHED TO THE SWITCH IAW MM 20-50-1. CIRCUIT BREAKER NO LONGER TRIPS, RT HAND NASI TEMPERATURE READINGS ARE NORMAL, ALL VALVES CYCLE NORMAL.

Part: CONTROL VALVE — DEFECTIVE (A/C PACK) · airframe 85,545 hrs · 26,040 cycles

AFTER TAKEOFF, WHEN THE RT AIR CONDITIONING PACK WAS TURNED ON, THE RT ENVIRONMENTAL CONTROL CIRCUIT BREAKER AND THE RT ACM CONTROL CIRCUIT BREAKER OPENED AND WOULD NOT RESET. THE CREW RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT. MX TROUBLESHOT THE SYS AND REPLACED THE RT FLOW CONTROL VALVE ASSY, IAW MM 21.04. THE OPS CHECK WAS GOOD AND THE ACFT WAS RETURNED TO SERVICE.

Part: FUEL FILTER — CLOGGED (ZONE 400) · airframe 84,605 hrs · 25,778 cycles

AFTER LEVEL OFF, WITH ANTI-ICE OFF NR 3 ENG N1 ROLLED BACK TO 80 PERCENT, N2 89 PERCENT, OIL PRESSURE 50PSI, FUEL FLOW FLUCTATING 2000-2800 AND PPH EPR 1.4-1.6. TURNED ON ANTI-ICE, NO HELP OIL TEMP BEGAN TO RISE FROM 90 TO 120. THE CREW SHUTDOWN NR 3 ENG. THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED NR 3 ENG OIL FILTER WITH NO PROBLEMS, NR 3 FUEL FILTER WAS CLOGGED. REPLACED FUEL FILTER. WHEN PERFORMED MAX POWER INSP NR 3 ENG COOL DOWN OIL PRESSURE LIGHT ILLUMINATED, REPLACED OIL PRESSURE TRANSMITTER, ENGINE OIL TEMP SENSOR AND ENGINE OIL FILTER. OPS CHECK GOOD IAW MM 79-32-1, 79-34-1, 79-2-07, 79-33-1 AND ERH 70.01. ACFT WAS RETURNED TO SERVICE.

Part: PULLEY — FROZEN (MLG) · airframe 84,512 hrs · 25,754 cycles

DURING CLIMB OUT, AFTER GEAR RETRACTION GEAR DOOR LIGHT ILLUMINATED. THE CREW CYCLED GEAR AND LIGHT REMAINED ON. THE ALTERNATE LIGHT TESTED GOOD WHEN FWD RED GEAR DOOR LIGHT WAS ON. THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED AND FOUND EXCESSIVE AMOUNT OF WATER IN GEAR DOORS AND LT AND RT UPLATCH POSITION INTERLOCK CABLE TOP PULLEY WAS FROZEN. THEY ADJUSTED PULLEY AND LUBED ALL MECHANISM IN THE SYS. OPS CHECK GOOD IAW MM 32-10-0 AND 32-12-1. ACFT WAS RETURNED TO SERVICE.

Part: STRIKER — OUT OF ADJUST (ZONE 700) · airframe 84,211 hrs · 25,670 cycles

DURING CLIMBOUT, AFTER GEAR RETRACTION THE DOOR NOT LATCH LIGHT REMAINED ON. THE CREW CYCLED THE GEAR AND LIGHT REMAINED ON. THEY LANDED WITHOUT FURTHER INCIDENT. MX FOUND THE LT GEAR DOOR STRIKER OUT OF ADJUSTMENT. THEY ADJUSTED THE DOOR STRIKER. OPS CHECK GOOD IAW MM 32-10-0. ACFT WAS RETURNED TO SERVICE.

Part: ANTI-ICE VALVE — DEFECTIVE (ZONE 400) · airframe 84,176 hrs · 25,662 cycles

DURING CLIMB OUT WITH ANTI-ICE ON NR 4 ENG COMPRESSOR STALLED. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED NR 4 INBD ANTI-ICE CONTROL VALVE REGULATOR. OPS CHECK GOOD IAW MM 75-10-1. ACFT WAS RETURNED TO SERVICE.

Part: STRIKER — OUT OF ADJUST (LT MLG DOOR) · airframe 84,127 hrs · 25,649 cycles

DURING CLIMBOUT, THE DOOR NOT LATCH LIGHT REMAINED ON AFTER GEAR RETRACTION, CREW CYCLED THE GEAR AND LIGHT REMAINED ON. THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED MLG AND FOUND THE LT MLG DOOR STRIKER OUT OF ADJUSTMENT. THEY ADJUSTED THE DOOR STRIKER. OPS CHECK GOOD IAW WD 32-1-0 AND MM 32-10-0. ACFT WAS RETURNED TO SERVICE.

Part: OIL SYSTEM — LOW PRESSURE (NR 2 ENGINE) · airframe 83,999 hrs · 25,615 cycles

DURING CRUISE FROM NR 2 ENGINE LOW OIL PRESSURE LIGHT CAME ON. THE CREW SHUTDOWN NR 2 ENG AND LANDED WITHOUT FURTHER INCIDENT. MX REPLACED MAIN OIL FILTER, LOW OIL PRESSURE SWITCH AND OIL PRESSURE DIFFERENTIAL SWITCH. OPS CHECK GOOD IAW MM 79-20-7, ERH 01.03.1. ACFT WAS RETURNED TO SERVICE.

Part: PRESSURE SWITCH — MALFUNCTIONED (NR 2 OIL SYS) · airframe 83,999 hrs · 25,614 cycles

DURING CRUISE, NR 2 ENG LOW PRESSURE LIGHT CAME ON. THE CREW SHUTDOWN NR 2 ENG AND LANDED WITHOUT FURTHER INCIDENT. MX REPLACED LOW OIL PRESSURE SWITCH AND OIL DIFFERENTIAL SWITCH. OPS CHECK GOOD IAW MM 79-33-1 AND 79-32-2. ACFT WAS RETURNED TO SERVICE.

Part: FAN — SMOKE (CABIN)

DURING CRUISE, THE LT RECIRCULATION FAN EMITTING BURNED ODOR. THE CREW TURNED OFF LT RECIRCULATION FAN AND LANDED WITHOUT FURTHER INCIDENT. IN WORK.

Part: WIRE — BURNED (ZONE 400) · airframe 83,634 hrs · 25,530 cycles

DURING CLIMB OUT FROM TAPA NR 4 ENG EPR INOP, NR 4 GENERATOR CAUSED A MOMENTARY LOSS OF ALL POWER THEN LOCKED OUT-SHORTLY AFTER ZOLTS AND FREQUENCY WENT TO ZERO, AND NR 4 ENG BEGAN TO SPARK EVERY 25 SECONDS THE CREW SHUTDOWN NR 4 ENG. THEY RETURNED TO TAPA WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED EPR RATIO TRANSMITTER, RT IGNITER PLUG. DURING ENGINE RUN NUMBER FOUR EXPERIENCED OTHER MALFUNCTION. MAINTENANCE INSPECTED NUMBER FOUR ENGINE AND FOUND PYLON WIRING WAS BURNED. NR 4 ENGINE PYLON WIRING DEFERRED TO MCC IAW ATI MM 13.04, GMM 3.117. MAINTENANCE IN MCC REPLACED PYLON ELECTRICAL WIRING. OPERATIONAL CHECK GOOD IAW WD 23-4-3, 24-2-1, 24-2-4, 24-2-8, 24-3-6, 24-37, 24-3-8, 24-3-9, 26-1-1, 28-4-1, 28-5-

Part: POWER SUPPLY — DEFECTIVE (FUEL FLOW) · airframe 83,633 hrs · 25,529 cycles

DURING CRUISE, ALL FOUR FUEL FLOW INDICATORS WENT TO ZERO AND NUMBER FOUR EPR FAILED. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED BOTH FUEL FLOW POWER SUPPLY. OPERATIONAL CHECK GOOD IAW ATI ERH 71.01 AND ERH 70.01. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CLAMP — LOOSE (BLEED VALVE) · airframe 83,625 hrs · 25,525 cycles

DURING APPROACH INTO KBWI NUMBER FOUR ENGINE FIRE WARNING CAME ON INTERMITTENTLY. THE CREW SHUTDOWN NUMBER FOUR ENGINE AS A PRECAUTION, THEY LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED AND TIGHTENED LOOSE CLAMP ON HIGH STAGE BLEED VALVE. OPERATIONAL CHEK GOOD IAW MAINTENANCE MANUAL 20-11-0. ACFT WAS RETURNED TO SERVICE.

Part: AMPLIFIER — DEFECTIVE (NR 2 COMPASS) · airframe 83,314 hrs · 25,437 cycles

DURING CLIMB OUT, NR 2 COMPASS SYS PRECESSED EXCESSIVELY. CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED NR 2 INSTRUMENT AMP RACK. OPS CHECK GOOD IAW MM 34-20-2. ACFT WAS RETURNED TO SERVICE.

Part: DOOR — LACK OF LUBE (MLG) · airframe 83,314 hrs · 25,438 cycles

DURING CLIMB OUT, CREW HEARD A VIBRATION SOUND COMING FROM THE NLG AREA. THEY CYCLED THE NLG AND THE NOISE CONTINUED. CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX INSPECTED AND FOUND RT NOSE GEAR DOOR WAS DOWN. MX LUBED DOOR LOCK MECHANISM. OPS CHECK GOOD IAW MM 32-22-2. ACFT WAS RETURNED TO SERVICE.

Part: INDICATOR — DEFECTIVE (EPR SYSTEM) · airframe 83,280 hrs · 25,427 cycles

DURING TAKEOFF FROM NR 1 EPR GUAGE WOULD NOT ACCELERATE. THE CREW RETURNED TO BLOCKS WITHOUT FURTHER INCIDENT. MX REPLACED NR 1 EPR TRANSMITTER. OPS CHECK GOOD IAW MM 77-11-1, AND ERH 70.01.1. ACFT WAS RETURNED TO SERVICE.

Part: ANTI-SKID SYS — DEFECTIVE (ZONE 700) · airframe 83,274 hrs · 25,425 cycles

DURING TAKEOFF, ANTI-SKID INOP LIGHT ILLUMINATED ON SKID CONTROL MONITOR. THE CREW RETURNED TO BLOCK WITHOUT FURTHER INCIDENT. MX REPLACED ANTI-SKID CONTROL VALVE AND ANTI-SKID TRANSDUCER. OPS CHECK GOOD IAW MM 32-43-0, 32-43-3. ACFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (ZONE 300) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR UPPER SKIN CRACKED AT STATION XE 166.312. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND FINGER DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. PERFORMED BALANCE. FOUND WITHIN LIMITS MOMENT 1532.0 IN-LBS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XE 132.000 - 246.000 IAW SRM 55-4-1 FIGURE 1 SHEET 1-2 ITEMS "E" & "F", SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, SRM 51-1-8B, SRM 5-1-11, AND SRM 51-4-4 TR 51-116 PAGES 1-4.

Part: SKIN — CORRODED (ZONE 500) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING CENTER LEADING EDGE LOWER SKIN CORRODED AT STATION 428.750. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION NOTED. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLER. CLEANED, TREATED, PRIMED AREA, AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02-25-09, DRAWING ED-4910 DATED 01-30-09, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G, SRM 57-1-0 PAGE 1, SRM 51-1-21, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, SRM 51-3-0, SRM 51-1-20D, AND SRM 51-3-1.

Part: SPLICE — CRACKED (ZONE 500) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT WING CENTER LEADING EDGE UPPER SPLICE CRACKED AT STATION XS 427.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. FABRICATED SPLICE. PERFORMED DYE PENETRANT INSPECTION. NO CRACK AND NO CORROSION FOUND. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-2-1 FIGURE 12 SHEETS 1-4, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, SRM 57-2-1 FIGURE 12 SHEETS 1-3, SRM 51-5-2, SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: CARGO TRACK — CORRODED (BS 970-1020) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT NUMBER 4 TRACK CORRODED AT STATION 970.000 - 1020.000. REMOVED EXISTING SPLICES. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED TRACK SEGMENT. FABRICATED SPLICES. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS AND REINSTALLED EXISTING SPLICES IAW SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, SRM 51-3-0, SRM 53-1-0 PAGE 1, SRM 51-1-8 PAGES 17-18, SRM 53-2-3 FIGURE 12, SRM 53-7-2 FIGURE 3A SHEETS 1-2, SRM 51-2-0 FIGURE 50 SHEET 73, SRM 51-1-8B, SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1.

Part: SEAT TRACK — CORRODED (BS 1420-1564) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IN PASSENGER CABIN NUMBER FOUR TRACK CORRODED AT STATION 1420.000-1564.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED TRACK SEGMENT. FABRICATED SPLICES. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW TRACK SEGMENT AND REPAIR PARTS IAW DC8 SRM 53-1-0 PAGE 1, SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, DC8 SRM 51-1-8B PAGES 17-18, DC8 SRM 51-1-8B, DC8 SRM 53-7-2 FIGURE 3A ITEM "R", SRM 51-2-0 FIGURE 50, SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1.

Part: DOUBLER — CRACKED (ZONE 500) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING CENTER LEADING EDGE UPPER SURFACE INTERNAL DOUBLER CRACKED AT STATION XFS 422.750. REMOVED CRACKED INTERNAL DOUBLER. FABRICATED INTERNAL DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED INTERNAL DOUBLER IAW DC8 SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1, DC8 SRM 57-3-0 PAGE 28, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 100) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT ACCESSORY COMPARTMENT CRACKED FITTING AT STATION 822.500 LONGERON 21-22 LEFT. REMOVED CRACKED FITTING. CLEANED, TREATED, PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-05.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IN PASSENGER CABIN AUX TRACK CORRODED AT STATION 1500.000-1564.000 LEFT BOTTOM LINE-11. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED TRACK SEGMENT. FABRICATED SPLICES. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW TRACK SEGMENT AND REPAIR PARTS IAW SRM 53-1-0 PAGE 1, SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, SRM 51-1-8B PAGES 17-18, SRM 51-1-8B, SRM 53-7-2 FIGURE 3A ITEM "R", SRM 51-2-0 FIGURE 50, SRM 51-1-11, SRM 51-3-0, AND SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 100) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT FITTING CRACKED AT STATION 980.000 - 1000.000 L23R. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. FABRICATION NEW FITTING. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, ATI REPAIR SPECIFICATION 2003-05, AND 07 IPI 2009205.

Part: FITTING — CRACKED (BS 1440 S21-22R) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT ACCESSORY COMPARTMENT CRACKED FITTING AT STATION 1440.000 LONGERON 21-22 RIGHT. REMOVED CRACKED FITTING. CLEANED, TREATED, PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-05.

Part: FRAME — CORRODED (BS 181) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE NOSE SECTION RIGHT TUNNEL FRAME CORRODED AT STATION 181.000 LONGERON29-30 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED DAMAGED AREA. FABRICATED FRAME SEGMENT. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-0 FIGURE 2 SHEET 1, 3, AND 6, SRM 51-1-21, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 53-2-0 FIGURE 2 SHEETS 2 AND 6, SRM 53-3-2 FIGURE 3 SHEETS 2-2A ITEMS "L", SRM 51-9-0 FIGURE 68A, SRM 51-1-1 PAGES 1,1 3, AND 17, SRM 51-1-8B, SRM 51-1-11, SRM 51-3-0, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING INBOARD FLAP UPPER SKIN HAS IMPROPER REPAIR AT STATION XW 105.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-7-1 FIGURE 1 PAGE 2 ITEM "D", SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, AND SRM 51-1-11.

Part: SKIN — CORRODED (ZONE 100) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE LEFT SKIN CORRODED AT STATION 1540.000 LONGERON 28 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION 1540.000 - 1606.000 IAW MESSAGE 1-1171160198-2 DATED 01/22/09, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 53-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 53-5-2 FIGURE 1 ITEM "E", AND SRM 51-1-11.

Part: SKIN — CRACKED (RT WING TE FLAP) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD FLAP UPPER SKIN CRACKED AT STATION XF 210.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-7-1 FIGURE 4 TR 57-94 DATED 10/1/02, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIGURE 4 TR 57-94 ITEM "C", SRM 51-1-8B, AND SRM 51-1-11.

Part: SKIN — SCRATCHED (LT WING TE FLAP) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING INBOARD FLAP UPPER SURFACE SCRATCHED AT STATION XW 120.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 1 ITEMS D/K/M, DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.

Part: SKIN — CRACKED (ZONE 300) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND HORIZONTAL STABILIZER LOWER FORWARD PANEL WITH STIFFENER CRACKED AT RIGHT BOTTOM LINE-10. REMOVED CRACKED SKIN. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW SKIN IAW S/B 55-15 REV 3 CONDITIONS 4, SRM 55-1-0 PAGE 1, SRM 51-3-0, SRM 51-1-20D, SRM 51-1-8B, AND 51-3-1.

Part: SKIN — CORRODED (ZONE 300) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER TRAILING EDGE UPPER SKIN CORRODED AT STATION XE 83.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN, AND STIFFENERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW SKIN IAW FORM 8110-3 DATED 02-25-09, DRAWING ED-4908 DATED 01-27-09, SRM 51-1-8 PAGES 17-18, SRM 55-2-0 FIGURE 6, SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-1-21.

Part: CARGO TRACK — CORRODED (BS 494-570) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT NUMBER 3 TRACK LUG CORRODED AT STATION 494.000 - 570.000. REMOVED EXISTING SPLICES. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED TRACK SEGMENT. FABRICATED SPLICES. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW TRACK SEGMENT, EXISTING SPLICES, AND REPAIR PARTS IAW DC8 SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 59-50, DC8 SRM 51-1-21, SRM 51-3-0, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 52-2-3 FIG 12, DC8 SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, DC8 SRM 51-1-8B, DC8 SRM 53-7-2 FIGURE 3A SHEET 1 ITEM "X", SRM 51-2-0 FIGURE 50, SRM 53-2-3 FIGURE 14 SHEET 1 PAGES 49-50, SRM 51-1-11, AND SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 200) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE RIGHT SIDE EXTERNAL SKIN CRACKED AT STATION 1586.000 LONGERON 15-16 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLERS, INTERNAL FINGER DOUBLERS, AND FILLER. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-1 FIGURE 7 TR 53-203 DATED 01/21/08, SRM 51-1-21, SRM 53-5-2 FIGURE 1 ITEM "D", DC8 SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 100) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE LEFT SKIN CORRODED AT STATION 1606.000 LONGERON 28 LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION 1540.000 - 1606.000 IAW MESSAGE 1-1171160198-2 DATED 01/22/09, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 53-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-8B, SRM 53-5-2 FIGURE 1 ITEM "E", AND SRM 51-1-11.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE NOSE SECTION BROKEN INTERNAL DOUBLER AT PNEU AIR INLET AT STATION 35.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED INTERNAL DOUBLER. FABRICATED INTERNAL DOUBLER. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND INTERNAL DOUBLER. INSTALLED NEW FASTENERS AND REPAIR PART IAW DC8 SRM 53-3-2 FIGURE 1, DC8 SRM 53-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 53-3-2 FIGURE 1 ITEM "J", DC8 SRM 51-1-1 PAGES 1,13, AND 17, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.

Part: SKIN — CRACKED (ZONE 600) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING UPPER SKIN CRACKED AT STATION XCW 69.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND NO CORROSION NOTED. FABRICATED NEW SKIN, FILLER PLUG. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR DOUBLER. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-2-1 FIGURE 20 SHEETS 1-3, SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 57-3-2 FIGURE 15 ITEM "J", SRM 51-10-0 FIGURE 1 SHEET 21, SRM 51-1-1 PAGES 1,13,AND 17, SRM 51-1-12, SRM 51-1-8B, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT CENTER LEADING EDGE UPPER SKIN CORRODED AT STATION XW 253.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION NOTED. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLER. CLEANED, TREATED, PRIMED AREA, REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XFS 285.250 - 297.500 IAW FORM FAA 8110-3 DATED 02-25-09, DRAWING ED-4911 DATED 01-29-09, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND IMPROPER REPAIR AT RIGHT AFT FUSELAGE SKIN AT LONGERON 28 REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK OR NO CORROSION FOUND. FABRICATED INTERNAL AND EXTERNAL DOUBLER, FINGER DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8100-9 DATED 02/16/09, AD 2008-06-23, S/B DC8 S3A080, DRAWING SR08530032, DRAWING ED-4905 DATED 01/27/09, MESSAGE SEV-TIN-09-0002-08B DATED 02/10/09, SRM 51-1-21, SRM 51-1-20D, 51-3-0, NDT PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT CENTER LEADING EDGE UPPER SKIN CORRODED AT STATION XFS 280.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION NOTED. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLER. CLEANED, TREATED, PRIMED AREA, REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XFS 285.250 - 297.500 IAW FORM FAA 8110-3 DATED 02-25-09, DRAWING ED-4911 DATED 01-29-09, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, AND SRM 51-3-1.

Part: DOOR FRAME — CRACKED (CARGO DOORWAY) · airframe 82,730 hrs · 25,264 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND "A" CARGO DOOR FORWARD LOWER JAMB CORNER CRACKED. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION. FABRICATED DOUBLERS, FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW AD 2005-18-07, S/B 53-078, DRAWING SR08530019, SRM 51-1-21 AND SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.

Part: ELBOW — BROKEN (HYD LINE) · airframe 82,623 hrs · 25,231 cycles

DURING CLIMB FROM KMCC, THE CREW NOTICED A LOSS OF HYDRAULIC QUANTITY TO THE FIVE GALLON LEVEL. THE CREW RETURNED TO KMCC AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE HYDRAULIC SYSTEM AND FOUND THE RIGHT MAIN LANDING GEAR ACTUATING CYLINDER, UPPER LINE ELBOW BROKEN. MAINTENANCE REPLACED THE RIGHT MAIN LANDING GEAR ACTUATING CYLINDER, SERVICED THE HYDRAULIC SYSTEM. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: VIDEO MONITOR — BURNED OUT (CABIN) · airframe 79,389 hrs · 24,481 cycles

APPROXIMATELY 15 MINUTES AFTER TAKEOFF FROM KSUU, THE CREW DETECTED AN ELECTRICAL ODOR IN THE CABIN. THE CREW RETURNED TO KSUU AND LANDED WITHOUT INCIDENT. MAINTENANCE VERIFIED ELECTRICAL ODOR WAS COMING FROM THE FORWARD VIDEO MONITOR. THE FORWARD VIDEO MONITOR WAS REMOVED TO PREVENT FURTHER ODOR. THE MONITOR WAS PLACED ON ORDER AND THE AIRCRAFT WAS RETURNED TO SERVICE IAW DACO M/M 56-00-01.

Part: OIL SYSTEM — LEAKING (NR 4 ENGINE) · airframe 82,444 hrs · 25,191 cycles

DURING CRUISE, NR 4 ENGINE OIL PRESSURE WAS FLUCTUATING & OIL PRESSURE LIGHT FLICKERING, OIL QUANTITY READ 0. CREW RAN ABNORMAL OIL PRESSURE CHECKLIST FOLLOWED BY EMERGENCY SHUTDOWN CHECKLIST. WINDMILL OIL PRESSURE 14 PSI. RESTORED FUEL TO FUEL CONTROL EVERY HOUR. MX REPLACED GEARBOX RELIEF VALVE & INSPECTED NR 4 ENGINE INLET & EXHAUST FOR OIL WETTING, NONE FOUND. INSPECTED OIL TANK FOR SERVICE LEVEL, REQUIRED 16 QTS. INSPECTED LUBE SYS FOR LEAKS & FOUND ONLY MINOR SEEPS, RETORQUED FITTINGS. RAN ENGINE AT IDLE FOR 40 MIN TO LEAK CHECK FUEL/OIL COOLER, NONE NOTED. PERFORMED 10 MIN POWER RUN UP TO INCLUDE TAKEOFF POWER NO LEAKS. OIL TANK REMAINED FULL, INSPECTED MAIN OIL FILTER, FILTER CLEAN REINSTALLED FILTER. OPS CHECK GOOD IAW MM 70-30-0, 79-20-7, AND ERH.

Part: FAN — DEFECTIVE

AFTER LANDING, DURING TAXI IN THE CREW DETECTED AN ODOR OF SMOKE. THE CREW TURNED OFF RT RECIRCULATION FAN THE ODOR WENT AWAY. MAINT DEFERRED RT RECIRCULATION FAN. MAINT REPLACED RT RECIRCULATION FAN, OPS CHECK GOOD IAW MM 21-21-1. AC WAS RETURNED TO SERVICE. (K)

Part: PRESSURE SWITCH — LEAKING (ENGINE OIL) · airframe 81,636 hrs · 25,016 cycles

DURING CRUISE FROM HIK, THE CREW SHUTDOWN NR 1 ENGINE AT 2102Z DUE TO FLUCTUATING OIL PRESSURE AND FLICKERING OIL PRESSURE LIGHT. WIND MILLING OIL PRESSURE FLUCTUATION BETWEEN 18PSI TO 25PSI AT CRUISE ALTITUDE, OIL QUANTITY INDICATED 2.5 GALLONS AND OIL TEMP 75C PRIOR TO SHUTDOWN. THE CREW LANDED WITHOUT INCIDENT AT SUU. MAINTENANCE INSPECTED AND FOUND LOW OIL DIFFERENTIAL PRESSURE SWITCH TO BE LEAKING. MAINTENANCE REPLACED LOW DIFFERENTIAL PRESSURE SWITCH, OPERATIONAL CHECK GOOD IAW DACO DC-8 MAINTENANCE MANUAL 79-33-1 AND GENERAL MAINTENANCE MANUAL 3.116. AIRCRAFT WAS RETURNED TO SERVICE.

Part: UPLOCK — STIFF (MLG) · airframe 80,669 hrs · 24,767 cycles

DURING CRUISE FROM PHIK BOTH MAIN GEAR DOORS OPENED DURING UPLATCH CHECK, THE CREW CYCLED THE GEARS THREE TIMES REQUIRED TO GETTING A VALID UPLATCH CHECK. THE CREW LANDED AT KSUU WITHOUT INCIDENT. MAINTENANCE INSPECTED MAIN GEAR DOORS AND FOUND BOTH UPLATCH OVERCENTER LOCKS STIFF AND NOT LOCKING COMPLETELY, MAINTENANCE CLEANED AND LUBED AS REQUIRED FOR FREE MOVEMENT, JACKED AIRCRAFT AND PERFORMED SEVERAL EXTENSION AND RETRACTION CYCLES AND UPLATCH CHECKS OPERATIONAL CHECK WAS GOOD IAW DACO DC8 MAINTENANCE MANUAL 7-11-0, AND DACO DC8 MAINTENANCE MANUAL 32-30-0.AIRCRAFT WAS RETURNED TO SERVICE.

Part: FAN — FAILED (RECIRCULATION) · airframe 80,653 hrs · 24,763 cycles

DURING CRUISE FROM PKWA, THE CREW DETECTED A BURNING ODOR IN COCKPIT. LEFT RECIRC FAN BECAME NOISY, THE CREW TURNED OFF THE RECIRC FAN AND ODOR WENT AWAY. THE CREW LANDED IN PHIK WITHOUT INCIDENT. MAINTENANCE REPLACED LEFT RECIRC FAN IAW DC MAINTENANCE MANUAL 21-21-1 OPERATIONAL CHECK WAS GOOD AIRCRAFT RETURNED TO SERVICE.

Part: FUEL CONTROL — MALFUNCTIONED (NR 1 ENGINE) · airframe 80,560 hrs · 24,743 cycles

DURING CRUISE FROM WSAP TO RJTY NR 1 ENGINE LOST POWER EPR REDUCED 1.2 AND FUEL FLOW DECREASED 1000 POUNDS PER HOUR. THE CREW PERFORMED THE ENGINE SHUTDOWN CHECKLIST AND SHUTDOWN THE ENGINE, THE AIRCRAFT LANDED AT RJTY WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE AND USING PROPER TECHNICAL DATA, REPLACED THE FUEL CONTROL. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LANDING GEAR — MALFUNCTIONED (NOSE) · airframe 80,385 hrs · 24,708 cycles

DURING CLIMB OUT FROM OBBI, THE CREW FELT VIBRATION FROM NOSE GEAR AREA AFTER GEAR RETRACTION. THE CREW CYCLED THE GEAR AND STILL FELT VIBRATION. THE CREW RETURNED TO OBBI WITH OUT INCIDENT. MAINTENANCE INSPECTED NOSE GEAR AREA AND FOUND LEFT NOSE GEAR DOOR WAS OPENED, MAINTENANCE INSPECTED ALL HINGES, ALL ATTACHED HARDWARE, LINKAGE, AND LOCKING MECHANISM, ALL CHECKED GOOD. MAINTENANCE LUBRICATED ALL LOCKING MECHANISMS AND OPERATED DOOR SEVERAL TIMES, IAW DACO DC8 MAINTENANCE MANUAL CX/AP20. OPERATIONAL CHECK GOOD AIRCRAFT WAS RETURNED TO SERVICE.

Part: CLAMP — BROKEN (ANTI ICE SYS) · airframe 80,234 hrs · 24,679 cycles

DURING CLIMB FROM KTOL NR 1 ENGINE ANTI-ICE LIGHT ILLUMINATED, OIL PRESSURE LIGHT FLICKERED, EGT DROPED TO 270°C, LOW PRESSURE PNEUMATIC CONTROL CIRCUIT BREAKER POPPED, ENGINE GENERATOR FAIL LIGHT ILLUMINATED WHILE VOLTS AND FREQUENIES WERE NORMAL. CLIMB POWER WAS SET AT EPR 1.70, AND EGT 560°C. THE ENGINE POWER LEVER WAS RETARDED TO IDLE AND ALL INDICATIONS RETURNED TO NORMAL. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE AND FOUND THE CENTER INTERMEDIATE ANTI-ICING AIR MANIFOLD FORWARD CLAMP BOLT BROKEN. MAINTENANCE REPLACED THE BOLT AND REPAIRED WIRES IN THE PYLON IAW DACO DC8 MM 20-50-1. THE OPERATIONAL CHECKS WERE GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIBER OPTIC GYRO — PRECESSES (NR 2) · airframe 79,529 hrs · 24,513 cycles

APPROXIMATELY 1.5 HOURS AFTER TAKEOFF FROM WSAP THE NR 2 COMPASS STARTED PROCESSING AT THE RATE OF 60° TO 70° PER HOUR, DG MODE PROCESSING AT THE RATE OF 25° PER HOUR. THE CREW ELECTED TO RETURN TO WASP AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND AND CLEANED MOISTURE IN THE FIBER OPTIC GYRO CONNECTORS, WIRE BUNDLE BURNDY BLOCKS, BELOW GYROS AND LEFT FORWARD SIDE OF THE GYRO BAY. MAINTENANCE ALSO CLEANED MOISTURE FROM THE WIRE SPLICE CONNECTORS ON THE GYRO SYSTEM. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER UPPER SKIN INTERNAL SURFACE CORRODED FROM STATION XE272.000 TO STATION XZ297.2347. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW PANEL IAW DC8 SRM 51-1-21, DC8 SRM 57-2-0 PAGE16, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-8 PAGE 17-18, FAA FORM 8110-3, NUMBER 06581 DATED 11-28-06, SEMAN DRAWING, NUMBER ED-4384 DATED 11-25-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006923 DATED 11-28-06.

Part: SKIN — DENTED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD AILERON SKIN DENTED AT STATION XA694.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. BONDED REPAIR PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS AND NEW FASTENERS. BALANCED AILERON. INSTALLED 04 EACH WEIGHTS PART NUMBER 5764617-49 AT STATION XA625. FOUND WITHIN TOLERANCE MOMENT OF 3339.0 INCH-POUNDS IAW DC8 SRM 57-2-1 FIGURE 2X PAGE 35, DC8 SRM 57-2-1 PAGE 31 PARAGRAPH 16 LETTER "D" ITEM 3, DC8 SRM 57-8-1 FIG 4 PAGE 9 ITEM "F", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-21 AND DC8 SRM 51-4-3 PAGES 1-4.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER LOWER SKIN INTERNAL SURFACE CORRODED FROM STATION XE195 2190 TO STATION XE221.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN PANEL. FABRICATED NEW SKIN PANEL AND STIFFENERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 55-2-0 PAGE 12, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 55-1-0.PAGE 1, FAA FORM 8110-3, NUMBER 06591 DATED 12-08-06, SEMAN DRAWING NUMBER, ED-4399DATED 12-05-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006922 DATED 12-08-06.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER LOWER SKIN CORRODED AT STATION XE77.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. INSTALLED NEW SKIN IAW DC8 SRM 51-1-8 PG 17-18 DC8 SRM 55-2-0 PG 12, DC8 SRM 51-1-8B AND DC8 SRM 51-1-21.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER LOWER SKIN CORRODED FROM STATION XE219.919 TO STATION XE221.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED PANEL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 57-2-0 PAGE 16, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21. FAA FORM 8110-3, NUMBER 06581 DATED 11-28-06, SEMAN DRAWING, NUMBER ED-4384 DATED 11-25-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006923 DATED 11-28-06.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FITTING CRACKED AT STATION 1610.000. LONGERON 17 LEFT. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-8B DC8 SRM 51-1-20D, DC8 SRM 51-1-21, AND DC8 SRM 51-3-1.

Part: DOUBLER — CORRODED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND INTERNAL DOUBLER CORRODED BETWEEN STATION 1460.000 AND STATION 1480.000 AND BETWEEN LONGERON 33 RIGHT AND LONGERON 33 LEFT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED INNER DOUBLER. FABRICATED NEW DOUBLER. CLEANED, TREATED AND PRIMED AREA. APPLIED SEALANT TO FAYING SURFACES. INSTALLED INNER DOUBLER, IAW DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 AND BOEING MESSAGE 1-249148147-2.

Part: FITTING — CRACKED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING FITTING CRACKED AT STATION XW408.000, STRINGER 58. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED HEAT TREATMENT FROM AL7075-T651 TO AL 7075-T6. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND NEW FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-21 PAGES 1, 13, 17, DC8 NDT SRM PART 08-00-02 TO 07, DC8 SRM 51-1-8B, DC8 SRM 51-1-20D, DC8 SRM 51-3-1 AND DOUGLAS DRAWING 5644973.

Part: SKIN — CORRODED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LEADING EDGE UPPER SKIN CORRODED AT STATION XFS422.750. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVAL. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8B, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-1 FIGURE 2G, DC8 NDT SPM PART 06-10-01-001, FAA FORM 8110-3, NUMBER 06565 DATED 11-13-06, SEMAN DRAWING, NUMBER ED-4367 DATED 11-11-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006823 DATED 11-13-06.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER LOWER SKIN CORRODED AT STATION XE28.843. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21.DC8 SRM 51-1-8 PG 17-18, DC8 SRM 55-2-0 PG 12, AND DC8 SRM 51-1-8B,

Part: PRESSURE PANEL — CORRODED (BS 902) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT MAIN LANDING GEAR WHEEL WELL PRESSURE WALL SKIN CORRODED AT STATION 902.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS AS NEEDED. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 06551 DATED 11-09-06, SEMAN DRAWING NUMBER ED-4359 DATED 11-07-06, AND SEMAN ENGINEERING ORDER NUMBER 2006799 DATED 11-09-06.

Part: SKIN — CRACKED (NR 4 PYLONJ) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NUMBER 4 PYLON RIGHT UPPER SKIN CRACKED AT STATION YN225.000. REMOVED LEFT SKIN. REMOVED RIGHT SIDE STRAP AND HINGE HALVES FROM RIGHT SIDE AND ATTACHING PARTS FROM PYLON STRUCTURE AS NEEDED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 MM 54-30-0, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SERVICE BULLETIN 54-70 DATED 08-21-70.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT OUTBOARD FLAP LEADING EDGE UPPER SKIN HAS A NON-STANDARD REPAIR AT STATION XF227.000. 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 51-1-21, 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 51-1-20D, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 06552 DATE D11-09-06, SEMAN DRAWING NUMBER ED-4363 DATED 11-06-06 AND SEMAN ENGINEERING ORDER NUMBER 2006806.

Part: SKIN — DENTED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING OUTBOARD FLAP LOWER SKIN DENTED AT STATION XF430.000. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. BONDED REQUIRED PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS AS NEEDED. INSTALLED PANEL PLATING IAW DC8 SRM 57-7-1 FIGURE 4 PAGE 2, TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 PAGE 2, DC8 SRM 51-1-9, AND DC8 SRM 51-1-8B.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER LEADING EDGE CRACKED AT STATION XFS47.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS, IAW DC8 SRM 55-3-1 FIG 1 SHEET 2 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 55-2-1 FIG 4 PG 17, AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (LT WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING REPAIR OUTBOARD LEADING EDGE UPPER SKIN HAS A NON STANDARD REPAIR AT STATION XFS566.000. REMOVED EXISTING NON STANDARD 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 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, FAA FORM 8110-3 NUMBER 06574 DATED 11-23-06, SEMAN DRAWING NUMBER ED-4362 DATED 11-16-06, AND SEMAN ENGINEERING ORDER NUMBER 2006803 DATED 11-23-06.

Part: SKIN — CRACKED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NUMBER 2 PYLON RIGHT UPPER SKIN CRACKED AT STATION YN210.000. REMOVED LEFT SKIN. REMOVED RIGHT SIDE STRAP AND HINGE HALVES FROM RIGHT SIDE AND ATTACHING PARTS FROM PYLON STRUCTURE AS NEEDED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 MM 54-30-0, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SERVICE BULLETIN 54-70 DATED 08-21-70.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER LOWER SKIN CORRODED FROM STATION XE29.812 TO STATION XE52.825. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21, DC8 SRM 51-1-8 PG 17-18, DC8 SRM 55-2-0 PG 12, AND DC8 SRM 51-1-8B.

Part: DOUBLER — CORRODED (RT WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD LEADING EDGE UPPER SKIN DOUBLER CORRODED AT STATION XFS195.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED PANEL WITH EXISTING DOUBLER. FABRICATED NEW PANEL. CLEANED, TREATED AND PRIMED AREA AND NEW PANEL. INSTALLED NEW PANEL IAW DC8 SRM 51-1-8 PG 17-18, DC8 SRM 57-2-1 FIG 2G, DC8 SRM 57-1-0 PG 1, 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 AND DOUGLAS DRAWING NUMBER 9750482.

Part: FITTING — CORRODED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CORRODED AT STATION 530.000 RBL 45. REMOVED CORRODED FITTING. FABRICATED NEW FITTING. HEAT TREATED NEW FITTING FROM 7075-T651 TO 7075-T6. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND NEW FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1 DC8 SRM 51-1-1 PAGES 1, 13, 17, DC8 NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-8B, AND DOUGLAS DRAWING, NUMBER 5711283.

Part: SKIN — CRACKED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NUMBER 1 PYLON RIGHT UPPER SKIN CRACKED AT STATION YN210.000. REMOVED LEFT SKIN. REMOVED RIGHT SIDE STRAP AND HINGE HALVES FROM RIGHT SIDE AND ATTACHING PARTS FROM PYLON STRUCTURE AS NEEDED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 MM 54-30-0, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SERVICE BULLETIN 54-70 DATED 08-21-70.

Part: FITTING — CRACKED (CENTER WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND WING CENTER SECTION FITTING CRACKED AT STATION 759.000 RBL-24. REMOVED FITTING. CLEANED TREATED AND PRIMED AREA. INSTALLED FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, AND DC8 SRM 51-3-1.

Part: DOUBLER — DAMAGED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING NR 2 STUB WING SLOT DOUBLER HAS ELONGATED HOLES AT STATION XS 250.000. 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 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3, NUMBER 06565 DATED 11-13-06, SEMAN DRAWING, NUMBER ED-4381 DATED 11-09-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006961 DATED 11-13-06.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER UPPER SKIN CORRODED FROM STATION XE221.000 TO STATION XE270.979. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN PANEL. FABRICATED NEW SKIN PANEL AND STIFFENERS CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW SKIN PANEL IAW DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 57-2-0 PG.17, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, FAA FORM 8110-3 NUMBER 06582 DATED 11-28-06, SEMAN DRAWING NUMBER ED-4394 DATED 11-27-06, AND SEMAN ENGINEERING ORDER NUMBER 2006921 DATED 11-28-06.

Part: LONGERON — CORRODED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LONGERON 34 RIGHT CORRODED FROM STATION 1190.000 TO STATION 1200.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK 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 51-3-1, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER 06564 DATED 11-13-06, SEMAN DRAWING NUMBER ED-4374 DATED 11-09-06, AND SEMAN ENGINEERING ORDER NUMBER 2006943 DATED 11-13-06.

Part: BEAM — CORRODED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND WHEEL WELL PRESSURE PANEL BEAM LOWER FLANGE CORRODED AT STATION 902.000, LBL62” TO LBL69. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED 02 EACH EXISTING SPLICE ANGLES AND 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 AS REQUIRED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. IAW. DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 53-2-0 PAGE 2P, 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 51-1-20D, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 06552 DATED 11-09-06, SEMAN DRAWING NUMBER ED

Part: SKIN — CORRODED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER LOWER SKIN CORRODED FROM STATION XE272.000 TO STATION XE301.656. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND STIFFENERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PG 17-18, DC8 SRM 55-2-0 PG 12, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, FAA FORM 8110-3 NUMBER 06581 DATED 11-28-06, SEMAN DRAWING NUMBER ED-4389 DATED 11-25-06 AND SEMAN ENGINEERING ORDER NUMBER 2006962 DATED 11-28-06.

Part: SKIN — MISREPAIRED (LT WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING HAS A NON STANDARD REPAIR ON THE LOWER SKIN AT STATION XFS566.000. 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 REQUIRED. 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, FAA FORM 8110-3 NUMBER 06574 DATED 11-23-06, SEMAN DRAWING NUMBER ED-4362 DATED 11-16-06 AND SEMAN NUMBER 2006803 DATED 11-23-06.

Part: HINGE FITTING — CRACKED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP RIGHT INBOARD HINGE FITTING CRACKED AT STATION XW94.000. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-3-0, DC8 SRM 51-1-8B, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD FLAP TRAILING EDGE PANEL UPPER SKIN HAS A NON-STANDARD REPAIR AT STATION XW83.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED REPAIR PARTS. BONDED NEW PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIG 1 PG 2 ITEM "A" AND "L", DC8 SRM 57-2-5 FIG 1 SHEET 1 AND 2, DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 57-2-5 FIG 1 SHEET 1 AND 2, AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD FLAP LEADING EDGE UPPER SKIN HAS A NON-STANDARD REPAIR AT STATION XW105.000. REMOVED SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN, IAW DC8 SRM 57-7-1 FIG 1, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 1 ITEM "D", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 51-3-0 AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD FLAP LEADING EDGE UPPER SKIN HAS A NON-STANDARD REPAIR AT STATION XW90.000. REMOVED DAMAGED SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE OF NEW SKIN. APPLIED SEALANT TO FAYING SURFACE. INSTALLED NEW SKIN IAW DC8 SRM 57-7-1 FIG 1, DC8 SRM 57-1-0 PG 1, DC8 SRM 57-7-1 FIG 1 ITEM "D", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-1-21.

Part: SKIN — CORRODED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT MAIN LANDING GEAR WHEEL WELL PRESSURE WALL SKIN CORRODED AT STATION 902.000. 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 AS NEEDED. INSTALLED REPAIR PARTS IAW 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 51-1-21, DC8 SRM 51-1--20D, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 06551 DATED 11-09-06, SEMAN DRAWING NUMBERED-4360 DATED 11-07-06, AND SEMAN ENGINEERING ORDER NUMBER 2006800 DATED 11-07-06.

Part: SKIN — MISREPAIRED (TE FLAPS) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT WING INBOARD FLAP LEADING EDGE UPPER SKIN HAS A NON-STANDARD REPAIR AT STATION XF210.000. REMOVED SKIN WITH NON STANDARD REPAIR FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE OF NEW SKIN. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN IAW DC8 SRM 57-7-1 FIG 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIG 4 ITEM "C", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-0, AND DC8 SRM 51-3-1.

Part: SKIN — CRACKED (RT WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING OUTBOARD LEADING LOWER SKIN DRAIN HOLE CRACKED AT STATION XFS597.000. 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 FILLER. 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 51-1-20D, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 06564 DATED 11-13-06, SEMAN DRAWING NUMBER ED-4364 DATED 11-11-06 AND SEMAN ENGINEERING ORDER NUMBER 2006807 DATED 11-1

Part: SKIN — NICKED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP LOWER SKIN NICKED AT STATION XW32.000. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. BONDED PARTS AS REQUIRED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 57-7-1 FIG 1, DC8 SRM 57-1-0 PG 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIG 1, DC8 SRM 51-1-19 AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD AILERON LOWER SKIN DENTED AT STATION XA665.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. PERFORMED BALANCE O LEFT OUTBOARD AILERON. FOUND MOMENT WITHIN TOLERANCE LIMITS MOMENT 3329.9 IAW DC8 SRM 57-8-1 FIGURE 4 PAGE 9, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-8-1 FIGURE 4 PAGE 9 ITEMS "E" AND "L", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21 AND DC8 SRM 51-4-3 PAGES 1-3.

Part: SKIN — CRACKED (TAILCONE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE TAIL CONE LEFT SIDE EXTERIOR SKIN CRACKED AT STATION 1756.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIGURE 1D SHEET 3 PAGE 2K, DC8 SRM 53-5-2 FIG 2 PAGE 3 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-1-21.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE SKIN CORRODED AT STATION XE198.0039. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN FROM STATION XE149.000 TO STATION XE221.000. IAW DC8 SRM 55-3-1 FIGURE 1 SHEET 1-2, DC8 SRM 51-1-8, PAGES 17-18, DC8 SRM 55-2-0, PAGE 12, DC8 SRM 55-1-0, PAGE 1, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-1-21.

Part: REPAIR — IMPROPER (RT ELEVATOR) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR LOWER SKIN HAS A NON STANDARD REPAIR AT STATION XE272.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS. BALANCED RIGHT ELEVATOR. FOUND MOMENT WITHIN TOLERANCE LIMITS. MOMENT 1456-8 IN POUND, DC8 SRM 55-4-1 FIGURE 1 SHEET 1-2, DC8 SRM 55-1-0, DC8 SRM 55-4-1 FIGURE 1 SHEET 1-2 ITEM "E" AND "F", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, AND DC8 SRM 51-4-4 PAGE 2-3.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LONGERON 17 RIGHT CRACKED AT STATION 1610.000. REMOVED CRACK LONGERON. CLEANED, TREATED AND PRIMED AREA AND NEW LONGERON. INSTALLED NEW LONGERON. IAW DC8 SRM 53-5-2 FIGURE 5 SHEET 1, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 53-5-2 FIGURE 5 SHEET 1 PAGE 16 ITEM "B", DC8 SRM 51-2-0 FIGURE 50 SHEET 37 PAGE 39, DC8 SRM 51-1-20D, AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (T/E FLAP) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP LEADING EDGE INTERNAL FORWARD FITTING CRACKED AT STATION XW92.000. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-21, AND DC8 SRM 51-1-8B.

Part: SKIN — CORRODED (LE FLAP) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP CORRODED ON LOWER ANGLE BETWEEN STATION XN24.000 AND STAXN32.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA AND FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-2-1 FIGURE1 TR NUMBER 51-130 DATED 06-26-04, DC8 SRM 51-1-20D, DC8 SRM 51-1-8, PAGES 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 51-2-1 FIGURE 1 SHEET 5, 6, 10, 12 TR NUMBER 51-130, DC8 SRM 57-7-1 FIGURE 2 SHEET 3 ITEM "D", DC8 SRM 51-2-0 FIGURE 50 SHEET 68, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-2-1 FIGURE 1 SHEET 5, 6, 1

Part: SKIN — CORRODED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NUMBER 4 STUB WING UPPER SKIN CORRODED AT STATION XF520.000. 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. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-0 PAGE 16, 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, FAA FORM 8110-3 N°06591 DATED 12-08-06, SEMAN DRAWING NUMBER ED-4395 DATED 11-27-06 AND SEMAN ENGINEERING ORDER NUMBER 2006979 DATED 12-08-06.

Part: SKIN — DELAMINATED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER UPPER SKIN DELAMINATED FROM STATION XE77.000 TO STATION XE147.906. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 57-1-0, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER 06581 DATED 11-28-06, SEMAN DRAWING NUMBER ED-4390 DATED 11-25-06, AND SEMAN ENGINEERING ORDER NUMBER 2006 917 DATED 11-28-06.

Part: SKIN — CRACKED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD AILERON LOWER LEADING EDGE SKIN CRACKED AT STATION XA615.000. REMOVED DAMAGED LEADING EDGE. FABRICATED NEW LEADING EDGE. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE OF NEW LEADING EDGE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW LEADING EDGE. CHECKED BALANCE OF LEFT OUTBOARD AILERON. FOUND MOMENT WITHIN TOLERANCE LIMITS MOMENT 3329.9. IAW DC8 SRM 57-8-1 FIG 4 PAGE 9, DC8 SRM 57-1-0, DC8 SRM 51-1-21, DC8 SRM 57-8-1 FIG 4 PAGE 9 ITEM "H", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-3-0, DC8 SRM 51-3-1 AND DC8 SRM 51-4-3 PAGES 1-3.

Part: ACCESS DOOR — CORRODED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, RIGHT CENTER TANK NUMBER 505 G ACCESS DOOR CORRODED. REMOVED FASTENERS AS NEEDED TO REMOVE CORROSION. REMOVED CORROSION. FOUND OUT OF LIMITS. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-1 FIGURE 43, DC8 SRM 51-1-21, DC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 51-1-25 FIGURE 1 PAGE 2, DC8 SRM 51-1-1 PAGE 1, 13, 17, DC8 SRM 51-1-12 PAGE 7-25, DC8 SRM 51-1-25 PAGE 1, 3, 5, 6 AND 7, DC8 SRM 51-1-11, DC8 SRM 51-3-0 AND DC8 SRM 51-3-1.

Part: PANEL — CORRODED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT WING INBOARD LEADING EDGE SLANT PANEL UPPER CAP CORRODED AT STATION XFS7.000 TO STATION XFS195.000. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED SLANT PANEL UPPER CAP. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW SLANT PANEL UPPER CAP IAW DC8 SRM 51-1-8 PG 17-18, DC8 SRM 57-2-1 FIG 2G, DC8 SRM 57-1-0 PG 1, 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 AND DOUGLAS DRAWING, NUMBER 9750482.

Part: BEAM — CRACKED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND WHEEL WELL PRESSURE PANEL BEAM LOWER FLANGE CORRODED AT STATION 902.000 FROM RBL62” TO RBL69”. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED 02 EACH EXISTING SPLICE ANGLES AND REMOVED DAMAGE. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS AS REQUIRED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 51-1-8 PAGE 17-18, 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 51-1-20D, DC8 SRM 51-3-1. FAA FORM 8110-6 NUMBER 06551 DATED 11-09-06, SEMAN DRAWING NUMBE

Part: SKIN — DAMAGED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE TAIL CONE EXTERIOR LOWER SKIN DAMAGED AT STATION 1730.000. REMOVED FASTENERS. FABRICATED REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR DOUBLER IAW DC8 SRM 53-5-2 FIG 2 PG 3 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 53-2-0 FIG 1D, SHEET 3 PG 2K, AND DC8 SRM 51-1-21.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, LEFT WING NUMBER 2 STUB WING HAS A NON STANDARD REPAIR AT STATION XS 250.000. REMOVED FASTENERS AS NEEDED TO PERFORM 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 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-0, DC8 SRM 51-3-1, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3, NUMBER 06574 DATED 11-23-06, SEMAN DRAWING, NUMBER ED-4376 DATED 11-14-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006954 DATED 11-23-06.

Part: SKIN — CRACKED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NR 4 PYLON LEFT UPPER SKIN CRACKED AT STATION YN225.000. REMOVED LEFT PANEL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SERVICE BULLETIN NUMBER 54-70 DATED 08-21-70, DC8 MM 54-30-0, DC8 SRM 51-1-8B, DC8 MM 20-20-0, DC8 SRM 51-1-11, DC8 SRM 51-1-20D, AND DC8 SRM 51-3-1.

Part: PANEL — CORRODED (RT WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD LEADING EDGE UPPER SLANT PANEL CORRODED FROM STATION XFS7.000 TO STATION XW751.000. REMOVED CORROSION. FOUND OUT OF LIMITS. 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 AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-1 FIGURE 2G, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3, NUMBER 06582DATED 11-28-06, SEMAN DRAWING, NUMBER ED-4361 DATED 11-18-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006802 DATE D11-28-06.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER LOWER SKIN CORRODED FROM STATION XE221.000 TO STATION XE270.979. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN PANEL. FABRICATED NEW SKIN PANEL AND STIFFENERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 55-2-0 PAGE 12, DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER 06591 DATED 12-08-06, SEMAN DRAWING NUMBER ED-4399 DATED 12-05-06, AND SEMAN ENGINEERING ORDER NUMBER 2006922 DATED 12-08-06.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT HORIZONTAL STABILIZER UPPER SKIN CORRODED FROM STATION XE272.000 TO STATION XE301.656. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN AND STIFFENERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAWDC8 SRM 51-1-8 PAGE 17-18, DC8 SRM 57-2-0 PAGE 16, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER 06581 DATED 11-28-06, SEMAN DRAWING NUMBER ED-4384 DATED 11-25-06, AND SEMAN ENGINEERING ORDER NUMBER 2006923 DATED 11-28-06.

Part: ANGLE — CORRODED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP CORRODED ON LOWER ANGLE BETWEEN STATION XN24.000 AND STATION XN32.000. DC8. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA AND FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-2-1 FIGURE 1 TR NUMBER 51-130 DATED 06-26-04, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 53-2-0 PAGE 2P, DC8 SRM 51-2-1 FIGURE 1 SHEET 5, 6, 10, 12 TR NUMBER 51-130, DC8 SRM 57-7-1 FIGURE 2 SHEET 3 ITEM "D", DC8 SRM 51-2-0 FIGURE 50 SHEET 68, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-2-1 FIGURE 1 SHEET 5, 6, 10 AND 12

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SLOT CENTRAL LEADING EDGE HAS A NON STANDARD REPAIR AT STATION XS430.000. REMOVED EXISTING NON STANDARD 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 51-3-1, 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, FAA FORM 8110-3, NUMBER 06564 DATED 11-13-06, SEMAN DRAWING, NUMBER ED-4372 DATED 11-09-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006944 DATED 11-13-06.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SLOT CENTRAL LEADING EDGE HAS A NON STANDARD REPAIR AT STATION XOLDI6.224. REMOVED EXISTING NON STANDARD REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVAL. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMER AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-21, DC8 NDT SRM PART 06-10-01-001, DC8 SRM 51-1-11, FAA FORM 8110-3, NUMBER 06564 DATED 11-13-06, SEMAN DRAWING, NUMBER ED-4374 DATED 11-09-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006943 DATED 11-13-06.

Part: ANGLE — CRACKED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER LOWER TRAILING EDGE ANGLE CRACKED AT STATION XE29.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. STOP DRILLED CRACKED ENDS AND 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 51-2-1 FIGURE 1 SHEETS 5, 6, 10, 12 TR NUMBER 51-130 DATED 01-26-04, DC8 SRM 55-3-1 FIGURE 3 SHEET 5 PAGE 10 ITEM "H", DC8 SRM 51-2-0 FIGURE 50 SHEET 68, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND THE RUDDER SKIN CRACKED AT STATION 2R 219.000 LEFT SIDE. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. BONDED NEW SKIN AND INTERNAL DOUBLER WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. CHECKED RUDDER BALANCE, FOUND MOMENT WITHIN ALLOWABLE LIMITS, MOMENT: 2669.12 IN POUND IAW DC8 SRM 55-6-1 FIGURE 1 PAGE 2, DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND DC8 SRM 51-4-6 PAGES 1-4.

Part: STRUCTURE — MISREPAIRED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING LEADING EDGE HAS A NON STANDARD REPAIR AT STATION XOLDI6.224. REMOVED EXISTING NON-STANDARD 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 DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3, NUMBER 06565 DATED 11-13-06, SEMAN DRAWING, NUMBER ED-4377 DATED 11-09-06, AND SEMAN ENGINEERING ORDER, NUMBER 2006955 DATED 11-13-06.

Part: SKIN — CRACKED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD SERVICE DOOR UPPER FORWARD CORNER CRACKED AT STATION 225.000 LONGERON 11 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM 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 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, AD-2000-20-08, SERVICE BULLETIN DC8 53-075, DOUGLAS DRAWING SR08530021 AND DOUGLAS DRAWING 5750776.

Part: SKIN — CORRODED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C-CHECK INSPECTION, FOUND RIGHT WING INTERNAL LEADING EDGE LOWER SKIN CORRODED FROM STATION XFS157.000 TO STATION XFS163.750. REMOVED FASTENERS AS NEEDED TO REMOVE CORROSION. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED DOUBLER, INTERNAL DOUBLER AND FILLER. HEAT TREATED INTERNAL DOUBLER FROM AL7075-T6 TO AL7075-T6. 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 51-1-8 PAGES 17-18, DC8 SRM 57-2-1 FIG 2G, DC8 NDT SPM PART 06-10-001, DC8 SRM 51-1-21 PAGES 1, 13, 17, PARTS DC8 SRM

Part: SKIN — CORRODED (LT ELEVATOR) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR TRAILING EDGE UPPER SKIN CORRODED BETWEEN STATION XE71.250 AND XE198.039. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 57-1-0, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER 06581 DATED 11-28-06, SEMAN DRAWING NUMBER ED-4390 DATED 11-25-06, AND SEMAN ENGINEERING ORDER NUMBER 2006 917 DATED 11-28-06.

Part: SKIN — CRACKED (LT ELEVATOR) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR UPPER SKIN CRACKED AT STATION XE87.000. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. BALANCED LEFT ELEVATOR. REMOVED 01 EACH WEIGHT PART NUMBER 5701580-503 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR149, 03 EACH WEIGHTS PART NUMBER 3701579-503, 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR122, 03 EACH WEIGHTS PART NUMBER 3701579-505, 01 EACH RETAINER PART NUMBER 5701581-7 AT STATION XR149, 03 EACH WEIGHTS PART NUMBER 3701579-501, 01 EACH RETAINER PART NUMBER 5701581-5 AT STATION XR77. FOUND WIT

Part: SKIN — DELAMINATED (LT ELEVATOR) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR LOWER SKIN DELAMINATED AT STATION XE50.000. REMOVED DELAMINATED SKIN. FABRICATED REPAIR PARTS. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN. BALANCED ELEVATOR. REMOVED 01 EACH WEIGHT PART NUMBER 5701580-503, 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR149, 03 EACH WEIGHTS PART NUMBER 3701579-503, AND 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR122, 03 EACH WEIGHTS PART NUMBER 3701579-505, 01 EACH RETAINER PART NUMBER 5701581-7 AT STATION XR149, 03 EACH WEIGHTS PART NUMBER 3701579-501, 01 EACH RETAINER PART NUMBER 5701581-5 AT STATION XR77. F

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER LOWER SKIN CORRODED FROM STATION XE75.000 TO STATION XE147.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN FABRICATED NEW SKIN AND STIFFENERS. CLEANED, TREATED AND PRIMED AREA AND NEW REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 55-2-0 PAGE 12, DC8 SRM 55-1-0 PAGE 1, 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, FAA FORM 8110-3 NR 06581 DATE 11-28-06, SEMAN DRAWING NUMBERED-4391 DATED 11-25-06, AND SEMAN ENGINEERING ORDER NUMBER 2006920 DATED 11-28-06.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 857.000 LONGERON 2 RIGHT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. HEAT TREATED NEW FITTING FROM 7075-T6 51 TO 7075-T6. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND. INSTALLED NEW FITTING IAW DC8 SRM 51-1-21, DC8 SRM 51-1-1 PAGES 1, 13, 17 DC8 NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-20D, DC8 SRM 51-1-23, DC8 SRM 51-3-1, AND DOUGLAS DRAWING NUMBER 3645860.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 902.000 LONGERON 7 LEFT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. HEAT TREATED FROM AL7075-T651 TO 7075-T6. PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND. INSTALLED NEW FITTING, DC8 SRM 51-1-20D, DC8 SRM 51-1-1, PAGES 1, 13, 15, DC8 NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-23, DC8 SRM 51-3-1 AND DOUGLAS DRAWING NUMBER 3645860.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT HAND ELEVATOR UPPER SKIN CORRODED AT STATION XE28.843. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND FINGER DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. BALANCED LEFT HAND ELEVATOR. REMOVED 01 EACH WEIGHT PART NUMBER 5701580-503 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR149, 03 EACH WEIGHT PART NUMBER 3701579-503, 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR122, 03 EACH WEIGHTS PART NUMBER 3701579-505, 01 EACH RETAINER PART NUMBER 5701581-7 AT STATION XR149, 03 EACH WEIGHTS PART NUMBER 3701579-501, 01 EA

Part: SKIN — CORRODED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD STUB WING UPPER SKIN CORRODED AT STATION XFS246.000 REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION FOUND. FABRICATED REPAIR DOUBLER FILLERS AND STRAP. TREATED REPAIR AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC/SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, FAA FORM 8110-3 NUMBER 06574 DATED 11-23-06, SEMAN DWG NUMBERED-4375 DATED 11-13-06 AND SEMAN NUMBER 2006953 DATED 11-23-06.

Part: SKIN — CORRODED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SKIN CORRODED STATION XF195.500 UPPER SIDE. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED NEW SKIN SEGMENT AND DOUBLER CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-1-8 PG 17-18, DC8 SRM 57-2-1 FIG 2G, 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, FAA FORM 8110-3 NUMBER 06574 DATED 11-23-06, SEMAN DRAWING NUMBER ED-4379 DATED 11-23-06 AND SEMAN ENGINEERING ORDER NUMBER 200

Part: SKIN — MISREPAIRED (AILERON) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION , FOUND RIGHT WING OUTBOARD AILERON AT STATION XA656.000 HAS A NON STANDARD REPAIR. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW SKIN. BALANCED RIGHT OUTBOARD AILERON. INSTALLED 04 EACH WEIGHTS PART NUMBER 5764617-49 AT STATION XA625. FOUND WITHIN TOLERANCE. MOMENT: 3339.0 INCH-POUNDS IAW DC8 SRM 57-8-1 FIG 4 PAGE 9, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-8-1 FIG 4 PAGE 9 ITEM "E" AND "L", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-21, AND DC8 SRM 51-4-3 PAGES 1-4.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR UPPER SKIN CORRODED AT STATION XE127.960. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN PANEL. FABRICATED NEW SKIN PANEL AND FINGER DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. BALANCED LEFT ELEVATOR. REMOVED 01 EACH WEIGHT PART NUMBER 5701580-503, 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR149, 03 EA WEIGHTS PART NUMBER 3701579-503, 01 EACH RETAINER PART NUMBER 5701581-15 AT STATION XR122, 03 EACH WEIGHTS PART NUMBER 3701579-505, 01 EACH RETAINER PART NUMBER 5701581-7 AT STATION XR149, 03 EACH WEIGHTS PART NUMBER 37015

Part: SKIN — CRACKED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE EXTERIOR SKIN CRACKED AT STATION 1586.000 BETWEEN LONGERON 20 LEFT TO LONGERON 21 LEFT. REMOVED FASTENERS AS NEEDED TO ACCOMPLISH REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER INTERNAL FINGER DOUBLERS AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 53-2-1 FIG 7 SHEET 1 AND 3, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 53-2-1 FIG 7 SHEETS 1-3, DC8 SRM 53-5-2 FIG 1 PAGE 2 ITEM "E", DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 53-2-1 FIG 7 SHEET 1 AND 3, DC8 SRM 51-1-21, AND DC8 SRM 51-1-20D, DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP UPPER SKIN HAS A NON STANDARD REPAIR AT STATION XF304.000. REMOVED SKIN WITH EXISTING NON STANDARD REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN. APPLIED SEALANT TO FAYING SURFACES. INSTALLED PLATING IAW DC8 SRM 57-7-1 FIG 4 TR NUMBER 57-94 DATED 10-01-02, DC8 SRM 57-1-0, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIG 4 ITEM "A", DC8 SRM 51-1-8B, DC8 SRM 51-1-11 AND DC8 SRM 51-1-21.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 780.000 LBL-22. REMOVE CRACKED FITTING CLEANED TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-20D AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 902.000 LONGERON 5 LEFT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. HEAT TREATED FROM 7075-T6-51 TO 7075-T6 PERFORMED NDT INSPECTION NO CRACKS OR CORROSION FOUND. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-1 PAGE 1, 13, 17, DC8 NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-23,DC8 SRM 51-3-1, AND DOUGLAS DRAWING NUMBER 3645860.

Part: SKIN — DELAMINATED (HORIZ STAB) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER UPPER SKIN DELAMINATED FROM STATION XE52.822 TO STATION XE75.672. REMOVED DAMAGED SKIN. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN FROM STATION XE77.000 TO STATION XE29.000 IAW DC8 SRM 57-1-0 PG 1, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, FAA FORM 8110-3 NUMBER 06582 DATED 11-28-06, SEMAN DRAWING NUMBER ED-4392 DATED 11-28-06, AND SEMAN ENGINEERING ORDER NUMBER 2006916 DATED 11-28-06.

Part: SKIN — CORRODED (ZONE 300) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER LOWER SKIN CORRODED FROM STATION XE29.812 TO STATION 763.844. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND STIFFENERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 55-2-0. PAGE 12, DC8 SRM 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER 06582 DATED 11/28/06, SEMAN DRAWING NUMBER ED-4393 DATED 11-28-06 AND SEMAN ENGINEERING ORDER NUMBER 2006919 DATED 11-28-06.

Part: FITTING — CRACKED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND A FITTING SPLICE CRACKED AT STATION 690.000, LONGERON 1. REMOVED DAMAGED SPLICE FITTING. FABRICATED NEW SPLICE FITTING. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA AND NEW SPLICE FITTING. INSTALLED NEW SPLICE FITTING IAW DC8 SRM 51-1-20D, DC8 NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-8B, DC8 SRM 51-3-1, AND DOUGLAS DRAWING NUMBER 3753985.

Part: SKIN — CORRODED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING DOUBLER CORRODED, LOWER CENTER WING AREA AT STATION XCW10.000, STRINGER 62. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND, FABRICATED REPAIR PARTS. HEAT TREATED AS NEEDED FROM 7075"O" TO 7075-T6. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW 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 51-1-1.PAGES 1-13-17, DC8 SRM 51-1-12 PAGE 7, DC8 SRM 51-1-11, FAA FORM 8110-3, NUMBER 06552 DATED 11-09-06, SEMAN DRAWING NUMBER ED-4354 DATED 11-03-06 AND SEMAN ENGINEERING ORDER NUMBER 2

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 857.000 LONGERON 3 RIGHT. REMOVED CRACKED FITTING. FABRICATED FITTING. HEAT TREATED FROM AL 7075-T6 51 TO AL7075-T6. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-1 PAGES 1-13-17, DC8 NDT SPM PART 08-00-02TO 07, DC8 SRM 51-1-23, DC8 SRM 51-3-1 AND DOUGLAS DRAWING NUMBER 3645860.

Part: FITTING — CRACKED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 717.000 , LONGERON 13 LEFT. REMOVED DAMAGED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC-8 SRM 51-3-0, DC-8 SRM 51-3-1 AND DC-8 SRM 51-1-8B.

Part: SKIN — DAMAGED (LT AILERON) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER FASTENERS INSTALLED ON THE LEFT OUTBOARD AILERON EXTERNAL LOWER SKIN FROM STATION XA542.000 TO STATION XA566.000. REMOVED IMPROPER FASTENERS AND FOUND SKIN DAMAGED. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN AND FASTENERS. BALANCED AILERON. REMOVED 01 EACH COUNTERWEIGHT PART NUMBER 5706734-41 AND 02 EACH COUNTERWEIGHTS PART NUMBER 5706734-43 FROM STATION XA531.000 TO STATION 546.000. FOUND MOMENT WITHIN LIMITS. MOMENT: 3228.31 INCH-POUNDS IAW DC8 SRM 57-8-1 FIG 1 PAGE 2, DC8 SRM 57-1-0 PAGE 1, DC8 SRM

Part: FITTING — CRACKED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 879.000, LONGERON 13 RIGHT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED FITTING. INSTALLED FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 51-1-8B, DOUGLAS DRAWING NUMBER 3779970, AND DC8 NDT SPM PART 08-00-02.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, EXISTING REPAIR AT STA FS 1500, LONGERON 16 RIGHT HAS AN INTERIM REPAIR. REMOVED EXISTING REPAIR DC8 REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND DAMAGE REMOVED. FABRICATED NEW REPAIR DOUBLER AND FILLER CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW SRM 51-1-21, DC8 SRM 51-3-0, DC8 NDT SPM PART 06-10-01-001, FAA FORM 8110 NR 06552 DATE 11-09-06, SEMAN DWG NUMBERED-4349 DATED 10-26-06, AND SEMAN ENGINEERING ORDER NUMBER 2006776 DATE D11-09-06.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

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

Part: FITTING — CRACKED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND CRACKED FITTING AT STATION 680.000, LONGERON 11 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: FITTING — CRACKED (ZONE 200) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 742.000, LONGERON 13 LEFT. REMOVED CRACK FITTING. CLEANED TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FITTING CRACKED AT STATION 857.000, LONGERON 19 RIGHT. REMOVED CRACK 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 — CORRODED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SKIN CORRODED FROM STATION XF422.520 TO STATION XOLDI6.225 UPPER SIDE. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA, FILLER AND REPAIR PARTS INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES, AND INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-1 FIG 2G, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, FAA FORM 8110-3 NUMBER 06565 DATED 11-13-06, SEMAN DRAWING NUMBER ED-4367 DATED 11-11-06, AND SEMAN ENGINEERING ORDER NUMB

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR FROM STATION 1240 TO 1280 LONGERON 32 RIGHT TO LONGERON 35 RIGHT IS NOT IN COMPLIANCE WITH AD.2005-18-07 OR SB DC8-53-078. REMOVED EXISTING REPAIR. MANUFACTURED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW REPAIR PARTS IAW DC8 SRM 53-4-1 FIG 16, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 53-4-1 FIG 18B SHEET 2 PAGE 44C-44D, DC8 SRM 53-1-0 PAGE 1 AND DC8 SRM 51-1-8B.

Part: SKIN — CORRODED (LT WING) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SKIN CORROSION AT STATION XF803.750. REMOVED CORROSION. FOUND OUT OF LIMITS. 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 AS NEEDED. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-8 PAGES 17-18 DC8 SRM 57-2-1 FIG 2G, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 8110-3 NUMBER11-28-06, SEMAN DRAWING NUMBER ED-4361, DATED 11-18-06 AND SEMAN ENGINEERING ORDER NUMBER 2006802, DATED 11-28-06.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION FOUND FITTING CRACKED AT STATION 742.000 LONGERON 11 RIGHT. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. HEAT TREATED NEW FITTING FROM 7075-T651 TO 7075-T6. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND NEW FITTING. INSTALLED NEW FITTING. IAW DC8 SRM 51-1-20D, DOUGLAS DRAWING NUMBER 3754901, DC8 SRM 51-1-1 PAGES 1, 13, 17, NDT SPM PART 08-00-02 TO 07, DC8 SRM 51-1-8B, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 238) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK, FOUND FREON EXHAUST FORWARD LOWER CORNER HAS INTERMEDIATE REPAIR AT STATION, FS 238.000 LONGERON 29.5 LEFT. REMOVE EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIG 13 (SHEET 1), TR NR 53-169 DATE 09-20-03, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 255) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK, FOUND FREON EXHAUST AFT LOWER CORNER HAS INTERMEDIATE REPAIR AT STATION, FS 255, LONGERON 29.5 LEFT. REMOVE EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIG 13. (SHEET 1), TR NR 53-169 DATE 09-20-03, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND DC8 SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 600) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING CENTER LEADING EDGE LOWER SKIN CORRODED AT STATION XFS341.500. REMOVED FASTENERS AS NEEDED TO REMOVE CORROSION. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA, FILLER AND INTERNAL SURFACE OF REPAIR DOUBLER. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-21, DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DC8 SRM 51-1-8 PG 17-18, DC8 SRM 57-2-1 PG 2G, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, FAA FORM 811

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD AILERON LOWER SKIN HAS IMPROPER FASTENERS FROM STATION XA620.000 TO STATION XA722.000. REMOVED IMPROPER FASTENERS AND DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACE. INSTALLED PANEL PLATING, DC8 SRM 51-1-21, DC8 SRM 57-8-1 FIG 4 PAGE 9, DC8 SRM 57-1-0, PAGE 1, DC8 SRM 57-8-1 FIG 4 PAGE 9 ITEMS "E" AND "L", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, AND DC8 SRM 51-1-11.

Part: SKIN — DENTED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD AILERON LOWER SKIN DENTED AT STATION XA558.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED BOTH PARTS WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND NEW SKIN INTERNAL SURFACE. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN AND FASTENERS. BALANCED AILERON. FOUND MOMENT WITHIN LIMITS, MOMENT: 3228.31 INCH-POUNDS IAW DC8 SRM 57-8-1 FIG 1 PAGE 2, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21A, DC8 SRM 57-8-1 FIG 1 PAGE 2, ITEM "B" AND "K", DC8 SRM 51-1-9, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND DC8 SRM 51-4-1.PAGES 1-2-3-4.

Part: SKIN — CRACKED (ZONE 500) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING SKIN CRACKED AT STATION XW74.000, STRINGER 11. REMOVED FASTENERS AS NEEDED. REMOVED DAMAGED AREA PERFORMED NDT INSPECTION, NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND FILLER CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-1 FIG 10 SHEET 3, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 57-3-2 FIG 13 ITEM "A", DC8 SRM 51-10-0 FIG 1 SHEET 20, 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 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK, FOUND FREON EXHAUST FORWARD UPPER CORNER HAS INTERMEDIATE REPAIR AT STATION, FS 238.000 LONGERON 28.5 LEFT. REMOVE EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIG 13. (SHEET 1), TR NR 53-169 DATE 09-20-03, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 255) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK, FOUND FREON EXHAUST AFT UPPER CORNER HAS INTERMEDIATE REPAIR AT STATION, FS 255.000 LONGERON 28.5 LEFT. REMOVE EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIG 13. (SHEET 1), TR NR 53-169 DATE 09-20-03, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 79,389 hrs · 24,481 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXISTING REPAIR AT STATION FS 1460, LONGERON 21 LEFT, DO NOT MEET CURRENT AD, SB, AND SRM REQUIREMENTS. REMOVED NON STANDARD REPAIR EXISTING. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND AFTER DAMAGE REMOVED. FABRICATED REPAIR DOUBLER AND REPAIR TRIPLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW FAA, FORM 8100-9 DATED 11-07-06, BOEING MESSAGE NUMBER 1-239671725-5 DATED 11-07-06, SEMAN DRAWING ED-4348 DATED 10-27-06,DC8 SRM 53-2-0 FIG 18 (SHEET 1) TR NR 53-134 DATED 01-23-02, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 53-2-0 FIG 18 SHEET 5,6,7,8 TR

Part: ENGINE — LEAKING (NR 2) · airframe 78,755 hrs · 24,305 cycles

APPROXIMATELY FIVE HOURS AFTER TAKEOFF FROM TAPA THE NR 2 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED AND OIL PRESSURE DROPPED TO 20 PSI. THE ENGINE WAS SHUTDOWN AND CHECKLIST WAS COMPLIED WITH THE CREW RETURNED TO TAPA AND LANDED. MAINTENANCE FOUND THE OIL EXITED FROM THE TURBINE AREA. THE ENGINE WAS REPLACED AND OPERATIONAL CHECKS WERE SATISFACTORY. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONTROL VALVE — LEAKING (HYD SYSTEM) · airframe 78,755 hrs · 24,305 cycles

APPROXIMATELY 2 AND A HALF HOURS INTO CRUISE FROM TAPA TO FHAW, THE HYDRAULIC QUANTITY STARTED DECREASING. THE CREW SWITCHED TO EMERGENCY, AND THE LOSS OF HYDRAULIC FLUID STOPPED. LOSS OF HYDRAULIC FLUID CHECK LIST WAS COMPLIED WITH AND THE CREW RETURNED TO TAPA AND LANDED. MAINTENANCE FOUND THE WHEEL BRAKE CONTROL VALVE LEAKING. THE WHEEL BRAKE CONTROL VALVE WAS REPLACED AND THE LEAK CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PRBC — STICKING (NR 3 ENGINE) · airframe 78,744 hrs · 24,302 cycles

DURING TAKE-OFF FROM KWRI NUMBER 3 ENGINE FAILED TO ACHIEVE TAKE-OFF POWER. THE FLIGHT CREW REJECTED THE TAKE-OFF AND RETURNED TO PARKING. MAINTENANCE TROUBLESHOT THE DISCREPANCY AND FOUND THE PRESSURE RATIO BLEED CONTROL VALVE STICKING. MAINTENANCE REPLACED THE PRBC AND THE OPERATIONAL CHECK WAS GOOD. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PRBC — MALFUNCTIONED (NR 3 ENGINE) · airframe 78,738 hrs · 24,300 cycles

DURING TAKE-OFF FROM LPLA NUMBER 3 ENGINE DID NOT ACHIEVE TAKE-OFF POWER. THE CREW REJECTED THE TAKE-OFF AT 100 KNOTS AND RETURNED TO BLOCKS. MAINTENANCE FOUND THE PRBC TO BE DEFECTIVE. THE PRBC WAS REPLACED AND THE OPERATIONAL CHECK WAS SATISFACTORY, THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FITTING — LOOSE (HYD PUMP) · airframe 78,481 hrs · 24,229 cycles

AFTER TAKEOFF FROM LPLA, CREW EXPERIENCED LOSS OF HYDRAULIC FLUID. WHILE RUNNING CHECKLIST GOT A DOOR UNSAFE LIGHT ON THEN GEAR UNSAFE LIGHT. GEAR UPLATCH CHECK AFTER TAKEOFF WAS GOOD. FLUID LOST TO ALMOST TOP OF STANDPIPE. CREW RETURNED AIRCRAFT TO LPLA AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND HYDRAULIC LINE FITTING ON THE OUTLET SIDE OF THE NR 3 ENGINE HYDRAULIC PUMP LOOSE. TIGHTENED FITTING AS REQUIRED AND LEAKED CHECKED. MAINTENANCE PERFORMED INSPECTION OF THE MAIN AND NOSE GEAR DOORS WITH NO DEFECTS NOTED. PERFORMED OPERATIONAL AND LEAK CHECK AND ALL WAS NORMAL PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: TRANSMITTER — LOOSE (NR 1 FUEL PRESS) · airframe 78,468 hrs · 24,224 cycles

DURING CRUISE FROM KBWI TO BGTL THE NR 1 ENGINE FUEL PRESSURE WAS INTERMITTENT AND THERE WAS A FUEL ODOR IN THE COCKPIT WITH THE NR 3 HIGH STAGE BLEED IN HIGH. MAINTENANCE FOUND A LOOSE CONNECTION TO THE TRANSMITTER. REPAIRED PER ALL APPLICABLE MANUALS AND FUEL SMELL WAS ELIMINATED DURING THE ENGINE RUN, AIRCRAFT WAS RETURNED TO SERVICE. NO LEAK OR FUEL SMELL NOTED.

Part: VALVE — LEAKING (ANTI ICE SYS) · airframe 77,263 hrs · 23,888 cycles

DURING CRUISE, LT MANIFOLD INFLIGHT DECAY CHECK FAILED 30-20 PSI IN ONLY 1.5 SECONDS. CREW RETURNED A/C AND LANDED W/O INCIDENT. ON THE GROUND, DECAY CHECK WAS 5 SECONDS. RT MANIFOLD GROUND DECAY FAILED 30-20-PSI IN ONLY 5 SECONDS. UPON INSPECTION MX FOUND LEAKING DUCT CLAMPS IN CROSS WING MANIFOLD. TIGHTENED AND REPLACED AS NECESSARY. FOUND PRESSURE RELIEF VALVES ON NR 1 AND 3 WOULD NOT CLOSE ON SCHEDULE, ALSO, FOUND LT FLOW CONTROL VALVE LEAKING THROUGH VALVE WHEN CLOSED. FOUND NR 4 WING ANTI-ICE VALVE LEAKING, CENTER SLOTTED EXTEND WING VALVE BLEED AIR DUCT LT SIDE LEAKING AT CLAMP AND A BROKEN DUCT FLANGE. ALL VALVES AND DUCTS WERE REPLACED PER ALL APPLICABLE MANUALS AND A/CT WAS RETURNED TO SERVICE.

Part: TRANSCEIVER — NO INDICATION (WX RADAR SYS) · airframe 76,548 hrs · 23,684 cycles

IN CLIMB FROM KWRI, THE AIRCRAFT'S WEATHER RADAR WOULD NOT PAINT WEATHER OR GROUND. CREW RETURNED AIRCRAFT TO KWRI AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE WEATHER RADAR TRANCEIVER AND WEATHER RADAR ANTENNA. THE SYSTEMS OPERATIONAL CHECK AND SELF-TEST WERE GOOD PER ALL APPLICABLE MANUALS AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE — BURNED (WATER PUMP) · airframe 76,373 hrs · 23,636 cycles

DURING CRUISE AT APPROX 1 HOUR AND 20 MINUTES INTO FLIGHT FROM KSUU, F/A CALLED AND REPORTED A BURNING ODOR IN THE LEFT LAV. THE POWER SOURCE WAS ISOLATED AND ODOR WAS STILL PRESENT. CREW DIVERTED AIRCRAFT TO KSFO AND LANDED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT AND FOUND SOURCE TO BE COMING FROM THE WATER PUMP. ELECTRIC WIRING DISCONNECTED AND C/B COLLARD. THIS ITEM WAS TRANSFERRED TO DMI 32156 IN ACCORDANCE WITH ATI MEL AND IS A CATAGORY D. AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATOR — INOPERATIVE (EPR) · airframe 75,870 hrs · 23,531 cycles

CREW REJECTED TAKEOFF FROM RJTY, DUE TO LOW EPR ON NR 1 ENGINE. ALL OTHER PARAMETERS WERE NORMAL. CREW RETURNED AIRCRAFT TO BLOCKS. MAINTENANCE TROUBLESHOT TO A BAD EPR INDICATOR IN THE NR 1 POSITION. THE INDICATOR WAS REMOVED AND REPLACED AND THE OPERATIONAL CHECK GOOD PER ALL APPLICABLE MANUALS. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — FAILED (NR 4) · airframe 75,676 hrs · 23,491 cycles

DURING CLIMBOUT FROM KBWI, NR 4 ENGINE OIL PRESSURE LIGHT CAME ON. OIL PRESSURE/QUANTITY NORMAL. OIL TEMP WAS SLIGHTLY HIGHER THEN OTHERS AT 105C. COMPLETED CHECKLIST AND LIGHT WOULD NOT GO OUT. CREW SHUT DOWN ENGINE INFLIGHT THEN DIVERTED AIRCRAFT TO KWRI AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED, REPLACED AND RAN NR 4 ENGINE AND THE OPERATIONAL AND LEAK CHECK WERE GOOD PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: COMPUTER — WEAK (RUDDER) · airframe 75,072 hrs · 23,334 cycles

DURING CRUISE FROM RJTY AIRCRAFT YAWS TO THE RIGHT WHEN YAW DAMPER IS TURNED ON. THE AUTOPILOT RUDDER IS OFF SCALE RIGHT INDICE AUTOPILOT RUDDER OFF SCALE RIGHT. MAINTENANCE TROUBLESHOT AUTOPILOT SYSTEM AND FOUND YAW AND ROLL CHANNEL COMPUTERS WEAK. REMOVED AND REPLACED YAW CHANNEL AND ROLL COMPUTERS PER ALL APPLICABLE MANUALS AND THE OPERATIONAL CHECK WAS GOOD ON THE GROUND. AIRCRAFT WAS RETURNED TO SERVICE.

Part: COMPUTER — FAILED (YAW DAMPER) · airframe 74,833 hrs · 23,286 cycles

AFTER TAKEOFF FROM WSAP, YAW DAMPER ENGAGED, RUDDER KICKED TO THE LEFT. DISENGAGED YAW DAMPER. CREW TRIED TO RE-ENGAGE YAW DAMPER AND RUDDER KICKED LEFT AGAIN, TURNED OFF YAW DAMPER. CREW RETURNED AIRCRAFT TO WSAP AND LANDED WITHOUT INCIDENT. AN INVESTIGATION IS ONGOING. AS SOON AS INFORMATION IS AVAILABLE IT WILL BE PROVIDED. MAINTENANCE THAT THE YAW CHANNEL COMPUTER HAD FAILED THE SELF TEST. THE YCC WAS REMOVED AND REPLACED PER ALL APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: YAW DAMPER — MALFUNCTIONED (AUTOFLIGHT) · airframe 74,833 hrs · 23,286 cycles

AFTER TAKEOFF FROM WSAP, YAW DAMPER ENGAGED, RUDDER KICKED TO THE LEFT. DISENGAGED YAW DAMPER. CREW TRIED TO RE-ENGAGE YAW DAMPER AND RUDDER KICKED LEFT AGAIN, TURNED OFF YAW DAMPER. CREW RETURNED AIRCRAFT TO WSAP AND LANDED WITHOUT INCIDENT. AN INVESTIGATION IS ONGOING. AS SOON AS INFORMATION IS AVAILABLE IT WILL BE PROVIDED.

Part: B-NUT — LOOSE (HYD SYSTEM) · airframe 74,511 hrs · 23,224 cycles

DURING TAKEOFF FROM PGUA, HYDRAULIC FLUID DROPPED TO STAND PIPE LEVEL. HYDRAULIC FLUID WAS LEAKING FROM NR 2 ENGINE. AIRCRAFT RETURNED TO PGUA AND LANDED WITH INCIDENT. AN INSPECTION IS ON GOING. INFORMATION WILL BE PROVIDED AS SOON AS IT IS AVAILABLE. MAINTENANCE FOUND HYDRAULIC FLUID DRIPPING FROM NR 2 ENGINE COWL. THE COWL WAS OPENED AND BOTH ENGINE AND COWL WERE CLEANED. DRY MOTORED NR 2 ENGINE AND FOUND HYDRAULIC LEAK AT NR 10 B-NUT BY THE HYDRAULIC FILTER. MAINTENANCE TIGHTENED B-NUT, DRY MOTORED ENGINE AND PERFORMED LEAK CHECK. ALL CHECKS ARE NORMAL PER ALL APPLICABLE MANUALS. NR 2 ENGINE COWL WAS CLOSED AND HYDRAULIC RESEVIOR WAS SERVICED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ARM — BENT (MLG DOOR) · airframe 73,457 hrs · 73,235 cycles

IN CRUISE "DOORS NOT LATCHED LIGHT" CAME ON FOR 10 MINUTES. MAINTENANCE FOUND LT LANDING GEAR DOOR LATCH ROLLER ARMS BENT. REMOVED AND REPLACED LATCH ROLLER ARMS. WITH DOORS CLOSED FOUND LT DOOR LATCH ROLLER STOP BOLT SPACER CONTACTING RAIL ASSEMBLY. PERFORMED MAIN GEAR DOOR UPLACTH MECHANISM ADJUSTMENT/TEST TO PROVIDE A MINIMUM 1/8 INCH CLEARANCE BETWEEN STOP BOLT SPACER AND RAIL ASSEMBLEY. PERFORMED LANDING GEAR DOOR SWITCH TEST. OPERATIONAL CHECK WAS GOOD PER ALL MAINTENANCE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: FAN — BURNED OUT (COCKPIT) · airframe 73,382 hrs · 23,001 cycles

DURING CRUISE FROM WSAP TO RJTY, SMOKE WAS IN COCKPIT. CREW TURNED OFF BOTH RECIRC FANS AND SMOKE CLEARED. CREW CONTINUED TO RJTY AND LANDED WITHOUT INCIDENT. AN INSPECTION IS ON GOING. WHEN MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE TROUBLESHOT TO BAD RIGHT RECIRC FAN. THIS ITEM WAS TRANSFERRED TO THE DEFERRED MAINTENANCE ITEM LOG BOOK 29190 CAT -C- NO FLY DATE 3/15/04. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SWITCH — BROKEN (MLG DOOR) · airframe 73,382 hrs · 23,001 cycles

DURING CRUISE FROM WSAP TO RJTY, DOORS NOT LATCHED LIGHT CAME ON. BOTH ALTERNATE LIGHTS STAYED OUT. MAINTENANCE REMOVED AND REPLACED RIGHT LATCH DOOR SWITCH PER ALL APPLICABLE MANUALS OPERATIONAL CHECK GOOD ON GROUND. AIRCRAFT WAS RETURNED TO SERVICE.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 73,234 hrs · 22,972 cycles

LEFT L24 HAS ABOUT 1.25 INCH CRACK AFT OF THE FWD MAIN ATTACH BOLT. REMOVED AND REPLACED LT L24 AT STA 903 TO 960 IAW DC8 SRM 51-1-21 & 51-3-0. TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8. TORQUED FWD MAIN ATTACH BOLT IAW DRW 5750553.

Part: FINGER DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 73,234 hrs · 22,972 cycles

RIGHT AFT FUSELAGE BETWEEN STA 1540 & 1551 FROM L22R TO L25R PREVIOUS REPAIR HAS 2 RIVETS BLOWN OUT & CORROSION. REMOVED & FABRICATED DOUBLER & FINGER DOUBLER IAW DC8 SRM 53-02-01. TREATED AND PRIMED IAW DC8 SRM 51-1-8. INSTALLED DOUBLER & FINGER DOUBLER IAW DC8 SRM 53-02-01.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 73,234 hrs · 22,972 cycles

RIGHT AFT FUS BETWEEN STA 1540 & 1551 HAS CORROSION UNDER PAINT. STARTED REMOVING CORROSION FOUND SMALL POCKET OF INTERGRANULAR, CUT DAMAGED AREA OUT, FABRICATED FILLER & DOUBLER IAW DC8 SRM 53-02-01, TREATED AND PRIMED IAW DC8 SRM 51-1-8, INSTALLED FILLER & DOUBLER IAW DC8 SRM 53-02-01.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 73,234 hrs · 22,972 cycles

AFT PASS AREA AT STA 1480 FLOOR PANEL SUPPORT CORRODED UNDER FLOOR PLANK. FABRICATED DOUBLER FROM .063 7075T6 IAW DC8 SRM 53-2-3, TREATED AND PRIMED IAW DC8 SRM 51-1-8. INSTALLED DOUBLER IAW DC8 SRM 53-2-3.

Part: SUPPORT FITTING — CRACKED (LT AILERON) · airframe 73,234 hrs · 22,972 cycles

LEFT O/B AILERON NR 7 SUPPORT FITTING CRACKED. REMOVED LEFT AILERON IAW DC8 MM 27-11-2, REMOVED AND REPLACED LEFT O/B AILERON O/B ATTACHMENT BRACKET IAW DC8 DRAWING 5619462. REINSTALLED AILERON IAW DC8 MM 27-11-2.

Part: SUPPORT FITTING — CRACKED (RT AILERON) · airframe 73,234 hrs · 22,972 cycles

RIGHT O/B AILERON NR 7 SUPPORT HINGE FITTING HAS A CRACK AT LWR O/B BOLT HOLE. REMOVED RIGHT O/B AILERON IAW DC8 MM 27-11-2. REMOVED AND REPLACED RIGHT O/B AILERON HINGE SUPPORT FITTING IAW DC8 DRAWING 5619462. REINSTALLED RIGHT O/B AILERON IAW DC8 MM 27-11-2.

Part: SUPPORT FITTING — CRACKED (MLG) · airframe 73,234 hrs · 22,972 cycles

RIGHT MLG SUPPORT FITTING CRACKED AT TOP ATTACH POINT. REMOVED AND REPLACED RIGHT MLG SUPPORT FITTING (TRAP) IAW DC-8 SRM 51-1-20 & 51-1-21. BORED RIGHT MLG SUPPORT FITTING PER DOUGLAS BLUE PRINT 5611440.

Part: PANEL — CRACKED (NR 4 PYLON) · airframe 73,234 hrs · 22,972 cycles

NR 4 INBOARD PYLON PLANK CRACKED ABOUT 30 SCREWS AFT FROM L/E BOTTOM ROW. REMOVED NR 4 ENGINE PYLON I/B PLANK PANEL FOR REPAIRS, FABRICATED REPAIR IAW DC-8 SRM 54-2-2, INSTALLED REPAIR IAW DC-8 SRM 54-2-2. REINSTALLED NR 4 ENGINE PYLON PLANK IAW DC-8 SRM 54-2-2.

Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 73,234 hrs · 22,972 cycles

RIGHT WING UPPER SURFACE FROM WING ROOT TO STA 624 HAS NUMEROUS LOCATIONS OF EXFOLIATION RUNS FROM FRONT SPAR TO AFT SPAR. REMOVED CORROSION IAW DC8 SRM 51-1-8, NDT VERIFIED ALL WITHIN LIMITS. TREATED AND PRIMED IAW DC8 SRM 51-1-8. INSTALLED FASTENERS IAW DC8 SRM 51-1-20.

Part: ENGINE — LEAKING (NR 4) · airframe 72,948 hrs · 22,879 cycles

DURING FLIGHT FROM GOOY TO EDDS NR 4 ENGINE HAD A LOW OIL PRESSURE, LOW OIL QUANTITY AND HIGH TEMPERTURE WARNING. THE ENGINE WAS SHUT DOWN AND THE CREW RETURNED AIRCRAFT TO GOOY. MAINTENANCE INSPECTION IS ON GOING. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE REMOVED AND REPLACED NR 4 ENGINE IN ACCORDANCE WITH ALL APPLICABLE MANUALS. OPERATIONAL CHECK GOOD, AIRCRAFT RETURNED TO SERVICE.

Part: PRESSURE SWITCH — SHORTED (NR 1 ENGINE) · airframe 72,746 hrs · 22,823 cycles

ON CLIMB FROM KTOL TO KNGU, NR 1 OIL PRESSURE LIGHT CAME ON WITH NORMAL PRESSURE INDICATION. CREW PERFORMED ABNORMAL CHECKLIST. AIRCRAFT LANDED AT KNGU WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED OIL PRESSURE SWITCH IN ACCORDANCE WITH THE DOUGLAS AIRCRAFT MAINTENANCE MANUEL. OIL FILTER INSPECTED OK. RAN NR 1 ENGINE PER ATI ENGINE RUN HANDBOOK. OPERATIONAL AND LEAK CHECKS GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING HORN — FALSE ACTIVATION (TE FLAPS) · airframe 72,746 hrs · 22,822 cycles

ON TAKE OF, FROM TOL TO WRI, WITH FLAPS RETRACTING, TAKE OFF WARNING HORN SOUNDS UNTIL PTC IS PLACED IN NORMAL. CREW DID AN AIR TURN AROUND TO TOL. MAINTENANCE PERFORMED A TEST OF FLAP TAKEOFF WARNING SWITCH AND ALL OPERATIONAL CHECKS ARE GOOD AT THIS TIME IN ACCORDANCE WITH DOUGLAS DC-8 MAINTENANCE MANUAL.

Part: ENGINE — DEFECTIVE (#2 ENGINE ASSY) · airframe 72,017 hrs · 22,669 cycles

ENROUTE FROM FJDG TO OBBI CREW NOTED #2 OIL QUANTITY DROPPED. CREW ELECTED TO FOLLOW ATI PROCEDURE AND SHUTDOWN THE #2 ENGINE. THE FLIGHT CONTINUED ON TO OBBI FOR AN UNEVENTFUL LANDING.OIL PRESSURE INDICATION ON #2 ENGINE REMAINED IN THE "POSITIVE"RANGE FOR DURATION OF FLIGHT. UPON INSPECTION OF THE #2 ENGINE MAINTENANCE NOTED OIL DISCHARGE THRU TURBINE AND FOREIGN MATERIAL IN OIL STRAINER. MAINTENANCE REMOVED AND REPLACED THE #2 ENGINE IAW APPLICABLE AIRFRAME AND ENGINE MANUALS. UPON COMPLETION OF SUCCESFULL ENGINE RUN AND CHECK OUT THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: GYRO — FAULTY · airframe 71,785 hrs · 22,621 cycles

AFTER TAKEOFF FROM HIK CREW NOTED #2 "ADI" ATITUDE DIRECTIONAL INDICATOR ROLLING RANDOMLY. AS PRECAUTION CREW ELECTED TO RETURN TO HIK. AFTER AN UNEVENTFUL LANDING. MAINTENANCE TROUBLE SHOT AND REPLACED THE GYRO PER THE ATI DC-8 MAINTENANCE MANUAL AND E.O. 34-DC8-1806 UPON GROUND TEST SYSTEM CHECKED NORMAL AND THE AIRCRAFT WAS RELEASED FOR SERVICE.

Part: LINKAGE — BINDING (OUTFLOW VALVE) · airframe 70,713 hrs · 22,398 cycles

EN ROUTE FROM QPG THE FLIGHT CREW NOTICED THE CABIN PRESSURIZATION COULD NOT BE MAINTAINED. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES WITH NO EVAL AND RETURNED TO QPG FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE OUTFLOW VALVE LINKAGE BINDING THE SUGAR SCOOP. MAINTENANCE FREE, CLEANED, LUBRICATED AND ADJUSTED THE LINKAGE. MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: DOOR — CRACKED (FWD ENTRANCE) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED UNDER A TEMPORARY REPAIR OF THE FORWARD ENTRANCE DOOR CUTOUT FORWARD UPPER CORNER. REPAIR ACCOMPLSISHED REMOVAL OF THE TEMPORART REPAIR AND DAMAGED AREA. FABRICATED AND INSTALLED REPAIR FILLER AND EXTERNAL DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — CORRODED (RT WING) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE RIGHT HAND WING LEADING EDGE AT STATION XFS 566. REPAIR ACCOMPLISHED REMOVAL DAMAGED AREA, FABRICATION AND INSTALLATION OF FILLERS AND EXTENDED DOUBLER IN ACCORDANCE WITH DOUGLAS MAINTENANCE MANUAL.

Part: DOOR FRAME — CORRODED (AFT SERVICE) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION AND CRACKS WERE DETECTED ALONG THE LOWER EDGE OF THE FUSELAGE AFT SERVICE DOOR AND DOOR FRAME BETWEEN LONGERONS 16 AND 17 AT AXXPRXIMATE FS1500. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLERS IN ACCORDANCE WITH DOUGLAS STRUCTURAL MAINTENANCE MANUAL AND ENGINEERING DIRECTIVE EDP82-2.

Part: LONGERON — DENTED (STA 500) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE EXTERNAL PLATING AT FUSELAGE STATION 480 AT STRINGER 21L. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MAINTENANCE MANUAL AND ENGINEERING DIRECTIVE EDP82-1.

Part: AILERON — CRACKED (OB WING) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT WING OUTBOARD AILERON INBOARD SIDE LOWER PLATING. REPAIR ACCOMPLISHED, DAMAGED AREA CUT OUT, FABRICATED AND INSTALLED FILLER AND DOUBLER REPAIR IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: THRESHOLD — CORRODED (C-1 DOOR) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE C-1 DOOR UNDER THE THRESHOLD PLATE. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR FILLER AND DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MAINTENANCE MANUAL.

Part: WING — CORRODED (LEFT WING) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED AROUND SCREW HEADS ON THE LEFT WING OUTBOARD LEADING EDGE XFS892 TO XFS930. REPAIR ACCOMPLISHED REMOVAL OF THE CORROSION, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL MAINTENANCE MANUAL.

Part: WING — CORRODED (LT WING L/E) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION CORROSION WAS DETECTED AROUND THREE SCREW HOLES ON THE LEFT WING OUTBOARD LEADING EDGE AT STATION XFS 885. REPAIR ACCOMPLISHED, REMOVAL OF THE CORROSION, FACRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL MAINTENANCE MANUAL.

Part: SKIN — CORRODED (LT WING) · airframe 70,276 hrs · 22,304 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED AROUND THE HI-LOK HEAD ON THE LEFT WING UPPER LEADING EDGE APPROXIMATELY 21 INCHES OUTBOARD OF THE NR 2 PYLON. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: CONTROL CABLE — BROKEN (ELEVATOR TAB) · airframe 69,159 hrs · 22,001 cycles

DURING TAXI AT ANU, BINDING OF THE ELEVATOR WAS EXPERIENCED WHILE THE FLIGHT CREW WAS PERFORMING THE FLIGHT CONTROL CHECK. THE AIRCRAFT RETURNED TO THE BLOCKS. MAINTENANCE INSPECTED THE AIRCRAFT FLIGHT CONTROLS WHICH REVEALED A DEFECTIVE RIGHT ELEVATOR CONTROL TAB CABLE. MAINTENANCE REPLACED THE CONTROL CABLE IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 68,532 hrs · 21,811 cycles

DURING ROUTINE B-CHECK INSPECTION, A CRACK WAS DETECTED ON THE FUSELAGE EXTERNAL PLATING AT FUSELAGE STATION 242, BETWEEN LONGERONS 28L AND 29L. REPAIR ACCOMPLISHED STOP DRILLING CRACK. FABRICATION AND INSTALLATION A REPAIR DOUBLER IN ACCORDANCE WITH DACO STRUCTURAL REPAIR MANUAL 51-1-20 AND 53-2-0.

Part: SKIN — CRACKED (PAX DOOR) · airframe 68,532 hrs · 21,811 cycles

DURING ROUTINE B-CHECK INSPECTION, A CRACK WAS DETECTED ON THE CREW ENTRY DOOR SKIN LOWER CORNER AT FUSELAGE STATION 241. REPAIR ACCOMPLISHED STOP DRILLING CRACK, FABRICATION AND INSTALLATION A REPAIR DOUBLER IN ACCORDANCE WITH DACO STRUCTURAL REPAIR MANUAL 52-2-0, 51-1-8 AND 51-1-21.

Part: SWITCH — DEFECTIVE (RT GEAR) · airframe 68,461 hrs · 21,792 cycles

ENROUTE FROM OKO TO QPG, THE LANDING GEAR UNSAFE WARNING LIGHT ILLUMINATED DURING THE GEAR UPLATCH CHECK. THE FLIGH CREW CYCLED THE LANDING GEAR WITH THE WARNING INDICATION REMAINING THE SAME. THE FLIGHT RETURNED TO OKO FOR AN UNEVENTFUL LANDING. MAINTEANCE INSPECTED THE LANDING GEAR LOCATING A DEFECTIVE RIGHT MAIN GEAR UPLATCH SWITCH. MAINTENANCE REPLACED THE SWITCH AND PERFORMED A SUCCEFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FAN — ODOR (A/C BAY) · airframe 68,114 hrs · 21,716 cycles

EN ROUTE FROM JON TO HIK, AN ODOR WAS SENSED IN THE CABIN WHEN THE RIGHT RECIRULATION FAN WAS TURNED ON. THE FLIGHT CREW SECURED THE FAN AND THE ODOR SUBSIDED. THE FLIGHT CONTINUED TO HIK FOR AND UNEVENFUL LANDING. MAINTENANCE INSPECTED THE FAN AND IT WAS FOUND TO BE DEFECTIVE. MAINTENANCE PLACED THE FAN ON DEFERRAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: COMPRESSOR — DAMAGED (NR 2 ENGINE) · airframe 67,503 hrs · 21,588 cycles

EN ROUTE FROM JON TO HIK, DURING CRUISE THE NUMBER TWO ENGINE EXPERINCED A COMPRESSOR STALL FOLLOWED BY PARTIAL POWER REDUCION. THE FLIGHT CREW SECURED THE ENGINE FOLLOWING COMPANY PROCEDURES. THE FLIGHT CONTINUED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE WHICH REVEALED COMPRESSOR DAMAGE. THE ENGINE IS SCHEDULED TO BE REPLACED PRIOR TO THE AIRCRAFT RETURNING TO SERVICE. DURING SHOP TEARDOWN REVEALED BROKEN BLADES ON THE TWELFTH STAGE HPC, WHICH CAUSED DAMAGE TO HPC STAGES TEN THRU SIXTEEN. ALL DEFECTIVE COMPONENTS WILL BE REPLACED.

Part: BALLAST — DEFECTIVE (COCKPIT) · airframe 67,495 hrs · 21,585 cycles

EN ROUTE FROM HIK TO KWA, WHEN THE FLIGHT CREW ILLUMINATED THE COCKPIT LIGHTING SYSTEM SMOKE WAS DETECTED IN THE COCKPIT. THE FLIGHT CREW EXTINGUISHED THE LIGHTING SYSTEM AND THE SMOKE SUBSIDED. THE FLIGHT CONTINUED TO KWA FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LIGHT SYSTEM WHICH REVEALED A DEFECTIVE COCKPIT LIGHT BALLAST. MAINTENANCE PLACED THE COCKPIT LIGHTING SYSTEM ON DEFERRAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FLAP — CHAFED (RT TE FLAP)

MCN - DURING SCHEDULED INSPECTION, RIGHT WING, OUTBOARD FLAP, UPPER SKIN, FOUND 2 CHAFFED THROUGH AREAS OF SURFACE DAMAGE: ONE 2.8 INCH BY 2.2 INCH AREA AT XFS 212, AND ONE 1.5 INCH BY 1.9 INCH AREA AT XFS 227. REPAIRED DAMAGED AREAS IAW DER (COTNEY ENGINEERING) DWG C79-R03 ADN DC8 SRM 51-1-21, 57-1-20C. (M)

Part: TRACK — CHIPPED (LT TE FLAP)

MCN - DURING SCHEDULED INSPECTION, FOUND LT WING, OUTBOARD FLAP, ICE BREAKER TRACK AT XFS345 BENT AND CHIPPED. REPAIRED DAMAGE IAW DER (COTNEY ENGINEERING) DWG C79-R04 AND DC8 SRM 51-1-8, 57-1-21. (M)

Part: TRACK — CHIPPED (LT TE FLAP)

MCN - DURING SCHEDULED INSPECTION, FOUND LEFT WING, OUTBOARD FLAP, ICE BREAKERS TRACK AT XFS415 BENT AND CHIPPED. REPAIRED DAMAGE IAW DER (COTNEY ENGINEERING) DWG C79-R04 AND DC8 SRM 51-1-8, 57-1-21. (M)

Part: FLAP — CHAFED (RT TE FLAP)

MCN - DURING SCHEDULED INSPECTION, RIGHT WING, INBOARD FLAP, UPPER SKIN, FOUND 2 CHAFFED THROUGH AREAS OF SURFACE DAMAGE ONE 2.2 INCH BY 1.7 INCH AREA AT XFS 90, AND ONE 2.2 INCH BY 2.1 INCH AREA AT XFS 105. REPAIRED DAMAGED AREAS IAW DER, COTNEY ENGINEERING, DWG C79-R02 AND DC8 SRM 51-1-21, 57-1-20C. (M)

Part: LONGEREON — CORRODED (BS 570)

MCN - DURING SCHEDULED INSPECTION, FOUND LEVEL 2 CORROSION ON LONGERON NR 36 FROM FS 560 TO FS 570. REMOVED CORROSION AND REPAIRED IAW WITH DER APPROVED (COTNEY ENGINEERING) DWG NR C79-R01, AND DC8 SRM 51-1-8, 51-1-20D, 51-1-21. (M)

Part: DOOR SILL — DAMAGED (FUSELAGE)

MCN - DURING SCHEDULED INSPECTION, FOUND TEMPORARY REPAIR INSTALLED ON NR 2 PIT DOOR SILL AREA AT FS 523. REMOVED TEMPORARY REPAIR AND INSTALLED PERMANENT REPAIR IAW WITH DACO ROD NR 97-06-25-04, AND DC8 SRM 51-1-8, 51-1-21, AND 51-2-20D. (M)

Part: SKIN — CRACKED (FUSELAGE)

MCN - DURING SCHEDULED INSPECTION, FOUND FWD CREW ENTRY DOOR HOLD OPEN LATCH CUTOUT ON FUSELAGE SKIN WITH A .250 INCH CRACK. REPAIRED IAW WITH DER (COTNEY ENGINEERING) DWG C72-R01, AND DC8 SRM 51-1-8 AND 51-1-10. (M)

Part: PRESSURE WEB — CRACKED (BS 680)

MCN - DURING SCHEDULED INSPECTION, FOUND 1.25 INCH CRACK AT FS 680, LOWER COMPARTMENT PRESSURE WEB, RT OUTBOARD LOWER CORNER. REPAIRED IAW DC8 SRM 53-2-5, PAGE 31-34. (M)

Part: BLEED VALVE — MALFUNCTIONED (ENGINE)

DAY - DURING TAKEOFF ROLL WITH POWER SET, LARGE BANG AND FIREBALL WAS OBSERVED ON RIGHT SIDE OF THE AIRCRAFT. RETURNED TO RAMP. INSPECTED NR 3 AND NR 4 ENGINES FOR DAMAGE. NONE FOUND. COULD NOT DUPLICATE ON GROUND RUN. SUBMITTER STATES, SUSPECT MOMENTARY STUCK INTERSTAGE AIR BLEED VALVE. (M)

Part: SKIN — CORRODED (LE RT XFS 260)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE SKIN LE RT CTR RT XFS 260 CORRODED. REPAIRED IAW DWG A74-R38. (X)

Part: SKIN — CORRODED (LT XFS 560-575)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE UPPER SKIN LT XFS 560-575 CORRODED. REPAIRED IAW DWG A74-R17; SRM 51-1-8. (X)

Part: SKIN — CORRODED (RT XFS 164-207)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE UPPER SKIN XFS 164-207 CORRODED. REPAIRED IAW DWG A74-R19; SRM 51-1-8. (X)

Part: SKIN — CORRODED (LT XWR85-XFS566)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE UPPER SKIN LT XW485-XFS 566 CORRODED. REPAIRED IAW DWG A74-R22. (X)

Part: ANGLE — CORRODED (XW428)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE L-ANGLE XW428 CORRODED. REPAIRED IAW DWG A74-R23. (X)

Part: FRAME — CORRODED (RT WINDOW)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RT WINDOW FRAME CORRODED. FS 1040-1060. REPAIRED IAW DWG A74-R28; SRM 51-1-20D-21. (X)

Part: SUPPORT — CRACKED (KEEL FS 920)

MCH - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED FUSELAGE KEEL VERT SUPPORT CRACKED. REPAIRED IAW SRM 51-1-8 AND 51-1-120D. (X)

Part: LONGERON — CRACKED (FS 1190 34R)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED LONGERON CRACKED. FS 1190 34R. REPAIRED IAW DWG A74-R35. (X)

Part: HOIST POINT — CORRODED (LT WS672-720-803)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE HOIST POINT LT WS 672-720-803 CORRODED. REPAIRED IAW DWG A74-R06. (X)

Part: SKIN — CORRODED (LT XFS 566-603)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE LOWER SKIN LT XFS 566-603 CORRODED. REPAIRED IAW DWG A74-R08/R09. (X)

Part: FLANGE — CORRODED (LT XFS 525-560)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LT FLANGE, LT XFS 525-560 CORRODED. REPAIRED IAW DWG A74-R24. (X)

Part: SKIN — BULGING (HORZ STAB LT)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED HORIZ STAB UPPER SKIN LT AT 2ND ELEV HINGE CORRODED. REPAIRED IAW DWG A74-R32. (X)

Part: SKIN — CORRODED (FS 1085 33/35R)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED FUSELAGE SKIN CORRODED FS 1085 33/35R. REPAIRED IAW SRM 51-1-20D/21. (X)

Part: FRAME — CORRODED (RT WINDOW)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RT WINDOW FRAME CORRODED. FS 1240-1260. REPAIRED IAW DWG A74-R28; SRM 51-1-20D/21. (X)

Part: FRAME — CORRODED (RT WINDOW)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RT WINDOW FRAME CORRODED. FS 1240-1260. REPAIRED IAW DWG A74-R28; SRM 51-1-20D/21. (X)

Part: SKIN — CORRODED (RT XFS 172-292)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE UPPER SKIN RT XFS 172-292 CORRODED. REPAIRED IAW DWG A74-R31. (X)

Part: FRAME — CORRODED (RT WINDOW)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RT WINDOW FRAME CORRODED. FS 1000-1020. REPAIRED IAW DWG A74-R28; SRM 51-1-20D-21. (X)

Part: FLOOR BEAM — CRACKED (FS 880 BL 60L)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED FUSELAGE FLOOR BEAM CRACKED. REPAIRED IAW DWG 174-R20. (X)

Part: FRAME — CORROSION (FS 1080 35 L/R)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED CORROSION ON FUSELAGE FRAME FS 1080 35 L\R. REPAIRED IAW SRM 51-1-8; DWG A74-R27. (X)

Part: SKIN — CORRODED (RT OTBD AIL)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RT OTBD AILERON LOWER SURFACE CORROSION. REPAIRED IAW DWG A74-R05. (X)

Part: NOZZLE — CRACKED (NR 4)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED NR 4 NOZZLE CRACKED, 6 O'CLOCK. REPAIRED IAW DWG A74-R11. (X)

Part: SKIN — CORRODED (LT XFS 285-309)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE UPPER SKIN LT XFS 285-309 CORRODED. REPAIRED IAW DWG A74-R07/R21. (X)

Part: SKIN — CORRODED (LT XFS 710-746)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE UPPER SKIN LT XFS 710-746 CORRODED. REPAIRED IAW DWG A74-R18. (X)

Part: SKIN — CORRODED (RT XFS 139)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE LE UPPER SKIN RT XFS 139 CORRODED. REPAIRED IAW DWG A74-R30. (X)

Part: SKIN — CRACKED (XRS162-263)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED WING STRUCTURE UPPER SKIN XRS612-263 CRACKED. (X)

Part: SKIN — CORRODED (FS 1190 33/35R)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED FUSELAGE SKIN CORRODED. FS 1190 33/35R. REPAIRED IAW SRM 51-1-20D/21. (X)

Part: SKIN — DAMAGED (RUD LWR WELL)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RUDDER STRUCTURE LT SKIN LWR WELL DAMAGED. REPAIRED IAW DWG A74-R25. (X)

Part: SKIN — CORRODED (ZR45)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED VERT STAB LT SKIN CORRODED. ZR45. REPAIRED IAW DWG A74-R29; SRM 51-1-8. (X)

Part: LONGERON — CRACKED (FS 1190 36)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED LONGERON CRACKED. FS 1190 36. REPAIRED IAW DWG A74-R35. (X)

Part: FLANGE — CORRODED (RT ELEV)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED RT ELEV LOWER AFT FLANGE CORRODED. REPAIRED IAW DWG A74-426; SRM 51-1-21. (X)

Part: SKIN — CORRODED (FS 440-460 RT)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED FUSELAGE SKIN CORRODED. FS 440-460 RT. REPAIRED IAW DWG A74-R15. (X)

Part: NOZZLE — OUT OF ROUND (NR 2)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED NR 2 NOZZLE OUT OF ROUND, 10-12 O'CLOCK. REPAIRED IAW DWG A74-R01. (X)

Part: WINDOW LAND — CORRODED (LT WINDOW)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED LT WINDOW LAND CORRODED. FS 879-900. REPAIRED IAW DWG A74-R28; SRM 51-1-20D/-21. (X)

Part: FRAME — CORRODED (FS 1100 35/36)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVALED CORROSION ON FUSELAGE FRAME FS 1100 35/36. REPAIRED IAW A74-404. (X)

Part: LONGERON — CRACKED (FS 1090)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED LONGERON CRACKED. FS 1090 L35R. REPAIRED IAW DWG A74-R35. (X)

Part: SKIN — BULGING (HORZ STAB LT)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED HORIZ STAB LOWER SKIN LT AT 2ND ELEV HINGE CORRODED. REPAIRED IAW DWG A74-R32. (X)

Part: FRAME — CORRODED (LT WINDOW)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED LT WINDOW FRAME CORRODED. FS 1320-1340. REPAIRED IAW DWG A74-R28; SRM 51-1-20D/-21. (X)

Part: FRAME — CORRODED (FS 1020 CL)

MCN - DURING SCHEDULED CHECK, VISUAL, REFLECTIVE PROBE EDDY CURRENT AND ULTRASONIC INSPECTION TECHNIQUES REVEALED CORROSION ON FUSELAGE FRAME FS 1020 CL. REPAIRED IAW DWG A74-R03. (X)

Part: SKIN — CORROSION (LT WING)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT WING XW 408 EXT XRS 763. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT STUB LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT STUB LE EXT. XFS 560-575. XFS 575. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT IB STUB)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT INB STUB EXT XW 223-257. XW 246-251. XW 246.519. XW 246-519 AFT INB SLOT. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT WING LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT WING LE EXT WS 575-599. XFS 566-603. REPAIRED IAW APPLICABLE SRM'S, DWG, ETC. (X)

Part: SKIN — CORROSION (RT I/B LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT WING I/B LE EXT. WFS 200. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: KEEL BEAM — CORROSION (RT W/W)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT W/W KEEL BEAM FS 902-940 WEB. FS 879-FITTING. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (FS 1190)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. AFT LOWER CARGO BILGE. FS 1190 LONG 35L. FS 1085-1090 SKIN. FS 1080 LONG 35R-36R. FS 1020-CIRCUM. FS 1020 LONG 35R-36R. FS 1100-CIRCUM. FS 1100 LONG 35R-36R. FS 980-1250 TRACK. FS 1120 LONG 35R-36R. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SPAR — CORROSION (VERT STAB AFT)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. VERT STAB AFT SPAR ZR 218-281. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (C)

Part: HINGE — CORROSION (UPPER CARGO DOOR)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. UPPER CARGO DOOR HINGE ABOVE FWD SWIVEL DOOR AFT END. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (AFT ACCY COMPT)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. AFT ACCY COMPT-FS 1440-1500. FS 1563 LONG 18-34R. FS 1563. FS 1563 LONG 34R. FS 1564 LONG 24L. FS 1563 LONG 18L. FS 1560 LONG 18L ANGLES. FS 1440 LONG 34L-35R. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (RT INB STUB)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT INB STUB EXT. WS 163.750. SLOT PANEL. UPPER SURFACE. XFS 291.500. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: PANEL — CORROSION (NR 1 PYLON)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. NR 1 PYLON EXT PANEL, RT YN220. REPLACED.

Part: SKIN — CORROSION (RT WING LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT WING LE EXT. XFS 422.750. MIDDLE PANEL. XFS 566.250. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (FS 400-420)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. FWD LWR RT TUNNEL INT FS 400-420. FS 300-320. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (RT AIL)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT AIL INT XA 474-535. XA 646-678. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SPAR — CORROSION (LT WING LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT WING LE SPAR XFS 500. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT WING)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT WING XW 257-408. XFS 285-309. XFS 329. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT HOR O/B)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT HOR O/B EXT. XE 271-273. XE 310-312.5. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (RT WING LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT WING LE EXT CORROSION. XW 761.695-765. REPAIRED IAW APPLICABLE SRM'S, DWG, ETC. (X)

Part: SKIN — CORROSION (RT HOR O/B)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT HOR O/B EXT. XE 290. XE 222. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (VERT STAB)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. VERT STAB EXT LT SKIN, LT ATTACH ANGLE. RT SKIN ZR 225, RT SKIN ZR 270. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (MAIN CABIN)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. MAIN CABIN INTERIOR, FRAMES, LONGERONS, TRACK FROM FS 340 THROUGH FS 1590 BOTH LT AND RT. 54 AREAS NOTED ON TASK H 57300551. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (FUSE UPPER FWD)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. FUSE UPPER FWD EXT SKIN LONG 20-21R. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (FS 1060 L 27R)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. AFT LWR RT TUNNEL INT FS 1060 LONG 27R. FS 1040 LONG 26L-27R. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT INB STUB)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT INB STUB INT. UPPER FLANGE. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: KEEL BEAM — CORROSION (LT W/W)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT W/W KEEL BEAM. FS 944-980 TORQUE BOX. FS 947-974 WEB. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: EXTRUSION — CORROSION (FS 780)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. FS 780 AT FRAME. LT CUSP EXTRUSION. FS 520 AT FRAME. FS 1340 AT FRAME. FS 600 AT FRAME. FS 1020 AT FRAME. FS 1040 AT FRAME. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (LT WING LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. LT WING LE EXT CORROSION. XFS 710-746. XW 761.695. XFS 817-820. REPAIRED IAW APPLICABLE SRM'S, DWG, ETC. (X)

Part: SKIN — CORROSION (RT WING LE)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT WING LE EXT. XIS 697 SEAM. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: SKIN — CORROSION (FS 1100 L 35L)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. AFT LWR LT TUNNEL INT. FS 1100 LONG 35L. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: EXTRUSION — CORROSION (FS 780)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT CUSP EXTRUSION: FS 600 AT FRAME. FS 1240-1260. FS 879.375 FITTING. FS 1400-AT FRAME. FS 1442-1450 WEB. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)

Part: EXTRUSION — CORROSION (FS 460-480)

DURING ACCOMPLISHMENT OF AD 92-22-07 (DC-8 CORROSION PROGRAM) THE FOLLOWING INITIAL INSPECTIONS REVEALED LEVEL 2 CORROSION. RT CUSP EXTRUSION. FS 460-480. FS 870-LONG 24R. FS 220-RT UPPER. REPAIRED IAW APPLICABLE SRM'S, DWG., ETC. (X)