N214AM

Part: CIRCUIT BREAKER — FAULTED (AUTOPILOT) · airframe 2,440 hrs · 5,671 cycles

AFTER TAKEOFF WHILE AT CRUISE FLIGHT AT 1000 AGL HELISAS AUTO PILOT FAILED IN FLIGHT. AIRCRAFT PITCHED NOSE UP ABOUT 5 DEGREES IN A CLIMB. PIC ARRESTED CLIMB AND ATTEMPTED TO REENGAGE HELISAS MUT SYSTEM WOULD NOT REENGAGE. LANDED BACK AT BASE MECHANIC RESET THE CUIRCTIT BREAKER AND PERFORMED FUNCTION CHECK AND SYSTEM OPERATED AS NORMAL

Part: SWITCH — OUT OF POSITION (CABIN PRESSURE) · airframe 42,529 hrs · 34,231 cycles

AIRCRAFT PERFORMED AN EMERGENCY DESCENT 20 MINUTES PRIOR TO LANDING, DUE TO UNCONTROLLABLE DEPRESSURATION. MAINTENANCE PERSONNEL VERIFIED THE PNEUMATIC SYSTEM FOR LEAKS AS WELL AS THE AIR CONDITIONED SYSTEM AND THE DUCTS OF ANTI-ICE SYSTEM IAW MPCM 36-10-00, 21-10-00 AND 30-10-00, ALL CORRECT. PRESSURIZATION TESTS WAS PERFORMED WITH BOTH ENGINES IAW MM 21-30-00, ALL CORRECT. DURING CABIN CHECK, THE SW (RADIO RACK) WAS CHANGED FROM VENTURY TO FAN POSITION, TESTED CORRECT.

Part: SHUTOFF VALVE — LEAKING (HYD SYSTEM) · airframe 42,318 hrs · 34,074 cycles

AIRCRAFT RETURN TO PLATFORM DURING TAXI, CREW SELECTED SLATS EXTEND AND THE HYDRAULIC QUANTITY LIGHT TURNED ON. MAINTENANCE DETECTED HYDRAULIC LEAK IN RT SYSTEM AND QUANTITY ZERO, SO THE SYSTEM WAS SERVICED AND HYDRAULIC PRESSURE WAS APPLIED AND THE LEAK WAS LOCATED AT THE RUDDER SHUTOFF VALVE, THIS VALVE WAS REPLACED IAW MM 27-20-09 TESTED CORRECT, ADDITIONALLY, WATER SEPARATORS OF BOTH AIR CONDITIONED PACKAGES WERE REPLACED IAW MM 21-20-02, TESTED CORRECT.

Part: SWITCH — FAILED (FUEL PRESSURE) · airframe 42,009 hrs · 33,878 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO CAPTAIN REPORTED THAT THE LT INLET FUEL LOW PRESSURE AND MASTER CAUTION LIGHTS TURNED ON. REPORT WAS DEFERRED IAW MEL 73-3. DURING OVERNIGHT CHECK AT MEX, MAINTENANCE PERSONNEL REPLACED THE LOW FUEL PRESSURE CAUTION SWITCH AND PERFORMED OPERATIONAL TEST AND LEAKS CHECK IAW MM 73-33-01, ALL CORRECT.

Part: A/C PACK — LEAKING · airframe 41,988 hrs · 33,860 cycles

AIR TURNED BACK DUE TO HIGH TEMPERATURE IN TAIL CONE, LIGHT TURNED ON AND RT ENGINE WITH LOW ACCELERATION. MAINTENANCE CORRECTED PNEUMATIC LEAKS IN THE LT AND RT AIR-CONDITIONED SYSTEMS IAW MM 36-20-02 AND MPCM 21-10-00; ADDITIONALLY, THE ACCELERATION CAMS AND THE BLEED VALVES WERE LUBRICATED IAW MM 73-20-01 AND MM 75-31-05, TESTED CORRECT IAW 71-00-00. AIRCRAFT LANDED WITH 57000 KILOGRAMS, SO IT WAS NOT NECESSARY AN OVERWEIGHT LANDING INSPECTION IAW MM 05-51-04.

Part: STRAKE — DAMAGED (RT SIDE) · airframe 40,177 hrs · 32,720 cycles

DURING TRANSIT CHECK, THE RIGHT FUSELAGE NOSE STRAKE WAS DETECTED DAMAGED WITH 1 INCH LENGTH X .7500 INCH WIDTH AND .1875 INCH OF DEPTH. RT FUSELAGE NOSE STRAKE WAS REPLACED IAW MM 53-30-01, TESTED CORRECT.

Part: DOOR — GROUND DAMAGE (PAX DOOR) · airframe 38,903 hrs · 31,941 cycles

DURING TRANSIT CHECK, AIRCRAFT WAS STRUCK ON THE MAIN PASSENGERS DOOR BY MOBIL STAIRS. AIRCRAFT WAS INSPECTED IAW SRM 51-02 AND DAMAGE WAS WITHIN LIMITS. DURING OVERNIGHT CHECK AT MEX, FINAL REPAIR WAS PERFORMED IAW SRM 51-02, FIG 1, ALL CORRECT.

Part: GCU — FAILED (RIGHT) · airframe 38,661 hrs · 31,800 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO AC CROSS TIE LIGHT TURNED ON. AT PLATFORM, THE RIGHT GCU WAS REPLACED IAW MM 24-20-04, TESTED CORRECT IAW MM 24-20-00.

Part: HYDRAULIC LINE — LEAKING (RIGHT SYSTEM) · airframe 38,463 hrs · 31,685 cycles

AIRCRAFT RETURNED FLIGHT, AFTER TAKEOFF AND LANDING GEARS UP, THE RIGHT HYDRAULIC FLUID QUANTITY WENT DOWN TO 2 QUARTS. AFTER LANDING, THE BRAKES TEMPERATURE REACHED 350 °C AND GOT STUCK. DURING MAINTENANCE REVISION A RIGHT HYDRAULIC SYSTEM LEAK WAS DETECTED IN AN AUXILIARY HYDRAULIC PUMP LINE. HYDRAULIC LINE, BRAKES AND WHEELS 1 AND 2, TRANSDUCER AND WATER SEPARATORS WERE REPLACED IAW MM 32-42-01 AND 21-20-00, RESPECTIVELY. OVERWEIGHT INSPECTION WAS PERFORMED IAW MM 05-51-00, BEING CORRECT. THE LANDING GEAR AND ENGINE WERE TESTED IAW 32-10-00 AND 71-00-01, RESPECTIVELY, ALL CORRECT.

Part: COMPUTER — FAILED (LEFT EPR) · airframe 35,932 hrs · 30,047 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF LEFT ENGINE EPR INDICATOR WAS OUT OF SERVICE. EPR TRANSMMITER WAS REPLACED IAW MM 77-11-02, ENGINE WAS TESTED, ALL CORRECT.

Part: FCU — FAILED (LT ENGINE) · airframe 35,833 hrs · 2,991 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF DURING TAXING, THE LEFT ENGINE GENERATOR WENT OUT OF ITS BAR TURNING ON THE MASTER CAUTION LIGHT AND THE LEFT OIL PRESSURE WAS LOW (30 PSI). DURING ENGINE CHECK THE FCU DID NOT MAINTAIN THE RPMS IN IDLE AND DECREASED TO 32 RPM OF N2. LEFT FCU WAS REPLACED IAW MM 73-20-01 AND ENGINE WAS TESTED IAW MM 71-00-00, ALL CORRECT.

Part: TRANSMITTER — DIRTY (OIL PRESSURE) · airframe 35,807 hrs · 29,973 cycles

AIRCRAFT RETURNED TO PLATFORM. DURING PUSH BACK, LT ENGINE STARTED NORMALLY AND AFTER RT ENGINE STARTED, THE LT ENGINE PRESSURE DECREASE TO 35 PSI’S. DURING REVISION WAS DETECTED OVERFILL OIL. THE EXCESS OIL WAS DRAINED AND PRESS OIL TRANSMITTER CONNECTOR WAS CLEANED. THE LT ENGINE WAS TESTED AND THE PRESSURE WAS STABILIZED AT 40 PSI’S WITH LIGHT TURNED ON AND LT GENERATOR WITH LOW FREQUENCY AND VOLTAGE WITH FLUCTUATIONS IN LT BAR, ACCELERATED TO 1.65 AT EPR AND VOLTAGE AND FREQUENCY STABILIZED WITH OIL PRESSURE ON 42 PSI. DURING OVERNIGHT SERVICE THE LT ENGINE OIL PRESSURE WAS ADJUSTED IAW MM AND OPERATIONAL TEST WAS PERFORMED IAW MM , ALL CORRECT.

Part: STARTER — FAILED (LEFT ENGINE) · airframe 35,734 hrs · 29,928 cycles

DURING ENGINES STARTING, CAPTAIN REPORTED THAT THERE WAS NOT LEFT ENGINE PARAMETERS INDICATION. THE PNEUMATIC PRESSURE AND STARTER VALVE OPENING WERE VERIFIED IAW MM 80-00-00, BEING CORRECT, SO IT WAS DETERMINED THE STARTER REPLACEMENT. THE LEFT ENGINE WAS STARTED IAW 80-10-01, TESTED CORRECT.

Part: FUEL CONTROL — FAILED (LT ENGINE) · airframe 35,514 hrs · 28,778 cycles

CAPTAIN REPORTED LEFT ENGINE WITH OSCILLATIONS IN ALL ITS PARAMETERS. THE COMBUSTION CHAMBER WAS SERVICED AND WATER TRAMP WAS DRAINED IAW 72-40-01, ALL CORRECT. DURING OVERNIGHT SERVICE LEFT FCU WAS REPLACED IAW MM 73-12-01 AND THE LEFT ENGINE WAS TESTED IAW MM 71-00-00, ALL CORRECT.

Part: IGNITION UNIT — FAILED (RIGHT) · airframe 34,727 hrs · 29,290 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF DURING ENGINES STARTING, IGNITION SYSTEM FAILED IN BOTH ENGINES. DURING MAINTENANCE REVISION WAS DETECTED THAT 115VAC WAS NOT AVAILABLE AND SWITCH FASTENERS LOOSEN IN TWO LINES. FASTENERS WERE TIGHTENED AND ENGINES STARTING WAS CORRECT. DURING TRANSIT AT MEX, IGNITION BOX WAS REPLACED IAW MM 74-10-01, TESTED CORRECT.

Part: IGNITION UNIT — FAILED (LT ENGINE) · airframe 34,396 hrs · 29,068 cycles

DURING ENGINES STARTING, LT ENGINE DID NOT START. CIRCUIT BREAKER WAS CHECKED AND EDP TEST WAS PERFORMED IAW MM 72-21-01, ALL CORRECT. LT ENGINE START WAS PERFORMED AND FAIL CONTINUE, EGT AND RPM INDICATIONS WERE NOT SHOWN. IGNITION BOX AND EXCITER PLUG CABLE WERE REPLACED IAW MM 74-10-01 AND 74-20-01, RESPECTIVELY, TEST CORRECT.

Part: TAB — DAMAGED (ELEVATOR) · airframe 33,383 hrs · 28,369 cycles

DURING OVERNIGHT SERVICE LIGHTING STRIKE DAMAGE WAS DETECTED IN LT ELEVATOR TAB, WITH 1 INCH OF DIAMETER. LIGHTING STRIKE INSPECTION WAS PERFORMED IAW MM 05-53-00 AND ELEVATOR TAB WAS REPLACED IAW MM 27-30-03, TEST CORRECT.

Part: COMPUTER — FAILED (ENGINE) · airframe 32,694 hrs · 27,894 cycles

AIRCRAFT SUSPENDED TAKE OF AT 100 KTS AND RETURNED TO PLATFORM AS A CONSEQUENCE OF THE RIGHT ENGINE DID NOT REACH THE TAKE OF THRUST, IT ONLY REACHED 1.6 OF EPR. AT MEX PLATFORM, TECHNICAL PERSONNEL PERFORMED AN ACCELERATION TEST REACHING ONLY 1.7 OF EPR'S. AIRCRAFT WAS SENT TO THE HANGAR AND DURING OVERNIGHT SERVICE THE RIGHT ENGINE EPR'S COMPUTER ASSY WAS REPLACED IN ACCORDANCE WITH MM 77-11-02. ENGINE RUN TEST WAS PERFORMED IN ACCORDANCE WITH MM 72-00-00, ALL CORRECT.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 32,545 hrs · 27,802 cycles

AIRCRAFT RETURNED OF FLIGHT AS A CONSEQUENCE OF DURING CLIMB AT 33,000 FEET, AFT CARGO DOOR AND AFT STAIRWAY DOOR LIGHTS TURNED ON AND CABIN STARTED TO DEPRESSURIZE. CARGO COMPARTMENT DOORS WERE CHECKED, ALL CORRECT. AIRCRAFT WAS PRESSURIZED WITH A GROUND PNEUMATIC UNIT NO LEAK WAS FOUND. ENGINES PRESSURIZATION TESTS WAS PERFORMED, ALL CORRECT. AS A PREVENTIVE ACTION PRESSURIZATION CONTROLLER NR ONE WAS REPLACED. DURING OVERNIGHT SERVICE TESTS TO PRESSURIZATION SYSTEM WERE PERFORMED IN ACCORDANCE WITH MM 21-32-03, 52-31-00 AND 52-63-00, ALL CORRECT.

Part: BUNGEE CYLINDER — DAMAGED (NLG)

CAPTAIN REPORTED THAT THE NLG RED LIGHT TURNE ON AND OFF SEVERAL TIMES DURING CLIMB, CRUISE AND DESCENT. AT PLATFORM IT AWS PERFORMED A BITE TO THE PROXIMITY SWITCH UNIT IAW MM. TEST, OK, AFTER CAPTAIN REPORTED THAT DURING CLIMB, A LOUD NOISE WAS HEARD IN THE NLG DURNG ITS RETRACTION. THE AIRCRAFT WAS CARRIED TO HANGAR TO ATTEND THE REPORT. NLG PROXIMITY SENSORS AND BUNGEE SPRINGS WERE REPLACED AND SYSTEM TESTED IAW MM, ALL CORRECT.

Part: DUCT — BROKEN (TAIL CONE)

AIRCRAFT RETURNED DUE TO LIGHT OF TAIL CONE HIGH TEMPERATURE CAME ON, AFTER 3 MINUTES THAT THE ANTI-ICE PROTECTION WAS USED. AIRCRAFT WAS CARRIED TO THE HANGAR TO ATTEND REPORT. AT OVERNIGHT SERVICE, THE ANTI-ICE DUCT ASSY WAS REPLACED AND SYSTEM WAS TESTED IAW MM. HARD LANDING INSPECTION WAS PERFORMED IAW MM, DETECTING A FUEL LEAKAGE IN THE CENTRAL LOWER SECTION OF THE FUEL TANK FRONT SPAR. THE FUEL TANK WAS SEALED IAW SRM, ALL CORRECT.

Part: BLADE — DAMAGED (RT ENGINE)

AIRCRAFT AIR TURN BACK, DURING CLIMB THE RIGHT ENGINE STALLED. AT PLATFORM, IT WAS DETECTED DAMAGES IN FOUR C1 BLADES AND IN 2 C2 BLADES. INSPECTOR AND TECHNICAL PERSONNEL WERE SENT TO EVALUATE THE DAMAGES AND START THE CORRECTIVE ACTIONS. ENGINE WAS REPLACED. (M)

Part: CONTROL VALVE — MALFUNCTIONED (ANTI SKID SYS)

AIRCRAFT RETURN TO PLATFORM DUE TO DURING TAXI THE FOURTH ANTI-SKID LIGHT TURNED ON. CIRCUIT BREAKERS WERE RESET AND ANTI-SKID BOX CONNECTORS WERE CLEANED NON REPRODUCING THE FAIL. AFTER WORKS, CAPTAIN REPORTED THE ANTISIDE LIGHTS TURNED ON AGAIN. DURING CHECK, IT WAS DETECTED THAT THE DUAL PRESS CONTROL VALVE WAS OUT OF SERVICE. IT WAS REPLACED IAW MM 32-43-03, ALL TESTS CORRECT. (M)

Part: BATTERY — OVERHEATED (E/E BAY)

FLT 519 - MEX-VSA - AIRCRAFT ARRIVED WITH CAPTAIN REPORT OF HOT BATTERIES AND SMOKE UNDER THE FUSELAGE. DURING REVISION DETECTED BATTERIES AND BATTERIES CHARGER WITH OVERHEAT. THE BATTERIES AND BATTERY CHARGER WAS REPLACED IAW MM 24-30-01/02, ALL CORRECT. (M)

Part: EXCITER — FAILED (ENGINE)

AIRCRAFT RETURNED TO PLATFORM DUE TO AN IGNITION FAILURE IN RT ENGINE. AT PLATFORM THE TECH TRIED TO START THE ENGINE BUT THERE WAS TROUBLE WITH THE EXCITER IGNITION BOX. UNIT WAS REPLACED IAW MM.

Part: ENGINE — FAILED (APU)

CREW REPORTED THE PRESENCE OF SMOKE IN CABIN DUE TO AN OIL LEAK IN THE LT A/C PACK. THE MAGNETIC CAP OF THE COOLING TURBINE HAD METAL CHIPS, A/C PACK WAS INOPERATIVE PER MEL. APU WAS REPLACED IAW MM, FOR LACK OF OIL AND LEAKAGE THROUG THE LOAD CONTROL VALVE. THE CHIP DETECTOR OF THE COOLING TURBINE WAS VERIFIED AND FOUND IT OK. AFTER APU REPLACEMENT, BOTH PACKAGES WERE WORKING OK.

Part: FUEL CONTROL — FAILED (ENGINE)

FLT 419 - MEX-VSA - PILOT REPORTED A MISALIGNMENT OF MORE THAN .5 INCH BETWEEN THROTTLE LEVERS. ROD END OF FCU WAS REPLACED AND RIGGING AND OPERATIONAL TEST TRIM, WERE PERFORMED IAW MM 71-00-01. (M)

Part: COMPUTER — FAILED (COCKPIT)

FLT 478 - MZT-HMO - THE CAPTAIN REPORT THAT DURING CLIMB MZT-HMO, THE AIRCRAFT HAD HEADING PROBLEMS. THE FO'S WAS OUT OF SERVICE AND THE FLIGHT DIRECTOR BARS WERE LOST WHEN EFIS BOTH WAS SELECTED ON 1, THE PROBLEM WAS INTERMITTENT DURING ALL THE FLIGHT. AT HMO, WERE VERIFIED THE MEMORIES OF DFGC NR 1 AND 2 AND THE AHRS NR 2 WAS CHANGED. IT WAS TESTED IAW MM 24-20-00. (M)

Part: CONTROL VALVE — FAILED (MLG ANTI-SKID)

HMO-LAS - WHEN LANDING GEAR GOT DOWN, ANTI-SKID IGHTS TURNED ON. AS CONSEQUENCE OF SPARE PARTS MISSING, AN AIRCRAFT CHANGE TOOK PLACE. LEFT ANTI-SKID DUAL CONTROL VALVE WAS REPLACED IAW MM 32-43-02, TESTS WERE PERFORMED OK.