N847AX

Part: LONGERON — CRACKED (BS 250 - 270) · airframe 57,047 hrs · 26,373 cycles

FORWARD CARGO, LONGERON 35 LEFT, CRACKED, FS 250 - 270. INSTALLED LONGERON REPAIR AT FORWARD CARGO FS 250 - 270, LONGERON 35 LEFT IAW RFTS 40033 AND PROJECT E-40463. SPLICE REPAIR INSTALLED IAW DC8 SRM 53-2-2 AT LONGERON 35 LEFT.

Part: SKIN — CORRODED (BS 620 - 640) · airframe 57,047 hrs · 26,373 cycles

FORWARD CARGO FUSELAGE SKIN BULGED, CRACKED, FASTENER SHEARED, EVIDENCE OF EXFOLIATION CORROSION AT PREVIOUS REPAIR, FS 620 - 640, LONGERON 35 LEFT - 36 LEFT. REMOVED CORROSION FORWARD CARGO COMPARTMENT FUSELAGE SKIN IAW DC8 SRM 51-1-8 AT LONGERON 36. INSTALLED DOUBLER AND 2 EACH FINGER DOUBLERS IAW DC8 SRM.

Part: LONGERON — CRACKED (BS 879) · airframe 57,047 hrs · 26,373 cycles

LEFT MAIN LANDING GEAR WHEEL WELL LONGERON 24, FS 879 HAD A CRACK AT LOWER FASTENER FORWARD SIDE. REMOVED AND INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D AND 53-2-0.

Part: LONGERON — CRACKED (BS 879) · airframe 57,047 hrs · 26,363 cycles

RIGHT FS 879.375, LONGERON 24, HAD CRACK AT LOWER AREA. STOP DRILLED AND INSTALLED ANGLE REPAIR IAW DC8 SRM 53-2-2.

Part: INDICATOR — DEFECTIVE (ENG OIL PRES) · airframe 56,851 hrs · 26,180 cycles

ON TAKEOFF AND CLIMB, NR 3 ENGINE OIL PRESSURE CLIMBED TO 75 - 80 PSI. TOOK THROTTLE TO IDLE, PRESSURE WENT TO 60 PSI. SECURED NR 3 ENGINE. AIR TURN BACK. AFTER SECURING THE ENGINE, THE PRESSURE READ 14 PSI STATIC ON TAXI. REPLACED NR 3 ENGINE OIL PRESSURE INDICATOR. OPS CHECKED GOOD.

Part: BRACKET — BENT (RT FAIRLEAD) · airframe 56,550 hrs · 25,928 cycles

DECLARED EMERGENCY, DURING RT TURNS IN FLT AILERONS HARD TO MOVE IN POWERED MODE. WHEN AILERONS DEPOWERED, OPS NORM. FOUND RT FAIRLEAD BRACKET BENT & INTERFERRING WITH CABLE DUE TO BROKEN BUS AILERON CABLE RUNS. REPLACED BRACKET STA RW XRS 380. REPLACED DAMAGED PULLEY ON LT AILERON BUS CRANK & BROKEN AILERON BUS CABLE PULLEY RT I/B AILERON HINGE. FABBED & INSTALLED NEW LINE ON LT WING AILERON TAB LOCKOUT CYLINDER EXTEND LINE BTW TUBE CLAMP & SLEEVE/B-NUT AT CYLINDER. REPLACED LT AILERON TAB LOCKOUT CYLINDER, CABLE 365495-536 RUN AB-A, CABLE 3763151-501 RUN AB-B, LT WING AILERON BUS CABLE P/N 3654950-536 RUN AB-D. ADJ/TEST & THROW CHECKED GOOD. ADJUSTED LT O/B AILERON DAMPER & THROW CHECKED. OPS GOOD.

Part: COMPRESSOR — DAMAGED (CABIN AIR) · airframe 56,525 hrs · 25,909 cycles

AFTER TURNING ON THE NR 4 CTC, THE AIRCRAFT FILLED WITH A BURNING OIL SMELL. TURNED NR 4 CTC OFF AND SMELL DISSIPATED. NOTE: DID NOT GET AN OVERHEAT LIGHT, RPM'S NORMAL. FOUND NR 4 CTC FAN BLADE DAMAGED. REMOVED AND REPLACED NR 4 CTC. OPS CHECKED GOOD IAW DC-8 MM CHAPTER 21. ADDITIONAL INFO: THE CREW HAD THE PROBLEM WITH THE NR 4 CTC ON TAKEOFF OUT OF ILN EN ROUTE TO SAT, FLIGHT 392. DID NOT DO AN AIR TURNBACK, NOR ABORT TAKEOFF. MAINTENANCE ALSO FOUND THE NR 3 CTCS DAMAGED. BOTH THE NR 3 AND NR 4 CTCS WERE CHANGED OUT. A BIRD STRIKE INSPECTION WAS ALSO PERFORMED WITH NO ADDITIONAL FINDINGS.

Part: ENGINE — VIBRATION (NR 3) · airframe 56,433 hrs · 25,818 cycles

AT 2000 FEET AND LEVELING OFF, POWER ADVANCED TO MAINTAIN AIRSPEED, HAD SEVERE NR 3 ENGINE VIBRATION. AIRCRAFT WAS INSPECTED AND FOUND TO BE IN SAFE CONDITION FOR FERRY FLIGHT FROM IAD TO ILN. UPON ARRIVAL AT ILN, THE NR 3 ENGINE WAS REPLACED.

Part: SMOKE DETECTOR — DEFECTIVE (CARGO BAY) · airframe 56,300 hrs · 25,709 cycles

UPPER CARGO FIRE SMOKE SOUNDED IN FLIGHT. ISOLATED TO NR 3 DETECTOR. TESTED NORMAL AFTER LANDING. REPLACED NR 3 SMOKE DETECTOR IAW DC-8 MM 26-10-05-2-0001. OPS CHECKED GOOD.

Part: PLATE — MISREPAIRED (FUSELAGE) · airframe 56,251 hrs · 25,667 cycles

FOUND MAIN ENTRY DOOR SCUFF PLATE DID NOT MEET REQUIREMENTS OF SERVICE REWORK DRAWING SRO8530021. TEMPORARY REPAIRED MAIN ENTRY DOOR SCUFF PLATE IAW REA D853-49056MR. PLACED ON CARRY OVER NR COI 46070. PROPER FASTENERS TO BE INSTALLED ON OR BEFORE 9-6-2005.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 56,106 hrs · 25,546 cycles

L1 DOOR FORWARD UPPER CORNER HAD A B-CLASS REPAIR IAW ABX JC NEA 53100102-002. REMOVED EXISTING REPAIR, PERFORMED X-RAY INSPECTION TO CUTOUT. NO CRACKS NOTED. FABRICATED DOUBLERS AND FILLER IAW DC-8 SRM 53-2-0. INSTALLED REPAIR AND REPAIRED AREA IAW DC-8 SRM 51-1-20D, 51-1-21, 51-1-21A, AND REA D853-48060MR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 56,106 hrs · 25,546 cycles

L2 LOWER AFT DOOR CORNER HAD A REPAIR THAT DID NOT CONFORM TO SERVICE REWORK DWG SR08530021 OR ENG SKETCH ES00863. REMOVED EXISTING REPAIR AND STRUCTURAL COMPONENTS TO FOM. FABRICATED REPAIR DOUBLERS, ALODINED, PRIMED AND REINSTALLED COMPONENTS IAW DC-8 SRM 51-1-20D, 51-1-21, 53-2-0 AND REA D853-48057MR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,106 hrs · 25,546 cycles

L2 AFT PASSENGER LOWER FORWARD DOOR JAMB CORNER HAD CRACKS ON EXTERNAL SKIN AND INTERNAL DOUBLERS, LENGTH RANGE FROM 2 - 4 INCHES APPROXIMATELY. REMOVED DAMAGE FROM AREA, PERFORMED HFEC ON EXTERNAL SKIN AND TITANIUM DOUBLER, NO CRACKS PAST CUTOUT. FABRICATED DOUBLERS AND FILLERS, ALODINED, PRIMED, AND INSTALLED IAW DC-8 SRM 53-2-0, 51-1-21, 51-1-20D AND REA D853-48059MR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 56,106 hrs · 25,546 cycles

R1 DOOR UPPER FORWARD CORNER HAD A REPAIR THAT DID NOT CONFORM TO SERVICE REWORK DRAWING SR08530021 OR ENG SKETCH ES00863. REMOVED EXISTING DOUBLER AND TRIPLER, PERFORMED X-RAY AND ELC INSPECTION, NO CRACKS. FABRICATED DOUBLER AND TRIPLER REPAIR, ALODINED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-21, 53-2-0, 51-1-8, 51-1-20D AND REA D853-48055MR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,106 hrs · 25,546 cycles

R1 FORWARD SERVICE DOOR LOWER AFT CORNER HAD CRACK INDICATION ON EXTERNAL SKIN. CUT OUT DAMAGED AREA, PERFORMED HFEC AFTER DAMAGE REMOVAL. NO CRACKS NOTED. FABRICATED DOUBLERS AND FILLER, ALODINED, PRIMED, AND INSTALLED IAW DC-8 SRM 53-2-0, 51-1-8, 51-1-20D, 51-1-21, AND REA D853-48054MR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,106 hrs · 25,546 cycles

FORWARD CARGO BILGE AREA HAD CRACK ON FRAME FS 240, LONG 34 RIGHT - LONG 35 RIGHT. CUT OUT DAMAGE AND FABRICATED REPAIR ANGLE AND FILLER IAW DC-8 SRM STD5310-02. ALODINED AND PRIMED ANGLE AND FILLER IAW DC-8 SRM 51-1-8. INSTALLED DOUBLER AND FILLER IAW DC-8 SRM 51-1-20D. ALL WORK COMPLIED WITH IAW ABX REA D853-48062MR.

Part: STRUCTURE — CORRODED (VERTICAL STAB) · airframe 56,106 hrs · 25,546 cycles

VERTICAL STABILIZER REAR SPAR RIGHT CHORD HAD CORROSION AT ZR 270. REMOVED CORROSION AT REAR SPAR RIGHT CHORD, FOUND TO BE OUT OF LIMITS. FABRICATED REPAIR DOUBLER, ALODINED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 55-2-0 AND REA D855-48068MR.

Part: STRUCTURE — CORRODED (VERTICAL STAB) · airframe 56,106 hrs · 25,546 cycles

VERTICAL STABILIZER REAR SPAR LEFT CHORD HAD CORROSION ON AFT LEG BETWEEN ZR 262 AND ZR 268. REMOVED CORROSION ON REAR SPAR LEFT CHORD, FOUND OUT OF LIMITS. FABRICATED REPAIR DOUBLER, ALODINED, PRIMED AND INSTALLED IAW DC-8 SRM 51-1-8, 55-2-0 AND REA D855-48067MR.

Part: ELEMENT — MISSING (FIRE LOOP) · airframe 56,032 hrs · 25,486 cycles

ENROUTE , NR 3 ENGINE FIRE WARNING CAME ON. ONLY OTHER INDICATION WAS HIGH OIL TEMP. CREW ELECTED TO USE RT WING OB ENGINE FIRE BOTTLE. MAINTENANCE PERFORMED A VISUAL INSPECTION OF THE NR 3 ENGINE. NO EVIDENCE OF FIRE OR FIRE DAMAGE FOUND. DURING INSPECTION, FOUND NR 3 ENGINE LOWER FIRE SENSING ELEMENT MISSING TAN CENTERING BRACKETS CAUSING CENTER CONNECTOR TO CHAFE AGAINST SHIELD. REPLACED LOWER FIRE SENSING ELEMENT IAW AMM. PERFORMED ADJ/TEST. OPS NORMAL. REMOVED AND INSP. OIL STRAINER. NO DEFECTS FOUND. RAN ENGINE, LEAK CHECKED NORMAL. ALL ENGINE PARAMETERS NORMAL. REPLACED RT WING OB FIRE EXTINGUISHING CONTAINER AND CARTRIDGES IAW AMM. COMPLIED WITH ENGINE FIRE DETECTION JOB CARD 8870501 FOR NR 3 ENGINE.

Part: SKIN — DAMAGED (PAX DOOR) · airframe 55,767 hrs · 25,283 cycles

CREW ENTRY DOOR WOULD NOT CLOSE AND LOCK, OR OPEN PROPERLY. REPAIRED AFT UPPER CORNER OF MAIN ENTRY DOOR SKIN IAW DC-8 SRM 52-2-0 AND REA D852-46903. OPS CHECKED GOOD.

Part: LINK — SHEARED (NLG STEERING) · airframe 55,714 hrs · 25,236 cycles

ON ROLLOUT, NO BRAKING BELOW 15 KNOTS. STICK SHAKER WENT OFF, BLOW AWAY JET INOPERATIVE. SUSPECT GROUND SHIFT FAILURE. FOUND NOSE LANDING GEAR STEERING SHUTOFF VALVE LINK SHEARED. REPLACED LINK ASSEMBLY IAW DC-8 MM 32-21-01. OPS CHECKED GOOD.

Part: INDICATOR — DEFECTIVE (COCKPIT) · airframe 55,463 hrs · 25,033 cycles

NR 1 ENGINE OIL TEMP WENT TO 150 DEG CELSIUS FOR APPROXIMATELY 20 MINUTES. SECURED THE NR 1 ENGINE. ALL OTHER INDICATIONS WERE NORMAL. REPLACED THE NR 1 ENGINE OIL TEMP BULB IAW DC-8 AMM 79-34-01-2 AND THE NR 1 ENGINE OIL TEMP GAUGE IAW DC-8 AMM 31-00-00-2. PERFORMED GROUND RUN OF THE NR 1 ENGINE IAW P/W MM 72-00. OPS CHECKED GOOD.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 55,185 hrs · 24,802 cycles

RIGHT WHEEL WELL, LONGERON 24 RIGHT WAS CRACKED AND CORRODED AT STATION 980. REPAIRED AREA AND INSTALLED NEW DOUBLER AND ANGLE IAW DC-8 SRM 51-1-21, 51-1-8, 51-1-20D AND REA D853-40964MR.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 55,185 hrs · 24,802 cycles

FORWARD ACCESSORY COMPARTMENT LONGERON 36 WAS CORRODED AT FS 662. REPAIRED AREA AND INSTALLED NEW REPAIR ANGLE IAW DC-8 SRM 53-2-0, 51-1-20D, 51-1-8 AND REA D853-40966MR.

Part: WEB — CORRODED (FUSELAGE) · airframe 55,185 hrs · 24,802 cycles

FORWARD CARGO, AT FS 80, RIGHT CUSP AT LONGERON 21 RIGHT, ATTACH ANGLE WAS CORRODED. REPAIRED AREA IAW DC-8 SRM 51-1-8 AND REA D853-40960MR.

Part: THRUST LINK — CHAFED (#2 PYLON) · airframe 55,185 hrs · 24,802 cycles

#2 PYLON THRUST LINK CHAFED ON BOTTOM SIDE FROM PNEUMATIC DUCT CLAMP (REF. EA 5403277MR) REPAIR OR REPLACEMENT PER CARD 8821016, STEP 02.A) REPAIRED AREA IAW DC-8 SRM 51-1-8, MM 71-00-00, SB 54-92 AND REA D854-40959MR.

Part: FITTING — CRACKED (RIGHT WING) · airframe 55,185 hrs · 24,802 cycles

RIGHT WING AUX SPAR, LOWER "L" ANGLE, WAS CRACKED APPROXIMATELY 10 INCHES LONG AT XRS 47. REPLACED FITTING IAW DC-8 SRM 51-1-24, 51-1-8 AND 51-1-20D.

Part: FITTING — CRACKED (RT WING) · airframe 55,185 hrs · 24,802 cycles

RIGHT WING REAR SPAR, XRS 340, ACTUATOR ATTACH FITTING TO REAR SPAR WAS CRACKED. REPLACED FITTING IAW DC-8 DAC DWG 5773254, MM 20-16-00, 20-14-00 AND 27-51-09.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 55,185 hrs · 24,802 cycles

FORWARD CARGO AT FS 600 - 620, LONGERON 31 RIGHT, SPLICE FITTING WAS CRACKED, OUTBOARD SIDE. REPLACED FITTING IAW DC-8 SRM 51-1-24, 51-3-2 AND 51-1-20D.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 55,185 hrs · 24,802 cycles

FORWARD CARGO AT FS 600 - 620, LONGERON 25 RIGHT, SPLICE FITTING WAS CRACKED. REPLACED FITTING IAW DC-8 SRM 51-3-2, 51-1-20D AND 51-1-11.

Part: LINK — CHAFED (NR 3 PYLON) · airframe 55,185 hrs · 24,802 cycles

NR 3 PYLON THRUST LINK CHAFED ON LOWER SIDE FROM PNEUMATIC DUCT CLAMP (REF EA AD 54-03277MR) FOR REPAIR OR REPLACEMENT PER ABX CARD 8931015, STEP 02.A). REPAIRED AREA IAW DC-8 SB 54-92.

Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT) · airframe 54,967 hrs · 24,629 cycles

YELLOW MAINTENANCE LIGHT ILLUMINATED WITH GREEN SYSTEM OK. LED ILLUMINATED AND NO MALFUNCTION CODES DISPLAYED. CREW DEFERRAL IAW MEL 26-10-3A. MAINTENANCE ACTION REQUIRED. CDU MX TEST INDICATED AC 4725 FALSE ALARM, RESET BREAKERS. FINAL CDU INDICATION SYSTEM OK IAW DC-8 MM 26-15-00-0-0001.

Part: RETAINER — BENT (ENTRY DOOR) · airframe 54,847 hrs · 24,534 cycles

UNABLE TO OPEN CREW ENTRY DOOR FROM INSIDE AIRCRAFT AFTER LANDING. FOUND BENT SEAL RETAINER AND DOOR JAMB. STRAIGHTENED RETAINER AS REQUIRED. DOOR OPS CHECKED GOOD WITH AIRCRAFT PRESSURIZED IAW DC8 MM 52-11-01.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 54,825 hrs · 24,519 cycles

THE FUSELAGE SKIN WAS CORRODED AND FASTENERS WERE BULGING AND MISSING AT FUSELAGE STA 50, LONGERON 34R. MAINTENANCE INSPECTED AND REPAIRED AND DEFERRED IAW ABX REA D853-41127-MR.

Part: BATTERY PACK — DISCHARGED (COCKPIT) · airframe 54,387 hrs · 24,280 cycles

EMERGENCY LIGHTING INOP. REPLACED EMERGENCY LIGHT BATTERY PACK ASSEMBLY IAW DC8 MM. OPS CHECKED GOOD.

Part: LINK — WORN (NLG DOOR)

ON GEAR RETRACTION EXPERIENCED VIBRATION FROM AREA UNDER THE COCKPIT. RECYCLED LANDING GEAR TWICE, NOISE CEASED AFTER SECOND RECYCLED. REPLACED NOSE GEAR DOOR LEFT CRANK ASSEMBLY AND ADJUSTED IAW DC8 MM 32-22-1.

Part: SKIN — CORRODED (BS 1640-1660)

CORROSION ON LOWER SKIN BETWEEN STATION 1640 TO 1660 LONGERON 22R-26R. REPAIRED IAW ABX REA D853-17876MR.

Part: STIFFENER — CORRODED (BS 940)

LEVEL 2 CORROSION ON STIFFENER AT LONGERON 24L, STATION 940, LEFT WHEEL WELL. REPAIRED IAW ABX REAS D853-17845 AND D853-17844.

Part: SKIN — CORRODED (BS 1280-1300)

LEVEL 2 CORROSION ON CUSP UPPER SKIN BETWEEN STATION 1280 TO 1300, LEFT SIDE. REPAIRED IAW ABX D853-17871MR.

Part: SKIN — CORRODED (BS 360-380)

CORROSION FOUND UNDER SKIN AT STATION 360 TO 380, STRINGER 35L. REPAIRED IAW ABX REA D853-17894MR.

Part: LONGERON — CORROSION (BS 920)

FOUND CORROSION AND CRACK ON LONGERON 24 AT STATION 920 IN RIGHT WHEEL WELL. REPAIRED IAW DC8 SRM 53-2-2.

Part: STRINGER — CORRODED (RT WING)

RIGHT REAR SPAR, ANGLE SUPPORT CORRODED UNDER TRAILING EDGE UPPER SKIN STRINGER. REPAIRED IAW ABX REA D857-17836.

Part: SKIN — CORRODED (WS 310.25)

FOUND CORROSION, LEFT WING EXTERIOR AT XFS 310.250. REPAIRED IAW ABX REA D857-17806MR.

Part: SKIN — CORROSION (LT WING)

DEEP CORROSION ON LEFT WING UPPER TRAILING EDGE SKIN. REPAIRED IAW ABX REA D857-17828MR.

Part: STRINGER — CORRODED (WS 162-436)

LEVEL 2 CORROSION, ON LEFT WING STRINGERS, AFTER TRAILING EDGE SKIN REMOVAL STATION XRS 162 TO 436. REPAIRED IAW ABX REA D857-17828MR.

Part: INTERCOSTAL — CORRODED (WS 13.25)

RIGHT WING LEADING EDGE CORROSION ON INTERCOSTAL AND INNER DOUBLER AT STATION XFS 13.250. REPAIRED IAW ABX REA D857-17831.

Part: WEB — CORRODED (BS 680)

LEVEL 2 CORROSION ON LOWER WEB BETWEEN STRINGER 36L - 35L, STATION 680 LOWER SKIN. REPAIRED IAW ABX REA D853-17877.

Part: BATTERY — DISCHARGED (CABIN)

EMERGENCY LIGHTS SYSTEM FAILED. REPLACED EMERGENCY LIGHTS BATTERY IAW DC8 MM 33-50-11, SYSTEM CHECKED NORMAL.

Part: WIRE — BURNED (COCKPIT)

DURING CRUISE, EXPERIENCED SMELL OF BURNING PLASTIC. TURNED ALL LIGHTING OFF AND ODOR WENT AWAY. REPAIRED WIRE IN NR 4 FUEL CONSOLE LIGHTING PANEL. OPS CHECKED GOOD IAW DC8 MM CHAPTER 33.

Part: GENERATOR — BURNED (NR 3 ENGINE)

DURING CRUISE, FIRE WARNING ON NR 3 ENGINE. SECURED NR 3 ENGINE AT 0552Z, DISCHARGED ONE BOTTLE. WINDMILLING OIL PRESSURE 25 PSI, N1 25 PERCENT, N2 40 PERCENT. *S/D* INSPECTION OF THE GENERATOR INDICATES THAT FAILURE OF ONE OR MORE OF THE FOLLOWING COMPONENTS: INPUT DRIVE BEARING, ROTOR WINDING, OR COOLING FAN, DAMAGED THE CSD/GENERATOR UNIT CAUSING OVER SPEED, OVERHEATED CONDITION, LOSS OF OIL, AND RESULTANT FIRE AND FIRE WARNING. ENGINE WAS REPLACED ON AIRCRAFT AND COWLING REPAIRS MADE.

Part: BULB — FAILED (COCKPIT)

DURING PREFLIGHT, FOUND THE COCKPIT EMERGENCY LIGHTS INOPERATIVE. RELAMPED AND OPS CHECKED GOOD.

Part: RUDDER — DELAMINATED (EMPENNAGE)

RUDDER FOUND DELAMINATED. OVERHAULED RUDDER PER MANUFACTURERS SPECS.

Part: FITTING — CRACKED (WS 98)

CRACK 2.75 INCH LENGTH AT STA 98L AUX SPAR AT LOWER FLAP FITTING. WORK IN PROGRESS.

Part: DRIVE LINK — CRACKED (LT TE FLAP)

DURING COMPLIANCE OF A.D.88-10-07, FOUND LEFT INBOARD FLAP DRIVE LINK CRACKED AT POINT J. REPLACED LEFT INBOARD FLAP DRIVE LINK IAW DC-8 M.M. 27-51-4.

Part: DRIVE LINK — CRACKED (TE FLAP)

ULTRASONIC INSPECTION, SHOWS CRACK INDICATION ON LEFT FLAP INBOARD DRIVE LINK ON INBOARD LUG AT POINT J. REPLACED FLAP DRIVE LINK IAW DC-8 MM 27-51-4.

Part: DOOR SEAL — LOOSE (PAX DOOR)

DURING ENGINE START, FORWARD CABIN DOOR OPEN LIGHT ILLUMINATED. COULD NOT OPEN DOOR FROM THE INSIDE. FOUND A STRIP OF METAL LOOSE ON THE LOWER FORWARD DOOR SEAL. RESECURED AS REQUIRED.

Part: RETRACT MECH — OUT OF ADJUST (RT MLG DOOR)

LANDING GEAR UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION ON CLIMBOUT. RIGHT MAIN LANDING GEAR DOOR NOT LATCHED LIGHT WAS FOUND TO BE ILLUMINATED. LANDING GEAR WAS RECYCLED SEVERAL TIMES. ALL INDICATIONS WERE NORMAL WITH GEAR DOWN AND ALL ABNORMAL INDICATIONS EXTINGUISHED DURING FINAL APPROACH. RIGGED RIGHT MAIN LANDING GEAR DOOR FOLLOW-UP SYSTEM IAW DC8 MM, CHAPTER 32-31-5. PERFORMED RETRACTION CHECK AND ALL INDICATIONS WERE GOOD.

Part: CONTROL VALVE — BROKEN (BRAKE SYST)

LEFT BRAKES GO FULL TRAVEL WITH NO BRAKING ACTION. BRAKE PRESSURE AND FLUID QUANTITY ARE NORMAL. REPLACED BROKEN BRAKE CONTROL VALVE IAW DC8 MM. OPS CHECK GOOD.

Part: FIRE ELEMENT — DEFECTIVE (NR 4 ENG)

DURING CRUISE, THE NUMBER FOUR ENGINE FIRE LIGHT ILLUMINATED AND THE FIRE BELL SOUNDED. THE ENGINE WAS SECURED AND A FIRE BOTTLE WAS DISCHARGED. DURING THE WINDMILLING PROCEDURE, THE FIRE LIGHT FLICKERED MOMENTARILY. THE FLIGHT CONTINUED WITHOUT FURTHER INCIDENT TO ILN. FOUND THE FORWARD UPPER FIRE DETECTOR ELEMENT DEFECTIVE. REMOVED AND REPLACED THE NUMBER FOUR ENGINE FIRE DETECTOR ELEMENT. SYSTEM OPERATIONAL CHECKED GOOD IAW DC-8 MM CHAPTER 26.

Part: FIRE LOOP — LOOSE (NR 4 ENGINE)

DURING CRUISE, THE NR FOUR ENGINE FIRE WARNING LIGHT ILLUMINATED. THE ENGINE WAS SECURED AND THE FIRE BOTTLES WERE DISCHARGED. LIGHT REMAINED ON. FLIGHT REROUTED TO DEN. LANDED WITHOUT INCIDENT. FOUND LOWER FIRE LOOP LOOSE AND CONNECTOR FULL OF OIL. SECURED FIRE LOOP, CLEANED CONNECTOR, REPLACED FIRE BOTTLES AND SQUIBS. SYSTEM OPS CHECKED GOOD IAW DC-8 M.M., CHAPTER 26. OVERWEIGHT LANDING INSPECTION COMPLIED WITH IAW ABX CARD DC-8-3A. NO DISCREPANCIES NOTED.