N520AM

Part: SENSOR — DAMAGED (CARGO DOOR) · airframe 62,969 hrs · 22,978 cycles

AIRCRAFT REJECTED TAKE OFF BEFORE AT 70 KNOTS DUE TO AFT CARGO DOOR LIGHT TURNED ON. MAINTENANCE PERSONNEL PERFORMED REVISION TO AFT SERVICE DOOR IAW AMM 52-71-31, DETECTING THE S961 DAMAGED; SO THE SO THE SW961 WAS DEFERRED IAW MEL 52-03-01 CAT. C. THE HIGH ENERGY STOP INSPECTION WAS NOT NECESSARY DUE TO THE MAXIMUM GROSS WEIGHT 65 317 KG AND THE BRAKES ON SPEED 110 KNOTS WERE NOT EXCEEDED IAW MM 05-51-07. AT MEX, THE S961 P/N 10-62215-1 WITH S/S WAS REPLACED IAW AMM 52-71-31, TESTED CORRECT.

Part: HYDRAULIC LINE — DAMAGED (HYDRAUYLIC SYS) · airframe 59,181 hrs · 21,539 cycles

LOW PRESSURE HYDRAULIC PUMP SYSTEM B. CAPTAIN REPORTED THAT DURING CRUISE THE LOW PRESSURE HYDRAULIC PUMP SYSTEM B LIGHTS TURNED ON, SO FLIGHT CREW ACCOMPLISHED THE QRH 13.6 PROCEDURE. MAINTENANCE PERSONNEL PERFORMED REVISION DETECTING THE HYDRAULIC LINE LOOSED AND DAMAGED INDUCING LEAKING IAW FIM 29-30 TASK 813 PROCEDURE; SO THE HYDRAULIC PRESSURE LINE P/N 155016-20-11 WAS REPLACED IAW AMM 29-11-21, TESTED CORRECT. AT MEX, AS PRECAUTIONARY ACTION, THE RIGHT HYDRAULIC PUMP WAS REPLACED IAW AMM 29-11-11, TESTED CORRECT.

Part: VALVE — FAILED (CABIN PRESSURE) · airframe 58,824 hrs · 21,392 cycles

AIRCRAFT PERFORMED AN EMERGENCY DESCENT DUE TO PRESSURIZATION SYSTEM FAILURE. MAINTENANCE PERSONNEL PERFORMED BITE TO CABIN PRESSURE CONTROLLERS IAW AMM 21-31-00, DETECTING CABIN PRESSURIZATION SYSTEM INOPERATIVE. THE PRESSURE CONTROLLERS WERE REPLACED IAW AMM 21-31-01-000-801 AND AMM 21-31-01-400-801 AND MANUAL MODE TEST AND SYS GROUND TEST WERE PERFORMED IAW AMM 21-31-00-710-801 AND 21-31-00-700-802, CONTINUING THE FAILURE. DURING THE REVISION, THE HIGH STAGE VALVE WAS DETECTED THAT DOES NOT CLOSE PROPERLY. THE HIGH STAGE VALVE WAS REPLACED IAW AMM 36-11-06-000-801 AND 36-11-06-400-801. A CABIN DEPRESSURIZATION CONDITION INSPECTION WAS PERFORMED IAW AMM TASK 05-51-81, NO DAMAGES WERE FOUND, ALL TESTED CORRECT.

Part: STARTER — DAMAGED (LT ENGINE) · airframe 58,464 hrs · 21,252 cycles

AIRCRAFT PERFORMED AN UNSCHEDULED LANDING AT MZT DUE TO DURING CRUISE, THE LEFT ENGINE PRESENTED LOW OIL QUANTITY INDICATION; SO FLIGHT CREW ACCOMPLISHED THE QRH 7.21 PROCEDURE. AT MZT, MAINTENANCE PERSONNEL PERFORMED LEFT ENGINE LEAK CHECK IAW AMM 71-00-00, FIM 79-05 TASK 808 PROCEDURE, DETECTING THE LEFT ENGINE STARTER DAMAGED; SO THE LEFT ENGINE STARTER WAS REPLACED IAW AMM 80-11-00, OPERATIONAL TEST AND DRY MOTOR LEAK TEST WERE PERFORMED IAW AMM 79-00-00 AND AMM 71-00-00 AND BITE TO EEC IAW FIM 73-00 TASK 801 PROCEDURE, ALL TESTED CORRECT.

Part: SENSOR — MALFUNCTIONED (FLAP SLATS) · airframe 57,003 hrs · 20,673 cycles

CAPTAIN REPORTED THAT AFTER LANDING, FLAPS AND SLATS LEADING EDGE DID NOT RETRACT, MAINTENANCE PERFORMED A BITE TEST IAW FIM 27-51 DETECTING FAULT 27-53252, THE SKEW SENSOR WAS CLEANED IAW AMM 27-59-00. SENSOR FLAP SKEW POSITION 3 WAS REPLACED IAW AMM 27-59-01, ALL TESTED CORRECT.

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 56,592 hrs · 20,510 cycles

CAPTAIN REPORTED THAT AFTER LANDING THE FLAPS AND SLATS DO NOT RETRACT. MAINTENANCE PERSONNEL PERFORMED BITE TO FSEU IAW FIM 27-53 TASK 803 PROCEDURE, NO CONFIRMING FAILURE. PERFORMED TRAILING EDGE FLAP SYSTEM OPERATIONAL TEST IAW FIM 27-51 TASK 803 PROCEDURE, NO CONFIRMING FAILURE AND ALL TESTED CORRECT.

Part: SPOILER SYS — MALFUNCTIONED · airframe 55,199 hrs · 19,948 cycles

AIRCRAFT RETURNS TO PLATFORM DUE TO DURING FLIGHT CONTROLS TESTS CAPTAIN REPORTED THAT SPOILERS DID NOT REACH THE MAXIMUM EXTENSION. AIRCRAFT WAS SENT TO HANGAR AND MAINTENANCE PERSONNEL PERFORMED INSPECTION IAW AMM 27-11-61 BEING IN NORMAL CONDITION, AS A PREVENTIVE ACTION, A LUBRICATION OF THE FLIGHT SPOILER ACTUATORS WAS PERFORMED IAW AMM 12-22-61, ALL CORRECT.

Part: CONTROL PANEL — MALFUNCTIONED (AUTOTHROTTLE) · airframe 55,021 hrs · 19,871 cycles

CAPTAIN REPORTED THAT DURING APPROACH AUTOTHROTTLE DISENGAGES CONTINUOUSLY, LEFT COURSE CAN NOT BE ADJUSTED DURING DESCENT PROCEDURE AND FLIGHT DIRECTOR CAPTAIN SIDE OUT OF SERVICE. MAINTENANCE PERSONNEL PERFORMED AUTOTHROTTLE SYSTEM OPERATIONAL TEST IAW AMM 22-31-00, CONFIRMING FAILURE. THEREFORE AUTOTHROTTLE SYSTEM WAS DEFERRED IAW MEL 22-4 CAT. C, FLIGHT DIRECTOR SYSTEM WAS DEFERRED IAW MEL 34-12 CAT. C AND LEFT COURSE WAS DEFERRED IAW MEL 22-16-2-F CAT. C. AT MEX, MCP WAS REPLACED IAW AMM 22-11-34, TESTED CORRECT. ADDITIONALLY, AS A PRECAUTIONARY ACTION, THRUST LEVER ANGLE RESOLVER ADJUSTMENT WAS PERFORMED IAW AMM 76-11-05. ALL CORRECT.

Part: COAX — DAMAGED · airframe 54,609 hrs · 19,707 cycles

DURING TRANSIT CHECK CAPTAIN REPORTED IAS/MACH STAYS IN 100 OF ALTITUDE BUT SHOWS 50000 FT OF ALTITUDE AND NO NAV INDICATION, MAINTENANCE PERFORMED FIM PROCEDURE TO NAVIGATION CONTROL PANEL IAW FIM 34-31, TASK 808, AND COAXIAL VOR 1 RF POWER DRIVER WAS RECONNECTED IAW SSM 34-51-11, ALL TESTED CORRECT.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 53,945 hrs · 19,429 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A FOREIGN OBJECT DAMAGE IN THE LEFT INBOARD FLAP OF 4.843 LENGTH, 0.062 DEPTH, 2.718 WIDE. MAINTENANCE PERSONNEL PERFORMED CONDITIONAL INSPECTION IAW AMM 05-41-05-210-801 FOUND IT WITHIN LIMITS, ALL CORRECT.

Part: SENSOR — DAMAGED (RIGHT) · airframe 53,434 hrs · 19,238 cycles

AIRCRAFT PERFORMED AN EMERGENCY DESCENT AT GDL DUE TO DURING CLIMB, THE LEFT BLEED TRIP OFF LIGHT TURNED ON AND CONTROL PRESS AUTO, SEMI AUTO AND MANUAL WITH NO CONTROL, SO THE FLIGHT CREW ACCOMPLISHED THE QRH 2.6 PROCEDURE, CONFIRMING THE FAILURE. MAINTENANCE PERSONNEL PERFORMED THE FIM 36-10 TASK 807 DETECTING SENSOR ASSY BLEED AIR AND OVER TEMPERATURE SWITCH FROM RIGHT ENGINE DAMAGED, THEREFORE SENSOR ASSY AND SWITCH WERE REPLACED IAW AMM 36-11-08. ADDITIONALLY PRECOOLER CONTROL VALVE WAS REPLACED IAW AMM 36-12-02, THE HIGH STAGE PRECOOLER VALVE WAS REPLACED IAW AMM 36-11-06 AND CABIN PRESSURE CONTROLLER WAS REPLACED IAW AMM 21-31-01. THE OVERWEIGHT INSPECTION WAS PERFORMED IAW AMM 05-51-35 NO FOUND DAMAGES, ALL TESTED CORRECT.

Part: SENSOR — FAILED (PAX DOOR) · airframe 52,792 hrs · 18,980 cycles

AIRCRAFT RETURNED TO GATE DUE TO A LE FLAP TRANSIT LIGHT ILLUMINATED AND LE DEVICE SLAT 1 LIGHT DID NOT ILLUMINATE. PERFORMED A BITE OF THE FSEU IAW FIM 27-51 TASK 801 PROCEDURES, SHOWING FAILURE CODES 27-81216F1 PROXIMITY RETRACT FIM 27-88 TASK 805 PROCEDURE WAS PERFORMED, DETECTING PROXIMITY SENSOR S1 168 WITH FAILURE. THE SENSOR S1 168 WAS INTERCHANGED WITH AFT ENTRY DOOR SENSOR IAW AMM 27-88-11. THE AFT ENTRY DOOR SENSOR WAS REPLACED IAW AMM 52-71-11-000-801 AND -400-801, TESTED CORRECT.

Part: AXLE — DAMAGED (RT MLG) · airframe 50,537 hrs · 18,092 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A HIGH TEMPERATURE LOW PRESSURE AT MAIN WHEEL ASSY NUMBER 4. MAINTENANCE PERSONNEL PERFORMED THE FLAT SPOTTED TIRES CONDITIONAL INSPECTION IAW AMM 05-51-16-210-801 DETECTING PAINT ERODED IN THE TRANSDUCTOR HOUSING AND DISCOLORATION ON SHAFT CHROME AND INSPECTION PERSONNEL EVALUATED THE DAMAGE AND FOUND IT OUT OF LIMITS IAW AMM 32-11-85. AIRCRAFT WAS SENT TO THE HANGAR, THE NRC’S A0238685, A0238686 AND A0238687 WERE ISSUED TO REPAIR THE DAMAGE DETECTED AND THE MAIN WHEEL ASSY AND BRAKE ASSEMBLY NUMBERS 3 AND 4 WERE REPLACED IAW AMM 32-45-11, AMM 32-41-41, THE RIGHT MAIN LANDING GEAR AXLE WAS REPLACED IAW AMM 32-11-85, THE RIGHT OUTBOARD ANTISKID VALVE WAS REPLACED IAW AMM 32-42-31, TESTED CORRECT.

Part: OVEN — DEFECTIVE (GALLEY) · airframe 49,811 hrs · 17,841 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO AFTER ENGS START, SMOKE WAS DETECTED IN AFT GALLEY. PERFORMED SMOKE OR FUMES IN CABIN CONDITIONAL INSPECTION IAW MM 05-51-56 & FIM 21-00 TASK 806 PROCEDURE, DETECTING SMOKE IN THE OVEN NR 1 IN AFT GALLEY, SO THE OVEN NR 1 WAS DEFERRED IAW NEF 02-25-02 CAT C. THE OVEN NR 1 IN AFT GALLEY WAS REPLACED IAW CMM 25-32-75, TESTED CORRECT & THE REPORT WAS CLOSED.

Part: DOOR — OUT OF ADJUST (CABIN) · airframe 49,454 hrs · 17,719 cycles

CAPTAIN REPORTED THAT DURING CLIMB, THE FWD ENTRY DOOR LIGHT TURNED ON. ACFT WAS SENT TO THE HANGAR & MX PERFORMED FWD ENTRY DOOR ADJUSTMENT IAW AMM 52-11-00 TASK 52-11-00-820-801 & ENTRY DOOR SYS TEST WAS PERFORMED IAW AMM 52-11-00 TASK 52-11-00-700-804, TESTED CORRECT.

Part: PITOT TUBE — BLOCKED (LEFT) · airframe 48,084 hrs · 17,258 cycles

AIRCRAFT REJECTED TAKEOFF AT 80 KNOTS DUE TO EICAS MSG IAS DISAGREE & A DIFFERENCE OF 10 KNOTS BETWEEN SPEEDOMETERS BEING BIGGEST LT SIDE. PERFORMED FIM 31-62 TASK 876 PROCEDURE, DETECTING THE LT STATIC PITOT TUBE BLOCKED, SO THE STATIC PITOT TUBE WAS REPLACED IAW AMM 34-11-01. LT PITOT SYS LEAK TEST WAS PERFORMED IAW AMM 34-11-00-00-79-810 811, TESTED CORRECT. THE HIGH ENERGY STOP INSPECTION WAS NOT NECESSARY DUE TO THE MAXIMUM GROSS WEIGHT 67 131 KG AND BRAKES ON SPEED 110 KNOTS WERE NOT EXCEEDED IAW AMM 05-51-07.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 47,942 hrs · 17,210 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING BOTH ENGINE START, THE EEC ALT MODE LIGHTS TURNED ON. PERFORMED BITE TO BOTH EEC’S IAW AMM 73-21-00, CONTINUING THE FAILURE. THE ENG RUN EEC BITE TEST NR 13 WAS PERFORMED IAW AMM 71-00-00 TASK 700-800-F00, RESTORED BOTH EEC, TESTED CORRECT.

Part: FLAP SYSTEM — MALFUNCTIONED (TE FLAPS) · airframe 46,731 hrs · 16,797 cycles

CAPTAIN REPORTED THAT DURING APPROACH, TE FLAP DISAGREE WITH FLAPS INDICATOR STAYING IN 2 UNITS & DECLARED AN EMERGENCY. ACCOMPLISHED WITH THE PROCEDURE TO EXTEND FLAPS TO 30 UNITS USING ALTERNATE FLAP EXTENSION. PERFORMED BITE TO FSEU IAW FIM 27-51 TASK 830 PROCEDURE, SHOWING FAILURE CODE 21-51351 & THE FIM 27-51 TASK 803 PROCEDURE. THE CB`S A8 & A9, DC1 & DC2 IN P6 2 WERE RESEATED IAW AMM 27-51-00, TESTED CORRECT.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 45,996 hrs · 16,552 cycles

AIRCRAFT PERFORMED AN UNSCHEDULED LANDING, DUE TO DURING CRUISE, THE FUEL QTY PRESENTED LOW FUEL QTY INDICATION. PERFORMED REVISION OF FUEL LEAKS & CABIN FUEL INDICATORS WERE CHECKED IAW AMM 28-10-00 & A FQIS WITH THE FUEL MEASURING STICKS. COMPARISON CHECK WAS PERFORMED IAW AMM 28-41-00 TASK 720-801 & BITE TO FQIS WAS PERFORMED IAW AMM 28-41-00 TASK 730-801, NO FAILURES & NO FUEL LEAKS WERE FOUND, ALL CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE ACFT LANDED WITH 63,000 KILOGRAMS & THE MAXIMUM ALLOWABLE LANDING WEIGHT IS 65,317 KILOGRAMS.

Part: SHUTOFF VALVE — MALFUNCTIONED (FUEL SYS) · airframe 45,869 hrs · 16,505 cycles

DURING FUELING, A FUEL SPILLAGE IN THE LT TANK OCCURRED DUE TO THE SOV DID NOT CLOSE. THE PLATFORM WAS CLEANED BY FIREMEN & MX PERSONNEL CLEANED THE SELECTOR & THE SOV WAS RESEATED & TESTED SEVERAL TIMES IAW MM 28-21-00, NO LEAKS WERE DETECTED & SOV WORKED CORRECT CONTINUING THE FUELING.

Part: DRIVE UNIT — FAILED (WEATHER RADAR) · airframe 45,598 hrs · 16,407 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXING, THE EICAS MSG WXR FAIL WAS SHOWN. DURING MX REVISION, THE TRANSCEIVER & RADAR WERE DETECTED FAILED IAW AMM 34-42-00. THE WEATHER RADAR ANTENNA DRIVE UNIT WAS REPLACED IAW AMM 34-43-00 & AMM 34-43-11, TESTED CORRECT.

Part: PITOT LINE — LOOSE (PITOT/STATIC SYS) · airframe 43,520 hrs · 15,639 cycles

AIRCRAFT REJECTED TAKEOFF AT 100 KNOTS DUE TO EICAS MSG IAS DISAGREE. PERFORMED PITOT SYS REVISION BY CONDITION, DETECTING A LT ADM LINE LOOSEN, SO THE ADM LINE WAS TIGHTENED & LT PITOT SYS LEAK TEST WAS PERFORMED IAW AMM 34-11-00 PAGE 501, ALL CORRECT. THE HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-51-07, NO DAMAGES WERE FOUND.

Part: WHEEL — DAMAGED (MLG) · airframe 42,945 hrs · 15,434 cycles

DURING TRANSIT CHECK, DETECTED THE FOUR MLG WHEELS WITH DAMAGES OUT OF LIMITS. THE WHEELS WERE REPLACED IAW AMM 32-45-11, ALL CORRECT.

Part: CONTROL VALVE — FAILED (AC BAY) · airframe 41,019 hrs · 14,670 cycles

AIRCRAFT RETURNED TO PLATFORM, DURING TAXING THE RT PACK TEMP REACHED MORE THAN 60 CELSIUS DEGREES & BOTH PACKS REACHED LESS THAN 18 CELSIUS DEGREES IN PAX CABIN. THE TEMP CONTROL VLV FAILED SO THE REPORT WAS DEFERRED IAW MEL 21-33 CAT C AT GDL, THE TEMP CONTROL VLV WAS REPLACED IAW AMM 21-51-10, TESTED CORRECT.

Part: MECHANISM — OUT OF ADJUST (SPEED BRAKES) · airframe 40,326 hrs · 14,362 cycles

AIRCRAFT REJECTED TAKEOFF AT 70 KNOTS WITH 54,600 KG WEIGHT, DUE TO CONFIGURATION ALARM. DURING MX REVISION, THE SPEED BRAKE LEVER FAILED; THE HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW AMM 05-51-07, NO DAMAGE FOUND. THE AUTO SPEED BRAKE ACTUATOR MECHANISM WAS ADJUSTED IAW AMM 27-62-31 AND THE SPEED BRAKE SWITCH TEST WAS PERFORMED IAW AMM 27-62-00, ALL CORRECT.

Part: FIRE WARNING — FALSE ACTIVATION (CARGO BAY) · airframe 39,368 hrs · 13,952 cycles

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

Part: ACTUATOR — DAMAGED (LT MLG) · airframe 38,993 hrs · 13,784 cycles

CAPTAIN REPORTED THAT DURING APPROACH WITH LANDING GEAR LEVER DOWN, THE LT MLG RED LIGHT TURNED ON; SO FLIGHT CREW ACCOMPLISHED THE QRH 14.10 PROCEDURE AND MANUAL GEAR EXTENSION WAS PERFORMED. MX PERSONNEL REPLACED THE LT MLG ACTUATOR IAW AMM 32-32-11 AND PERFORMED EXTENSION AND RETRACTION OPS TEST IAW 32-32-00, ALL CORRECT.

Part: GASKET — LEAKING (ACCESS PANEL) · airframe 38,987 hrs · 13,783 cycles

DURING TRANSIT CHECK, A FUEL LEAK WAS DETECTED ON LT PANEL 533BB. MX PERSONNEL REPLACED THE PANEL AND CORRESPONDING GASKET IAW AMM 28-11-11- 020-005, TESTED CORRECT.

Part: SENSOR — DAMAGED (TE FLAPS) · airframe 38,824 hrs · 13,720 cycles

CAPTAIN REPORTED THAT AFTER START ENGINES, THE L/E FLAPS TRANSIT LIGHT TURNED ON. DURING MX REVISION, THE SENSOR FLAP SKEW NR 6 WAS DETECTED DAMAGED; SO THE SENSOR WAS REPLACED IAW AMM 27-59-01, TESTED CORRECT.

Part: HEAT EXCHANGER — DIRTY (LEFT) · airframe 37,897 hrs · 13,305 cycles

ACFT RETURNED TO PLATFORM DUE TO LT AIR CONDITIONING PACK UNABLE TO CONTROL TEMPERATURE AT MANUAL AND AUTO POSITIONS. MX PERSONNEL CLEANED THE LT HEAT EXCHANGER IAW MM 21-51-03, TESTED CORRECT.

Part: SLEEVE — DAMAGED (THRUST REVERSER) · airframe 36,957 hrs · 12,866 cycles

DURING TRANSIT CHECK, FOUND A LIGHTNING STRIKE ON RT OUTER THRUST REVERSER TRANSLATION SLEEVE SKIN LOCATED AT 03:00 HRS POSITION. MX PERSONNEL PERFORMED A LIGHTNING STRIKE CONDITIONAL INSP IAW MM 05-51-19, DETECTING A CRACK IN THE AFT L/E OF 0.5" LENGTH AND FOUND IT WITHIN LIMITS IAW SRM 54-30-01 ALLOWABLE DAMAGE 1, PARA 4.B.(7). THE NRC A0194377 WAS ISSUED TO PERFORM PERMANENT REPAIR ON THE DAMAGES.

Part: UNKNOWN — SMOKE (CABIN) · airframe 36,932 hrs · 12,847 cycles

CAPTAIN REPORTED THAT DURING CRUISE AT 36,000 FEET, SMOKE WAS PERCEIVED IN PASSENGER CABIN. FLIGHT CREW ACCOMPLISHED THE QRH 8.8 PROCEDURE. MX PERFORMED SMOKE OR FUMES IN CABIN CONDITIONAL INSPECTION IAW MM 05-51-50 AND FIM 21-00 TASK 806 PROCEDURE, NO SMOKE EVIDENCES FOUND. THE AIR CONDITIONING SYS TEST WAS PERFORMED IAW MM 21-00-05, ALL CORRECT.

Part: WHEEL — DAMAGED (ZONE 700) · airframe 36,302 hrs · 12,587 cycles

DURING TRANSIT CHECK, DETECTED MAIN WHEEL NR 2 DEFLATED AND BRAKE ASSY NR 2 WITH BURN AND CRACK. PERFORM BRAKE SEIZURE CONDITIONAL INSPECTION AT NR 2 WHEEL AXLE IAW MM 05-51-15, NO ISSUES WERE FOUND, REPLACED OF MAIN WHEEL NR 2, IAW MM 32-45-11 AND BRAKE ASSY NR 2, IAW MM 32-41-41, TESTED CORRECT.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 35,595 hrs · 12,304 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A LIGHTNING STRIKE IN THE FUSELAGE SKIN. MX PERFORMED A LIGHTNING STRIKE CONDITIONAL INSPECTION IAW MM 05-51-19, BURN MARKS OUT OF LIMITS IN THE LT FUSELAGE SKIN AT STA 727H AND 747 BETWEEN LONGERON 23L AND 25L. ACFT WAS SENT TO THE HANGAR AND THE NRC A0190213, A0190214 AND A0190217 WERE ISSUED TO REPAIR THE DAMAGES DETECTED. THE BURNED MARKS WERE REPAIRED IAW SRM 53-00-01 REPAIR 13 PARAGRAPHS 4C, 5H AND SRM 51-40-02 PARAGRAPH 4B, ALL CORRECT.

Part: BRAKE — LEAKING (MLG) · airframe 34,880 hrs · 12,018 cycles

DURING TRANSIT CHECK, MX PERSONNEL DETECTED A HYD LEAK AT MAIN BRAKES NUMBERS 1, 3 AND 4. ACFT WAS SENT TO THE HANGAR AND MX PERSONNEL REPLACED MAIN BRAKES NUMBERS 1, 3 AND 4 IAW MM 32-41-41, TESTED CORRECT.

Part: TIRE — DEFLATED (NLG) · airframe 34,684 hrs · 11,937 cycles

DURING TRANSIT CHECK, THE LT NOSE WHEEL WAS FLAT. REPLACED IAW MM 32-45-21. AS A PRECAUTIONARY ACTION, THE RT NOSE WHEEL WAS REPLACED IAW MM 32-45-21, ALL CORRECT.

Part: GEARBOX — LACK OF LUBE (STAB TRIM) · airframe 32,896 hrs · 11,104 cycles

CAPTAIN REPORTED THAT DURING APPROACH, THE STABILIZER TRIM WITH HIGH VIBRATION AND SOUND. MX PERSONNEL WAS PERFORMED THE FIM 27-41-00 TASK 803 / 804 PROCEDURE, CONFIRMING THE FAILURE. ACFT WAS SENT TO THE HANGAR AND THE HORIZ STABILIZER CONTROL SYS WAS CHECKED IAW MM 27-41-00, DETECTING STUCK THE GEARBOX; SO THE HORIZ STABILIZER JACKSCREW, BALL NUT AND UPPER GIMBAL WERE LUBRICATED AND TESTED IAW MM 12-22-41 AND MM 27-41-00, ALL CORRECT.

Part: BRAKE ASSY — DAMAGED (MLG) · airframe 32,617 hrs · 10,957 cycles

DURING TRANSIT CHECK AND PERFORMING A MLG WHEEL CHANGE, MX DETECTED BRAKE NR 2 WITH 11 LINKS BROKEN, ONE LINK LOOSED AND 4 RIVETS DAMAGED, SO THE BRAKE WAS REPLACED IAW MM 32-41-41, TESTED CORRECT.

Part: FMC — MALFUNCTIONED · airframe 32,535 hrs · 10,908 cycles

ACFT PERFORMED AN UNSCHEDULED LANDING, DURING CRUISE AN INDICATION OF INSUFFICIENT FUEL APPEARED ON THE FMC. MX PERFORMED BITE TO FMC AND FQIS IAW FIM 34-61 TASK 801 AND FIM 49-40 TASK 801 AND VERIFIED BY FUEL MEASURING STICKS IAW FMS 12-11-03, NO FAILURE WAS FOUND; REFUEL WAS PERFORMED AND VERIFIED BY FUEL MEASURING STICKS IAW FMS 12-11-03, ALL CORRECT.

Part: SWITCH — OUT OF ADJUST · airframe 31,972 hrs · 10,573 cycles

ACFT REJECTED TAKEOFF AT 10 KNOTS AND A GROSS WEIGHT OF 58 500 KG DUE TO CONFIGURATION ALARM WAS ACTIVATED AND MASTER OVERHEAT PSEU LIGHT TURNED ON. DURING MX REVISION, THE MESSAGE 31-53007 WAS SHOWN, THE FIM 27-62 TASK 808 PROCEDURE WAS PERFORMED; SO THE SPEED BRAKE TAKEOFF SWITCH S651 WAS ADJUSTED AND CHECKED IAW MM 31-51-03, TESTED CORRECT. THE HIGH ENERGY STOP INSP WAS NOT NECESSARY BECAUSE TO THE MAXIMUM GROSS WEIGHT 62 000 KG AND THE BRAKES ON SPEED 110 KNOTS LIMITS WERE NOT EXCEEDED IAW MM 05-51-07.