N618US

Part: CONTROL PANEL — FAILED (COCKPIT) · airframe 99,201 hrs · 24,482 cycles

DURING CRUISE THE PMS (PERFORMANCE MANAGEMENT SYSTEM) WENT BLANK. SMELLED ELECTRICAL SMOKE, AND SMOKE WAS VISIBLE FROM PEDESTAL AROUND PMS BASE. FLIGHT CREW PUT ON O2 MASKS AND GOGGLES, REFERRED TO RED CHECK LIST AND COM PROCEDURE. FOUND PMS CDU C/B POPPED, AND PULLED OTHER PMS C/B'S AND SMOKE DISSIPATED. AIRCRAFT DIVERTED TO FAI (FAIRBANKS, ALASKA) AND LANDED WITHOUT INCIDENT. PMS WAS MEL'D IN FAI. THEN AIRCRAFT CONTINUED ON.

Part: FRAME — CORRODED (BS 1146) · corrosion level 2 · airframe 99,170 hrs · 24,476 cycles

DURING L-CHECK FOUND CORROSION AND CRACK ON FRAME IN LT BLG WHEEL WELL AT BS 1146. REPAIRED IAW EA 67-165244.

Part: FRAME — CRACKED (BS 380) · airframe 99,170 hrs · 24,476 cycles

DURING L-CHECK FOUND CRACK IN FRAME AT BS 380 S27R AND S28R. REPAIRED IAW EA 67-165241.

Part: FUEL CELL — LEAKING · airframe 98,808 hrs · 24,405 cycles

DURING TAKE-OFF THERE WAS A STRONG FUEL ODOR IN COCKPIT. SMELL CLEARED ONCE PACKS WERE TURNED ON. AIRCRAFT CONTINUED ON TO DESTINATION AND LANDED WITHOUT INCIDENT. ANC MAINTENANCE FOUND LEAK ON SEAM 15 INCHES AHEAD OF NR 2 SUMP DRAIN, AND SEALED EXTERNAL TANK AREA LEAK. FUELED TANKS TO 30,000LBS NO LEAKS FOUND. AIRCRAFT OK FOR RETURN TO SERVICE.

Part: ODOR — DETECTED (CABIN) · airframe 98,790 hrs · 24,401 cycles

DURING ROTATION AT TAKE-OFF, THERE WAS A STRONG SMELL OF FUEL ODOR. SMELL CLEARED IN 2-3 MINUTES AFTER PACK ACTIVATION. AIRCRAFT CONTINUED ON TO DESTINATION AND LANDED WITHOUT INCIDENT. SIN MAINTENANCE CHECKED FOR FUEL LEAKS, NONE FOUND. AIRCRAFT OK FOR RETURN TO SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 98,100 hrs · 24,268 cycles

DURING OVERNIGHT LINE CHECK, FOUND CRACK IN FUSELAGE SKIN AT BS 1705 S34L. REFERENCE SB 747-53A2487, AD 2002-23-15 AND AD 2004-07-22. REPAIRED PER EA 67-192649.

Part: ENGINE — FIRE (NR 2) · airframe 95,667 hrs · 23,796 cycles

DURING TAXI IN, THE NR 2 ENGINE FIRE WARNING ANNUNCIATED. THE CREW SHUT DOWN THE ENGINE AND DISCHARGED THE LT FIRE BOTTLE FOR NR 2 ENGINE. THE FIRE WARNING CEASED. NO OTHER ABNORMAL ENGINE INDICATIONS WERE OBSERVED. MAINTENANCE INSPECTION FOUND EVIDENCE OF A FIRE AND THE ENGINE WAS REPLACED.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 94,527 hrs · 23,561 cycles

DURING H-CHECK FOUND CRACK IN BULKHEAD CHORD AT BS 1000 FROM 36L TO 40L. REPAIRED PER EA 67-165121.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 94,527 hrs · 23,561 cycles

DURING H-CHECK FOUND CRACK IN UPPER DECK FLOORBEAM CHORD AT BS 520. REPAIRED PER EA 67-165122.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 94,527 hrs · 23,561 cycles

DURING H-CHECK FOUND CRACK IN UPPER DECK FLOORBEAM CHORD AT BS 420 BETWEEN LBL 8 AND RBL 58. REPAIRED PER EA 67-165119.

Part: FITTING — CRACKED (FUSELAGE) · airframe 94,527 hrs · 23,561 cycles

DURING H-CHECK FOUND CRACK IN NOSE CARGO DOOR FRAME CLOSURE FITTING. REPAIRED PER EA 67-165115.

Part: AMPLIFIER — FAULTY (MAIN DECK) · airframe 93,236 hrs · 23,290 cycles

DURING CRUISE, THE NR 5 MAIN DECK CARGO SMOKE DETECTION SYSTEM INDICATED A FIRE. THE OVERHEAD CARGO FIRE LIGHT ILLUMINATED AND THE MASTER FIRE WARNING ACTIVATED. VISUALLY INSPECTED CARGO ON MAIN DECK WITH NO SIGNS OF FIRE OR SMOKE. AIRCRAFT CONTINUED TO DESTINATION AND LANDED WITHOUT INCIDENT. REPLACED THE NR 5 -A- AND -B- SMOKE DETECTORS AND THE NR 5 SMOKE DETECTOR AMP. OPERATIONAL CHECK GOOD.

Part: COMPUTER — INOPERATIVE (YAW DAMPER) · airframe 93,631 hrs · 23,164 cycles

DURING CLIMB THE LOWER YAW DAMPER LIGHT ILLUMINATED BRIEFLY AND THE AIRCRAFT WAS DIFFICULT TO CONTROL IN HEADING. SLOWED AIRCRAFT TO 270 KNOTS AND TURNED OFF LOWER YAW DAMPER BUT AIRCRAFT WAS STILL DIFFICULT TO CONTROL IN HEADING. AIRCRAFT DECLARED AN EMERGENCY DUMPED 20,000 LBS OF FUEL AND RETURNED TO JFK AND AFTER LANDING EIGHT TIRE FUSES BLEW. REPLACED UPPER AND LOWER RUDDER POWER CONTROL UNITS BOTH YAW DAMPER COMPUTERS AND EIGHT TIRE ASSEMBLIES. OPERATIONAL CHECK GOOD.

Part: WEB — CRACKED · airframe 90,520 hrs · 22,730 cycles

During "L" check found crack in frame web at BS 380 S23R. Repaired per EA 67-165035.

Part: BULKHEAD — CRACKED · airframe 90,520 hrs · 22,730 cycles

During "L" Check found crack on #2 pylon rear engine mount bulkhead. Repaired per EA 67-165032.

Part: WEB — CRACKED · airframe 90,520 hrs · 22,730 cycles

During "L" check found crack in frame web at BS 360 at S23 and S24. Repaired per EA 67-165034.

Part: BULKHEAD — CRACKED · airframe 90,520 hrs · 22,730 cycles

During "L" check found crack on #4 pylon rear engine mount bulkhead. Repaired per EA 67-165031.

Part: WEB — CRACKED · airframe 90,520 hrs · 22,730 cycles

During "L" check found crack in nose wheel wheel top panel frame web at BS 284 LBL 10. Repaired per EA 67-165037.

Part: BATTERY — OVERHEATED · airframe 87,174 hrs · 22,061 cycles

DURING FLIGHT, A STRONG ELECTRICAL FUME EMITTED IN THE COCKPIT. FUME SMELL DID NOT DISSIPATE AFTER COMPLYING WITH THE EMERGENCY PROCEDURES AND THE COM. CREW DIVERTED TO NRT, DECLARED AN EMERGENCY, AND DUMPED 100,000 LBS OF FUEL. DURING LANDING WHILE IN REVERSE THRUST, THE NBR 3 ENGINE COMPRESSOR STALLED AND OVERTEMPED. AIRCRAFT TAXIED TO THE GATE WITHOUT FURTHER INCIDENT. REPLACED THE MAIN BATTERY, BATTERY CHARGER, AND THE NBR 3 ENGINE. OPERATIONAL CHECK GOOD.

Part: WIRE — BURNED (CAPT GLARESHIELD) · airframe 86,499 hrs · 21,921 cycles

DURING FLIGHT, A STRONG ELECTRICAL FUME EMITTED IN THE COCKPIT. REMOVED CAPTAIN'S FLUORESCENT GLARESHIELD LIGHTS AND FUMES DISSIPATED. AIRCRAFT CONTINUED TO DESTINATIONA AND LANDED WITHOUT INCIDENT. REPLACED WIRE AT CAPTAIN'S GLARESHIELD LIGHT. OPERATIONAL CHECK GOOD.

Part: SEAT TRACK — CRACKED (CABIN) · airframe 81,648 hrs · 20,952 cycles

DURING M CHECK, FOUND CRACK IN SEAT TRACK CROWN AT BS 1727 RBL 33. REPAIRED PER EA 67-177772.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 81,648 hrs · 20,952 cycles

DURING M CHECK, FOUND CORROSION ON FLOORBEAM AT BS 1840 BL 0. REPAIRED PER EA 67-177822.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 81,648 hrs · 20,952 cycles

DURING M CHECK, FOUND CORROSION ON HORIZONTAL FLANGE OF LONGITUDINAL FLOORBEAM AT BS 1140 LBL 50. REPAIRED PER EA 67-177827.

Part: SKIN — CRACKED (NR 4 PYLON) · airframe 81,648 hrs · 20,952 cycles

DURING M-CHECK, FOUND CRACK IN THE NUMBER 4 INBOARD PYLON SKIN, AT SLOT SEAL, NACELLE STATION 180. REPAIRED PER EA 67-175573.

Part: FLANGE — CORRODED (RT SIDEWALL) · corrosion level 2 · airframe 81,648 hrs · 20,952 cycles

DURING -M- CHECK FOUND CORROSION ON CABIN FLOOR, RT SIDEWALL FLANGE AT BS 1500. REPAIRED PER EA 67-176782.

Part: FRAME — CRACKED (FUSELAGE) · airframe 81,648 hrs · 20,952 cycles

DURING M-CHECK, FOUND CRACK ON FRAME AT BS 1416, STRINGER 23R. REPAIRED PER EA 67-177809.

Part: SKIN — CRACKED (NR 4 PYLON) · airframe 81,429 hrs · 20,907 cycles

DURING LINE MAINTENANCE INSPECTION FOUND CRACK IN NR 4 PYLON INBOARD SKIN, SLOT SEAL CUTOUT, NAS STATION 180. REPAIRED PER EA 67-175573.

Part: FIRE LOOP — MALFUNCTIONED (NR 4 ENGINE)

DURING CRUISE, THE NR 4 ENGINE NACELLE FIRE DETECTION FAULT LIGHT ILLUMINATED. THE FIRE DETECTION LIGHT ILLUMINATED INTERMITTENTLY AND THE 'A' AND 'B' NACELLE TEMP INDICATORS INTERMITTENTLY INDICATED HIGH. AIRCRAFT DIVERTED TO DTW AND LANDED WITHOUT INCIDENT. REPLACED THE LOWER AFT LOOP DETECTOR AND BLEED ELEMENT SENSING LINE DUE TO LINE TOUCHING THE UPPER AFT LOOP LINE. OPERATIONAL CHECK GOOD.

Part: FRAME — CRACKED (BS 281)

DURING M CHECK, FOUND CRACK IN C3 CLOSURE FRAME ON THE MAIN DECK FS 281, LBL 45. REPAIRED CLOSURE FRAME PER EA 67-164977.

Part: FRAME — CRACKED (BS 380)

DURING PERIODIC CHECK, FOUND CRACKS AT FS 380, STR 25L FRAME WEB AND STR 25R FRAME. REPAIRED PER EA 67-164976.

Part: TACHOMETER — MALFUNCTIONED (NR 4 ENGINE)

DURING TAKEOFF ROLL AT APPROXIMATELY 115 KTS, THE NR 4 ENGINE N1 RPM INDICATION MALFUNCTIONED. THE TAKEOFF WAS ABORTED. MAINTENANCE PLACED THE NR 4 ENGINE N1 INDICATION SYSTEM ON MEL AND THE AIRCRAFT RETURNED TO SERVICE.

Part: FLOORBEAM — CRACKED (BS 380)

DURING PERIODIC CHECK, FOUND A CRACK IN A UPPER DECK FLOORBEAM UPPER CHORD FASTENER HOLE AT THE FUSELAGE FRAME FS 380, RIGHT SIDE. REPAIRED PER EA 67-121410.

Part: FLOORBEAM — CRACKED (BS 340)

DURING PERIODIC CHECK, FOUND A CRACK IN 2 UPPER DECK FLOORBEAM UPPER CHORD FASTENER HOLES AT THE FUSELAGE FRAME FS 340, LEFT SIDE. REPAIRED PER EA 67-121410.

Part: FLOORBEAM — CRACKED (BS 360)

DURING PERIODIC CHECK, FOUND A CRACK IN A UPPER DECK FLOORBEAM UPPER CHORD FASTENER HOLE AT THE FUSELAGE FRAME FS 360, RIGHT SIDE. REPAIRED PER EA 67-121410.

Part: FLOORBEAM — CRACKED (BS 500)

DURING PERIODIC CHECK, FOUND A CRACK IN 2 UPPER DECK FLOORBEAM UPPER CHORD FASTENER HOLES AT THE FUSELAGE FRAME FS 500, RIGHT SIDE. REPAIRED PER EA 67-121410.

Part: COMPRESSOR — STALLED (NR 1 ENGINE)

WHILE AT CRUISE FL350, THE NR 1 ENGINE COMPRESSOR STALLED. THE ENGINE WAS SHUT DOWN AFTER REACHING AN EGT OF 1002C FOR 5 SECONDS. NO RESTART WAS ATTEMPTED. THE FLIGHT CONTINUED TO KIX WITHOUT FURTHER DIFFICULTY. THE AIRCRAFT WAS REMOVED FROM SERVICE AND THE NR 1 ENGINE WAS REPLACED AFTER ARRIVING IN KIX.

Part: BREATHER TUBE — CRACKED (NR 1 ENGINE)

WHILE IN CRUISE, THE NR 1 ENGINE OIL QUANTITY WENT TO ZERO WITH THE OIL PRESSURE DROPPING RAPIDLY DOWN TO 8 TO 9 PSI. THE ENGINE WAS SHUT DOWN PER COM PROCEDURE AND THE AIRCRAFT RETURNED TO ANC WITHOUT DIFFICULTY. MAINTENANCE INSPECTED THE ENGINE AND REPLACED THE REAR MAIN BEARING BREATHER TUBE DUE TO A CRACK. THE FOLLOW-UP LEAK CHECK AND ENGINE WINDMILL CHECK WERE NORMAL.

Part: SPAR WEB — CORRODED (WS 997-1001)

DURING PERIODIC CHECK, FOUND CORROSION ON FRONT SPAR WEB AT THE LOWER CHORD FS 997 TO 1001. REPAIRED PER EA 67-153201.

Part: SPAR WEB — CORRODED (WS 1014-1018)

DURING PERIODIC CHECK, FOUND CORROSION ON FRONT SPAR WEB AT THE LOWER CHORD FS 1014 TO 1018. REPAIRED PER EA 67-153201.

Part: FITTING — CORRODED (BS 2360)

DURING PERIODIC CHECK, FOUND CORROSION ON END FITTINGS FOR STR 38R AND 40R AT FS 2360. REPLACED FITTINGS (P/N 65B04370-46) PER BOEING DRAWING 65B04160.

Part: FITTING — CORRODED (BS 2360)

DURING PERIODIC CHECK, FOUND CORROSION ON END FITTINGS FOR STR 42R, 44R, 46R, 48R, 49R, 50R, AND 51R AT FS 2360. REPLACED FITTINGS (P/N 65B04370-8) PER BOEING DRAWING 65B04161.

Part: FITTING — CORRODED (BS 2360)

DURING PERIODIC CHECK, FOUND CORROSION ON END FITTINGS FOR STR 38L AND 40L AT FS 2360. REPLACED FITTINGS (P/N 65B04370-45) PER BOEING DRAWING 65B04160.

Part: FITTING — CORRODED (BS 2360)

DURING PERIODIC CHECK, FOUND CORROSION ON END FITTINGS FOR STR 42L, 44L, 46L, 48L, 49L, 50L, AND 51L AT FS 2360. REPLACED FITTINGS (P/N 65B04370-7) PER BOEING DRAWING 65B04161.

Part: FITTING — CORRODED (BS 2360)

DURING PERIODIC CHECK, FOUND CORROSION ON END FITTINGS FOR LONGERONS 38L, 40L, 42L, 44L, 46, 48L, 49L, 50L, AND 51L AT FS 2360. REPLACED FITTINGS PER BOEING DRAWING 65B02699.

Part: FITTING — CORRODED (BS 2360)

DURING PERIODIC CHECK, FOUND CORROSION ON END FITTINGS FOR LONGERONS 38R, 42R, 44R, 46R, 48R, 49R, 50R, AND 51R AT FS 2360. REPLACED FITTINGS PER BOEING DRAWING 65B02699.

Part: OIL FILTER — DIRTY (NR 3 ENGINE)

WHILE IN CRUISE, THE NR 3 ENGINE OIL FILTER BYPASS LIGHT BEGAN TO FLICKER, AFTER 2-3 MINUTES THE LIGHT WAS STEADY AND REMAINED STEADY WHEN POWER WAS REDUCED TO IDLE. THE ENGINE WAS SHUT DOWN AND LANDED AT DESTINATION WITHOUT INCIDENT. MAINTENANCE FOUND THE MAIN OIL FILTER CONTAMINATED WITH SMALL CARBON PARTICLES. THE FILTER WAS REPLACED AND FOLLOW-UP ENGINE RUN WAS NORMAL. EXACT PART CAUSING PROBLEM TO BE DETERMINED.

Part: SPAR WEB — CORRODED (WS 607)

DURING ARMAR, FOUND CORROSION ON LEFT WING FRONT SPAR WEB FSS 607. REPAIRED PER \NEA 67-121744.

Part: DOUBLER — CRACKED (BS 400)

DURING ARMAR, FOUND CRACKED DOUBLER IN NOSE WHEEL WELL BS 400, RBL 26. REPAIRED PER EA 66-121741.

Part: FRAME — CRACKED (BS 434)

DURING ARMAR, FOUND CRACK IN FRAME AT CABLE CUT OUT BELOW STR 26L, FS 434. REPAIRED PER EA 67-121723.

Part: FRAME — CRACKED (BS 360)

DURING ARMAR, FOUND CRACK IN FRAME AT STR 24L, FS 360. PAIRED PER EA 67-121746.

Part: ENGINE — BIRD STRIKE (NR 1)

DURING TAKEOFF, THE NR 1 ENGINE N1 WENT TO ZERO WITH VIBRATION NOTED. THE ENGINE WAS SHUT DOWN, DUMPED 55.000 LBS OF FUEL AND THE AIRCRAFT RETURNED TO SFO WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTION REVEALED A BIRD STRIKE. PERFORMED ENGINE RUN-UP AT TAKEOFF POWER AND NO VIBRATION WAS EXPERIENCED.

Part: DNLOCK ACTUATOR — FAILED (RT MLG)

DURING APPROACH, THE RIGHT WING LANDING GEAR WOULD NOT EXTEND DURING LANDING GEAR EXTENSION. RECYCLED LANDING GEAR AND LANDING GEAR EXTENDED. AIRCRAFT LANDED WITHOUT INCIDENT. REPLACED THE RIGHT WING GEAR DOWNLOCK ACTUATOR, OPERATIONAL CHECK GOOD.

Part: UPLOCK ACT — FAILED (RT MLG)

DURING APPROACH, THE RIGHT WING LANDING GEAR WOULD NOT EXTEND DURING LANDING GEAR EXTENSION. RECYCLED LANDING GEAR AND LANDING GEAR EXTENDED. AIRCRAFT LANDED WITHOUT INCIDENT. REPLACED THE RIGHT WING GEAR UPLOCK ACTUATOR, OPERATIONAL CHECK GOOD.

Part: ACTUATOR — MALFUNCTION (LT MLG)

DURING APPROACH, THE LEFT WING LANDING GEAR WOULD NOT EXTEND. RECYCLED LANDING GEAR AND UTILIZED ALTERNATE LANDING GEAR EXTENSION. AIRCRAFT LANDED WITHOUT INCIDENT. REPLACED THE LEFT WING LANDING GEAR RETRACT ACTUATOR AND DOWNLOCK ACTUATOR, OPERATIONAL CHECK GOOD.

Part: DOUBLER — CORRODED (FS 1339-1346)

DURING P-CHECK, FOUND CORROSION ON THE UPPER SURFACE OF THE BONDED DOUBLER LOCATED OVER THE KEEL BEAM BOX UPPER WEB; BS 1339 - 1346, LBL 2 - 7, WL 116. REPAIRED DOUBLER (P/N 65B15069-288) PER EA 67-99636.

Part: FLOOR BEAM — CRACKED (FS 1300)

DURING P-CHECK, FOUND A CRACK IN THE LBL 34 LONGITUDINAL FLOOR BEAM LOWER CHORD AT BS 1300. REPAIRED CHORD (P/N 65B15485-1) PER EA 67-99624.

Part: FLOOR BEAM — CORRODED (FS 620)

DURING P-CHECK, FOUND CORROSION ON THE BS 620 FLOOR BEAM LOWER CHORD AT LBL 11. REPAIRED BEAM (P/N 65B38031-1) PER EA 67-99621.

Part: FITTING — CRACKED (FS 2360)

DURING P-CHECK, FOUND A CRACK AND CORROSION IN THE STR 36L END FITTING AT BS 2360. REPLACED FITTING PER SRM 51-10-01, PAR 10, PG 18.

Part: EGT INDICATOR — MALFUNCTIONED (NR 1)

DURING TAKEOFF ROLL, THE NR 1 ENGINE EGT EXCEEDED 1,000 DEGREES WITH NO INDICATOR LIGHT. CREW ABORTED TAKEOFF; SUBSEQUENT ENGINE SHUT-DOWN AND RETURNED TO GATE. REPLACED THE NR 1 EGT INDICATOR AND PERFORMED INSTALLATION RESISTANCE CHECK INCLUDING EGT INDICATING ACCURACY TEST. AIRCRAFT IS SCHEDULED FOR NR 1 ENGINE CHANGE IN MSP.

Part: POWER LEVER — MALFUNCTIONED (NR 3 ENGINE)

DURING TAKEOFF ROLL, THE NR 3 ENGINE THROTTLE WOULD NOT ADVANCE PAST 80 PERCENT N2. TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE INSPECTED THE NR 3 THROTTLE CABLE AT FUEL CONTROL AND FOUND OK. SEQUENCE MECHANISM AND THRUST LEVER AT FULL TRAVEL, FOUND NORMAL.

Part: DNLOCK ACT — LEAKING (RT MLG)

AFTER GEAR EXTENSION, THE RIGHT WING RED GEAR LIGHT ILLUMINATED. ALSO, THE RIGHT WING GEAR FAILED TO INDICATE DOWN AND LOCKED IN PRIMARY AND ALTERNATE POSITION. CREW FOLLOWED COCKPIT OPERATING MANUAL AND LANDED AIRCRAFT WITHOUT FURTHER INCIDENTS. MAINTENANCE REPLACED THE DOWNLOCK ACTUATOR AND PERFORMED SWING OPERATION. CHECK WAS NORMAL. CONTROL NUMBER 812096718 CHANGED TO 9512096718.

Part: BULKHEAD — CORRODED (FS 1394)

DURING PERIODIC CHECK (LON), FOUND CORROSION ON THE RIGHT BODY MAIN LANDING GEAR WELL PRESSURE DECK WEB FS 1394, RBL 91 - 97. REPAIRED PER EA 67-98212.

Part: CONTROL MODULE — LEAKING (TE FLAPS)

DURING APPROACH UPON FLAP EXTENSION, THE NR 1 HYDRAULIC QUANTITY DROPPED TO ZERO. SECURED NR 1 HYDRAULIC SYSTEM AND AIRCRAFT LANDED WITHOUT INCIDENT. REPLACED THE TRAILING EDGE FLAP CONTROL MODULE. OPERATIONAL CHECK OK.

Part: TR UNIT — MALFUNCTIONED (NR 1 ENGINE)

DURING LANDING WHILE IN REVERSE THRUST, THE NR 1 ENGINE EXPERIENCED AN OVERTEMP OF 950 DEGREES FOR 20 SECONDS AND THE LOW OIL PRESSURE LIGHT CAME ON. THE REVERSER WOULD NOT STOW AND THE ENGINE WAS SHUTDOWN WHILE ON THE TAXIWAY. THE ENGINE WAS INSPECTED AND A GROUND RUNUP CONFIRMED PROPER OIL PRESSURE AND ENGINE AND REVERSER OPERATION.

Part: TR UNIT — MALFUNCTIONED (NR 1 ENGINE)

DURING LANDING, THE NR 1 ENGINE REVERSER WOULD NOT COME OUT OF FULL REVERSE TO THE STOWED POSITION AND THE ENGINE WAS SHUT DOWN WHILE ON THE RUNWAY. A GROUND RUN-UP WAS ACCOMPLISHED AND PROPER REVERSER OPERATION WAS CONFIRMED BY ITS OPERATION THROUGH SEVERAL REVERSING CYCLES.