N803ML

Part: ENGINE — MALFUNCTIONED (RIGHT)

ACFT REJECTED TAKE OFF 70 KNOT DUE TO RT ENGINE DID NOT ACCELERATE (EPR 1.14). MX PERSONNEL CHECKED THE RT ENGINE IAW MM 72-00-00 PAGE 501, ALL CORRECT. ADDITIONALLY, A HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-57-00, NO DAMAGES WERE FOUND. DURING OVERNIGHT CHECK, MX PERSONNEL PERFORMED SLOW ACCELERATION TROUBLE SHOOTING IAW 72-00-04, ALL CORRECT.

Part: PRBC — MALFUNCTIONED (RT ENGINE)

ACFT REJECTED TAKE OFF AT 70 KNOTS DUE TO RT ENGINE DID NOT ACCELERATE. MX PERSONNEL REPLACED PRBC`S IAW MM 75-31-01 AND FCU IAW 73-20-01. ADDITIONALLY THE PS3 WAS VERIFIED AND CLEANED, THE BLEED VALVES WERE LUBRICATED IAW 75-31-05 AND TRIM BOTH ENGINES WAS PERFORMED IAW MM 71-00-00, ALL CORRECT. AS A COMPLIMENTARY ACTION, A HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-57-00, NO DAMAGES WERE FOUND.

Part: BLADES — DAMAGED (ENGINE) · airframe 50,524 hrs · 29,997 cycles

DURING OVERNIGHT CHECK, 10 FAN BLADES OF THE RT ENG WERE DETECTED WITH DENTS AND LOSS OF MATERIAL DUE TO AN FOD. MAINTENANCE PERFORMED A BOROSCOPIC INSP IAW MM 72-00-00 AND NO ADDITIONAL DAMAGES WERE FOUND; THE 10 DAMAGED BLADES WERE REPAIRED IAW MM 72-33-21, AFTER REPAIRS, 2 BLADES WERE RESTRICTED TO ONLY 24 HOURS CONTINUE-IN-SERVICE CONDITION, SO DURING THE NEXT OVERNIGHT CHECK AT MEX, THE C1 DISK WAS REPLACED AND TESTED IAW MM 72-33-02 AND 71-00-00, ALL CORRECT.

Part: POWERPLANT — OVERSPEED (RIGHT) · airframe 49,476 hrs · 29,241 cycles

CAPTAIN REPORTED WINDSHEAR DURING APPROACH AND ATS DISCONNECTED, SPEED DECREASED, SO AUTOTHOTTLES WERE SET TO THE MAXIMUM POWER. AT PLATFORM, MAINTENANCE PERSONNEL DOWNLOAD THE ENGINES INFORMATION FROM THE MINIQAR DETECTING THAT THE RT ENGINE HAD VALUES OF N1 103.4 WITH AN EPR OF 2.16, OUT OF LIMITS IAW MM 72-00-00. RT ENGINE WAS REPLACED IAW MPCM 71-00-02 AND OPERATIONAL TEST WAS PERFORMED IAW MPCM 71-00-01, ALL CORRECT.

Part: TURBINE BLADES — CRACKED (LT ENGINE) · airframe 48,934 hrs · 28,891 cycles

DURING LT ENGINE BOROSCOPIC INSPECTION WAS DETECTED A FIRST STAGE TURBINE BLADE WITH A CRACK OF 0.500 INCH IN TIP. ENGINE WAS REPLACED IAW MM 71-00-02 AND OPERATIONALLY TESTED IAW MM 71-00-01, ALL CORRECT.

Part: UNKNOWN — UNKNOWN (ENGINE) · airframe 48,163 hrs · 28,418 cycles

AIRCRAFT REJECTED TAKEOFF AT 75 KNOTS DUE TO LT ENGINE REACHED ONLY 1.6 EPR WHILE RT ENGINE REACHED 2.04 EPR WITH N1 100 PERCENT, SO AIRCRAFT WAS SENT TO THE HANGAR AND MAINTENANCE PERSONNEL CHECKED ENGINE INLET/OUTLET, CONTROLS, PT2 AND PT7 LINES AND MANIFOLD IAW PROPER INSTALLATION, ALL CORRECT. LT ENGINE RUNNING TEST WAS PERFORMED IAW MM 71-00-00 AT 1.65, 1.80 AND 2.06 EPR'S, BEING SATISFACTORY. ADDITIONALLY, AUTO THROTTLE TEST WAS PERFORMED REACHING 2.06 EPR IAW MM 71-00-00 AND MPCM 71-00-01.

Part: ENGINE — OVERSPEED (LEFT) · airframe 48,168 hrs · 28,421 cycles

AIRCRAFT REJECTED TAKEOFF AT 77 KNOTS DUE TO LT ENGINE REACHED ONLY 1.6 EPR WITH N1 104 PERCENT. AIRCRAFT WAS SENT TO THE HANGAR AND ENGINE WAS REMOVED AND SENT TO THE SHOP. THE NRC A0111096 WAS ISSUED TO CHECK ENGINE PT2 AND PT7 LINES AND MANIFOLD BY LEAKS IAW MM 72-00-03, DETECTING A PT7 LINE LEAKING AND DELAMINATED, SO IT WAS REPLACED. ENGINE OVERSPEED AND OPERATIONAL TESTS WERE PERFORMED IAW MM 72-00-00 PAGE 516 PARAGRAPH 2H (3)(D), DETERMINING REPLACEMENT OF C1 IAW MM 72-00-00 AND MPCM 71-00-01, TESTED CORRECT. ADDITIONALLY, CHIP DETECTORS, EXHAUST PRESSURE PROBES, THROTTLE ADJUSTMENT AND ENGINE TRIM WERE PERFORMED IAW MM 77-11-04, 76-00-00 AND 71-00-00, ALL CORRECT. AS A PRECAUTIONARY ACTION, LT EPR TRAN

Part: SEAL — LEAKING (LT WING PANEL) · airframe 48,088 hrs · 28,371 cycles

DURING TRANSIT CHECK, A FUEL LEAK WAS DETECTED IN AN UPPER PANEL OF THE LT WING. MAINTENANCE PERSONNEL RELOCATED THE SEAL AND APPLIED SEALANT IAW SRM 51-20-04 AND 51-22-2A, LEAK WAS CORRECTED. AS A PRECAUTIONARY ACTION, DURING OVERNIGHT CHECK THE SEAL WAS REPLACED, SEALANT WAS APPLIED AND A LEAK TEST WAS PERFORMED IAW MM 28-10-01 PAGE 601, ALL CORRECT.

Part: UNKNOWN — UNKNOWN (GENERATOR) · airframe 47,836 hrs · 28,212 cycles

CAPTAIN REPORTED THAT A GEN LOW AND TAIL COMP TEMP HIGH LIGHTS TURNED ON. DURING MAINTENANCE CHECK, THE TAIL CONE COMPARTMENT WAS DETECTED WITH HIGH TEMPERATURE AND THE FIRE EXTINGUISHER CONTAINER ACTIVATED. AIRCRAFT WAS SENT TO THE HANGAR AND RT FIRE EXTINGUISHER CONTAINER WAS REPLACED IAW MM 26-20-01 AND AIR CONDITIONING, PNEUMATIC AND ANTI-ICE SYSTEMS WERE CHECKED BY LEAKS IAW MM 21-10-00, 30-10-00 AND 35-10-00, DETECTING A LEAK IN THE APU CONTROL VALVE DUE TO CLAMPS WERE DAMAGED. CLAMPS WERE REPLACED AND SYSTEM TESTED BY LEAKS IAW MM 21-10-00, ALL CORRECT.

Part: CSD — FAILED (LT SIDE) · airframe 47,231 hrs · 27,830 cycles

AIRCRAFT RETURNED DUE TO HIGH TEMPERATURE IN THE LT CSD AND APU DID NOT START AT 34,000 FEET. DURING OVERNIGHT CHECK, LT CSD AND HEAT EXCHANGER WERE REPLACED IAW MM 24-10-01 AND 24-10-03, AS WELL AS TRIM AND TEST WERE PERFORMED TO THE APU IAW MM 49-00-00, ALL CORRECT.

Part: SKIN — DAMAGED (SERVICE DOOR) · airframe 46,682 hrs · 27,490 cycles

DURING TRANSIT CHECK, AIRCRAFT HAD A STRIKE ON THE FORWARD SERVICE DOOR BY A CATERING SERVICE TRUCK, PRODUCING A DAMAGE OF 4 X 3 INCHES LENGTH AND 0.085 INCHES DEPTH, BETWEEN LONGERONS 20 AND 21 AND STATIONS 168 THROUGH 180. THE DAMAGED AREA WAS INSPECTED BEING WITHIN LIMITS, SO DAMAGE WAS REPAIRED IAW SRM 53-04, FIGURE 38, PAGE 11, CONDITION 1B.

Part: CONNECTOR — CONTAMINATED (FIRE DETECTION) · airframe 46,678 hrs · 27,486 cycles

AIRCRAFT RETURNED, (FIRE DETECTOR LOOP A), (APU FIRE) AND (LT CSD HIGH TEMPERATURE) LIGHTS TURNED ON, AUDIBLE ALARM WAS ACTIVATED, LT GENERATOR WAS INOPERATIVE AND CAPTAIN ACTIVATED FIRE EXTINGUISHER BOTTLES. AIRCRAFT WAS SENT TO THE HANGAR AND FIRE DETECTION SYSTEM WAS CHECKED DETECTING DETECTORS A AND B TERMINALS WITH EXCESIVE OIL AND DIRTY. CLEANING AND TEST WERE PERFORMED IAW MM 26-10-00, ALL CORRECT. DURING OVERNIGHT CHECK AND AS A PRECAUTIONARY ACTION, THE DETECTOR D1-6 OF LOOP A AND CONNECTORS P1-755 AND P1-751, WERE REPLACED IAW MM 26-10-00 AND 26-12-00, TESTED CORRECT.

Part: COUPLING — DAMAGED (LT ENGINE) · airframe 46,601 hrs · 27,434 cycles

AIRCRAFT RETURNED TO PLATFORM, LT ENGINE DID NOT HAVE TURN IN N1, NEITHER PNEUMATIC SUPPLY AND THE STARTER VALVE LIGHT OPERATING CORRECT. DURING MAINTENANCE REVIEW, THE ENGINE STARTER COUPLE WAS FOUND DAMAGED. THE COUPLE WAS REPLACED IAW MM 80-00-00, TESTED CORRECT. DURING TRANSIT CHECK AT MEX, THE LT ENGINE STARTER AND SHUTOFF START VALVE WERE REPLACED IAW MM 80-10-01, TESTED CORRECT.

Part: COUPLING — DAMAGED (LT ENGINE) · airframe 27,430 hrs · 46,595 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO THE LT ENGINE DID NOT HAVE TURN IN N2. DURING MAINTENANCE REVIEW, THE ENGINE STARTER COUPLE WAS FOUND DAMAGED. THE COUPLE WAS REPLACED IAW MM 80-00-00, TESTED CORRECT.

Part: ENGINE — MALFUNCTIONED (LEFT) · airframe 45,934 hrs · 27,003 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF DURING LEFT ENGINE START THE TEMPERATURE REACHED 510 DEGREES CELSIUS. DURING MAINTENANCE REVISION, FUEL WAS IN ENGINE CHAMBER NR 1. OVER TEMPERATURE INSPECTION WAS PERFORMED IAW MM 72-00-00, AND ENGINE STARTED CORRECTLY AT 370 DEGREES CELSIUS.

Part: WARNING SYSTEM — MALFUNCTIONED (LANDING GEAR) · airframe 45,865 hrs · 26,955 cycles

AIRCRAFT RETURNED OF FLIGHT AS A CONSEQUENCE OF -L & R LANDING GEAR- LIGHTS REMAINED ON WITH MAIN LANDING GEAR LEVER IN UP POSITION. PROXIMITY SWITCH COMPUTER AND D1-25 AND D1-26 SENSORS WERE TESTED AND CHECKED IAW MM 32-60-04 AND MM 32-31-04, RESPECTIVELY, BEING CORRECT. AIRCRAFT LANDED WITH 55418 POUNDS OF FUEL, SO IT WAS NOT NECESSARY THE OVERWEIGHT INSPECTION DUE THAT THE MAXIMUM LANDING WEIGHT IS 58060 IAW DISPATCH MANUAL 5-3-1/2. DURING EXTERNAL REVIEW WERE DETECTED THE MAIN LANDING GEAR LOCKS INSTALLED. INSTALLED DURING MAINTENANCE ACTIVITIES AT HANGAR. LOCKS WERE REMOVED IMMEDIATELY AND AIRCRAFT WAS DISPATCHED.

Part: CIRCUIT BREAKER — FAILED · airframe 45,572 hrs · 26,770 cycles

AIRCRAFT AIR TURNED BACK AS A CONSEQUENCE OF LOST OF INDICATION OF THE RIGHT OIL PRESS, OIL TEMP, FUEL TEMP, HYD QTY, HYD PRESS AND FLAPS. THE CIRCUIT BREAKERS ASSOCIATED WITH THE FAILURE WERE CHECKED, FOUND THEM IN CLOSE POSITION. THE CIRCUIT BREAKER T-34 OF THE RIGHT SYSTEM DISPLAY PANEL WAS RESEATED AND THE FAILURE WAS CORRECTED. CIRCUIT BREAKER T-34 WAS REPLACED IAW M/M 20-50-06 AND THE SYSTEM WAS TESTED IAW M/M 31-61-00, BEING ALL CORRECT. DURING OVERNIGHT CHECK THE SYSTEM WAS TESTED IAW M/M 31-61-00, ALL CORRECT.

Part: FCU — LEAKING (APU) · airframe 45,423 hrs · 26,680 cycles

A FUEL LEAK WAS DETECTED DURING APU STARTING. APU WAS DEFERRED IAW MM 49-1 AND AFT ACCESSORIES AREA WAS CHECKED, BEING CORRECT. DURING OVERNIGHT CHECK, THE FUEL CONTROL UNIT AND THE AIR CONDITIONING WATER SEPARATORS WERE REPLACED IAW MM 49-30-01 AND 21-20-02, TESTED CORRECT.

Part: WARNING HORN — ACTIVATED (STAB TRIM) · airframe 44,652 hrs · 26,182 cycles

DURING GROUND TESTS, THE CAUTION LONG TRIM STABILIZER WAS OUT OF RANGE ACTIVATING THE TAKEOFF ALARM. AIRCRAFT WAS SENT TO THE HANGAR AND THE TRIM STABILIZER WAS TESTED IAW MM 27-40-12 AND DURING OVERNIGHT CHECK, THE TAKEOFF ALARM SYSTEM WAS VERIFIED IAW MM 27-00-00 PAGE 214 STEP B, TESTED CORRECT.

Part: COUPLER — FAILED (RT ENGINE) · airframe 44,374 hrs · 26,003 cycles

DURING RIGHT ENGINE STARTING, THE RIGHT ENGINE DID NOT HAVE TURN IN N1 AND N2 AND START VALVE LIGHT TURNED ON. THE ADAPTER SHAFT STARTER WAS REPLACED IAW MM 80-10-01 PAGE 204, TESTED CORRECT. DURING OVERNIGHT CHECK, OPERATIONAL TEST WAS PERFORMED IAW MM 71-00-01, TESTED CORRECT.

Part: ENGINE — MAKING METAL (RIGHT) · airframe 43,731 hrs · 25,595 cycles

AIRCRAFT RETURNED TO PLATFORM, DURING RT ENGINE START, THE RT START VALVE OPEN LIGHT FLASHED AT 40 PERCENT RPM, N2 DECREASED TO 35 PERCENT AND RETURNED TO 50-56 PERCENT, 20 SECONDS AFTER THAT ENGINE STOPPED. AIRCRAFT WAS SENT TO THE HANGAR AND DURING MAINTENANCE REVISION WAS DETECTED METAL FLAKES IN THE RT ENGINE GEARBOX. THE RT ENGINE WAS REPLACED IAW MM 71-00-00, TESTED CORRECT.

Part: AUGMENT VALVE — OUT OF ADJUST (FIRE BOTTLE) · airframe 43,731 hrs · 25,595 cycles

AIRCRAFT RETURNED TO PLATFORM, DURING THE LT ENGINE START, THE FIRE EXTINGUISHER AGENT 2 LOW LIGHT TURNED ON. THE FIRE EXTINGUISHER POSITION 2 WAS REPLACED IAW MM 26-20-01; LT AUGMENTING VALVE WAS ADJUSTED IAW MM 36-10-01; THE CLAMS OF AUGMENTING VALVE AND REGULATOR VALVE WERE REPLACED IAW MM 20-10-11 AND LEAKS CHECK WAS PERFORMED IAW MM 21-10-00, MM 30-10-00 AND MM 36-10-00, TESTED CORRECT.

Part: PROXIMITY SWITCH — OUT OF ADJUST (PAX DOOR) · airframe 43,343 hrs · 25,388 cycles

AIRCRAFT RETURNED TO PLATFORM, PASSENGER DOOR LIGHT COME ON. PASSENGER DOOR TEST WAS PERFORMED WITH A COMPLETE OPEN/CLOSE CYCLE IAW MM, BEING CORRECT. DURING OVERNIGHT SERVICE, THE GAP BETWEEN PRINTED CIRCUIT AND PROXIMITY SWITCH OF PASSENGER DOOR WAS VERIFIED IAW MM 52-70-03, BEING CORRECT.

Part: ENGINE — MALFUNCTIONED (RIGHT) · airframe 4,288 hrs · 25,112 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF CAPTAIN REPORTED DID NOT HAVE ACCELERATION IN RIGHT ENGINE. DURING CHECK BOTH ENGINES WERE DETECTED STABILIZED AT 52 PERCENT OF N2, TESTS WERE CORRECT. AIRCRAFT WAS SENT TO THE HANGAR AND TRIM TO BOTH ENGINES WAS PERFORMED IAW MM 71-00-00, TESTED CORRECT.

Part: CADC — FAILED (LEFT SIDE) · airframe 42,840 hrs · 25,086 cycles

TECHNICAL PERSONNEL INFORMED THAT DURING TRANSIT CHECK AIR SPEED FLAG WAS SHOWN IN LEFT AIR SPEED INDICATOR AND ALTIMETER. TESTS WERE PERFORMED AND FAIL CONTINUED. CADC NR 1 WAS REPLACED IAW MM 34-16-01, TESTED CORRECT.

Part: CADC — FAILED (LEFT SIDE) · airframe 42,826 hrs · 25,076 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF ADC NR 1 FAILURE, AUTO SLATS FAIL LIGHT TURNED ON AND RIGHT EFIS LOST INFORMATION. TESTS WERE PERFORMED CONFIRMING THE FAILURES. ADC NR 1, LEFT STALL COMPUTER AND RIGHT AHRU WERE REPLACED IAW MM 34-16-01, 34-19-02 AND 34-21-10, ALL TESTS WERE CORRECT.

Part: VALVE — MALFUNCTIONED (RT ENGINE) · airframe 42,092 hrs · 24,653 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF AFTER ENGINES STARTED, EICAS MESSAGES "L ENG BLEED OFF" AND "PACK BITE" WERE SHOWN. CAPTAIN REPORTED THAT PURGE VALVE OF RIGHT ENGINE DID NOT OPEN, RESTARTED RIGHT ENGINE AND THE PURGE VALVE OPENED NORMALLY. DURING OVERNIGHT SERVICE THE FIM 36-10-00 PROCEDURE WAS PERFORM AND SYSTEM WAS TESTED IAW MM 36-10-09, ALL CORRECT.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 40,993 hrs · 23,926 cycles

AIRCRAFT RETURNED TO PLATFORM, LT HYDRAULIC PUMP FAILED. HYDRAULIC PUMP SOLENOID WAS CHECKED AND CIRCUIT BREAKERS WERE RESEATED AND FAIL CONTINUED. LT HYDRAULIC PUMP WAS REPLACED IAW MM 29-01-02, TEST CORRECT.

Part: SERVO VALVE — LEAKING (HYD SYSTEM) · airframe 40,627 hrs · 23,661 cycles

DURING TRANSIT CHECK, HYDRAULIC LEAKAGE WAS DETECTED IN INTERIOR DOUBLE SERVO VALVE. IT WAS REPLACED IAW MM32-43-02, TEST WERE CORRECT.

Part: WARNING LIGHT — ILLUMINATED (LT ENGINE) · airframe 40,494 hrs · 23,571 cycles

AIRCRAFT RETURNED TO PLATFORM, LT ENGINE WITH LOW POWER AND IN IDLE POSITION TEMPERATURE REACHED 485 DEGREE (C) OUT OF LIMITS. AIRCRAFT WAS SENT TO THE HANGAR AND DURING OVERNIGHT SERVICE, THRUST LEVER TRIM WAS CHECKED IAW MM 76-11-00, LT ENGINE BLEED VALVES WERE LUBRICATED IAW MM 75-30-00, THERMOCOUPLE NR 4 WAS REPLACED IAW MM 77-21-03 AND TRIMMING WAS PERFORMED IN BOTH ENGINES IAW MM 71-00-01, TESTS CORRECT.

Part: PRBC — FAILED (LT SIDE) · airframe 40,427 hrs · 23,526 cycles

DURING TRANSIT CHECK WAS DETECTED HIGH TEMPERATURE ON LT ENGINE, REACHED 482 DEGREE F. ENGINE RUNNING WAS PERFORMED TO VERIFY EGT INDICATION APPLYING PNEUMATIC AND ELECTRICAL CHARGES GETTING MAXIMUM TEMPERATURE INDICATION OF 445 DEGREE F, BEING WITHIN LIMITS IAW MM 71-00-01. DURING OVERNIGHT SERVICE, LT PRBC AND P AND D VALVE WERE REPLACED IAW MM 75-31-01 AND 73-13-05, TESTS CORRECT.

Part: WHEEL — DAMAGED (NLG) · airframe 40,295 hrs · 23,435 cycles

DURING TRANSIT CHECK, CAPTAIN REPORTED STRONG VIBRATION IN NOSE LANDING GEAR. BOTH NOSE LANDING GEAR WHEEL WERE REPLACED IAW MM 32-40-00, ALL CORRECT.

Part: BLADE — DAMAGED (LT ENGINE COMPR) · airframe 40,288 hrs · 23,429 cycles

DURING TRANSIT CHECK, LT ENGINE BLADE WAS DETECTED WITH DAMAGE FROM FOD. BLADE WAS REPAIRED IAW MM 72-33-21, ALL CORRECT.

Part: COMPUTER — FAILED (AHRU) · airframe 40,188 hrs · 23,367 cycles

AIRCRAFT RETURNED TO PLATFORM, DURING TAXING AHRU NR 2 FAILED. AHRU WAS REPLACED IAW MM 34-21-10, TEST CORRECT. DURING OVERNIGHT SERVICE SYSTEM WAS CHECKED, ALL CORRECT.

Part: GYRO — FAILED (COCKPIT) · airframe 40,161 hrs · 23,347 cycles

CAPTAIN REPORTED THAT DURING FLIGHT UNTIL APPROACH, RDMI AND ND WITH DIFFERENCE BETWEEN 30-40 DEGREES. DURING TRANSIT CHECK AT CUU, AHRU NR 1 WAS REPLACED IAW MM 34-21-10, TEST CORRECT. AIRCRAFT WAS DISPATCHED AND RETURNED OF FLIGHT, DFGC AND AHRU NR 2 FAILED AND FLIGHT DIRECTOR BUSES IN BOTH PFD´S AND FMA´S WITHOUT INFORMATION. AFTER LANDING, AHRU INFORMATION WAS RECOVERED, AHRU NR 2 WAS REPLACED, TEST CORRECT. DURING OVERNIGHT SERVICE, DFGC TEST WAS PERFORMED IAW MM 22-01-05, ALL CORRECT.

Part: AHRS — FAILED (NR 1) · airframe 40,161 hrs · 23,347 cycles

AIRCRAFT RETURNED, AHRU NR 1 FAILED. AIRCRAFT WAS DISPATCHED IAW ABNORMAL PROCEDURES MANUAL 10-4. DURING OVERNIGHT SERVICE, MAGNETIC FLOW VALVE WAS REPLACED IAW MM 34-21-06, TEST CORRECT.

Part: FCU — FAILED (NR 2 ENGINE) · airframe 39,658 hrs · 23,019 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF HIGH TEMPERATURE AND EGT OSCILLATIONS ON ENGINE NR 2. AIRCRAFT WAS SENT TO THE HANGAR. THE LEFT FUEL CONTROL UNIT (FCU) WAS REPLACED IAW MM 73-20-01, TEST CORRECT.

Part: WARNING HORN — ACTIVATED (COCKPIT) · airframe 39,352 hrs · 22,815 cycles

AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF TAKEOFF ALARM ACTIVATED. TECHNICAL PERSONNEL PERFORMED TESTS TO THE PROXIMITY SWITCH STALL COMPUTER AND STATUS TEST PANEL, BEING ALL CORRECT. DURING OVERNIGHT SERVICE AT MEX WIRING WAS REPAIRED ON S30-111 LEAD (PIN 29X) IN ACCORDANCE WITH MM 27-52-00, ALL CORRECT.

Part: CLAMP — LEAKING (BLEED AIR) · airframe 39,252 hrs · 22,758 cycles

DURING TRANSIT CHECK WAS DETECTED HIGH TEMPERATURE ON TAIL CONE. AIRCRAFT WAS SENT TO THE HANGAR AND DURING OVERNIGHT SERVICE AUGMENTATION VALVE AND REGULATOR PRESSURE VALVE CLAMPS WERE REPLACED IAW MM 20-10-11, GASKET AND NIPPLE OF 13A STAGE BLEED VALVE WERE REPLACED IAW MM 20-10-13, ENGINE RUN WAS PERFORMED AND TEST CORRECT IAW MM 71-00-00. OVER TEMPERATURE TAIL CONE LIGHT WAS CORRECT.

Part: SWITCH — MALFUNCTIONED (HYDRAULIC SYS)

DURING TRANSIT CHECK, HYDRAULIC LEAKAGE WAS DETECTED IN THE SWITCH S1-168, SUCH SWITCH WAS BEHEADED. THE SWITCH WAS REPLACED AND THE HYDRAULIC SYSTEM WAS TESTED IAW MM 29-30-03. DURING OVERNIGHT SERVICE, THE SYSTEM WAS CHECKED BY LEAKAGES, ALL OK.

Part: PUMP — FAILED (RT HYD SYSTEM)

AIRCRAFT RETURNED TO PLATFORM DUE TO HIGHT TEMPERATURE ON RT HYDRAULIC SYSTEM. THE RT HYDRAULIC PUMP WAS REPLACED. DURING OVERNIGHT SERVICE THE PTU AND RELIEF VALVE WERE REPLACED IAW MM 29-10-12 RESPECTIVELY.

Part: ENGINE — MALFUNCTIONED (LEFT)

AIRCRAFT RETURNED TO PLATFORM, AFTER LT ENGINE START, IT HAD HIGH TEMPERATURE INDICATIONS (447 WITHOUT BLEED AND 491 WITH BLEEDS). ENGINE WAS TESTED AND IT HAD 450 WITHOUT BLEED AND 460 WITH BLEEDS BEING WITHIN LIMITS IAW MM 72-00-00. DURING OVERNIGHT SERVICE, LT ENGINE WAS RUN UP AND IDLE TEMPERATURE WAS WITHIN OPERATION LIMITS IAW MM 71-00-01.(K)

Part: PROXIMITY SENSOR — WILL NOT TEST (MLG)

AIRCRAFT RETURNED TO PLATFORM DURING TAXING, NOSE LANDING GEAR RED LIGHT CAME ON. THE BITE WAS PERFORMED TO PROXIMITY SWITCH, SENSOR AND CONNECTOR WERE CLEANED AND CHECKED IAW MM, ALL CORRECT.

Part: WIRE — FAILED (FUEL PANEL)

DURING FUELING SERVICE, WAS DETECTED THE REFUELING CONTROL PANEL OUT OF SERVICE. DURING REVISION WAS DETECTED THE BREAKER E-5 OF PANEL P-11 DAMAGED. THE REFUELING CONTROL PANEL WAS DEFERRED IAW MEL 28-41-6. THE REFUELING CONTROL PANEL WIRING WAS REPAIRED IAW WDM 28-21-22 AND FUEL QUANTITY INDICATOR WAS REPLACED IAW MM 28-41-06, ALL CORRECT.

Part: LIGHT — INTERMITTENT (TAIL CONE)

AIRCRAFT RETURNED TO GATE, TAIL CONE LIGHT CAME ON INTERMITTENTLY. LIGHT TEST, SAFETY MECHANISM AND SW OF TAIL CONE WERE CHECK IAW MM 52-70-11, ALL TESTS CORRECT. (M)

Part: LOCK — BROKEN (RADOME)

THE RADOME RIGHT LOCK WAS BROKEN BY F.O.D. THE RADOME LOCK WAS REPLACED IAW MM 53-51-02, TEST CORRECT.

Part: INDICATOR — FAILED (EPR)

AIRCRAFT RETURN TO PLATFORM DUE TO LT ENGINE EPR INDICATION FAILURE. DURING REVISION THE INDICATION ON EDP IS LESS THAN 1, THEREFORE, THE LT ENGINE WAS SHUTDOWN. THE EPR TRANS WAS REPLACED IAW MM, TEST CORRECT.

Part: TRANSMITTER — FAILED (RADAR SYS)

AIRCRAFT AIR TURNBACK DUE TO RADAR FAIL. TX RADAR WAS REPLACED IAW MM, TEST CORRECT.

Part: PITOT TUBE — FAILED (NR 1)

CAPTAIN REPORTED LEFT PITOT SYSTEM OUT OFF SERVICES. PITOT TUBE WAS REPLACED IAW MM, TEST CORRECT.

Part: ENGINE — FAILED (NR 2)

AIRCRAFT RETURNED TO PLATFORM DUE TO NR 2 ENGINE TAKE OFF THRUST DID NOT ACCELERATE. THE MOISTURE TRAP WAS DRAINED AND TEST WAS CORRECT IAW MM.

Part: LINE — LEAKING (HYD SYSTEM)

DURING OVERNIGHT SERVICE, A BLADE ON T4 (TURBINE STAGE) WAS DETECTED WITH DAMAGE. ENGINE WAS REPLACED IAW MM AND TESTS IAW MM, ALL CORRECT. DURING REVERSE TEST, A HYDRAULIC FLUID LEAK WAS DETECTED AND HYDRAULIC LINES WERE REPLACED.

Part: WARNING SYSTEM — MALFUNCTIONED (SLAT DISAGREE)

AIRCRAFT RETURN TO PLATFORM DUE TO TAKEOFF ALARM ACTIVATED. STP TEST WAS PERFORMED DETECTING A SLATS DISAGREE LIGHT. TECHNICAL PERSONNEL OPERATED THE FLAPS SEVERAL TIMES AND FAIL WAS NOT REPRODUCED.

Part: CONTROLLER — FAILED (E/E COMPT)

FLT 584 - CUN-MEX - DURING FLIGHT THERE WAS 25 DEGREE DIFFERENCE IN HDG RDI OF PILOT AND ALSO ATS 1, AUTO PILOT AND FMA O;S, BOTH DFGC CONFIRMED FAIL IN ATT 1 AND 2, HDG 1 AND 2 AND COMPASS CONTROLLER 1 AND 2. THERE WAS AN INFORMATION LOST IN DFGC 2. BOTH C/B OF AHRS WERE RESET, AND AIRCRAFT WAS DISPATCHED. DURING FLIGHT, CREW REPORTED THE FAIL AGAIN. AT RON MEX 26/27 THE AHRU 1, DFGC 2 AND COMPASS CONTROLLER 2 WERE REPLACED IAW 34-21-10, 22-01-01 AND 34-21-13. AN RTS WAS PERFORMED, COMPUTERS OK IAW MM 22-01-05. (M)

Part: CONTROL UNIT — FAILED (E/E COMPT)

FLT 608 - MEX-DFW - AIRCRAFT STOPPED OVER IN MTY AS CONSEQUENCES OF AUTOMATIC THROTTLES, AUTO PILOT AND FLIGHT DIRECTORS FAIL, REPORTS ARE DEFERRABLES, HOWEVER PILOT ASKED THEIR CORRECTION. BOTH DFGC WERE REPLACED IAW MM 22-01-01. (M)

Part: GCU — FAILED (AC GENERATOR)

FLT 603 - DFW-MEX - AC CROSS TIE LIGHT TURN OFF, THERE WAS NOT A CROSS FEED AND APU O/S. CIRCUIT BREAKER OF GCU, GENERATION AND INTERCHANGE WAS RESET AND AIRCRAFT WAS DISPATCHED BY MEL WITH APU O/S. DURING TRANSIT CHECK IN MEX IT WAS REPLACED THE GCU OF THE APU, HOWEVER CROSSFEED WAS NOT POSSIBLE. REPORT DEFERRED BY MEL 24-3 CAT 'C'. LATER WAS REPLACED THE BCU IAW MM 24-20-05. AT RON MEX 22/23 SEVERAL TESTS WERE PERFORMED IAW 24-20-08 AND 24-20-07. (M)

Part: COMPUTER — FAILED (AHRS)

FLT 907 - MTY-MEX - PILOT REPORTED AHRS NR 2 OUT OF SERVICE.. (M)

Part: COMPUTER — FAILED (E/E COMPT)

FLT 403 - MEX-NYC - AIRCRAFT RETURNED TO MEX AS CONSEQUENCE OF NAVIGATIONAL INSTRUMENTS FAIL. DURING CLIMBING THE NR 2 SYMBOL GENERATOR MALFUNCTIONED. BOTH EFIS WERE SWAPPED, OPERATION REESTABLISHED, BUT AFTER BOTH SYMBOL GENERATORS AND BOTH FMA OUT OF SERVICE, FLIGHT COMPUTERS WERE CHANGED WITHOUT SOLUTION. AT RON MEX 04/05 THE FAIL WAS FOUND IN THE AHRS 2, IT WAS REPLACED IAW MM 34-21.00, TESTS OK. (M)