N845AX

Part: ROD — BROKEN (COCKPIT)

CAPTAIN'S WINDOW (EMERG EXIT) LATCH PIN WAS FOUND BROKEN DURING PREFLIGHT. REPLACED LOWER FORWARD LINKAGE ROD IAW DC8 MM 56-10-3, OPS CHECKED GOOD.

Part: CTC — SEIZED (NR 1)

AFTER TAKEOFF WHILE CLIMBING THRU FL200, A LOUD CTC HOWL WAS HEARD WITH A STRONG SMELL OF SOMETHING BURNING. OBSERVED NR 1 CTC SURGING. SHUT OFF NR 1 CTC AND BURNING ODOR DISAPPEARED IN APPROXIMATELY 5 MINUTES. NO ADDITIONAL PROBLEMS NOTED. FOUND NR 1 CTC COMPRESSION FAN SEIZED, NO ROTATION. REPLACED NR 1 CTC IAW DC-8 MM CH 21-50. OPS CHECKED GOOD.

Part: ENGINE — FAILED (NR 2)

DURING CRUISE FLIGHT AT FL 280, MACH.82, A SUDDEN VIBRATION WAS FELT. NR 2 ENGINE INDICATED; EGT 540, N2 80 PERCENT, OIL TEMP 125 DEG. OIL QUANTITY WAS ZERO AND EPR WAS 1.0. NR 2 ENGINE WAS SHUTDOWN AND EMERG CHECKLIST WAS ACCOMPLISHED. ENGINE WINDMILLED AT APPROX 35 PERCENT N2, OIL PRESSURE INDICATED 15-20 PSI. ENGINE WINDMILLED FOR 2 HRS AND 20 MIN. AIRCRAFT 3 ENGINE FERRIED TO ILN. NR 2 ENGINE WAS REPLACED.

Part: RETRACT MECH — LACK OF LUBE (NLG DOOR)

AFTER TAKEOFF WHEN LANDING GEAR RETRACTED, HEARD LOUD RUMBLING NOISE FROM NOSE GEAR AREA. ALL RETRACTION INDICATIONS WERE NORMAL. RECYCLED GEAR THREE TIMES WITH SAME RESULT. GEAR FAILED UPLATCH CHECK. AIR TURNED BACK TO ONT. NOSE LANDING GEAR DOOR WAS OPEN ON TAXI-IN. INSPECTED AND LUBRICATED NOSE LANDING GEAR CABLES AND LINKAGE. NO DEFECTS NOTED. PERFORMED NOSE GEAR OPERATIONAL CHECK. GEAR AND DOORS OPERATED PROPERLY. UPLATCH CHECK WAS GOOD IAW DC8 MM 32-31-6.

Part: VANE — CORRODED (RT TE FLAP)

RIGHT VANE HAD WIDESPREAD DELAMINATION AND CORROSION. REPLACED ALL HONEYCOMB CORE DOUBLERS AND SKIN.

Part: ROD — BROKEN (COCKPIT)

CAPTAIN'S WINDOW (EMERG EXIT) LATCH PIN WAS FOUND BROKEN DURING PREFLIGHT. REPLACED LOWER FORWARD LINKAGE ROD IAW DC8 MM 56-10-3, OPS CHECKED GOOD.

Part: ENGINE — FAILED (NR 2)

NR 2 OIL PRESSURE LIGHT ILLUMINATED, OIL PRESSURE FLUCTUATED BELOW 35 PSI TO 20 PSI. SECURED ENGINE AT 1243 Z, RPM NEVER FELL BELOW 24 PERCENT N-2 UNTIL TOUCHDOWN. HIGHEST WAS 35 PERCNET N-2, APPROXIMATELY 5 PSI OIL PRESSURE. REPLACED NR 2 ENGINE IAW ABX ENGINE CHANGE CARD J-7001. MAINTENANCE PROCEDURES COMPLIED WITH.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY LIGHTING FAILED A2 CHECK INSPECTION. REPLACED EMERGENCY LIGHTING BATTERY PACK. OPS CHECKED NORMAL I/A/W DC-8 M.M. 33-50-0.

Part: RUDDER PUMP — LEAKING (RUDDER)

ONE HOUR INTO FLIGHT NOTICED HYDRAULIC QUANTITY SLOWLY DECREASING. MARKED GAUGE AND CONTINUED TO DECREASE VERY SLOWLY. APPROXIMATELY ONE NEEDLE WIDTH ABOVE STANDPIPE PERFORMED HYDRAULIC FLUID LOSS CHECKLIST. ONCE HYDRAULICS DEPRESSURIZED AND ISOLATED, QUANTITY STABILIZED. ON DESCENT AT FL 180 REPOWERED HYDRAULICS AND QUANTITY DECREASED TO STANDPIPE. PERFORMED ABNORMAL CHECKLIST, QUANTITY AT STANDPIPE, PRESSURE AT 3,000 PSI QUANTITY REMAINED AT STANDPIPE FOR LANDING AND TAXI IN. FOUND STANDBY RUDDER PUMP TO BE LEAKING AT CASE DRAIN. REPLACED STANDBY RUDDER PUMP IAW DC-8 MM CHAPTER 29. SERVICED MAIN HYDRAULIC SYSTEM, PERFORMED OPERATIONAL CHECK OF ALL SYSTEMS. HYDRAULIC SYSTEM WORKING NORMAL.

Part: O-RING — CUT (NR 3 HYD SYST)

LOST HYDRAULIC QUANTITY DOWN TO THE N, RAN HYDRAULIC PRESS/LOSS CHECKLIST. THE QUANTITY STAYED AT THE N. VISUALLY INSPECTED AIRCRAFT, NO LEAKS NOTED. SERVICED HYDRAULIC SYSTEM, RAN NR 2 AND NR 3 ENGINES, CYCLED ALL SYSTEMS, FOUND NR 3 ENGINE HYDRAULIC PUMP PRESSURE LINE UNION LEAKING AT PUMP. REPLACED O-RING AND LEAK CHECKED GOOD IAW DC-8 MM 29-10-1.

Part: LAMP — DEFECTIVE (CABIN)

EMERGENCY EXIT LIGHT DOES NOT INDICATE DISARMED. RELAMPED EMERGENCY EXIT LIGHT, OPS CHECK GOOD.

Part: BOOST PUMP — DEFECTIVE (NR4 ENGINE)

NR 4 ENGINE FEED PUMP PRESSURE LIGHT ILLUMINATED WHILE CLIMBING THROUGH 24,000 FEET AND ENGINE FLAMED OUT. CHECKLIST PROCEDURES WERE ACCOMPLISHED AND THE ENGINE HAD RELIGHT. REPLACED BOOST AND FEED PUMPS FOR THE NR 4 ENGINE IAW DC8 MM, CHAPTER 28-20-00. GROUND RAN ENGINE AND NO DEFECTS NOTED. NASH PUMP FILTER WAS REMOVED AND FOUND CLEAN.

Part: O-RING SEAL — DEFECTIVE (NR 3 HYD PUMP)

DURING APPROACH, HYDRAULIC FLUID QUANTITY DROPPED TO THE STANDPIPE LEVEL AND THE HYDRAULIC PRESSURE DECREASED AFTER THE LANDING GEAR WAS EXTENDED. REPLACED DEFECTIVE O-RING SEAL ON THE NR 3 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE FITTING. OPERATED HYDRAULIC SYSTEM AND NO LEAKS WERE NOTED.

Part: ENGINE — FAILED (NR 4)

NR 4 ENGINE SHUTDOWN IN FLIGHT DUE TO ENGINE FAILURE. EGT MAXIMUM TEMPERATURE WAS 760 DEGREES CELSIUS. NR 4 ENGINE WAS SECURED IAW EMERGENCY PROCEDURE CHECKLIST. AIRCRAFT RETURNED TO ILN. REMOVED AND REPLACED ENGINE. TRIMMED DURING GROUND RUN IAW DC 8 MM.