N945AS

Part: COMPUTER — FAILED (COCKPIT) · airframe 53,456 hrs · 30,591 cycles

AIRCRAFT RETURNED OF FLIGHT, BOTH DFGC OUT OF SERVICE. THE DFGC RTC BITE WERE PERFORMED IAW MM 22-01-05, TESTED CORRECT. THE OVERWEIGHT LANDING CHECK WAS PERFORMED IAW MM 05-51-04, ALL CORRECT. DURING OVERNIGHT CHECK, BOTH DFGC TESTS WERE PERFORMED IAW MM 22-01-00, BEING CORRECT.

Part: ANTI-ICE VALVE — FAILED (LT SIDE) · airframe 52,733 hrs · 30,188 cycles

AIRCRAFT RETURNED TO PLATFORM, LT STARTER VALVE DID NOT OPEN AND ANTI-ICE BREAKER OF NOSE COWLING POPPED OUT. THE REPORT WAS DEFERRED BY MEL 80-2 AND THE ANTI ICE VALVE WAS REPLACED IAW MM 30-20-01, TESTED CORRECT. DEFERRED REPORT WAS CLOSED.

Part: SHUTOFF VALVE — FAILED (LT ENGINE) · airframe 52,638 hrs · 30,133 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE, DURING LEFT ENGINE STARTED, THE START VALVE OPEN LIGHT DID NOT TURN OFF. THE CIRCUIT BREAKERS WERE RESEATED, CROSS FEED AND CONNECTORS WERE CHECKED AND FAILURE CONTINUED. THE REPORT WAS DEFERRED IAW MEL 80-1. DURING TRANSIT SERVICE START VALVE WAS REPLACED IAW MM 80-10-02, TESTED CORRECT. DEFERRED REPORT WAS CLOSED.

Part: APU — MALFUNCTIONED · airframe 52,156 hrs · 29,874 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF AFTER PUSH BACK, THE RIGHT ENGINE HAD A HOT STARTING PROMOTED BY LOW PRESS FORM THE APU. ENGINES WERE STARTED WITH A GPU AND APU WAS DEFERRED IAW MEL 49-1-2. DURING OVERNIGHT SERVICE, APU WAS TESTED IN BOTH MODES IAW MM 49-00-00, ALL CORRECT. DEFERRED REPORT WAS CLOSED.

Part: SHUTOFF VALVE — FAILED (RT ENGINE) · airframe 50,705 hrs · 29,090 cycles

AIRCRAFT RETURNED TO PLATFORM, RT ENGINE SHUTOFF VALVE DID NOT OPEN. SHUTOFF VALVE WAS REPLACED IAW MM 80-10-02, TESTS WERE CORRECT.

Part: PUMP — FAILED (RT HYD SYSTEM) · airframe 50,017 hrs · 28,661 cycles

DURING APPROACH, RT HYDRAULIC SYSTEM PRESSURE WAS LESSENED AND ABNORMAL PROCEDURE WAS PERFORMED. AIRCRAFT LANDED WITH LANDING GEAR DOORS DOWN. SYSTEM WAS CHECKED AND NO FAILURE WAS DETECTED, IT WAS PURGED AND 2 QUARTS WERE ADDED, QUANTITY AND PRESSURE TRANSMITTERS WERE CHECKED, ALL CORRECT. AS A PREVENTIVE ACTION, HYDRAULIC PUMP WAS REPLACED IAW MM 29-10-05, TEST CORRECT. MLG DOORS WERE CHECKED IAW MM 32-12-00, ALL CORRECT.

Part: TRANSCEIVER — DAMAGED (RADAR) · airframe 49,778 hrs · 28,529 cycles

CAPTAIN REPORTED LIGHTING STRIKE AND RADAR DISPLAY FAILED. LIGHTING STRIKE INSPECTION WAS PERFORMED IAW MM 05-53-00, ALL CORRECT, BUT RADAR ANTENNA WAS INOPERATIVE. ANTENNA AND RADAR TRANSCEIVER WERE REPLACED IAW MM 31-41-01 AND 34-41-02, TESTS CORRECT.

Part: SOLENOID VALVE — FAILED (LT ENGINE) · airframe 49,743 hrs · 28,509 cycles

AIRCRAFT RETURNED TO PLATFORM, DIFFERENCE BETWEEN ENGINES PARAMETERS. LT FCU SOLENOID WAS REPLACED IAW MM 73-20-05 AND TEST IAW MM 73-20-01, ALL CORRECT. DURING ENGINE NR 1 START FAIL CONTINUED, AIR/GROUND SENSOR R2-308 WAS REPLACED, TEST CORRECT. FLIGHT WAS CANCELLED AND DURING OVERNIGHT SERVICE, FUNCTIONAL TEST AND ENGINE RUNNING WERE PERFORMED IAW MM 71-00-01, ALL CORRECT.

Part: PIN — INSTALLED (MLG) · airframe 49,656 hrs · 28,447 cycles

AIRCRAFT RETURNED OF FLIGHT, MAIN LANDING GEAR UNLOCK INDICATION AND STRONG VIBRATION. DURING MAINTENANCE REVISION, RT AND LT LOCK PINS WERE DETECTED INSTALLED IN MAIN LANDING GEAR. LOCK PINS WERE REMOVED AND MAIN LANDING GEAR AND OVERWEIGHT INSPECTION WERE PERFORMED IAW MM 32-30-00 AND 05-51-04, RESPECTIVELY, ALL CORRECT.

Part: PUMP — FAILED (FUEL SYSTEM) · airframe 49,627 hrs · 28,433 cycles

AIRCRAFT RETURNED TO PLATFORM, LT ENGINE LOW POWER. AIRCRAFT WAS SENT TO THE HANGAR AND DURING OVERNIGHT SERVICE FUEL PUMP AND FUEL CONTROL UNIT WERE REPLACED IAW MM 73-12-01 AND 73-20-01, RESPECTIVELY, TEST WAS PERFORMED IAW MPCM 71-00-01, ALL CORRECT.

Part: PITOT TUBE — FOD (PITOT STATIC) · airframe 49,272 hrs · 28,222 cycles

AIRCRAFT RETURNED OF FLIGHT, FLIGHT INSTRUMENTS WITH DAMAGE. DURING MAINTENANCE REVISION A FOD WAS DETECTED ON RIGHT PITOT TUBE AS CONSEQUENCE OF BIRD STRIKE. PITOT TUBE WAS CLEANED AND BRAKES WERE COOLED IAW MM 31-00-01.

Part: FCU — FAILED (RT ENGINE) · airframe 49,095 hrs · 28,117 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF RIGHT ENGINE DID NOT ACCELERATE. PARAMETERS WERE CHECKED AND WERE NORMAL IAW MM 71-00-01. ENGINE WAS SHUTOFF AND PURGE VALVES WERE CHECKED IAW MM 75-31-01. RIGHT FUEL CONTROL UNIT WAS REPLACED IAW MM 73-20-01 AND ACCELERATION TEST WAS PERFORMED IAW MM 71-00-00, ALL CORRECT.

Part: STRAINER — CLOGGED (LT ENG OIL) · airframe 49,024 hrs · 28,068 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF L OIL STRAINER CLOGGING LIGHT TURNED ON AFTER ENGINE START. MAIN OIL FILTER AND SWITCH OIL FILTER WERE REPLACED, IN ACCORDANCE WITH MM 79-20-00 AND 79-30-00, ALL CORRECT.

Part: THROTTLE — LACK OF LUBE (RT ENGINE)

AIRCRAFT RETURNED TO PLATFORM, DUE TO SLOW ACCELERATION IN THE RIGHT ENGINE. THE WATER SUMP WAS DRAINED AND THE THROTTLE CHAMBER WAS LUBRICATED IAW MM 73-20-03. AT OVERNIGHT SERVICE IN MEX, PERFORMED A TRIM TO BOTH ENGINES AND AN ACCELERTION TEST IAW MM 71-00-00, PARAMETERS WITHIN LIMITS. (M)

Part: ACTUATOR — FAILED (SLATS)

AIRCRAFT RETURNED TO PLATFORM DURING TAXING, WHEN SLATS WERE EXTENDED AUTO SLAT FAIL LIGHT TURNED ON. SYSTEM WAS CHECKED WITH OTHER COMPUTERS, CONFIRMING THE FAIL IN BOTH AUTO-SLAT ACTUATORS. ACTUATORS WERE REPLACED IAW MM27-80-08, TEST CORRECT. FURTHER. WHEN THE AIRCRAFT WAS DISPATCHED ART INOP LIGHT TURNED ON FAIL REPORT WAS DEFERRED IAW MEL 73-8.(K)

Part: ACTUATOR — FAILED (L/E SLAT)

AIRCRAFT RETURNED TO PLATFORM DURING TAXI, WHEN SLATS WERE EXTENDED AUTO SLAT FAIL LIGHT TURNED ON. SYSTEM WAS CHECKED WITH OTHER COMPUTERS, CONFIRMING THE FAIL IN BOTH AUTO SLAT ACTUATORS. ACTUATORS WERE REPLACED IAW MM 27-80-08 TESTS CORRECT. FURTHER, THEN THE AIRCRAFT WAS DISPATCHED ART INOP LIGHT TUNED ON FAIL REPORT WAS DEFERRED IAW MEL 73-8.

Part: VALVE — FAILED (ANTI ICE SYSTEM)

CAPTAIN REPORTED THAT DURING AIR FOIL ICE PROTECT WAS TURNED ON, THERE WAS A PRESSURIZATION LEAK WITH FLOW LIGHT ON AND CLIMB RATE BETWEEN 500 AND 800 FPM. TO ATTEND THE FAIL, THE TECH PERSONNEL REPLACED THE PNEUMATIC AUGMENTATION VALVE, PRESSURE REGULATOR VALVE OF LEFT AIR CONDITIONING AN THE ICE PROTECTION VALVE IAW MM 36-1001, 21-31-01 AND 31-10-01 RESPECTIVELY, TESTS CORRECT.(K)

Part: VALVE — FAILED (HYD SYSTEM980470)

DURING TRANSIT CHECK, DETECTED HYDRAULIC LEAK AT RIGHT MLG, HYDRAULIC TEST WAS ACCOMPLISHED DETECTING LEAK AT SHUTOFF AND SPOILER DEPRESSURIZATION VALVE. VALVE WAS REPLACED IAW MM 29-10-26, ALL TESTS CORRECT. (M)

Part: SWITCH — OUT OF POSITION (TAIL CONE)

AIRCRAFT RETURNED TO PLATFORM DUE TO ROTATION TAIL CONE LIGHT ILLUMINATED. DURING CHECK WAS DETECTED SWITCH OUT OF ITS POSITION. MECHANISM WAS CHECKED AND TAIL CONE LIGHT TURNED OFF. TEST WAS PERFORMED IAW MM. OVERWEIGHT LANDING INSPECTION WAS PERFORMED IAW MM, ALL CORRECT.

Part: GCU — FAILED (LEFT)

FLT 198 - MLM-TIJ - AIRCRAFT RETURNED TO GATE, FAIL LIGHT AC/CROSSTIE LOCK-OUT OFF RESET PROCEDURE WS PERFORMED AND LIGHT WAS TURN OFF, BUT LIGHT L GEN OFF APPEARS. GCU WAS NOT POSSIBLE RESET AND ENGINES WERE SHUTDOWN. REPORT WAS DEFERRED UNDER MEL 24-1-1 AND AIRCRAFT WAS REFUELED. DURING OVERNIGHT SERVICE, GENERATOR (P/N 976J252-8) AND GCU WERE CHANGED IAW MM 24-20-01, ALL CORRECT. (M)

Part: COMPUTER — FAILED (STALL WARNING)

AIRCRAFT RETURNED TO PLATFORM AS DUE TO AUTO SLAT FAIL LIGHT ON, BOTH STALL WARNING COMPUTERS WERE FOUND WITH FAILURES, PROXIMITY SWITCH AND "C" AND "D" SENSORS WERE TESTED AND FAIL CONTINUE. EXCESSIVE GREASE WAS DETECTED IN OUTBOARD SLATS ACTUATORS. ACTUATORS WERE CLEANED AND STALL WARNING COMPUTER WAS REPLACED IAW MM. TEST OK.

Part: CONTROL VALVE — FAILED (NLG STEERING)

FLT 583 - MEX-CUN - WHEN THE AIRCRAFT GETS PLATFORM BY ITSELF THE RIGHT GYRO WAS EXCEEDED AND THE ACTUATORS WERE STUCK. AIRCRAFT WAS SENT TO THE HANGAR AND THE STEERING CONTROL VALVE WAS CHANGED IAW MM 32-52-01. (M)

Part: HYDRAULIC LINE — LEAKING (RT MLG WW)

FLT 448 - BJX-LAX - DURING RAMP INSPECTION IT WAS DETECTED AN HYDRAULIC LEAK IN THE RIGHT MLG COMPARTMENT. A PRESSURE LINE OF THE BRAKE MANIFOLD AND MANIFOLD SEAL CAP WAS REPLACED IAW MM 32-42-03, IPC ITEM 102, TEST OK. 5 QUARTS OF HYDRAULIC FLUID WERE NEEDED, THE HYDRAULIC LINE WAS REPLACED AND IT WAS VERIFIED BY LEAKS, ALL OK. (M)

Part: SPLICE — DISCONNECTED (CABIN)

SEA - DURING MAINTENANCE CHECK, THE EMERGENCY FLOOR TRACK LIGHTS FROM THE CLASS DIVIDER TO ROW WERE FOUND INOPERATIVE. REPLACED SPLICE AT THE CLASS DIVIDER AND LIGHTS OPERATED NORMALLY. (M)

Part: TERMINAL — LOOSE (TAILCONE)

SEA - DURING MAINTENANCE CHECK, THE OVERHEAD TAILCONE EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. SECURED LOOSE TERMINAL ON LIGHT ASSEMBLY AND LIGHT OPERATED NORMALLY. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

PDX - DURING MAINTENANCE CHECK, THE OVERHEAD EMERGENCY LIGHTS IN THE TAILCONE AREA WERE FOUND INOPERATIVE. REPLACED THE BATTERY PACK AND OPERATED NORMALLY. (M)

Part: BATTERIES — DISCHARGED (CABIN)

PDX - DURING MAINTENANCE CHECK, THE OVERHEAD EMERGENCY LIGHTS FROM ROWS 1 TO 7 WERE FOUND INOPERATIVE. REPLACED THE BATTERIES AND OPERATED NORMALLY. (X)

Part: SEAL — EXCESS SEALANT (L1 DOOR)

SEA - AFTER ARRIVAL OF FLT NR 367, CREW REPORTED THE L1 DOOR WAS DIFFICULT TO OPEN. TRIMMED EXCESS SEALANT FROM UPPER DOOR SEAL AREA AND OPERATED NORMALLY. (M)

Part: BATTERY — DISCHARGED (CABIN)

SEA - DURING MAINTENANCE CHECK, THE AFT TWO OVERHEAD EMERGENCY EXIT LIGHTS AND ONE OF THE EMERGENCY TAIL CONE LIGHTS WERE FOUND INOPERATIVE. REPLACED OVERHEAD EMERGENCY EXIT LIGHT BATTERY AND LIGHTS OPERATED NORMALLY. (M)

Part: BATTERY — DISCHARGED (CABIN)

SEA - DURING MAINTENANCE CHECK, THE OVERHEAD EMERGENCY LIGHTS FROM ROWS 14 TO 18 WERE FOUND INOPERATIVE. REPLACED THE BATTERIES AND LIGHTS OPERATED NORMALLY. (X)

Part: EEL ASSY — DEFECTIVE (CABIN)

LAX - DURING MAINTENANCE CHECK, THE L-1 PORTABLE EMERGENCY EXIT LIGHT WAS FOUND DIM. REPLACED LIGHT ASSY AND OPERATED NORMALLY. (M)

Part: BAYONETS — OUT OF ADJUST (L1 DOOR)

ANC - PRIOR TO DEPARTURE OF FLIGHT 196, CREW REPORTED L1 DOOR JAMMED IN PARTLY OPEN POSITION WHILE ATTEMPTING TO CLOSE DOOR FOR DEPARTURE. OPENED AND INSPECTED L1 DOOR, RELEASED STUCK BAYONETS AND DOOR OPERATED NORMALLY. (M)

Part: TETHER — DETACHED (LIFE RAFT)

SEA - DURING LIFE RAFT DEMONSTRATION INFLATION, THE SURVIVAL EQUIPMENT PACKAGE BECAME DETACHED FROM THE RAFT WHEN THE TETHER SECURING THE EQUIPMENT PACKAGE TO THE RAFT STITCHING FAILED AT THE ATTACHMENT TO THE EQUIPMENT PACKAGE. THE RAFT WAS RETURNED TO THE MANUFACTURER. (W)