N368AR

Part: FLAP — FAILED

FLAPS TRANSIT LIGHT AMBER WITH TRAILING EDGE FLAPS EXTENDED AND THEY AGREE WITH FLAP HANDLE POSITION 27808001/08

Part: NONE — NONE

FUEL DRIP ENGINE 2 DURING STAR, WAS ACCOMPLISHED TEST IDLE POWER LEACK CHECK IAW AMM. 71-00-00-700-801-F00, ENGINE VENTS AND DRAINS

Part: ANTI-SKID VALVE — FAILED · airframe 34,500 hrs · 14,880 cycles

LUZ DE SISTEMA DE ANTI-SKID ENCENDIDA / ANTI-SKID SYSTEM LIGHT ON FALLA DE VALVULA DE ANTI-SKID / ANTI-SKID VALVE FAULTE

Part: TRIM MOTOR — FAILED (INIQUE) · airframe 34,053 hrs · 14,748 cycles

DURING TRANSIT CHECK, IT WAS DETECTED THE HORIZONTAL STABILIZER TRIM WITHOUT MOVEMENT. MAINTENANCE PERSONNEL PERFORMED BITE TO PSEU IAW FIM 27-41 TASK 805 PROCEDURE; DETECTING THE RIGHT HORIZONTAL STABILIZER TRIM MOTOR DAMAGED; SO THE HORIZONTAL STABILIZER TRIM MOTOR WAS REPLACED IAW AMM 27-41-71, TESTED CORRECT.

Part: NONE — DAMAGED (ZONE 300) · airframe 34,054 hrs · 14,748 cycles

DURING TRANSIT CHECK THE STABILIZER TRIM WITHOUT MOVEMENT, DURING TRANSIT CHECK, IT WAS DETECTED THE HORIZONTAL STABILIZER TRIM WITHOUT MOVEMENT. MAINTENANCE PERSONNEL PERFORMED BITE TO PSEU IAW FIM 27-41 TASK 805 PROCEDURE; DETECTING THE RIGHT HORIZONTAL STABILIZER TRIM MOTOR DAMAGED; SO THE HORIZONTAL STABILIZER TRIM MOTOR WAS REPLACED IAW AMM 27-41-71, TESTED CORRECT.

Part: FUEL HEATER — LEAKING (RIGHT) · airframe 33,231 hrs · 14,372 cycles

DURING TRANSIT CHECK, A FUEL LEAK WAS DETECTED IN THE RIGHT ENGINE. MAINTENANCE PERSONNEL PERFORMED REVISION ON RIGHT ENGINE VENTS AND DRAINS, DETECTING LEAK FUEL ON HEATER SERVO FUEL; SO THE HEATER SERVO FUEL WAS REPLACED IAW AMM 73-11-07-400/000-801-F00 AND RIGHT ENGINE WAS RUN IAW MM 71-00-00, TEST 3A, TESTED CORRECT.

Part: FUEL HEATER — LEAKING (RT ENGINE) · airframe 33,232 hrs · 14,372 cycles

FUEL LEAK IN THE RIGHT ENGINE, DURING TRANSIT CHECK, A FUEL LEAK WAS DETECTED IN THE RIGHT ENGINE. MAINTENANCE PERSONNEL PERFORMED REVISION ON RIGHT ENGINE VENTS AND DRAINS, DETECTING LEAK FUEL ON HEATER SERVO FUEL; SO THE HEATER SERVO FUEL WAS REPLACED IAW AMM 73-11-07-400/000-801-F00 AND RIGHT ENGINE WAS RUN IAW MM 71-00-00, TEST 3A, TESTED CORRECT.

Part: SELECTOR VALVE — FAILED (MLG) · airframe 31,003 hrs · 13,345 cycles

CAPTAIN REPORTED THAT DURING CLIMB, THE LANDING GEAR WAS MOVED UP AT THE THIRD ATTEMPT. AIRCRAFT WAS SENT TO THE HANGAR AND MAINTENANCE PERSONNEL PERFORMED BITE TO PSEU, IAW AMM 32-09-10 AND FIM 32-30 TASK 815 PROCEDURE, DETECTING MLG SELECTOR VALVE FAILED. SO THE MLG SELECTOR VALVE WAS REPLACED, IAW AMM 32-31-51-020-801AND AMM 32-31-51-400-801 AND OPERATIONAL TEST WAS PERFORMED, IAW 32-32-00-710-801, TESTED CORRECT.

Part: BEARING — EXCESS PLAY (ELEVATORS) · airframe 30,493 hrs · 13,114 cycles

DURING THE OVERNIGHT AT MEX STATION AND IN ACCORDANCE WITH 16A CHECK AND TASK CARD J3727-098-01-01, IT WAS DETECTED FREEPLAY OUT OF LIMITS AT BOTH ELEVATORS. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING FREEPLAY OUT OF LIMITS OF 0.218" AND 0.281 ON BOTH ELEVATORS, THE WO´S 7127834 AND 7127843 WERE ISSUED TO REPAIR THE DAMAGES DETECTED. THE TAIL CONES WERE REMOVED, IAW AMM 53-53-00-000-801. ELEVATOR OUTPUT TORQUE TUBE BUS LINKAGE FREEPLAY TEST WAS PERFORMED, IAW AMM 27-31-32-200-804, WITH 0.187" DISTANCE BETWEEN UP AND DOWN POSITION OF THE BOTH ELEVATORS, FOUND WITHIN LIMITS. CONTROL CRANK BEARINGS AND SLEEVES OF ELEVATOR WERE REPLACED, IAW AMM 27-31-74. THE TAIL CONE WERE INSTALLED, IAW AMM 53-53-00. ELEVATOR FREEPLAY CHECK WAS PERFORMED, IAW AMM 27-31-32, MEASURE BOTH SIDE OF 0.187". ELEVATOR POSITION TRANSMITTER TEST WAS PERFORMED, IAW AMM 31-31-51-700-801. MANUAL MODE TEST WAS PERFORMED, IAW AMM 27-31-00-700-807. ELEVATOR SURFACE FRICTION AND BALANCE TEST WAS PERFORMED, IAW AMM 27-31-00-700-802. ELEVATOR TRAVEL LIMIT TEST WAS PERFORMED, IAW AMM 27-31-00-700-804. ELEVATOR OUTPUT TORQUE TUBE BUS LINKAGE TEST WAS PERFORMED, IAW 27-31-00-700-805. ELEVATOR TAB LINKAGE TEST WAS PERFORMED, IAW AMM 27-31-00-700-806. CONTROL COLUMN TRAVEL AND CENTERING TEST WAS PERFORMED, IAW AMM 27-31-00-700-808. CONTROL COLUMN POWER AND FORCE TEST WAS PERFORMED, IAW AMM 27-31-00-700-809, TESTED CORRECT.

Part: SWITCH — FAILED (WARNING SYSTEM) · airframe 33,766 hrs · 15,412 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO TAKEOFF CONFIGURATION ALARM WAS ACTIVE. MAINTENANCE PERSONNEL PERFORMED TAKE OFF WARNING SYSTEM TEST, IAW AMM 31-51-00-730-803, CONFIRMING THE FAILURE. SO SPEED BRAKE TAKEOFF WARNING SWITCH S651 P/N V3L2228, S/S, MANUFACTURER HONEYWELL INTERNATIONAL INC WAS REPLACED, IAW AMM 31-51-03/401. LUBRICATION OF SPEED BRAKE LEVER BRAKE ASSEMBLY WAS PERFORMED, IAW AMM 12-22-81-600-801. THE SPEED BRAKE INSTALLATION TEST WAS PERFORMED, IAW AMM 31-51-03, TESTED CORRECT.

Part: ACOUSTIC PANEL — DAMAGED (LT ENGINE) · airframe 30,250 hrs · 12,982 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A SEVERAL SCRATCHES ON LEFT ENGINE INNER BARREL ACOUSTIC PANEL INLET COWL. MAINTENANCE PERSONNEL PERFORMED A REVISION, DETECTING A SEVERAL SCRATCHES OF 2.00 LENGTH AT 6 HRS AND 5:30 HRS POSITION WITH 4.5 AND 3.0 FROM THE AFT EDGE OF THE LIP SKIN. DAMAGES WERE REMOVED, IAW SRM 54-10-01-1A-1, PARAGRAPH 4C (2)(A), FIGURE 103, DETAIL C. ULTRASONIC, TAP TEST AND DVI INSPECTIONS WERE PERFORMED, IAW B737 NDTM PART 1, 51-05-01, NDTM PART 4, 51-00-00 PROCEDURE 2, SRM 54-10-01 ALLOWABLE DAMAGE 1, PARAGRAPH 4C(2) FIGURE 103, DETAIL C. NO DISBONDS OR CRACKS WERE FOUND WITH ORIGINAL THICKNESS OF 0.032" AND REMAINING OF 0.028" AND 0.029. CHEMICAL CONVERSION COATING WERE APPLIED, IAW SRM 51-20-01 PARAGRAPH 5. PERMANENT REPAIRS ON INNER BARREL ACOUSTIC PANEL WERE PERFORMED, IAW SRM 54-10-01-2R-7, REPAIR 7, PARAGRAPH 4, FIGURE 203. FINISHES TO THE REWORKED AREAS WERE APPLIED, IAW AMM 51-21-00. ALUMINIZED EPOXY PRIMER WAS APPLIED, IAW SRM 54-10-01-2R-7, REPAIR 7, PARAGRAPH 4F, ALL CORRECT.

Part: ACOUSTIC PANEL — DAMAGED (RT NACELLE) · airframe 30,224 hrs · 12,968 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A SEVERAL NICKS ON RIGHT ENGINE INNER BARREL ACOUSTIC PANEL INLET COWL. MAINTENANCE PERSONNEL PERFORMED A REVISION, DETECTING SEVERAL NICKS AL 2:30 HRS, 8 HRS AND 9:30 HRS POSITION. THE WO´S 7058591 AND 7058631 WERE ISSUED TO REPAIR THE DAMAGES DETECTED. NICKS WERE REMOVED, IAW SRM 54-10-01-1A-1, PARAGRAPH 4C (2) FIGURE 103, DETAIL C. AN ULTRASONIC THICKNESS MEASUREMENT INSPECTION, TAP TEST AND DETAIL VISUAL INSPECTIONS WERE PERFORMED ON NICKS AREAS, IAW B737 NDTM PART 4, 51-00-00, PROCEDURE 2, SRM 54-10-01 ALLOWABLE DAMAGE 1, PART 4C (2) FIGURE 103, DETAIL C WITHOUT DETECTING ANY CRACKS OR DISBONDS. WITH ORIGINAL THICKNESS OF 0.032" AND MINIMUM REMAINING THICKNESS 0.029" AND 0.027 OUT OF LIMITS, IAW SRM 54-10-01, ALLOWABLE DAMAGE 1, PART 4C(2), FIGURE 103, DETAIL C; PERMANENT REPAIRS WERE PERFORMED, IAW SRM 54-10-01-2R-7, PARAGRAPH 4. A CHEMICAL CONVERSION COATING WAS APPLIED, IAW SRM 51-020-0-0G-0, PARAGRAPH 5. ALUMINIZED EPOXY WAS APPLIED, IAW SRM 51-20-05 PARAGRAPH 4(F) ON LEFT ENGINE ACOUSTIC PANEL SKIN, ALL CORRECT.

Part: ACOUSTIC PANEL — DENTED · airframe 30,195 hrs · 12,954 cycles

DURING TRANSIT CHECK, IT WAS DETECTED SEVERAL NICKS, DENTS AND GOUGE ON BOTH ENGINES INNER BARREL ACOUSTIC PANEL. MAINTENANCE PERSONNEL PERFORMED A REVISION, DETECTING SEVERAL NICKS ON BOTH ENGINE INNER BARREL ACOUSTIC PANEL OF 0.093 LENGTH, OF 0.187" LENGTH AT 5:30 HRS, 6 HRS, BETWEEN 6 AND 7 HRS POSITION SEVERAL DENTS OF 0.250" WIDTH, 0.018" DEPTH, OF 0.375" WIDTH, 0.010" DEPTH; A DENT WITH A GOUGE INSIDE 0.375" DIAMETER, 0.008" DEPTH; THE DENTS WERE VERIFIED AND FOUND OUT OF LIMITS, IAW SRM 54-10-01-1A-1, ALLOWABLE DAMAGE 1, PARAGRAPH 4C (3), FIGURE 103 DETAIL F, W/Y=30 OR MORE 0.375/0.010=37.5 AND W/Y=30 OR MORE 0.250/0.018=13 AND A GOUGE OF 0.375" LENGTH. THE WO´S 7049591, 7049596, 7049602, 7049605, 7049623, 7049640 WERE ISSUED TO REPAIR THE DAMAGES DETECTED; SO THE DAMAGES WERE REMOVED, IAW SRM 54-10-01-1A-1, PARAGRAPH 4.C(2)(A), FIGURE 103, DETAIL C. A CHEMICAL CONVERSION COATING WAS APPLIED, IAW SRM 51-20-01-0G-0, PARAGRAPH 5; A ULTRASONIC, TAP TEST AND DVI INSPECTIONS WERE PERFORMED, IAW B737 NDTM PART 4, 51-00-00, PROCEDURE 2. NDTM PART 1, 51-05-01, SRM 54-10-01, ALLOWABLE DAMAGE 1, PARAGRAPH 4.C(2) FIGURE 103, DETAIL C, NO DISBONDS NOR CRACKS FOUND WITH ORIGINAL THICKNESS OF 0.032" AND REMAINING THICKNESS OF 0.031 AND 0.029 WITHIN LIMITS AND ORIGINAL THICKNESS OF 0.032" AND MINIMUM REMAINING THICKNESS OF 0.025" OUT OF LIMITS; A PERMANENT REPAIRS WERE PERFORMED ON INNER BARREL ACOUSTIC PANEL ON BOTH ENGINES IAW SRM 54-10-01-2R-7, REPAIR 7, PARAGRAPH 4, FIGURE 203; ALUMINIZED EPOXY PRIMER WAS APPLIED IAW SRM 54-10-01-2R-7, REPAIR 7, PARAGRAPH 4.F, ALL CORRECT.

Part: BLADE — DENTED (LT ENGINE FAN) · airframe 30,146 hrs · 12,932 cycles

DURING THE OVERNIGHT AT MEX STATION AND IN ACCORDANCE WITH EO 3772005 R4 OF LEFT ENGINE FAN DISK PRESSURE FACES INSPECTION, IT WAS DETECTED A DENT IN THE FAN BLADE ROOT NUMBER 3 AND 12, IAW AMM IT WAS NOT ALLOWED DAMAGES IN THAT AREA. SO THE LEFT ENGINE FAN BLADE P/N 340-000-410-0, MANUFACTURER CFM NUMBERS 3 AND 12 WERE REPLACED. IAW AMM 72-21-02-400-801-F00. FAN BLADE COMPLETE SET WAS LUBRICATED, IAW AMM 72-21-00 AND TEST 7 VIBRATION SURVEY WAS PERFORMED, IAW AMM 71-00-00, TESTED CORRECT.

Part: FUEL HEATER — LEAKING (LT ENGINE) · airframe 29,422 hrs · 12,597 cycles

DURING MAINTENANCE PROGRAM CHECK, IT WAS DETECTED A LEFT ENGINE FUEL LEAK. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING FUEL LEAK IN THE FUEL HEATER SERVO. THE LT HEATER SERVO FUEL WAS REPLACED IAW AMM 79-21-02, TESTED CORRECT.

Part: WHEEL — FAILED (MLG) · airframe 26,044 hrs · 11,304 cycles

CAPTAIN REPORTED HIGH VIBRATION DURING TAKEOFF IN MEX ON THE LEFT INBOARD / OUTBOARD MAIN LANDING GEAR. AT CUN, MAINTENANCE PERSONNEL PERFORMED THE TIRE TREAD LOSS OR TIRE BURST CONDITIONAL INSPECTION IAW AMM 05-51-54 AND GROUND HANDLING EQUIPMENT HITS AIRPLANE OR PART DEPARTS AIRPLANE CONDITIONAL INSPECTION IAW AMM 05-51-59, DETECTING MLG WHEEL AND TIRE POSITION 02 WITH THROWN TREAD AND DAMAGES ON LEFT FLAP INBOARD INDUCED BY MLG WHEEL AND TIRE POSITION 02. THE WO´S 5443578, 5443224 AND 5443356 WERE ISSUED TO REPAIR THE DAMAGES DETECTED. THE MLG WHEEL AND TIRE POSITIONS 01 AND 02 WERE REPLACED IAW AMM 32-45-11 AND LEFT WING AFT FLAP INBOARD WAS REPLACED IAW AMM TASK 27-51-12-000-801 AND AMM 27-51-12, TESTED CORRECT.

Part: INDICATION SYS — UNKNOWN (TE FLAPS) · airframe 18,570 hrs · 8,538 cycles

CAPTAIN REPORTED THAT DURING APPROACH, TRAILING EDGE FLAP DISAGREE, SO FLIGHT CREW ACCOMPLISHED THE QRH 9.28 PROCEDURE, BEING NECESSARY A MISSED APPROACH. MAINTENANCE PERSONNEL PERFORMED THE FIM 27-51 TASK 860 PROCEDURE, TESTED CORRECT. OVERSPEED CONDITIONAL INSPECTION WAS PERFORMED IAW AMM 05-51-04, NO DAMAGES WERE FOUND.

Part: SKIN — DAMAGED · airframe 14,916 hrs · 7,267 cycles

CAPTAIN REPORTED A LIGHTNING STRIKE IN THE FUSELAGE SKIN DURING DESCENT. MAINTENANCE PERSONNEL PERFORMED A LIGHTNING STRIKE INSPECTION IAW MM 05-51-19, DETECTING SEVERAL LIGHTNING STRIKES ON LEFT WINDOW FRAME NUMBERS 2 AND 3 AT D-F SILL AND E-F, G-H POSTS. INSPECTION PERSONNEL EVALUATED THE DAMAGE AND FOUND IT WITHIN LIMITS IAW AMM 05-51-19-210-801 AND AMM 05-51-19-710-801. AT MEX, A LIGHTNING STRIKE INSPECTION WAS PERFORMED IAW AMM 05-51-19 AND THE NON ROUTINE A0241119, A0241120 AND A0241121 WERE ISSUED, THE LIGHTNING STRIKES ON LEFT WINDOW FRAME NUMBERS 2 AND 3 AT D-F SILL AND E-F, G-H POSTS WERE REMOVED IAW SRM 56-10-02 PARAGRAPH 4.C.(5) FIGURE 102, DETAIL A, ALLOWABLE DAMAGE 1 AND IT WAS PERFORMED A HIGH FREQUENCY EDDY CURRENT INSPECTION IAW B737 NDTM PART 4 51-00-01 PROCEDURES 23 AND 28, NO CRACKS WAS FOUND, ALL CORRECT.