N812AX

Part: SPAR — CORRODED (LT WING) · airframe 60,188 hrs · 26,915 cycles

LEFT WING REAR SPAR AFT FACE HAD CORROSION AT WING ROOT XRS 5. ACCOMPLISHED REPAIR IAW REA D857-53586-MR, REV. IR AT LEFT WING REAR SPAR.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 60,188 hrs · 26,915 cycles

RIGHT ELEVATOR LOWER SKIN AT XS 77.0, HAD "OIL CAN" CONDITION AT HINGE NR 2 SMALL ACCESS HOLE. ACCOMPLISHED REPAIR IAW REA D855-53583-MR, REV. IR AT RIGHT ELEVATOR.

Part: SKIN — DAMAGED (BS 160-180) · airframe 60,188 hrs · 26,915 cycles

UPPER CARGO MAIN CARGO DOOR FUSELAGE CUT OUT PLATING DAMAGE, SEVERAL AREAS MISSING STA. 160 - 180, LONGERON 6 LEFT. ACCOMPLISHED REPAIR AT DOOR CUT OUT IAW REA D853-53588-MR, REV. IR.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

LEFT INBOARD HORIZONTAL STABILIZER LEADING EDGE SECTION OUTBOARD UPPER SURFACE AT XSTA 177, HAD INTERGRANULAR CORROSION AT SCREW HOLE AREA. INSTALLED REPAIR AT LEFT INBOARD STABILIZER LEADING EDGE SECTION OUTBOARD UPPER SURFACE IAW REA D855-53575-MR, REV. B.

Part: SKIN — CRACKED (WS 304) · airframe 60,188 hrs · 26,915 cycles

CRACK IN RIGHT WING LEADING EDGE PANEL ASSEMBLY INNER (WAFFLED) SKIN 8" FROM INBOARD EDGE, STA. XFS 304. STOP DRILLED CRACK AND INSTALLED REPAIR IAW REA D857-53580, REV. IR.

Part: SKIN — CRACKED (RT WING LE) · airframe 60,188 hrs · 26,915 cycles

RIGHT WING LEADING EDGE PANEL ASSEMBLY INNER (WAFFLED) SKIN HAD 3 EACH CRACKS AT XFS 410 - 423. REPAIRED CRACKS IAW REA D857-53581, REV IR.

Part: SKIN — CRACKED (RT WING) · airframe 60,188 hrs · 26,915 cycles

RIGHT WING LEADING EDGE PANEL ASSEMBLY INNER (WAFFLED) SKIN HAD 3 EACH CRACKS AT APPROX. XFS 410 - 423. REPAIRED CRACKS IAW REA D857-53581, REV. IR.

Part: SKIN — CRACKED (RT WING LE) · airframe 60,188 hrs · 26,915 cycles

CRACK IN RIGHT WING LEADING EDGE PANEL ASSEMBLY INNER (WAFFLED) SKIN 8 INCHES FROM INBOARD EDGE STA XFS 304. STOP DRILLED CRACK AND INSTALLED REPAIR IAW REA D857-53580, REV IR.

Part: LONGERON — CORRODED (BS 1220-1240 S27) · airframe 60,188 hrs · 26,915 cycles

EXFOLIATION CORROSION IN LONGERON 27 LEFT, STA. 1220 - 1240. ACCOMPLISHED REPAIR IAW REA D853-53585-MR, REV. IR, ON LONGERON 27 LEFT, STA. 1220 - 1240.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

LEFT HORIZONTAL STABILIZER OUTBOARD LEADING EDGE UPPER STRUCTURE HAD INTERGRANULAR CORROSION ON AFT TRAILING EDGE FROM XFS 178 - 341. ACCOMPLISHED REPAIR OF LEFT HORIZONTAL STABILIZER LEADING EDGE IAW REA D855-53574-MR, REV. A.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

RIGHT HORIZONTAL STABILIZER LEADING EDGE OUTBOARD SECTION UPPER TRAILING EDGE HAD INTERGRANULAR CORROSION AT 3 LOCATIONS: XFS 260, 316 AND 332. CUT OUT DAMAGED AREA AND INSTALLED REPAIR IAW REA D855-53089-MR, REV B.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

RIGHT HORIZONATL STABILIZER LEADING EDGE OUTBOARD SECTION UPPER TRAILING EDGE INTERGRANULAR CORROSION AT 3 LOCATIONS: XFS260, 316 & 332. CUT OUT DAMAGED AREA AND INSTALLED REPAIR IAW REA D855-53089-MR, REV. B.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 60,188 hrs · 26,915 cycles

THREE CRACKS ALONG THE UPPER EDGE OF CUTOUT, IN THE INNER SKIN OF THE AFT CARGO DOOR. TRIMMED OUT CRACKED IAW REA D852-53568.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

RIGHT HORIZONTAL STABILIZER OUTBOARD LEADING EDGE SECTION AT INBOARD UPPER LEADING EDGE HAD INTERGRANULAR CORROSION AT HILOC HOLE. INSTALLED REPAIR IAW REA D855-53090-MR, REV. IR AT RIGHT STABILIZER LEADING EDGE AT XSTA 178.75.

Part: SKIN — CRACKED (AFT CARGO DOOR) · airframe 60,188 hrs · 26,915 cycles

THREE CRACKS ALONG THE UPPER EDGE OF CUT OUT, IN THE INNER SKIN OF THE AFT CARGO DOOR. TRIMMED OUT CRACKS IAW REA D852-53568.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

RIGHT HORIZONTAL STABILIZER INBOARD LEADING EDGE SECTION AT UPPER TRAILING EDGE MID AREA AT XSTA 140, HAD INTERGRANULAR CORROSION AROUND SCREW HOLES. INSTALLED REPAIR IAW REA D855-53086-MR, REV. A, ON RIGHT HORIZONTAL STABILIZER INBOARD LEADING EDGE SECTION AT UPPER TRAILING EDGE MID AREA SCREW HOLES.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

RIGHT HORIZONTAL STABILIZER LEADING EDGE OUTBOARD UPPER SKIN HAD INTERGRANULAR CORROSION AT XFS 178.750. CUT OUT DAMAGED AREA AND INSTALLED REPAIR IAW REA D855-53088-MR, REV A.

Part: SKIN PANEL — CORRODED (665-700) · airframe 60,188 hrs · 26,915 cycles

PERMANENT REPAIR OF CORROSION ON LONGERON L36 (KEEL BEAM) PER COI 50571 AND SKIN PANELS AT STA. 670 AND 683 PER COI 50570 AND COI 50572. REPAIR ACCOMPLISHED IAW REA D853-53093 - MR, REV. A, ON KEEL BEAM AND SKIN PANELS AT STA. 665 - 700.

Part: SKIN — CORRODED (LEFT WING) · airframe 60,188 hrs · 26,915 cycles

LEFT WING LEADING EDGE UPPER AFT EDGE OF OUTER MOST LEADING EDGE ASSEMBLY AT XFS 291 - 422 LEFT, HAD EXFOLIATION AROUND SCREWS. ACCOMPLISHED REPAIR IAW REA D857-53573-MR, REV. A, AT LEFT WING OUTER MOST LEADING EDGE ASSEMBLY.

Part: LONGERON — DAMAGED (BS 857-980) · airframe 60,188 hrs · 26,915 cycles

REMOVE AND REPLACE EXISTING DISCREPANT LONGERON 24 RIGHT IN RIGHT WHEEL WELL, STA. 857 - 980, DUE TO PREVIOUS DAMAGE WITH AN INTERIM REPAIR IAW REA D853-52752-MR. REMOVED AND REPLACED LONGERON 24 RIGHT IN RIGHT WHEEL WELL IAW REA D853-53079-MR, REV. A.

Part: LONGERON — CORRODED (BS 520) · corrosion level 2 · airframe 60,188 hrs · 26,915 cycles

FORWARD CARGO COMPARTMENT LNOGERON 31 LEFT HAD CORROSION AT STA. 520. ACCOMPLISHED REPAIR IAW REA D853-53595-MR, REV. IR, ON LONGERON 31 LEFT.

Part: LONGERON — CORRODED (BS 560-600 S31L) · corrosion level 2 · airframe 60,188 hrs · 26,915 cycles

CORROSION AT LONGERON 31 LEFT, F.S. 560 - 600. ACCOMPLISHED REPAIR OF LONGERON 31 LEFT, F.S. 560 - 600 IAW REA D853-53592-MR, REV. IR.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,188 hrs · 26,915 cycles

RIGHT HORIZONTAL STABILIZER LEADING EDGE OUTBOARD UPPER SKIN HAD INTERGRANULAR CORROSION AT XFS 178.750. CUT OUT DAMAGED AREA AND INSTALLED REPAIR IAW REA D855-53088-MR, REV. A.

Part: LONGERON — CORRODED (BS 857-980) · airframe 60,188 hrs · 26,915 cycles

SEVERAL AREAS OF CORROSION ON LONGERON 24 LEFT, F.S. 857 - 980 IN LEFT WHEEL WELL. REPLACED LONGERON 24 LEFT, F.S. 857 - 980 IN LEFT WHEEL WELL IAW REA D853-53080-MR, REV.A.

Part: SKIN — CORRODED (BS 1600 S27R) · airframe 60,188 hrs · 26,915 cycles

RIGHT FUSELAGE SKIN HAD BULGE AND RIVETS POPPED OFF AT STA 1600, LONGERON 27 RIGHT. EXISTING REPAIR REMOVED, AND SKIN AND INNER DOUBLER CUT TO REMOVE ALL CORROSION. COMPLETED REPAIR IAW REA D853-53635-MR.

Part: SKIN — CORRODED (BS 1600) · airframe 60,188 hrs · 26,915 cycles

RIGHT FUSELAGE SKIN HAD BULGE AND RIVETS POPPED OFF AT STA. 1600, LONGERON 27 RIGHT. EXISTING REPAIR REMOVED AND SKIN AND INNER DOUBLER CUT TO REMOVE ALL CORROSION. COMPLETED REPAIR IAW REA D853-53635-MR.

Part: FUEL CONTROL — DEFECTIVE (NR 3 ENGINE) · airframe 60,148 hrs · 26,879 cycles

NR 3 ENGINE FAILED TO ACCELERATE IN-FLIGHT. EET 20 DEGREES N2 48%, FF AT 1000 LBS. ATTEMPTED RE-LIGHT TO NO AVAIL. SHUT DOWN NR 3 ENGINE AT 0518Z, 4 PSI INDICATED ON OIL PRESSURE. REMOVED AND REPLACED FUEL CONTROL UNIT ON NR 3 ENGINE AND TRIMMED NR 3 ENGINE IAW DC8 AMM 73-20-01-2-0003 AND 71-00. LEAK CHECKED GOOD.

Part: FITTING — CRACKED (BS 879) · airframe 60,112 hrs · 26,844 cycles

FITTING AT LONGERON 24, FS 879, CRACKED. REPAIRED FITTING IAW REA D853-53104.

Part: SKIN — CORRODED (BS 60) · airframe 60,006 hrs · 26,782 cycles

CORROSION FOUND ON THE WING TO FUSELAGE SKIN AT STATION 670 AND LONGERON 36. REA D853-52756MR PERFORMS AN INTERIM REPAIR SIMILAR TO SRM 53-2-1, FIG. 7, AS OPERATIONAL SCHEDULING DID NOT ALLOW FOR A PERMANENT REPAIR.

Part: LONGERON — CORRODED (BS 879) · airframe 60,006 hrs · 26,782 cycles

CORROSION FOUND ON LONGERON 24 RIGHT AT STATION 879. REA D853-52752MR PERFORMS AN INTERIM REPAIR TO THE LONGERON.

Part: WINDOW — LACK OF LUBE (COCKPIT) · airframe 59,989 hrs · 26,773 cycles

CAPTAIN'S CLEARVIEW WINDOW WOULD NOT OPEN. LUBRICATED CAPTAIN'S CLEARVIEW WINDOW ASSEMBLY IAW DC-8 MM 56-00-00. OPS CHECKED GOOD.

Part: SKIN — CORRODED (FUSELAGE) · airframe 59,558 hrs · 26,518 cycles

FUSELAGE SKIN COMMON TO THE FACTORY ANTENNA DOUBLER, CORRODED. FABRICATED SKIN AND DOUBLER FOR ANTENNA AND INSTALLED IAW REA D853-51782 ON WO NR 600221026.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 59,057 hrs · 26,265 cycles

EMERGENCY EXIT LIGHTS ARMED AMBER LIGHT INOPERTATIVE. RELAMPED, OPS CHECKED GOOD IAW DC-8 MM 33-50-02.

Part: FITTING — CRACKED (INTERCOSTAL) · airframe 58,840 hrs · 26,154 cycles

INTERCOSTAL END FITTING AT STA 1140, LONGERON 35 LEFT WAS CRACKED. REPLACED END FITTING IAW DC-9 SRM 51-1-20D.

Part: FITTING — CRACKED (INTERCOSTAL) · airframe 58,840 hrs · 26,154 cycles

INTERCOSTAL END FITTING AT STA 1160, LONGERON 35 RIGHT WAS CRACKED. END FITTING WAS REPLACED IAW DC-8 SRM 51-1-20D.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 58,840 hrs · 26,154 cycles

AFT FUSELAGE SKIN FORWARD OF NR 3 CARGO DOOR HAD BULGED REPAIR. REPAIRED AREA IAW REA D853-50277MR.

Part: LONGERON — CRACKED · airframe 58,799 hrs · 26,126 cycles

LT MAIN LANDING GEAR WHEEL WELL LONGERON 24 CRACKED ON LOWER FLANGE AT BOTTLE BOLT CAVITY. REPAIRED AREA IAW REA D853-49163MR.

Part: FITTING — CRACKED (FUSELAGE) · airframe 58,799 hrs · 26,126 cycles

FITTING CRACKED AT MOST FORWARD FASTENER HOLES. FABRICATED REPAIR PARTS IAW REA D853-49975MR. ALODINED AND PRIMED IAW SRM 51-1-8. INSTALLED IAW SRM 51-1-20B.

Part: FUEL CONTROL — DEFECTIVE (NR 4 ENGINE) · airframe 58,500 hrs · 25,955 cycles

NR 4 ENGINE, AFTER SETTING POWER FOR CRUISE, NR 4 ENGINE ROLLED BACK .15 EPR. EGT, FUEL FLOW N1 AND N2 ALL DROPPED. THROTTLE DID NOT MOVE. REPLACED NR 4 ENGINE FUEL CONTROL UNIT IAW 73-20-01. REPLACED NR 4 LOW PRESSURE FUEL FILTER. PERFORMED LEAK CHECK OF NR 4 ENGINE LOW PRESSURE FUEL FILTER ON ENGINE RUN. LEAK CHECKED GOOD.

Part: BLEED VALVE — DEFECTIVE (NR 2 ENGINE) · airframe 58,500 hrs · 25,955 cycles

AFTER TAKEOFF 2000 FEET, HEARD SHARP LOUD BANG/POP. NR 2 EPR DROPPED .18 AND BACK. FELT SLIGHT LEFT YAW. REPLACED NR 2 ENGINE COMPRESSOR BLEED VALVE AND CONTROL IAW 75-30-03-2-0002. NR 2 ENGINE LOW PRESSURE BLEED VALVE CHECKED GOOD IAW DC8 AMM 71-00-00. REPLACED LOW PRESSURE FUEL FILTER. LEAK CHECKED GOOD ON ENGINE RUN.

Part: LINK — BROKEN (GROUND SPOILER) · airframe 57,459 hrs · 25,285 cycles

DURING SERVICE CHECK, FOUND THE NR 5 INBOARD GROUND SPOILER WITH 2 EACH CENTER CRANK ASSEMBLIES AND INBOARD SPOILER OVERCENTER LINK BROKEN. REMOVED THE LEFT WING NR 5 SPOILER PANEL AND REPLACED BOTH SPOILER CRANK ASSEMBLIES IAW AMM. OPS CHECKED GOOD. INSTALLED SPOILER PANEL NR5. OPS CHECKED GOOD.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

MAIN CABIN FRAME AT STA 240 RIGHT SIDE WAS CRACKED AT FLOOR LEVEL. INSTALLED DOUBLER REPAIR AT STA 240 MAIN CABIN RIGHT SIDE IAW DRAWING K04888 AND DC-8 SRM.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

FUSELAGE RIGHT AFT DOOR X-RAY SHOWED CRACK AT AFT UPPER CORNER OF DOOR CUTOUT. INSTALLED REPAIR DOUBLER AT RIGHT AFT DOOR UPPER CORNER IAW DC-8 DRAWING SRO 8530024 AND DC-8 SRM 53-2-0.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

MAIN CABIN FRAME AT STA 220 RIGHT SIDE WAS CRACKED AT FLOOR LEVEL. INSTALLED DOUBLER REPAIR AT STA 220 RIGHT AT FLOOR LEVEL IAW DRAWING K04888 AND DC-8 SRM.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

A/C EXHAUST DUCT SKIN WAS CRACKED AT THE FORWARD UPPER CORNER AT FS 50, STRINGER 28 LEFT. CUT OUT DAMAGE AND INSTALLED REPAIR IAW DRAWING SR08530020 AND DC-8 SRM.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

CRACK AT FORWARD ENTRY DOOR CUTOUT AFT LOWER CORNER. CUT OUT DAMAGE AND INSTALLED REPAIR DOUBLER AND TRIPLER IAW DC-8 SRM 53-2-0.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 57,348 hrs · 25,212 cycles

CORROSION FOUND ON NOSE LANDING GEAR WELL HORIZONTAL PRESSURE PANEL, BETWEEN FS 12 TO FS 27. ALSO FOUND CORROSION ON FLOORBEAM LOWER FLANGE AT FS 12, BUTT LINE '0'. REPAIRED AREA IAW REA 853-41975MR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

FUSELAGE LEFT AFT DOOR X-RAY SHOWED CRACK AT THE LOWER FORWARD CORNER OF DOOR CUTOUT. CUTOUT CRACKED 3.8125 INCHES SECTION AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 51-1-21 AND 51-1-20.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

EXISTING REPAIR AT PASSENGER DOOR FORWARD UPPER CORNER DID NOT CONFORM TO DRAWING ES00863. REMOVED AND REPLACED REPAIR IAW DC-8 SRM 53-2-0.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 57,348 hrs · 25,212 cycles

FUSELAGE LONGERON 11 RIGHT HAD A 1 INCH CRACK AT FS 1660. REPAIRED LONGERON 11 IAW REA D853-41973MR.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 57,331 hrs · 25,204 cycles

DURING AIRCRAFT LINE OPERATIONS AT ILN, MAINTENANCE DISCOVERED LOWER INNER SKIN CORROSION AT FS STA 380 TO STA 395, BETWEEN LONGERONS 35 LEFT TO 35 RIGHT. REMOVED CORROSION FROM SKIN AND INTERNAL DOUBLER. THE SKIN AND INTERNAL DOUBLER WERE CUT OUT. FABRICATED DOUBLER, TRIPLER, AND FILLER. INSTALLED AND IDENTIFIED IAW REA D853-45139-MR.

Part: PUMP — SHEARED (# 2) · airframe 56,976 hrs · 24,990 cycles

#2 engine driven fuel pump was inop. Found spline shaft sheared on #2 engine driven fuel pump. Replaced pump IAW 73-10-2. Ops and leak checked good IAW 71-00.

Part: FLUID — LOW (HYDRAULIC SYS) · airframe 56,292 hrs · 24,572 cycles

GEAR WOULD NOT RETRACT AFTER TAKEOFF. HYDRAULIC PRESSURE WAS 0 PSI. HYDRAULIC QUANTITY WAS NORMAL. ACCOMPLISHED LOSS OF HYDRAULICS CHECKLIST. SYSTEM OPERATED NORMALLY ON AUX PUMP. FOUND AIRCRAFT WAS BELOW STANDPIPE LEVEL. SUSPECT AIRCRAFT HYDRAULIC QUANTITY WAS SERVICED INCORRECTLY AFTER HYDRAULIC TEST STAND REMOVED. NO LEAKS NOTED ON AIRCRAFT. REPLACED BOTH ENGINE DRIVEN HYDRAULIC PUMPS IAW DC-8 AMM 29-10-12-2 AND BOTH CASE DRAIN FILTERS IAW 29-10-15-2, DUE TO LACK OF HYDRAULIC FLUID. LEAK CHECKED GOOD. SERVICED HYDRAULIC QUANTITY IAW DC-8 AMM.

Part: LOCK — DEFECTIVE (COCKPIT DOOR) · airframe 56,261 hrs · 24,553 cycles

THE COCKPIT DOOR WOULD NOT OPEN. MAINTENANCE REPLACED THE DOOR LOCK IAW DC-8 MM 52-51-01. OPERATIONAL CHECKS WERE COMPLETED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LOCK — LACK OF LUBE (COCKPIT DOOR) · airframe 56,256 hrs · 24,551 cycles

THE COCKPIT DOOR STUCK INTERMITTENTLY AND WOULD NOT OPEN. MAINTENANCE INSPECTED AND LUBRICATED THE LOCK. OPERATIONAL CHECKS WERE COMPLETED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — SHORTED (CABIN) · airframe 56,095 hrs · 24,456 cycles

EMERGENCY BATTERY PACK WAS SHORTED INTERNALLY. REPLACED EMERGENCY BATTERY PACK. OPS CHECKED GOOD IAW DC-8 MM.

Part: SKIN — GOUGED (LEFT WING) · airframe 55,563 hrs · 24,188 cycles

LEFT WING LEADING EDGE STAB WING ABOVE #2 ENGINE, OUTBOARD END OF VANE HAD SEVERAL HOLES WITH VERY DEEP GOUGES CAUSED BY DIMPLE WASHERS, APPROXIMATELY W/STA. 225.0 REMOVED SEAL ASSEMBLY, FABRICATED REPAIR DOUBLER IAW REA D857-39765MR. ALODINED AND PRIMED IAW DC-8 SRM 51-1-8. INSTALLED REPAIR DOUBLER IAW REA D857-39765MR. INSTALLED SEAL ASSEMBLY IAW DC-8 SRM 51-1-8.

Part: FRAME — CRACKED (FUSELAGE) · airframe 55,563 hrs · 24,188 cycles

FORWARD LOWER CARGO, STATION 420, CRACK ON FRAME AT LONGERON 31 LEFT.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,144 hrs · 22,516 cycles

EXTERNAL FUSELAGE AT STATION 110 L36 WAS FOUND TO HAVE BULGING SKIN NEAR FLAPPER VALVE. MAINTENANCE INSPECTED AND REPAIRED THE AREA IAW ABX REA D853-39745-MR AND DC-8 SRM 51-1-21.

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,563 hrs · 24,188 cycles

EXTERIOR FUSELAGE, BULGING SKIN NEAR FLAPPER AT STATION 110, LONGERON 36. REMOVED FLAPPER VALVE IAW REA D853-39745MR. FABBED FILLER AND FINGER DOUBLER IAW REA D853-39745MR. ALODINED AND PRIMED IAW DC-8 SRM 51-1-8. INSTALLED FILLER, FINGER DOUBLER AND FLAPPER VALVE IAW DC-8 SRM 51-1-21, 51-1-20D, AND REA D853-39745MR.

Part: BRACKET — BROKEN (RT MLG DOOR) · airframe 55,543 hrs · 24,178 cycles

RIGHT MAIN LANDING GEAR LOWER FOLLOW UP DOOR, AFT LOWER ATTACH BRACKET WAS FOUND BROKEN AT GEAR ATTACH POINT. MAINTENANCE INSPECTED AND REPLACED THE ATTACH BRACKET IAW DC-8 MM.

Part: SPRING — BROKEN (FO SEAT) · airframe 55,314 hrs · 24,061 cycles

FIRST OFFICER''S SEAT FORE/AFT SEAT ADJUSTMENT WAS NOT HOLDING SEAT IN POSITION PROPERLY. SEAT MOVED THREE TIMES DURING FLIGHT. FOUND RETURN SPRING BROKEN. REPLACED SPRING. CHECKED RIGGING OF SEAT. OPS CHECKED GOOD IAW DC8 MM.

Part: AIR DIST — ODOR (COCKPIT)

DURING CRUISE, NOTICED LIGHT SMELL COMING FROM BEHIND FLIGHT ENGINEER'S PANEL. SMELLED LIKE BURNING PLASTIC. MAINTENANCE COULD NOT DUPLICATE. COULD NOT SMELL ANY UNUSUAL ODORS FROM FLIGHT ENGINEER'S PANEL.

Part: BOSS — CORRODED (RT MLG)

LEFT AND RIGHT MAIN GEAR RETRACT PIN BOSSES WERE CORRODED. REPAIRED IAW ABX REA B832-28106MR.

Part: SKIN — CORRODED (BS 1094)

LOWER EDGE OF LEFT CENTER SERVICE DOOR CORRODED FROM STATION 1094 INTO STATION 1109. REPAIRED IAW ABX REA B831-28121MR.

Part: FITTING — CORRODED (CARGO DOOR)

C-3 DOOR LOWER CORNER FITTING CORRODED. REPAIRED IAW ABX REA D852-28107MR.

Part: ENGINE — FAILED (NR 1)

ON APPROACH TO ILN, NR 1 ENGINE OIL PRESSURE DROPPED TO 28 PSI. SECURED NR 1 ENGINE. FOUND OIL FILTER CONTAMINATED WITH METAL. REPLACED NR 1 ENGINE.

Part: LOOP — DEFECTIVE (NR 4 ENGINE)

FIRE WARNING ON NR 4 ENGINE. SECURED ENGINE AND DISCHARGED FIRE BOTTLE. MASTER FIRE WARNING CAME ON MOMENTARILY WITH NO LIGHT IN ANY LEVER OR ON FLIGHT ENGINEER PANEL. TESTED EACH ENGINE FIRE WARNING SYSTEM, NR 4 ENGINE WOULD NOT TEST. MASTER WARNING FLASHED ON AND OFF. AFTER ENGINE WAS SECURED FIRE WARNING TESTED OK. FOUND BROKEN PIN IN NR 4 LOWER LOOP CONNECTOR. REPLACED LOWER LOOP. FIRE WARNING TESTED GOOD.

Part: PROXIMITY BOX — DEFECTIVE (LT MLG)

DURING APPROACH LEFT LANDING GEAR INDICATION LIGHT WOULD NOT ILLUMINATE AFTER GEAR RETRACTION. RECYCLED GEAR, LIGHT CAME ON AFTER 10 MINUTES OF FLIGHT. REPLACED LEFT MAIN LANDING GEAR PROXIMITY BOX. ACCOMPLISHED GEAR SWING IAW DC8 MM 32-60-00. OPS CHECKED GOOD.

Part: CONTROL BOX — DEFECTIVE (NLG WW)

LANDING GEAR UNSAFE LIGHT WAS ON WITH NOSE LANDING GEAR UNLATCHED INDICATION. RECYCLED GEAR, NO HELP. REPLACED PROXIMITY CONTROL BOX AND NOSE LANDING GEAR UPLIMIT SWITCH IAW DC8 MM 32-60-0. OPS CHECKED GOOD.

Part: FIRE LOOP — DEFECTIVE (NR 4 ENGINE)

NR 4 ENGINE FIRE WARNING BELL SOUNDED INTERMITTENTLY. ALL FOUR ENGINES WERE TESTED. NR 4 WOULD NOT TEST. NR 4 ENGINE WAS SECURED. CSD WAS DISCONNECTED AND NR 4 FIRE BOTTLE WAS DISCHARGED. NR 4 ENGINE FIRE LOOP ELEMENT WAS FOUND TO BE DEFECTIVE. REPLACED FIRE LOOP ELEMENT IAW DC8 MM 26-10-1.

Part: CYLINDER — DEFECTIVE (LT MLG)

DURING CLIMBOUT, RED LANDING GEAR UNSAFE LIGHT ILLUMINATED. LEFT MAIN LANDING GEAR INDICATED UNLATCHED. RECYCLED LANDING GEAR, NO HELP. LANDING WAS UNEVENTFUL. REPLACED LEFT MAIN LANDING GEAR UPLATCH MECHANISM CYLINDER IAW DC8 MM 32-31-3, OPS CHECKED GOOD.

Part: WIRE — OUT OF POSITION (LANDING GEAR)

DURING GEAR RETRACTION, THE LANDING GEAR LEVER WAS BINDING AND COULD NOT BE MOVED TO THE LATCH-CHECK OR UP POSITION. RECYCLED GEAR HANDLE TO DOWN POSITION. MOVED HANDLE TO UP POSITION, BINDING REMAINED BUT GEAR INDICATED UP. FOUND WIRING JAMMED BETWEEN LANDING GEAR CONTROL PULLEY AND CONTROL CABLES. REMOVED AND REPAIRED WIRING. PERFORMED OPS CHECK OF LANDING GEAR IAW WITH DC8 MM 32-31-1 AND OPS CHECKED GOOD.

Part: SWITCH — OUT OF ADJUST (LT MLG)

DURING UPLATCH CHECK, RED GEAR UNSAFE LIGHT ILLUMINATED ALONG WITH LEFT GEAR NOT LATCHED LIGHT. RECYCLED GEAR WITH NO EFFECT. ADJUSTED PROXIMITY SWITCH ON LEFT MAIN LANDING GEAR. LANDING GEAR OPS CHECKED GOOD IAW DC8 MM 32-31-4.

Part: SWITCH — DIRTY (LT MLG)

LANDING GEAR UNSAFE LIGHT ILLUMINATED WITH GEAR LEVER IN UP POSITION. ALL GEAR INDICATED UP. CYCLED GEAR SEVERAL TIMES WITH NO CHANGE. FOUND GREASE ON PROXIMITY SWITCH. CLEANED SWITCH, PERFORMED GEAR OPS CHECK.

Part: SWITCH — FAILED (LT MLG)

RED MAIN LANDING GEAR UNSAFE LIGHT STAYED ON AFTER GEAR RETRACTION. RECYCLED GEAR TWICE WITH NO EFFECT, LIGHTS STAYED ON. LIGHT EXTINGUISHED AFTER 3 MINUTES. REPLACED LEFT MAIN LANDING GEAR PROXIMITY SWITCH, SYSTEM OPS CHECKED GOOD IAW DC8 MM 32-60-0.

Part: LINE — LEAKING (RT MLG)

HYDRAULIC FLUID LOSS OCCURRED ON CLIMBOUT. EMERGENCY CHECKLIST WAS ACCOMPLISHED. SYSTEM WAS ISOLATED, HYDRAULIC QUANTITY STABILIZED ABOVE STANDPIPE. WHEN AUX PUMP WAS TURNED ON DURING DESCENT, LOSS OF FLUID RESUMED UNTIL SELECTING LANDING GEAR DOWN AND FLAP POSITION. FOUND HYDRAULIC LINE LEAKING FROM AFT MANIFOLD TO FORWARD MANIFOLD ON RIGHT MAIN LANDING GEAR BOGIE TRIM CYLINDER. INSTALLED NEW LINE IAW DC8 SRM.

Part: SLOT CONTL VALVE — LEAKING (RT WHEEL WELL)

AFTER APPROXIMATELY TWO HOURS OF FLIGHT, EXPERIENCED HYDRAULIC QUANTITY AND PRESSURE LOSS ACCOMPANIED BY AILERON AND RUDDER CONTROL MANUAL LIGHTS. COMPLIED WITH ABNORMAL PROCEDURES. AFTER UNEVENTFUL LANDING AND AIRCRAFT WAS TOWED FROM RUNWAY. FOUND SLOT CONTROL VALVE LEAKING. REPLACED SLOT CONTROL VALVE IAW DC8 MM 27-80-4. PERFORMED INSPECTION / CHECK OF SLOT SYSTEM IAW DC8 MM 27-80-0, NO DEFECTS NOTED. ALSO, REPLACED BOTH ENGINE DRIVEN PUMPS AS PRECAUTIONARY. SERVICED, BLED AND LEAK CHECKED SYSTEM.

Part: DIFFUSER CASE — CRACKED (NR 1 ENGINE)

NR 1 ENGINE LOW OIL PRESSURE LIGHT CAME ON IN CLIMBOUT. OIL TEMPERATURE 153 DEGREES, CSD TEMPERATURE 120 DEGREES. LIGHT WOULD NOT GO OUT WITH ENGINE AT IDLE. SHUT DOWN NR 1 ENGINE AT 2140. LUBED FUEL PUMP AT 0340. OIL PRESSURE 26 PSI IN FLIGHT AFTER SHUTDOWN. DID NOT GO BELOW 5 PSI UNTIL AFTER LANDING. NOTE: OIL PRESSURE AT SHUT DOWN 55 PSI. PRELIMINARY FINDINGS FOUND DIFFUSER CASE CRACKED. REMOVED AND REPLACED NR 1 ENGINE IAW ABX JOB CARD 7001.

Part: OXY FLEX LINE — RUPTURED (COCKPIT)

OBSERVER'S FLEXIBLE OXYGEN LINE TO THE REGULATOR RUPTURED INFLIGHT. CREW INITIATED DESCENT TO 21,000 FEET. REPLACED OBSERVER'S FLEXIBLE OXYGEN LINE TO THE REGULATOR.

Part: FIREWALL — CRACKED (NR 1 PYLON)

DURING C-CHECK INSPECTION, DISCOVERED NR 1 PYLON LOWER FORWARD FIREWALL CRACKED. REPAIRED NR 1 PYLON LOWER SPAR WEB ON FORWARD FIREWALL THAT WAS CRACKED IAW ABX REA D854-13627MR.

Part: LONGERON — CORRODED (BS 1200)

DURING C-CHECK INSPECTION, DISCOVERED AFT CROSS-SLIDE DOOR AREA AT STATION 1200, LONGERON 31R WAS CORRODED. REPAIRED C-3 DOOR TORQUE BOX WEB AT AFT CROSS-SLIDE DOOR THAT WAS CORRODED AT STATION 1200, LONGERON 31R.

Part: EEL CIRCUIT BKR — DEFECTIVE (CABIN)

THE EMERGENCY LIGHT ILLUMINATED WITHOUT ANY LOSS OF AIRCRAFT ELECTRICAL POWER. FOUND A DEFECTIVE EMERGENCY LIGHT CONTROL CIRCUIT BREAKER. REMOVED AND REPLACED CIRCUIT BREAKER. EMERGENCY EXIT LIGHT CONTROL SYSTEM OPS CHECKS GOOD, IAW DC-8 MM CHAPTER 33.

Part: UPLATCH ASSY — LACK OF LUBE (LT MLG)

UPON CLIMBOUT OF SJC, UNSAFE GEAR LIGHT ILLUMINATED DURING UPLATCH CHECK. LEFT LANDING GEAR NOT LATCHED WAS INDICATED. RECYCLED GEAR 3 TIMES, SAME RESULT. PERFORMED ALTERNATE UPLATCH CHECK AND ALL GEAR AND DOOR INDICATIONS SHOWED LATCHED. LUBED LEFT GEAR UPLATCH ASSY. SWUNG GEAR AND OPS CHECKED GOOD IAW DC 8 MM CHAPTER 32.