N823BX

Part: BULB — BURNED OUT (MLG INDICATOR) · airframe 93,028 hrs · 38,364 cycles

DURING APPROACH, NOSE GEAR LIGHT DID NOT ILLUMINATE UPON GEAR EXTENSION. CREW CYCLED NOSE GEAR AND VISUALLY CHECKED THE GEAR WAS DOWN AND LOCKED, THEY LANDED WITHOUT FURTHER INCIDENT. MX FOUND TOP LIGHT BULB BURNED OUT AND BOTTOM LIGHT WAS INTERMITTENT WHEN PUSHED ON GREEN LIGHT INDICATOR. THEY REPLACED BOTH BULBS. OPS CHECK GOOD IAW MM 32-60-0. ACFT WAS RETURNED TO SERVICE.

Part: RHEOSTAT — FAILED (CABIN LIGHTS) · airframe 93,018 hrs · 38,359 cycles

DURING DESCENT, THE OVERHEAD LIGHTS WENT OUT, FOLLOWED BY SMOKE AND FUMES THEN OVERHEAD SWITCH PANEL INTEGRAL LIGHTS CIRCUIT BREAKER POPPED AND SMOKE AND FUMES CLEARED. THE CREW LANDED WITHOUT FURTHER INCIDENT. MX REPLACED OVERHEAD LIGHT PANEL RHEOSTAT, NO HELP. MX DEFERRED LIGHTS IAW MEL 33-01-01 AND MM 33-13-0. ACFT WAS RETURNED TO SERVICE.

Part: VBV — OUT OF RIG (NR 2 ENGINE) · airframe 92,962 hrs · 38,332 cycles

DURING POWER REDUCTION TO CRUISE POWER, NR 2 ENG COMPRESSOR STALLED. CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX PERFORMED TROUBLESHOOTING FAULT 41 AND FOUND VBV'S OUT OF RIGGING. THEY RERIGGED THE VBV'S AND REPLACED CIT SENSOR. OPS CHECK GOOD IAW MM 71-00-00, 73-21-10, 73-21-20, ERH 70.01 AND GMM 3.124. ACFT WAS RETURNED TO SERVICE.

Part: RELAY — DEFECTIVE (ANTI ICE SYSTEM) · airframe 92,279 hrs · 37,980 cycles

UPON DESCENT INTO KTOL, THE CREW PUSHED IN ANTI FOGGING CIRCUIT BREAKER AND THE CREW DETECTED SMOKE, THE CREW PULLED THE CIRCUIT BREAKER AND SMOKE ODOR DIMINISHED. THE CREW LANDED IN KTOL WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED RELAY. OPERATIONAL CHECK GOOD IAW DACO MAINTENANCE MANUAL 30-41-0. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — FLAMED OUT (NR 4) · airframe 91,940 hrs · 37,814 cycles

DURING CLIMBOUT FROM KPDX AT 39000 FT NUMBER 4 ENGINE FLAMED OUT, AIRSPEED UNKNOWN, MACH .78, ALT 36.0, RAT UNKNOWN, WT 220.0 WEATHER CLEAR NO FIRE WARNING. GENERATOR WENT OFF LINE, OIL PRESS LIGHT ON, IGNITION OFF, FUEL FEED NOT CHANGED, WINDMILLING OIL PRESS 5 PSI, FUEL PRESS UNKNOWN. BEFORE FLAME OUT N1, N2 AND F/F WAS FLUCTUATING FOR 20 TO 30 SECONDS. THE CREW ATTEMPTED RESTART AT 35000 AND WAS UNSUCCESSFUL. CREW PERFORMED ENGINE SHUTDOWN CHECK LIST. THE CREW LANDED IN KLAX WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED REMOVED AND REPLACED FUEL PUMP FILTER, NO CONTAMINATION OR DEBRIS. INSPECTED CDP TUBE, MAG CHIP, FUEL PUMP LOW PRESSURE IMPELLER ROTATION, NO DEFECTS NOTED. MAINTENANCE REMOVED WATER AND RESIDUAL TANK SEALANT NEAR SCREEN. MAINTENANCE RAN NUMBER 4 ENGINE, OPERATIONAL CHECK GOOD IAW ERH 70.01.1, MAINTENANCE MANUAL 71-00-00, CFM MAINTENANCE MANUAL 73-11-10, 79-00-00, AND UAL MAINTENANCE MANUAL 28-10-03. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — FLAMED OUT (NR 2)

DURING CRUISE, AT 36,000 FT WITH POWER REDUCTION NR 2 ENGINE FLAMED OUT WITH 1-2 PSI OIL PRESSURE ATTEMPTED INFLIGHT RESTART, NO FUEL FLOW AND NO IGNITION. THE CREW PERFORMED INFLIGHT ENGINE SHUTDOWN PROCEDURE. THE CREW LANDED WITHOUT FURTHER INCIDENT. MAINT INSPECTED NR TWO ENGINE, NO DEFECTS NOTED. RAN ENGINE AT IDLE SETTING, ALL INDICATIONS NORMAL, TAXI ACFT AND PERFORMED HIGH POWER RUN WITH TWO DIFFERENT POWER ASSURANCE 55 PERCENT SETTING AND 70 PERCENT SETTING, NO DEFECT`S NOTED. MAINT INSPECTED TANK AND FUEL PUMP, NO DEFECTS NOTED. OPS CHECK GOOD IAW MM 71-00-00, 73-11-00, MM 28-22, ERH 70.01.01-07, ERH 91.04.4, 91.01.6. ACFT WAS RETURNED TO SERVICE. (K)

Part: ENGINE — FLAMED OUT (NR 2)

DURING CRUISE AT 36,000 FT WITH POWER REDUCTION NR 2 ENGINE FLAMED OUT, WITH 1-2 PSI OIL PRESSURE ATTEMPTED INFLIGHT RESTART, NO FUEL FLOW AND NO IGNITION. THE CREW PERFORMED INFLIGHT ENGINE SHUTDOWN PROCEDURE. THE CREW LANDED WITHOUT FURTHER INCIDENT. OPEN (K)

Part: FIRE WARNING — MALFUNCTIONED (NR 2)

DURING CRUISE, NR 2 FIRE WARNING CAME ON INTERMITTENTLY. THE CREW SHUTDOWN NR 2 ENGINE, WAS UNABLE TO ACCOMPLISH FIRE WARNING TEST. THE CREW DISCHARGED 1 FIRE BOTTLE, ACCOMPLISHED FIRE WARNING TEST. SEVERAL MINUTES LATER NR 2 FIRE WARNING CAME ON AGAIN, THE CREW DISCHARGED THE 2ND FIRE BOTTLE. FIRE WARNING TESTED GOOD. THE CREW LANDED WITHOUT FURTHER INCIDENT. (K)

Part: FINGER DOUBLER — CORRODED (ZONE 700) · airframe 91,810 hrs · 37,742 cycles

DURING ROUTINE D CHECK INSPECTION, FOUND TOP SURFACE OF MAIN LANDING GEAR WHEEL WELL PRESSURE PANEL FINGER DOUBLER CORRODED AT STATION 941.000 TO STATION 958.000 LEFT BOTTOM LINE 5 TO RIGHT BOTTOM LINE 5. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FINGER DOUBLER. FABRICATED FINGER DOUBLER. CLEANED TREATED AND PRIMED AREA AND FINGER DOUBLER. INSTALLED NEW FINGER DOUBLER IAW SRM 51-1-21, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 51-1-21, SRM 53-7-1 PAGE 21 FIGURE 10, AND SRM 51-1-8B.

Part: TRANSCEIVER — FAULTY (WX RADAR) · airframe 88,994 hrs · 36,527 cycles

APPROXIMATELY ONE HOUR INTO CRUISE FROM KMIA TO SKCL, THE WEATHER RADAR INDICATED WEAK SIGNAL THEN STARTED SPOKING AND SPOTTING. AT ONE HOUR AND TEN MINUETS INTO FLIGHT THE WEATHER RADAR WENT COMPLETELY GREEN. THE CREW ELECTED TO RETURN TO KMIA AND PERFORMED A ROUTINE LANDING. MAINTENANCE INSPECTED THE RADAR WAVE GUIDE AND ELECTRICAL CONNECTIONS FOR SECURITY, NO DEFECTS NOTED. FURTHER TROUBLESHOOTING FOUND A FAULTY RADAR TRANSCEIVER UNIT. THE RADAR TRANSCEIVER UNIT WAS REPLACED AND THE OPERATIONAL CHECK WAS GOOD. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CORRODED (ZONE 300) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND CORROSION ON HORIZONTAL STABILIZER UPPER SKIN LEADING EDGE FROM STATION XFS 178.00 TO STATION 203.750 TO THE RIGHT HAND REAR. DAMAGED AREA WAS CLEANED AND EXTERNAL DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 55-018.

Part: SKIN — CORRODED (L/E SLAT) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND CORROSION OUT OF LIMITS ON INBOARD EXTENDED LEADING EDGE UPPER SKIN, STATION XFS 13.750 - 20.000 RIGHT. PERMANENT REPAIR WAS PERFORMED IAW EWO ATI 57-084.

Part: PANEL — MISALIGNED (ZONE 600) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND SLOT PANEL AFT HOLES DO NOT ALIGN UP WITH THE HOLES IN THE WING ON CENTER EXTENDED LEADING EDGE AROUND LOWER SKIN RIGHT HAND. DAMAGED AREA WAS CLEANED, REPAIR DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW EWO ATI 57-085.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR AT STATION 1430, LONGERON 34 RIGHT, EXTERNAL DOUBLER BELOW D-PIT DOOR OPENING. ALSO AT FUSELAGE LOWER SECTION SKIN, FROM STATION 1360 TO 1580, LONGERON 36 TO 31 RIGHT AND LEFT FOUND CORROSION. REMOVED AND REPLACED SKIN BETWEEN STATIONS 1350.000 AND 1490.000, LONG 31 RIGHT TO 31 LEFT IAW DOUGLAS DRAWING 5616674, 5750776 AND 5615372. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1694 LONGERON 35 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 223 LONGERON 35.5 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 546 LONGERON 35.75 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1696 LONGERON 16.5 LEFT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1705 LONGERON 36. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1696 LONGERON 16.5 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND AN IMPROPER REPAIR ON FUSELAGE SKIN AT STATION 54 LONG 28 -30 LEFT. EXISTING REPAIR WAS REMOVED; NEW EXTERNAL DOUBLER & FILLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-062. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 615 LONGERON 36. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1143 LONGERON 35.75 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR ON FUSELAGE SKIN AT STATION 1450 BETWEEN LONGERONS 30 - 31 RIGHT, REPAIR PROXIMITY ISSUE WITH D-PIT DOOR BOTTOM DOUBLER. IMPROPER REPAIR WAS REMOVED, NEW FILLER AND EXTERNAL DOUBLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-064.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 404 LONGERON 35.75 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, AN IMPROPER REPAIR ON SKIN AT STATION 479, LONGERON 28-RIGHT. DAMAGED SKIN SECTION WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-055 AND SRM 53-2-5 FIGURE 14A. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND AN IMPROPER REPAIR ON PASSENGER WINDOW, AT STATION 1290 LONGERON 17.5- RIGHT HAND.CORRECTIVE ACTION: IMPROPER REPAIR WAS REMOVED AND PERMANENT REPAIR WAS PERFORMED IAW EWO ATI 53-057 AND SRM 53-2-0 FIG 22A. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR AT STATION 282 AT LONGERON 25.5R. DAMAGED SKIN SECTION WAS REMOVED AND EXTERNAL DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-061.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1394 LONGERON 35.75 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 555 LONGERON 35.5 LEFT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLERS EXTERNAL SKIN, STA 78 LONGERON 35.5 RT. REMOVED IMPROPER REPAIR, REMOVED DAMAGE, CLEANED, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND CUT OUT AND NO CRACKS FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3 WAS ISSUED APPROVING THOSE REPAIRS.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR ON SKIN AT STATION 1752 LONGERON 16.5 - LEFT. IMPROPER REPAIR WAS REMOVED AND FINGER DOUBLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-060 AND SRM 53-2-5 FIGURE 14A.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND TWO IMPROPER REPAIRS ON PASSENGER WINDOW; STATION 1472 LONGERON 16.5 RT AND STATION 1479 LONGERON 14.5 RT. BOTH IMPROPER REPAIRS WERE REMOVED AND PERMANENT REPAIRS WERE PERFORMED IAW EWO ATI 53-058 AND SRM 53-2-0 FIGURE 22A. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND AN IMPROPER REPAIR ON SKIN OF PASSENGER WINDOW, STATION 1310 LONGERON 16 RIGHT. IMPROPER STRUCTURAL REPAIR AT STATION 1310 LONGERON 16 RIGHT WAS REMOVED AND PERMANENT REPAIR DOUBLER WAS INSTALLED IAW EWO ATI 53-056 AND SRM 53-2-0 FIG 22A. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 1280 LONGERON 35.75 LEFT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 105 LONGERON 35.75 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK AN IMPROPER REPAIR AT PASSENGER WINDOW STATION 1310 LONGERON 16 RIGHT. IMPROPER REPAIR WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED & INSTALLED IAW EWO ATI 53-059 AND SRM 53-2-0 FIGURE 22A. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND AN IMPROPER REPAIR ON FUSELAGE SKIN AT STATION 30 BETWEEN LONGERONS 6 - 7 LEFT. IMPROPER REPAIR WAS REMOVED; NEW EXTERNAL DOUBLER AND FINGER DOUBLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-063. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR AT STATION 8.00 LONGERON 33 LT. REMOVED EXISTING REPAIR. FABRICATED NEW REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS. IAW TAMPA ENGINEERING WORK ORDER EWO ATI 53-052 DATED APRIL 14,2006.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 172 LONGERON 35.75 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR AT STATION 8.00 LONGERON 33 RIGHT. REMOVED EXISTING REPAIR. FABRICATED NEW REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED NEW REPAIR PARTS. IAW TAMPA ENGINEERING WORK ORDER EWO ATI 53-052 DATED APRIL 14,2006.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND IMPROPER REPAIR ON FUSELAGE DRAIN DOUBLER EXTERNAL SKIN AT STATION 78 LONGERON 35.5 RIGHT. REMOVED IMPROPER REPAIR, EDDY CURRENT INSPECTIONS WERE PERFORMED AROUND REMOVED DAMAGE, AND NO CRACKS WERE FOUND, REPAIR DOUBLERS AND FINGER DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-068. FAA FORM 8110-3.

Part: FITTING — CRACKED (ZONE 500) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND A CRACK ON THE OUTBOARD FLAP STATION XFS 339.723, INBOARD FITTING LEFT HAND. STOP DRILLED THE END OF THE CRACK. REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 57-075. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — IMPROPER (BS 80-100) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A IMPROPER REPAIR ON PRESSURE SKIN STA 80 TO 10 LONGERON 33 AND 34 RT. IMPROPER REPAIR WAS REMOVED AND NEW REPAIR DOUBLER AND FINGER DOUBLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-050 AND SRM 53-2-5 FIGURE 14A.

Part: SKIN — MISREPAIRED (BS 460-480) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A IMPROPER REPAIR ON PRESSURE SKIN STA 460 TO 480 LONGERON 30 - 31 RT. PERMANENT REPAIR WAS PERFORMED BY FABRICATING AND INSTALLING DOUBLER AND FINGER DOUBLER IAW EWO ATI 53-049 AND SRM 53-2-5 FIGURE 14A.

Part: SKIN — MISREPAIRED (BS 8 L33L) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND TWO IMPROPER REPAIRS ON NOSE SKIN AT STA 8 LONGERON 33 RT AND STA 8 LONGERON 33 LT. DAMAGED SKIN SECTION WAS REMOVED AND EXTERNAL DOUBLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-052. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CRACKED (BS1766) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A CRACK ON AFT PRESSURE BULKHEAD SKIN LONGERON 10, STA 1766 BETWEEN STIFFENER 5772638-49 AND 5772638-51 LT. DAMAGED AREA WAS CLEANED, CRACKS IN SKIN WERE REMOVED AND REPAIR DOUBLER WAS INSTALLED IAW EWO ATI 53-048 & SRM 53-2-5 FIGURE 14A.

Part: RIB — CRACKED (ZONE 500) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND LT WING TRAILING EDGE UPPER RIB CRACKED AT STA XOLID 6.225. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED, REPAIR PARTS. IAW TAMPA ENGINEERING WORK ORDER EWO ATI 57-081 DATED MAY 04, 2006.

Part: REPAIR — IMPROPER (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND AN IMPROPER REPAIR ON FUSELAGE CENTER FRAME STATION 781 LONGERON 31 LEFT. IMPROPER REPAIR WAS REMOVED AND PERMANENT REPAIR WAS PERFORMED IAW EWO ATI-53-067 AND BOEING SERVICE REQUEST 1-184705372.

Part: RIB — CRACKED (ZONE 500) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND LT WING TRAILING EDGE UPPER RIB CRACKED AT STATION XFS 304.0. REMOVED DAMAGE. FABRICATED REPAIR PARTS, LOCATED, DRILLED, TRIMMED, TREATED, PRIMED, AND INSTALLED, REPAIR PARTS. IAW TAMPA ENGINEERING WORK ORDER EWO ATI 57-077 DATED APRIL 26, 2006.

Part: SKIN — CRACKED (BS 1440 S25-28R) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A CRACK ON FUSELAGE SKIN AFT CARGO COMPARTMENT, UPPER AFT CORNER AT STA 1440.0, LONGERON 25 TO 28-RT. REPAIRED CRACK ON FUSELAGE SKIN AFT CARGO COMPARTMENT IAW EWO ATI 53-043 AND SRM 53-2-0 FIGURE 21.

Part: SKIN — CRACKED (BS 1660 S21-23L) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK WAS FOUND A CRACK ON FUSELAGE SKIN AFT PASSENGER DOOR LOWER FWD CORNER STA 1660 LT LONGERON 21 TO 23 LT. DAMAGED AREA WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-045 & SRM 53-2-0 FIGURE 18.

Part: SKIN — BULGED (T/E FLAP) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND DENTED AND BULGING SKIN ON INBOARD FLAP UPPER SKIN TRAILING EDGE SKIN BETWEEN STATIONS XW 91.6564 TO 84.534 – RIGHT. DAMAGED SECTION SKIN WAS REMOVED. REPAIR SPLICE WAS MANUFACTURED AND NEW SKIN SECTION WAS FABRICATED AND INSTALLED IAW EWO ATI 57-079.

Part: SKIN — CRACKED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND A CRACK ON FUSELAGE SKIN FWD PASSENGER DOOR UPPER AFT CORNER, STATION 55 LONGERON 9 TO 12L. CRACK WAS REMOVED AND REPAIR DOUBLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 53-046 & SRM 53-2-0 FIGURE 15. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND AN IMPROPER REPAIR ON INBOARD FLAP LOWER SKIN STATION XW 63.604 TO 50.232 RIGHT. IMPROPER REPAIR WAS REMOVED AND PERMANENT REPAIR WAS FABRICATED AND INSTALLED IAW EWO ATI 57-080. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — NICKED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND A NICK ON FUSELAGE SKIN AT STATION 1160, BETWEEN LONGERONS 30 - 31 LEFT. REMOVED DAMAGE. EXTERNAL DOUBLER AND EXTERNAL TRIPLER WERE FABRICATED AND INSTALLED IAW EWO ATI 53-066.

Part: SKIN — CRACKED (BS 1660 S9-12L) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A CRACK ON FUSELAGE SKIN AFT PASSENGER DOOR UPPER AFT CORNER STA 1660 LT, LONGERON 9 TO 12 LT. DAMAGED AREA WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-047 & SRM 53-2-0 FIGURE 18.

Part: SKIN — CRACKED (ZONE 200) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND A CRACK ON SKIN BETWEEN LONGERONS 1-2 RIGHT HAND, STATION 200. DAMAGED SKIN SECTION WAS REMOVED AND INTERNAL DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-053.

Part: SKIN — CRACKED (BS 440 S10-12R) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK WAS FOUND A CRACK ON FUSELAGE SKIN FWD SERVICE DOOR UPPER FWD CORNER STA 440 LONGERON 10 TO 12 RT. DAMAGED AREA WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-044 & SRM 53-2-0 FIGURE 14.

Part: PLATE — CORRODED (LT WING) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND CORROSION ON THE INBOARD EXTENDED LEADING EDGE NOSE PLATING AROUND STATION XFS 5000 LEFT HAND. CORRODED AREA WAS REMOVED AND INTERNAL DOUBLER WAS FABRICATED & INSTALLED IAW EWO ATI 57-074. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CRACKED (ZONE 500) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE CHECK, FOUND 3 CRACKS ON LEFT WING LEADING EDGE LOWER SURFACE BETWEEN STATION XFS 422 AND XS 435. REMOVED AND REPLACED SKIN IN LEFT WING LEAD EDGE LOWER SURFACE BETWEEN STATION XFS 422 AND XS 435 IAW DOUGLAS DRAWING NR 5769857.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND CORROSION ON HORIZONTAL STABILIZER LOWER SKIN AT STATION XAR 0.00 TO REAR SPAR LEFT HAND. REMOVED CORROSION IAW DC8 SRM 51-1-8 PAGE 20. THICKNESS MEASUREMENT PERFORMED AND IT WAS FOUND OUT OF LIMITS IAW DC8 SRM 55-2-0 PAGE 12. PERMANENT REPAIR WAS PERFORMED IAW EWO ATI 55-016.

Part: SKIN — CORRODED (BS 35-70) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A CORROSION ON FUSELAGE SKIN BETWEEN STA 35 TI 70, LONGERON 31 RT TO 31 LT. SKIN PORTION OF LOWER FUSELAGE FROM LONGERON 31 RT TO 31 LT AND STA 17 TO 70 WAS REMOVED AND REPLACED IAW DOUBLER DRAWING 5613862, AND SPLICE WAS FABRICATED AND INSTALLED IAW EWO ATI 53-041. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CRACKED (ZONE 300) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND A CRACK ON THE RUDDER FAIRING SKIN DRAIN HOLE AT STATION ZR 81.625 LEFT HAND. DAMAGED SKIN SECTION WAS REPAIRED IAW EWO ATI 55-017 AND DOUGLAS DRAWING 5655074. THIS REPAIR CONSTITUTES A MINOR REPAIR.

Part: SKIN PANEL — CRACKED (PYLON) · airframe 88,960 hrs · 36,512 cycles

DURING C-CHECK INSPECTION FOUND A CRACK ON INBOARD PYLON STUD EXTENDED EDGE UPPER, AROUND STA XS 250.089 LT. DAMAGED AREA WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 57-066 & EWO DRAWING ATI 57-066. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CRACKED (RT WING) · airframe 88,960 hrs · 36,512 cycles

DURING A C-CHECK INSPECTION FOUND A CRACK ON CENTER EXTENDED LEADING EDGE AROUND LOWER SKIN XFS 341.000 RT. REPAIR DOUBLER AND ALUMINUM FILLER WERE FABRICATED AND INSTALLED IAW EWO ATI 57-068. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CRACKED (L/E SLAT) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK FOUND A CRACK ON CENTER EXTENDED LEADING EDGE AROUND LOWER SKIN STATION XOLDI 6.225 - RIGHT HAND. RIGHT HAND WING CENTER LEADING EDGE WAS REMOVED IAW DC8 AMM 57-20-02 PAGE 203, REPAIRED OUTER SKIN IAW EWO ATI 57-069 AND INSTALLED RT WING CENTER LEADING EDGE IAW DC8 AMM 57-20-02 PAGE 206-208. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CORRODED (BS 340-360) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND CORROSION ON FUSELAGE SKIN BETWEEN STA 340 TO 360, LONGERON 32 RT TO 32 LT. CORRODED AREA WAS REMOVED AND EXTERNAL DOUBLER, FILLER DOOR JAMB INNER SKIN AND SPLICE WERE FABRICATED AND INSTALLED IAW EWO ATI 53-042. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CRACKED (RT WING) · airframe 88,960 hrs · 36,512 cycles

DURING A CHECK INSPECTION FOUND TWO CRACKS ON CENTER EXTENDED LEADING EDGE AROUNG LOWER SKIN A STA XFS 304.000 RT. REPAIR DOUBLER AND ALUMINUM FILLER WER FABRICATED AND INSTALLED IAW EWO ATI 57-067. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: VANE — ELONGATED (ZONE 600) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND ELONGATED HOLES ON EXTENDED LEADING EDGE OUTBOARD VANE, STATION XOLDI 6.224 RIGHT HAND. DAMAGED WAS REMOVED, REPAIR DOUBLER AND FILLERS WERE FABRICATED AND INSTALLED IAW EWO ATI 57-072. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR

Part: ANGLE — CORRODED (FUSELAGE) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND CORROSION ON FORMER (CAP ANGLE) AT STATION 99 - LEFT. CORRODED AREA WAS REMOVED, REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 53-065 AND SRM 53-2-5 FIG 8C-1. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — CANNING (RT ELEVATOR) · airframe 88,960 hrs · 36,512 cycles

DURING INSPECTION CHECK FOUND A OIL CAN ON RT ELEVATOR LOWER SURFACE, STA XE 246.875 TO XE 258.896. REMOVED AND REPLACED RT ELEVATOR LOWER SKIN IAW DOUGLAS DRAWING 5654970. ACCOMPLISHED WEIGHT AND BALANCE IAW DC8 SRM 51-4-4 TR 51-116 PAGE 2.

Part: VANE — CORRODED (L/E SLAT) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND ELONGATED HOLES AND CORROSION ON EXTENDED LEADING EDGE OUTBOARD VANE BETWEEN STATIONS XILD 0.7095 XILD 40.00 RIGHT. CORRODED AREA WAS REMOVED, DAMAGED SECTION HOLES WERE CUT OUT AND PERMANENT REPAIR WAS PERFORMED IAW EWO ATI 57-078.

Part: FITTING — CRACKED (ZONE 700) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND A CRACK ON RIGHT MAIN LANDING GEAR FITTING, LONGERON 24, STATION 879.000. FITTING WAS FABRICATED IAW DOUGLAS DRAWING 3641004 AND INSTALLED IAW SRM 51-3-0 PAGE 1-4 AND SRM 51-1-20D.

Part: SUPPORT BRACKET — CORRODED (ZONE 700) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND CORROSION AND ONE SCRATCH ON MAIN LANDING GEAR RETRACT BRACKET LEFT HAND. CORRODED AREA WAS REPAIRED IAW EWO ATI 57-073 AND AMM 57-40-1 PAGE 801. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SKIN — CORRODED (ZONE 500) · airframe 88,960 hrs · 36,512 cycles

DURING ROUTINE C CHECK, FOUND TWO AREAS OF CORROSION OUT OF LIMITS ON OUTER OUTBOARD EXTENDED LEADING EDGE UPPER SKIN, STATION XFS 722 - 835, LEFT HAND. DAMAGED AREA WAS REMOVED AND REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 57-071 AND SRM 57-2-1 FIGURE 38. THIS REPAIR CONSTITUTES A MAJOR REPAIR.

Part: SKIN — MISREPAIRED (LT WING) · airframe 88,960 hrs · 36,512 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND A TEMPORARY REPAIR ON INBOARD EXTENDED LEADING EDGE AROUND STA XFS 51.250 TO 57.500 LT. IMPROPER REPAIR WAS REMOVED AND NEW REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EWO ATI 57-065. FAA FORM 8110-3 WAS ISSUED APPROVING THIS REPAIR.

Part: SENSOR — INOPERATIVE (NR 4 ENGINE) · airframe 88,881 hrs · 36,477 cycles

APPROX 2 HRS INTO FLT ACFT ENCOUNTERED MOUNTAIN WAVE EFFECT AND INCREASING AIRSPEED WHEN POWER WAS REDUCED. NR 4 ENGINE POWER ROLLED BACK TO IDLE AND WOULD NOT RESPOND TO THROTTLE. PERFORMED PRECAUTIONARY SHUTDOWN AND DESCENDED. ON DESCENT PERFORMED IN FLIGHT START, ENGINE DID NOT LIGHT OFF DISCONTINUED START AND LANDED WITHOUT INCIDENT. PERFORMED T/S, CIT SENSOR FAILED CHECK. REMOVED AND REPLACED CIT SENSOR, INSPECTED FUEL FILTERS, FOUND NO DEFECTS. PERFORMED ENGINE RUN OF NR 4 ENGINE. CHECKED GROUND AT FLIGHT IDLE AND MAX POWER ASSURANCE. PERFORMED PMC CHECK AND ACCELERATION CHECK NR 4 ENGINE OPS CHECK NORMAL. WORK WAS DONE PER ALL APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — FLAMED OUT (NR 4) · airframe 88,139 hrs · 36,140 cycles

DURING DESCENT FROM BIKF TO KNGU, NR 4 ENGINE EXPERIENCED VIBRATION AND A FLAME OUT. CREW LANDED AIRCRAFT IN KNGU WITHOUT INCIDENT. MAINTENANCE COMPLIED WITH FAULT 53, FAN VIBRATION AND NO DEFECTS WERE NOTED. FAULT 51 COMPLIED WITH AND MAINTENANCE SUMPED WATER CONTAMINATION FROM THE NR 4 MAIN. A POWER ASSURANCE WAS PERFORMED PER ATI ERH 91.1 AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: MEC — OUT OF ADJUST (NR 4 ENGINE) · airframe 88,003 hrs · 36,091 cycles

DURING DESCENT FROM MPDC TO KTOL FLIGHT LEVEL 38.0, NR 4 ENGINE FLAMED OUT WHEN THROTTLE WAS RESTARTED. ALL ENGINE PARAMETERS WERE NORMAL CREW ACCOMPLISHED FLAME OUT IN FLIGHT START. WHEN A IGNITER WAS USED FOR IN-FLIGHT START ENGINE STARTED NORMALLY NO OTHER PROBLEMS OCCURRED DURING FLIGHT AND LANDED AT KTOL WITHOUT INCIDENT. MAINTENANCE PERFORMED FAULT 51 TROUBLE SHOOTING PROCEDURE AND FOUND THE SPECIFIC GRAVITY WAS OFF. IT WAS ADJUSTED, THE FLIGHT IDLE WAS LOW AND WAS ALSO ADJUSTED. PERFORMED A POWER ASSURANCE RUN PER ATI ERH & GMM NO DEFECTS WERE NOTED PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE

Part: ENGINE — FAILED · airframe 86,803 hrs · 35,589 cycles

ON CLIMB-OUT AT 30,000 CLIMB POWER SETTING, NR 4 ENGINE FUEL FLOW STATED FLUX AND ENGINE LOST POWER. ROLLED BACK TO FLIGHT IDLE AND WOULD NOT RESPOND TO THROTTLE MOVEMENT. OTHER ENGINE INDICATIONS WERE NORMAL ENGINE WAS SHUT DOWN AND AIRCRAFT LANDED WITHOUT INCIDENT. AN INVESTIGATION IS ON GOING AND AS SOON AS MORE INFORMATION IS AVAILABLE IT WILL BE PROVIDED. MX FOUND N1 AND N2 ROTORS LOCKED TO EACH OTHER. DEFFERED NR 4 ENGINE, COMPLIED WITH CFM MM 71-00-00 SECURED NI AND N2 ROTOR FOR A NO WINDMILL FERRY. AIRCRAFT WAS FERRIED FROM KIAH TO KTOL WERE MAINTENANCE REMOVED AND REPLACED THE NR 4 ENGINE. ENGINE WAS RUN PER ALL APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE — CHAFED (FIRE LOOP) · airframe 86,760 hrs · 35,571 cycles

ON APPROACH TO KRFD, THE NR 1 SHORT LIGHT AND NR 1 FIRE LIGHT ILLUMINATED INTERMITTENTLY THEN CAME ON STEADY, NR 1 ENGINE SHUTDOWN. DURING ENGINE SHUTDOWN, THE ENGINE DID NOT SHUTDOWN WITH THE FIRE HANDLE. ENGINE DID NOT SHUT DOWN UNTIL FUEL SHUTOFF LEVER WAS PLACED TO OFF. THE CREW LANDED THE AIRCRAFT WITHOUT INCIDENT. THE ENGINE SHORT LIGHT REMAINED ILLUMINATED AND FIRE TEST NR 1 ENGINE INOP. AN INVESTIGATION IS ON GOING. AS SOON AS INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE FOUND CHAFFED AND SHORTED WIRES IN J BOX AFT AREA UNDER T/R. THE WIRE WAS REPAIRED PER ALL APPLICABLE MANUALS, RAN ENGINES PER ALL APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — FAILED (NR 1) · airframe 86,740 hrs · 35,557 cycles

DURING TAKE OFF NR 1 GEN HAD NO FREQ AND LOW VOLT ON ENGINE DISCONNECTED GENERATOR. ON TAKE OFF TOWER WAS TOLD THAT NR 1 ENGINE HAD A TAIL PIPE FIRE. ENGINE SHUT DOWN, AIRCRAFT RETURNED TO BLOCKS AND TRIED TO ROTATE N1 FAN NO ROTATION, TRIED TO MOTOR ENGINE N2 INDICATION BUT NO N1 ROTATION, NO FIRE WARNING OR OTHER INDICATION IN COCKPIT. WORK IN PROGRESS AS ADDITIONAL INFORMATION IS AVAILABLE IT WILL BE PROVIDED.

Part: SEAL — DAMAGED (NLG) · airframe 86,410 hrs · 35,414 cycles

DURING TAKE OFF, ON GEAR RETRACTION, CREW HEARD NOISE AND VIBRATION IN THE NOSE GEAR AREA UNTIL GEAR WAS LOWERED. CREW CYCLED GEAR, RETURNED AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND LT NOSE LANDING GEAR DOOR SEAL PARTIALLY HANGING OUT. THE DAMAGED SEAL WAS REMOVED. THE NGL AND DOORS WERE INSPECTED WITH NO DEFECTS NOTED AND INITIATED CARRY OVER ITEM NR 30084. AIRCRAFT WAS RETURNED TO SERVICE.

Part: LINK — BROKEN (NLG) · airframe 86,413 hrs · 35,416 cycles

DURING TAKE OFF, ON GEAR RETRACTION, CREW HEARD NOISE AND VIBRATION IN NOSE GEAR AREA UNTIL GEAR WAS LOWERED. CREW CYCLED GEAR, RETURNED AND LANDED WITHOUT INCIDENT. AN INSPECTION IS ONGOING. AS SOON AS INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE JACKED AIRCRAFT, RETRACTED NLG AND FOUND NGL DOOR TIGHT AND POPPING OPEN. THE FORWARD NLG DOOR LINK ASSEMBLY WAS REMOVED AND REPLACED IAW ALL APPLICABLE MANUALS.

Part: RIVET — SHEARED (KEELBEAM) · airframe 86,027 hrs · 35,239 cycles

KEELBEAM AREA HAS SEVERAL RIVET HEADS SHEARED OFF BUTTLINE -0-. REMOVED FASTENERS AND DOUBLERS IAW DC-8 SRM 51-1-20. REMOVED CORROSION IAW DC-8 SRM 53-2-0 FOUND OUT OF LIMITS MORE THAN 20 PERCENT ORIGINAL MAT LOSS. FABRICATED DOUBLER REPAIR IAW DC-8 SRM 53-1-0 TREATED AND PRIMED. INSTALLED DOUBLERS IAW DC-8 SRM 51-1-20. (CLOSED)

Part: FINGER DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 86,027 hrs · 35,239 cycles

LEFT UPPER CARGO COMP BETWEEN STA 902 & STA 920 FINGER DOUBLER ABOVE WHEEL WELL CORRODED AND RIVET HEAD SHEARED. CORRODED FINGER DOUBLER REMOVED, CORROSION ON PANEL REMOVED IAW DC-8 SRM 53-2-0. THICKNESS OF PANEL .063 CORRODED SECTION BEYOND LIMITS IAW DC-8 SRM 53-2-0. CORRODED SECTION CUT OUT AND REPAIR DONE IAW DC-8 SRM 53-2-1 FIG. 7 USING .071 2024T3 DOUBLER, .063 FILLER. AREA TREATED AND PRIMED IAW DC-8 SRM 51-1-8. INSTALLED IAW DC-8 SRM 51-1-21. (CLOSED)

Part: SPLICE — CRACKED (FUSELAGE) · airframe 86,027 hrs · 35,239 cycles

RIGHT LONGERON SPICE AT R34 STA 1490 CRACKED. REMOVED LONGERON SPLICE IAW DC-8 SRM 51-1-21. PERFORMED NDT FOUND NO CRACK IAW DC-8 SRM 51-5-2 TREATED AND PRIMED IAW DC-8 SRM. INSTALLED LONGERON SPLICE IAW DC-8 SRM 51-1-21. (CLOSED)

Part: DOUBLER — CRACKED (RUDDER) · airframe 86,027 hrs · 35,239 cycles

RUDDER BOTTOM SIDE FWD AT FILLET ON RT SIDE DOUBLER CRACKED AT RIVET IN NUT PLATE TO END OF DOUBLER. REMOVED SEALANT AND PAINT FROM AREA NO EVIDENCE OF A CRACK IAW DC-8 SRM 51-1-8. TREATED AND PRIMED IAW DC-8 SRM 51-1-8 AND SEALED IAW DC-8 SRM 51-1-16 PG. 1-9. (CLOSED)

Part: STRINGER — CRACKED (LT WING) · airframe 86,027 hrs · 35,239 cycles

LEFT UPPER WING THRU ACCESS HOLE 506A AT STA 408.343 NR 7 UPPER STRINGER FROM REAR SPAR CRACKED AT SPLICE. CRACKED BLENDED OUT IAW DC-8 SRM 57-2-0. (CLOSED)

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 86,027 hrs · 35,239 cycles

RIGHT KEEL BEAM AREA, FORMER JUST I/B OF MLG DOOR ACT MOUNT CRACKED. CRACK WAS STOP DRILLED BUT WENT PAST, CRACK 3 INCHES ABOVE END OF 1ST CRACK GOES FWD AND AFT. REMOVED FORMED WEB IAW DC-8 SRM 51-1-21. FABRICATED WEB MATERIAL USED 7075 .071. INSTALLED WEB IAW DC-8 SRM 51-1-21 AND 51-1-20. (CLOSED)

Part: STRUCTURE — CRACKED (LT WING) · airframe 86,027 hrs · 35,239 cycles

LT WING INSIDE NR 1A FUEL TANK FROM ACCESS PANEL 505B BETWEEN STA. 495.665 AND 508.977 LWR STRINGER NR 53 CRACKED. CUT AND REMOVED STRINGER NR 53 BETWEEN STA 495 AND 508 IAW DC-8 SRM 57-2-2. CUT AND INSTALLED REPLACEMENT STRINGER AND SPICES IAW DC-8 SRM 57-2-2. (CLOSED)

Part: CLIP — CRACKED (LT WING) · airframe 86,027 hrs · 35,239 cycles

LEFT WING UPPER CLIP INSIDE NR 1M ACCESS HOLE 505C AT STA 252-351 BETWEEN REAR SPAR NR 1 STRINGER CLIP CRACKED. REMOVED LT UPPER WING CLIP INSIDE NR 1 MAIN TANK ACCESS HOLE 505C AT STA 252-351 ON STRINGER NR 1. FABRICATED AND INSTALLED REPLACEMENT PART IAW DC-8 SRM 51-1-20 MATERIAL 60-18391/7075T6511. (CLOSED)

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 86,027 hrs · 35,239 cycles

MAIN CARGO FLOOR FORM PALLET POSITION 4 AFT HAS MULTIPULE AREAS OF DISBONDING. REMOVED ALL HARDWARE FROM MAIN CARGO COMPARTMENT FLOOR P4 AFT IAW DC-8 SRM 51-03-00. FABRICATED REPLACEMENT FLOOR BOARDS FROM GIL FAB BOARD 16 EA. FROM 5042B ATI PO 16802. TREATED AND PRIMED IAW DC-8 SRM 51-1-8 AND INSTALLED IAW DC-8 SRM 51-3-0 THE REMAING FLOORBOARDS CONFORM TO ATI REQ. REF PART INFORMATION LETTER 47 DATED FEB. 17, 2004.(CLOSED)

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 86,027 hrs · 35,239 cycles

RIGHT SIDE STA 35 L30 SKIN HAS CORROSION. REMOVED FASTENERS IAW DC-8 SRM 51-1-20, DRILLED NEW DOUBLER PART NUMBER 5649028U AND INSTALLED IAW DC-8 SRM 51-1-21, DRILL AND INSTALLED NEW LONGERON PART NUMBER 3648667 IAW DC-8 SRM 51-1-21. (CLOSED)

Part: SUPPORT — CRACKED (MLG) · airframe 86,027 hrs · 35,239 cycles

LEFT MLG SUPPORT MITTING CRACKED (TRAP) TOP FLANGE. REMOVED LT TRAP FITTING IAW DC-8 MM 20-16-0. FITTED AND DRILLED NEW L/H TRAP IAW ATI DRAWING 5750127 SPOT FACED HOLES AS REQUIRRED. TREATED AND PRIMED IAW DC-8 SRM 51-1-8. TORQUED LT TRAP FITTING IAW SB DC-8 53-061.

Part: SENSOR — DAMAGED (NR 1 EGT) · airframe 85,434 hrs · 34,894 cycles

DURING FLIGHT FROM KBWA TO KTOL THE NR 1 ENGINE EGT ROSE ABNORMALLY. RETARDED THROTTLE, N1.N2, AND FUEL FLOW FOLLOWED. CREW DID A PRECAUTIONARY SHUTDOWN AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 1 ENGINE EGT PIGTAIL IAW ALL APPLICABLE MANUALS. MAINTENANCE RAN THE NR 1 ENGINE IAW ALL APPLICABLE MANUALS AND OPERATIONAL CHECK CONFIRMED CAUSE AND VERIFIED INDICATION PROBLEM ONLY. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE — CHAFED (RUDDER) · airframe 83,941 hrs · 34,768 cycles

ON CLIMB OUT FROM TOL TO ATL CREW REPORTED RUDDER MANUAL REVERSION LIGHT CAME ON. THE CREW REPORTED THAT THE RUDDER WAS POWERED BUT THE LIGHT WAS STAYING ON. CREW RETURNED TO TOL. MAINTENANCE VERIFIED HYDRAULIC PRESSURE AND QUANTITY ARE OKAY. MAINTENANCE FOUND BROKEN WIRE AT MANUEL REVERSION SWITCH, AND REPAIRED WIRE AT REVERSION SWITCH IN ACCORDANCE WITH DOUGLAS DC-8 MAINTENANCE MANUEL. OPERATIONAL CHECK GOOD AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONNECTOR — DIRTY (ENGINE EGT) · airframe 84,870 hrs · 34,537 cycles

AFTER DEPARTURE FROM LRD IN CRUISE EN ROUTE TO DFW, CREW NOTED ABNORMAL RISE IN NR 1 ENGINE EGT. POWER WAS RETARDED ON NR 1 ENGINE AND TEMP RISE STOPPED. DURING DESCENT INTO DFW NR 1 EGT AGAIN BEGAN TO RISE ABNORMALLY, AS A PRECAUTIONARY ACTION NR 1 ENGINE WAS SHUT DOWN. AN UNEVENTFUL LANDING WAS MADE IN DFW. MAINTENANCE PERFORMED INSPECTION OF NR 1 ENGINE EGT SYSTEM AND FOUND SEVERAL CONNECTORS DIRTY. MAINTENANCE CLEANED, SECURED CONNECTORS AND OPERATIONALLY CHECKED EGT SYSTEM. ALL WORK WAS COMPLETED PER APPLICABLE MANUALS. AFTER GOOD OPERATIONAL CHECK THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BELLCRANK — CRACKED (SPOILERS) · airframe 84,852 hrs · 34,527 cycles

AFTER TAKEOFF SPOILER EXTENDED LIGHT ILLUM. ACFT EXHIBITED INAPROPRIATE FLT CHARACTERISTICS. RETURNED FOR UNEVENTFUL LANDING. MX NOTED SPOILER HYD RESERVOIR LOW. MX SERVICED SPOILER RESERVOIR, INSPECTED SPOILER PANELS, CABLES, ACTUATORS AND ALL NORMAL. RETURNED TO SERVICE. UPON SUBSEQUENT TAKEOFF CLIMB SPOILER EXTEND LIGHT AGAIN ILLUMINATED. ACFT EXHIBITED INAPROPRIATE FLT CHARACTERISTICS. ABORTED CLIMB, RETURNED FOR UNEVENTFUL LANDING. MX INSPECTION REVEALED BROKEN INBD & OUTBOARD SPOILER CRANK ASSY ON INBD LT WING GROUND SPOILER. BOTH CRANK ARMS REPLACED, REPLACEMENT OF SPOILER TAKEOFF WARNING SWITCH ALL MX INCLUDING A OVERWEIGHT LANDING INSPECTION PERFORMED PER APPLICABLE ACFT MM.

Part: LINK — BROKEN (LEFT WING) · airframe 84,660 hrs · 34,464 cycles

!DURING LANDING AT ANC FROM SEA, THE FLIGHT CREW HEARD A LOUD NOISE FOLLOWED BY AIRCRAFT ROLL THE FLIGHT CREW CONTINUED WITH AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED A BROKEN FLAP ACTUATOR ATTACH BRACKET ON THE LEFT WING. MAINTENANCE REPLACED THE BRACKET AND PERFORMED SUCESSFUL OPERATIONAL CHECKS IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SEAL — DEFECTIVE (NR 2 ENGINE) · airframe 83,922 hrs · 34,133 cycles

EN ROUTE FROM LRD TO TOL, THE NUMBER TWO ENGINE FLAMED OUT DURING CLIMBOUT FROM LRD. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE WHICH REVEALED THE FUEL FLOW TRANSMITTER LEAKING EXCESSIVE FUEL. MAINTENANCE REPLACED THE SUPPLY LINE GASCO SEAL. MAINTENANCE PERFORMED A SUCCESSFUL LEAK AND OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: CYLINDER — DEFECTIVE (WHEEL WELL) · airframe 83,846 hrs · 34,094 cycles

ENROUTE FROM BFI TO PDX, THE LANDING GEAR UNSAFE LIGHT ILLUMINATED DURING THE LANDING UPLATCH CHECK. THE FIIGHT CREW CYCLED THE LANDING GEAR TO EXTINGUISH THE WARNING INDICATION. THE FLIGHT CONTINUED TO PDX FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE LEFT MAIN GEAR UPLATCH CYLINDER DEFECTIVE. MAINTENANCE REPLACED THE UPLATCH CYLINDER IN ACCORDANCE WITH THE MAINTENANCE MANUAL AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SPAR — CRACKED (RIGHT WING) · airframe 83,172 hrs · 33,844 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT WING LOWER SPAR INBOARD OF THE #4 ENGINE PYLON FORWARD SECTION. FABRICATED AND INSTALLED REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 57-DC8-1837.

Part: FITTING — GOUGED (FLAP) · airframe 83,172 hrs · 33,844 cycles

DURING ROUTINE C-CHECK INSPECTION A GOUGE WAS DETECTED ON THE FLAP SUPPORT FITTING INBOARD INNER EDGE, STATION 405. BLENDED OUT DAMAGED AREA IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 57-DC8-1839.

Part: DOOR — GOUGED (STATION 340) · airframe 83,172 hrs · 33,844 cycles

DURING ROUTINE C-CHECK INSPECTION, A GOUGE WAS DETECTED ON THE C-1 DOOR CUTOUT, AFT SECTION BY THE LIGHT SWITCH, STATION 340. BLENDED OUT DAMAGED AREA. FABRICATED AND INSTALLED NEW REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 52-DC8-1836.

Part: WING — CRACKED (LEADING EDGE) · airframe 83,172 hrs · 33,844 cycles

DURING ROUTINE C-CHECK INSPECTION A CRACK WAS DETECTED ON THE RIGHT WING CENTER LEADING EDGE FORWARD SIDE AT STATION WS485. STOP DRILLED CRACK, FABRICATED AND INSTALLED REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER EDP44-01.

Part: UPLOCK — DIRTY (MLG) · airframe 82,177 hrs · 33,252 cycles

EN ROUTE FROM BRO TO TOL, THE LANDING GEAR UNSAFE WARNING LIGHT ILLUMINATED. THE FLIGHT CREW CYCLED THE LANDING GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR, CLEANED AND LUBRICATED THE GEAR UPLATCH MECHANISMS AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: UPLATCH — DIRTY (NLG)

EN ROUTE FROM LAX TO TOL, THE LANDING GEAR UNSAFE LIGHT ILLUMINATED DURING THE GEAR UPLATCH CHECK. THE FLIGHT CREW CYCLED THE GEAR AND THE WARNING INDICATION EXTINGUISHED. THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR WHICH REVEALED THE NOSE GEAR UPLATCH IN NEED OF LUBRICATION. MAINTENANCE CLEANED AND LUBRICATED THE NOSE UPLATCH MECHANISM. MAINTENANCE PERFORMED A SUCCESSFUL GEAR SWING, AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BALLAST — DEFECTIVE (COCKPIT)

EN ROUTE FROM JFK TO TOL, AN ODOR WAS SENSED IN THE COCKPIT WHEN THE GLAIR SHIELD LIGHTING WAS ILLUMINATED. THE CREW TURNED THE LIGHTS OFF AND THE ODOR SUBSIDED. MAINTENANCE INSPECTED THE LIGHTING SYSTEM, WHICH REVEALED A DEFECTIVE LIGHT BALLAST. MAINTENANCE REPLACED THE BALLAST AND PER A SUCCESSFUL OPERATIONAL TEST. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SENSE LINE — CHAFED (NR 3 ENGINE)

DURING CLIMB-OUT FROM TOL TO DEN, THE NUMBER THREE ENGINE SHORT CIRCUIT LIGHT AND MASTER FIRE LIGHT ILLUMINATED. A FEW SECONDS LATER, THE FIRE WARNING LIGHT AND BELL CAME ON. THE CREW SHUTDOWN ENGINE AND DISCHARGED ONE FIRE AGENT BOTTLE AND THE AIRCRAFT RETURNED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE AND FOUND THE HIGH PRESSURE REGULATOR SENSE LINE CHAFFED THROUGH AT THE CLAMP LETTING HOT BLEED AIR VENT ON TO THE FIRE LOOP. MAINTENANCE REPLACED SENSE LINE. THE SYSTEM CHECK WAS GOOD IN ACCORDANCE WITH THE MAINTENANCE MANUAL, AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PLATING — CRACKED (WS 415-422)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON LEFT WING LOWER LEADING EDGE BETWEEN STATIONS XS415 AND 422. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION AN INTERNAL FILLER AND AN EXTERNAL REPLAIR DOUBLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING C00-8-070-98 AND ENGINEERING ORDER 57-DC8-805.

Part: FITTING — DAMAGED (LT WING)

DURING ROUTINE C-CHECK INSPECTION, FOUND LEFT WING NUMBER FIVE SPOILER HINGE FITTING CRACKED. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED FITTING, FABRICATION AND INSTALLATION NEW HINGE FITTING IN ACCORDANCE WITH DAC DRAWING 3654073 AND ENGINEERING ORDER 27-DC8-799.

Part: FITTING — CRACKED (BS 450)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON LONGERON 35 LEFT SPLICE FITTING AT FUSELAGE STATION 450. REPAIR WAS ACCOMPLISHED BY REMOVAL OF DAMAGED FITTING, FABRICATION AND INSTALLATION A NEW SPLICE FITTING IN ACCORDANCE WITH FAA DER APPROVED DRAWING COO-8-53-059-98 AND ENGINEERING ORDER 53-DC8-796.

Part: SPLICE — CRACKED (BS 1350)

DURING ROUTINE C-CHECK INSPECTION, A CRACK LOCATED ON LONERGON SPLICE FITTING 32 RIGHT AT FUSELAGE STATION 1350. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED FITTING, FABRICATION AND INSTALLATION AN NEW SPLICE FITTING IN ACCORDANCE WITH FAA PER APPROVED DRAWING C00-8-53-061-98 AND ENGINEERING ORDER 53-DC8-797.

Part: FITTING — CRACKED (CARGO DR SLIDE)

DURING ROUTINE C-CHECK INSPECTION, FOUND AFT CARGO COMPARTMENT FORWARD DOOR LEFT FRONT SLIDE SUPPORT FITTNIG TO BE CRACKED. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED FITTING, FABRICATION AND INSTALLATION A NEW SLIDE SUPPORT FITTING IN ACCORDANCE WITH FAA PER APPROVED DRAWING COO-8-52-121-98 AND ENGINEERING ORDER 52-DC8-817.

Part: FRAME — WORN (BS 1160)

DURING ROUTINE C-CHECK INSPECTION, FOUND EXCESS WEAR WAS DETECTED ALONG THE LOWER AFT CARGO COMPARTMENT CUT OUT, ALONG FRAME AT FUSELAGE STATION 1160 BETWEEN LONGERONS 35 LEFT AND 35 RIGHT. REPAIR ACCOMPLISHED BY FABRICATION AND INSTALLATION A REPAIR DOUBLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING COO-8-53-049098 AND ENGINEEERING ORDER 53-DC8-789.

Part: PLATING — CORRODED (BS 650-780)

DURING ROUTE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE EXTERNAL PLATING BETWEEN FUSELAGE STATION 650 TO 780, LONGERONS 32 LEFT AND 32 RIGHT. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION A NEW SECTION OF SKIN, INTERNAL AND EXTERNAL REPAIR DOUBLERS AND A EXTERNAL REPAIR TRIPLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING COO-8-53-057-98 AND ENGINEERING ORDER 53-DC8-793.

Part: SPLICE — CORRODED (BS 440-460)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON LONGERON SPLICE 27 RIGHT BETWEEN FUSELAGE STATIONS 440.0 TO 460.0. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION A NEW LONGERON SPLICE FITTING IN ACCORDANCE WITH FAA PER APPROVED DRAWING COO-8-069-98 AND ENGINEERING ORDER 53-DC8-810.

Part: ANTI FOG SYST — ODOR (COCKPIT)

ON TAKEOFF ATL, A STRONG ELECTRICAL SMELL EMANATED IN THE GALLEY / COCKPIT AREA. THE SMELL DISSIPATED WHEN THE WINDOW ANTI-FOG CIRCUIT BREAKER WAS OPENED. THE FLIGHT CONTINUED WITH AN UNEVENTFUL LANDING AT TOL. MAINTENANCE IDENTIFIED NO DEFECTS WHEN THE SYSTEM WAS TESTED ON THE GROUND AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (FUSELAGE)

DURING UNSCHEDULED MAINTENANCE VISIT, A CORROSION BULGE AND CRACK OF THE EXTERNAL PLATING WAS FOUND AT FUSELAGE STATION 40, BETWEEN LONGERONS 34 AND 35 RIGHT. REPAIR WAS ACCOMPLISHED BY REMOVAL OF THE CORRODED PLATING, FABRICATION AND INSTALLATION OF FINGER DOUBLER, FILLER AND EXTERNAL DOUBLERS IN ACCORDANCE WITH FAA DER APPROVED DRAWING C31-R01, DOUGLAS SRM 51-1-21, 51-1-16, AND ENGINEERING ORDER 53-DC8-608.

Part: CRANK ASSEMBLY — BROKEN (RT SPOILER)

DURING ROUTINE PRFLIGHT INSPECTION AND INVESTIGATION OF A RELATED PROBLEM, MAINTENANCE REPLACED THE SPOILER CRANKS AND RIGGED THE SYSTEM IAW DOUGLAS MM 27-60-0. (M)

Part: FRAME — CRACKED (BS 1300)

DURING ROUTINE C-CHECK INSPECTION, THE FUSELAGE FRAME AT STATION 1300 WAS FOUND TO BE CRACKED. THE CRACK WAS LOCATED BETWEEN LONGERONS 35 LEFT AND 35 RIGHT. THE CRACK WAS REPAIRED IAW THE DOUGLAS STRUCTURAL REPAIR MANUAL 53-2-0, FIGURE 1B, SHEET 3. (M)

Part: FITTING — CRACKED (LT MLG)

DURING ROUTINE C-CHECK INSPECTION, THE LEFT MAIN LANDING GEAR TORQUE TUBE SUPPORT FITTING WAS FOUND CRACKED. THE CRACK WAS STOP DRILLED AND REPAIRED IAW DOUGLAS SERVICE BULLETIN 53-61 R3 CONDITION 2 REQUIREMENTS. (M)

Part: TR COWL — CRACKED (NR 3 ENGINE)

DURING ROUTINE C-CHECK INSPECTION, THE NR 3 THRUST REVERSER OUTBOARD COWLING WAS FOUND CRACKED AT THE FOUR O'CLOCK POSITION. REPAIR WAS ACCOMPLISHED IAW CFMI SHOP MANUAL 78-32-11, REPAIR 30. (M)

Part: CONTROL VALVE — INTERMITTENT (RT ANTI-SKID)

ANTI-SKID FAIL LIGHT ILLUMINATED ON TAKEOFF ROLL DEPARTING ICT TO OKC. GEAR WAS RECYCLED AND THE LIGHT EXTINGUISHED. AIRCRAFT LANDING AT OKC WAS UNEVENTFUL. MX REPLACED THE RIGHT OUTBOARD ANTI-SKID DUAL CONTROL SERVO VALVE. THE SYSTEM OPERATIONALLY CHECKED GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: BRAKES — LOOKED UP (NR 5)

DURING LANDING AT BOS, THE NR 5 BRAKE EXPERIENCED SHINGLED LININGS, CAUSING THE BRAKE TO LOCK UP AND BLOW THE NR 5 MAIN TIRE. THE NR 5 BRAKE AND MAIN TIRE WERE REPLACED, AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE NR 6 MAIN TIRE CHANGE WAS CARRIED OVER TO THE NEXT STATION IAW THE ATI DC-8 MM PAGE 15-10. THE CAUSE OF THE LINING FAILURE TO BE DETERMINED IN THE SHOP. (M)

Part: SWITCH — DIRTY (LT MLG DOOR)

MKE - WHEN LANDING GEAR WAS RETRACTED ON TAKEOFF, DOOR WARNING LIGHT REMAINED ILLUMINATED. THE GEAR WAS CYCLED, BUT THE INDICATION REMAINED THE SAME. UPON ARRIVAL AT TOL, MAINTENANCE INSPECTED THE MLG DOOR AND FOUND THE LANDING GEAR DOOR STRIKER AND SWITCH DIRTY. THE SWITCH AND STRIKER WERE CLEANED AND LUBRICATED, AND OPS CHECKED PER DC-8 MM 56-60-01. ALL WAS NORMAL, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (X)

Part: WARNING LIGHT — MALFUNCTIONED (MLG DOOR)

MCO - ON TAKEOFF, MLG DOOR WARNING LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. THE LANDING GEAR WAS CYCLED, AND THE LIGHT EXTINGUISHED. FOLLOWING LANDING IN MCN, LANDING GEAR WAS OPERATIONALLY CHECKED IAW THE DC-8 MM. THE PROBLEM COULD NOT BE DUPLICATED DURING MULTIPLE CYCLES OF THE LANDING GEAR. THE AIRCRAFT WAS RETURNED TO SERVICE. (X)

Part: SKIN — CRACKED (FS 330)

DURING ROUTINE C-CHECK INSPECTION, THE EXTERNAL SKIN SURROUNDING THE 'A' PIT DOOR WAS FOUND DAMAGED AT THE AFT EDGE OF THE DOOR CUT OUT. THE REPAIR OF THE AREA REMOVED THE DAMAGED AREA, INSTALLED A FILLER, INSTALLED AN INTERNAL AS WELL AS TWO EXTERNAL REPAIR DOUBLERS. THE REPAIR WAS ACCOMPLISHED IAW DRAWING HSE27-53-131, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-125. (X)

Part: SKIN — DAMAGED (CARGO DR CUTOUT)

DURING C-CHECK, THE EDGE OF THE SKIN AT THE 'D' LOWER CARGO COMPARTMENT DOOR CUT OUT WAS FOUND MISSING A SMALL AMOUNT OF MATERIAL DUE TO PHYSICAL DAMAGE. THE DAMAGED AREA WAS CUT OUT, A FILLER INSTALLED, AND AN EXTERNAL DOUBLER AND SPLICE DOUBLER INSTALLED. THE REPAIR WAS ACCOMPLISHED IAW DRAWING HSE-27-129. WHICH WAS FAA DER APPROVED, AND ATI EO 53-DC8-121. (X)

Part: SKIN — CRACKED (FS8)

DURING ROUTINE C-CHECK MAINTENANCE, A CRACK WAS NOTED IN THE EXTERIOR SKIN AT FS 8 RT AND LONGERON 27. THE CRACK ORIGINATED IN THE NOSE LANDING GEAR DOOR CUT-OUT. REPAIR OF THE AFFECTED AREA WAS ACCOMPLISHED BY CUTTING OUT THE DAMAGED AREA, INSTALLATION OF A FILLER, AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER. THE REPAIR WAS ACCOMPLISHED IAW DRAWING HSE27-53-132, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-123. (X)

Part: SKIN — CRACKED (NLG WELL)

DURING ROUTINE C-CHECK INSPECTION, AN EXTERIOR SKIN CRACK WAS NOTED. THE CRACK WAS NOTED AT THE NOSE WHEELWELL AFT LT OUTBOARD CORNER OF THE DOOR CUT OUT. THE CRACK, .0250 INCH IN LENGTH, TERMINATED IN A FASTENER HOLE. AN EXTERNAL REPAIR DOUBLER WAS INSTALLED IAW DRAWING HSE27-53-133, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-122. (X)

Part: BELT FRAME — CORRODED (FS 520)

DURING ROUTINE C-CHECK INSPECTION, LOCALIZED CORROSION REMOVAL WAS BEYOND SRM LIMITS. DAMAGE WAS LIMITED TO LONGERON 34 RT AND 36.5 OF THE BELT FRAME AT FS 520. REPAIR OF THE AFFECTED AREA WAS ACCOMPLISHED BY REMOVAL OF THE CORRODED SECTION AND SPLICING IN A NEW SECTION. THE WORK WAS ACCOMPLISHED IAW DRAWING HSE27-53-130, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-124. (X)

Part: ENGINE — MALFUNCTIONED (NR 4)

AT 25,000 FEET, DURING DESCENT INTO OAK, THE NR 4 ENGINE THROTTLE WAS ADVANCED FROM IDLE TO 2500 PPH FUEL FLOW, AND THE ENGINE FLAMED OUT. THE ENGINE SPONTANEOUSLY RELIT AND MAINTAINED STEADY OPERATION FOR A SHORT PERIOD OF TIME. EGT AND FUEL FLOW THEN BEGAN TO FLUCTUATE. THE ENGINE WAS THEN PRECAUTIONARILY SHUT DOWN. INSPECTION ON THE GROUND IN OAK REVEALED NO ABNORMALITIES. THE MAIN FUEL FILTER WAS PRECAUTIONARILY CHANGED AND THE ENGINE OPERATIONALLY CHECKED IAW THE ATI JRH. ENGINE OPERATION WAS NORMAL. THE MAIN FUEL FILTER WAS NOT FOUND TO BE CONTAMINATED. (Z)