N825AM

Part: SPOILER — DAMAGED (LEFT) · airframe 26,685 hrs · 10,123 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A SEVERAL DAMAGES ON LEFT HORIZONTAL STABILIZER LEADING EDGE SKIN. MAINTENANCE PERSONNEL PERFORMED A HAIL STRIKE CONDITIONAL INSPECTION IAW AMM 05-51-18-210-801, DETECTING SEVERAL DAMAGES AT LEFT HORIZONTAL STABILIZER LEADING EDGE SKIN AT LE STA 108.93; A DENT WITH PULLED FASTENER IN RH HORIZONTAL STABILIZER LEADING EDGE SKIN AT LE STA 210.23; AT RIGHT HORIZONTAL STABILIZER LEADING EDGE SKIN; AT LEFT HORIZONTAL STABILIZER LEADING EDGE SKIN; AT VERTICAL STABILIZER LEADING EDGE SKIN; DENTS IN LEFT SLATS AND SPOILERS PANELS NUMBERS1, 2, 3, 4, 5, 6, 8, 9, 10, 12 TRAILING EDGE WEDGE SKIN. THE WO´S 7717376, 7717377, 7717381, 7717390, 7717414, 7717487, 7717952, 7720078, 7720357, 7720778, 7720957, 7720961, 7720975, 7720991, 7720993, 7720998, 7721001, 7721281, 7721283, 7721285, 7721286, 7721287, 7721288, 7721289, 7722217, 7722218 WERE ISSUED TO REPAIR THE DAMAGES DETECTED; DAMAGES WERE REMOVED IAW SRM 55-10-01, ALLOWABLE DAMAGE 1, PARAGRAPH 4, TABLE 101, FIG. 102 DETAIL D; ULTRASONIC AND HFEC INSPECTIONS ON BLEND OUT AND ON CUT AND SURROUNDING AREA WERE PERFORMED IAW B737 NDTM PART 6, 51-00-00 PROCEDURES 23, 16 AND 53-30-00 PROCEDURE 3; NDTM PART 4. 51-00-00 PROCEDURE 2; SRM 55-10-01, ALLOWABLE DAMAGE 1, TABLE 101, FIGURE 102, DETAIL D; CUTS WERE PERFORMED IAW SRM 55-10-01, REPAIR 1, PARAGRAPH 4.A.(1); PERMANENT REPAIRS WERE PERFORMED IAW SRM 55-10-01, REPAIR 1; DENTS HAND REWORKED WERE PERFORMED IAW SRM 55-10-01, ALLOWABLE DAMAGE 1, PARAGRAPH 5; DENTS WERE SEALED IAW SRM 55-30-01-1A-A, ALLOWABLE DAMAGE 1, PARAGRAPH 4, TABLE 101, NOTE 8 OPTION 2, PARAGRAPH 7; PERMANENT REPAIRS SHOULD BE PERFORM WITHIN 24 MONTHS IAW SRM 55-30-01-1A, PART 7.F AND DETAILED VISUAL INSPECTION OF THE SPEED TAPE AT INTERVALS OF 400FH SHOULD BE FOLLOW; DENTS WERE EVALUATED TO BE STRUCTURALLY ACCEPTABLE IAW MESSAGES BOEING NUMBERS AMX-AMX-21-0351-05B, AMX-AMX-21-0359-02/-02B, AMX-AMX-21-0360-02B, AMX-AMX-21-0361-02B, AMX-AMX-21-0362-02B, AMX-AMX-21-0352-01C/-04B, AMX-AMX-21-0358-03B, AMX-AMX-21-0357-05B AND MESSAGES MEXMR-AMXTR-099-21, MEXMR-AMXTR-104-21; SPOILERS NUMBERS 4, 5, 8, 9 WERE REPLACED IAW AMM 27-61-11, ALL CORRECT.

Part: FUEL NOZZLE — LEAKING (LT ENGINE) · airframe 24,997 hrs · 9,371 cycles

DURING OVERNIGHT CHECK AT MEX STATION, IT WAS DETECTED EVIDENCE OF FUEL LEAKAGE IN FUEL NOZZLES 11, 12, 13 AND 14 DURING THE COMBUSTION SECTION BORESCOPE INSPECTION AT LEFT ENGINE. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING EVIDENCE OF FUEL LEAKAGE IN FUEL NOZZLES 11, 12, 13 AND 14 AT LEFT ENGINE; SO THE FUEL NOZZLES 11, 12, 13 AND 14 WERE REPLACED IAW AMM TASK 73-11-01-000-805-F00 FUEL NOZZLE REMOVAL AND TASK 73-11-04-400-805-F00 FUEL NOZZLE INSTALLATION, TESTED CORRECT.

Part: VALVE — LEAKING (RT HPT) · airframe 24,961 hrs · 9,349 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A FUEL LEAK AT RIGHT ENGINE. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING THE RIGHT ENGINE HPTACC VALVE DRAIN AND SERVO FUEL HEATER LEAKING; SO THE HPTACC VALVE WAS REPLACED IAW AMM 75-21-01 AND THE SERVO FUEL HEATER WAS REPLACED IAW AMM 73-21-07, TESTED CORRECT.

Part: SKIN — DAMAGED (WING) · airframe 24,197 hrs · 9,007 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A GOUGE OF THE LEADING EDGE LOWER SKIN. MAINTENANCE PERSONNEL PERFORMED A REVISION, DETECTING A GOUGE 0.687 LENGTH, 208.75" WIDTH AT 56.25" OF THE RIGHT WING LEADING EDGE LOWER SKIN. THE DAMAGE WAS REMOVED, IAW SRM 57-20-01-1A-1, PARAGRAPH 4B(2), FIGURE 104, DETAIL D, TABLE 104. AN ULTRASONIC THICKNESS MEASUREMENT WAS PERFORMED, IAW 737 NDTM PART 4, 51-00-00, PROCEDURE 2 WITH MAXIMUM DEPTH OF REMOVED MATERIAL OF 0.029, IAW 737-800 SRM 57-20-01-1A-1, ALLOWABLE DAMAGE 1, TABLE 104, BEING WITHIN LIMITS. HIGH FREQUENCY EDDY CURRENT INSPECTION ON REWORKED AREA WAS PERFORMED, IAW 737 NDTM PART 6, 51-00-00, PROCEDURE 23, NO CRACKS WERE FOUND. A FLAP PEEN PROCEDURE ON REWORKED AREA WAS PERFORMED, IAW SRM 57-20-01-1A-1, PARAGRAPH 2H (1) AND SOPM 20-10-03. A CHEMICAL CONVERSION COATING WAS APPLIED, IAW SRM 51-20-01-0G-0, PARAGRAPH 5 A SURFACE FINISHES WERE APPLIED, IAW SRM 57-20-01-1A-1, PARAGRAPH 2H (4), ALL CORRECT.

Part: TRANSMITTER — FAILED (TE FLAP) · airframe 22,938 hrs · 8,432 cycles

CAPTAIN REPORTED THAT DURING APPROACH, IT WAS PRESENTED FLAP ASYMMETRY, SO FLIGHT CREW ACCOMPLISHED THE QRH 9.28 PROCEDURE, BEING NECESSARY A MISSED APPROACH. MAINTENANCE PERSONNEL PERFORMED THE FIM 27-51 TASK 801 PROCEDURE, SHOWING FAILURE CODE 27-52260 AND THE FIM 27-51 TASK 820 PROCEDURE, DETECTING THE FLAPS POSITION TRANSMITTER WITH FAILURE. AIRCRAFT WAS SENT TO THE HANGAR AND MAINTENANCE PERSONNEL REPLACED THE FLAPS POSITION TRANSMITTER IAW AMM 27-58-01, IT WAS PERFORMED FIM 27-51 TASK 803, TESTS CORRECT.

Part: FSEU — FAILED (TE FLAP) · airframe 222,883 hrs · 8,405 cycles

CAPTAIN REPORTED THAT DURING APPROACH, FLAPS LEADING EDGE DO NOT EXTEND DURING NORMAL SYSTEM OPERATION SHOWING MESSAGE 278 030 00 TRAILING EDGE FLAP DISAGREE. FLIGHT CREW ACCOMPLISHED THE QRH 9.40 PROCEDURE, CONFIRMING FAILURE. MAINTENANCE PERSONNEL PERFORMED THE FIM 27-51 TASK 820 PROCEDURE, DETECTING FSEU FAULT. AIRCRAFT WAS SENT TO THE HANGAR AND MAINTENANCE PERSONNEL REPLACED FLAP SLAT ELECTRONIC UNIT IAW AMM 27-51-01, TEST CORRECT.

Part: PITOT TUBE — DAMAGED (RIGHT) · airframe 8,428 hrs · 3,320 cycles

AIRCRAFT REJECTED TAKEOFF AT 80 KNOTS DUE TO EICAS MESSAGE IAS DISAGREE AND A DIFFERENCE OF 12 KNOTS BETWEEN SPEEDOMETERS BEING BIGGEST LEFT SIDE. MAINTENANCE PERSONNEL PERFORMED FIM 31-62 TASK 876 PROCEDURE, DETECTING THE RIGHT STATIC PITOT TUBE DAMAGED; SO THE STATIC PITOT TUBE WAS REPLACED IAW AMM 34-11-01 AND LEFT PITOT SYSTEM LEAK TEST WAS PERFORMED IAW AMM 34-11-00-790-811, TESTED CORRECT. THE HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-51-07, NO DAMAGES WERE FOUND.

Part: TIRE — DEFLATED (MLG) · airframe 7,873 hrs · 3,106 cycles

AIRCRAFT REJECTED TAKE OFF AT 110 KNOTS, DUE TO FWD ENTRY DOOR LIGHT TURNED ON. MAINTENANCE PERSONNEL PERFORMED REVISION DETECTING THE MLG TIRES NUMBERS 3 AND 4 THAT BEGIN TO DEFLATE; SO THE MLG WHEEL NUMBERS 3 AND 4 WERE REPLACED IAW AMM 32-45-11. AIRCRAFT WAS SENT TO THE HANGAR AND THE MLG WHEEL, TIRE AND BRAKES WERE REPLACED IAW AMM 32-45-11; THE FIM 52-10 TASK 801 PROCEDURE WAS PERFORMED, NO DAMAGES WERE DETECTED IN SENSOR S199 AND SW S1147; BITE TO PSEU IAW AMM 53-00-00, NO CONFIRMING FAILURE. HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-51-07, NO DAMAGES WERE FOUND, ALL CORRECT.

Part: TIRE — DEFLATED (MLG) · airframe 7,873 hrs · 3,106 cycles

AIRCRAFT REJECTED TAKE OFF AT 110 KNOTS, DUE TO FWD ENTRY DOOR LIGHT TURNED ON. MAINTENANCE PERSONNEL PERFORMED REVISION DETECTING THE MLG TIRES NUMBERS 3 AND 4 THAT BEGIN TO DEFLATE; SO THE MLG WHEEL NUMBERS 3 AND 4 WERE REPLACED IAW AMM 32-45-11. AIRCRAFT WAS SENT TO THE HANGAR AND THE MLG WHEEL, TIRE AND BRAKES WERE REPLACED IAW AMM 32-45-11; THE FIM 52-10 TASK 801 PROCEDURE WAS PERFORMED, NO DAMAGES WERE DETECTED IN SENSOR S199 AND SW S1147; BITE TO PSEU IAW AMM 53-00-00, NO CONFIRMING FAILURE. HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-51-07, NO DAMAGES WERE FOUND, ALL CORRECT.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 3,979 hrs · 1,646 cycles

AIRCRAFT REJECTED TAKEOFF AT 30 KNOTS TO THE AFT SERVICE DOOR LIGHT TURNED ON. PERFORMED THE QRH 1.15 PROCEDURE, NO CONFIRMING THE FAILURE & INITIATING AGAIN SEQUENCE OF TAKEOFF. AS PRECAUTIONARY ACTION, PERFORMED AFT SERVICE DOOR CHECK IAW AMM 52-13-00, TESTED CORRECT.

Part: SENSOR — FAILED (NLG) · airframe 3,657 hrs · 1,520 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXING, THE PSEU LIGHT TURNED ON. PERFORMED BITE TO PSEU IAW FIM 32-61 TASK 804 PROCEDURE, SHOWING FAILURE CODES 32-61103, D10982 PIN 9, 2 & MSG NOSE LKD & S0846 FAIL SAFE, SO THE WIRING WAS VERIFIED IAW WDM 32-64-11. THE NLG LOCK SENSOR S0846 WAS REPLACED IAW AMM 32-61-41, TESTED CORRECT.

Part: UNKNOWN — MALFUNCTIONED (BLEED AIR SYS) · airframe 902 hrs · 413 cycles

AIRCRAFT RETURNED FROM FLIGHT, DURING CLIMB, THE LT PNEUMATIC SYS INDICATOR SHOWED 5 PSI AT 1,000 FEET & IT WAS SHOWED 0 PSI AT 26,000 FEET WITH OSCILLATIONS. ACCOMPLISHED THE QRH 2.6 PROCEDURE, CONFIRMING THE FAILURE. DEFERRED THE LT PNEUMATIC SYS IAW MEL 36-5-2 CAT C. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE ACFT LANDED WITH 63,600 KILOGRAMS & THE MAXIMUM ALLOWABLE LANDING WEIGHT IS 65,317 KILOGRAMS. THE FIM 36-10 TASK 807, NO CONFIRMING FAILURE & THE REPORT WAS CLOSED.