N342AM

Part: ACOUSTIC PANEL — DENTED (LT NACELLE) · airframe 48,321 hrs · 21,171 cycles

DURING OVERNIGHT CHECK AT MEX STATION, IT WAS DETECTED A SEVERAL DENTS AND A NICK ON LEFT ENGINE INNER BARREL ACOUSTIC PANEL INLET COWL. MAINTENANCE PERSONNEL PERFORMED A REVISION, DETECTING A SEVERAL DENTS WITH 2.875" AND 1.500"OF SEPARATION; A DENT OF 0.500 LENGTH, 0.001" DEPTH, 0.468 WIDTH; A DENT OF 0.500 LENGTH, 0.001" DEPTH, 0.375 WIDTH; A DENT OF 0.0437 LENGTH, 0.001" DEPTH, 0.0.406 WIDTH; A DENT OF 0.0.718 LENGTH, 0.005" DEPTH, 0.0.468 WIDTH AND A NICK OF 0.109" LENGTH, 0.062" WIDTH AT AFT EDGE INNER BARREL ACOUSTIC PANEL AND FROM 1.156" OF FASTENER, 10", 6.781 AT 6 HRS, 8 HRS, BETWEEN 3 AND 4 HRS POSITION. THE WO´S 7056228, 7056229 AND 7056272 WERE ISSUED TO REPAIR THE DAMAGES DETECTED. AN ULTRASONIC THICKNESS MEASUREMENT INSPECTION, TAP TEST AND DETAIL VISUAL INSPECTIONS WERE PERFORMED ON DENT AREAS, IAW B737 NDTM PART 1, 51-05-01 AND NDTM PART 4, 51-00-00 PROCEDURE 2, WITHOUT DETECTING ANY CRACKS OR DISBONDS WITH ORIGINAL THICKNESS OF 0.032". OF MINIMUM REMAINING THICKNESS 0.021" OUT OF LIMITS, IAW SRM 54-10-01, ALLOWABLE DAMAGE 1, PART 4C (2) FIGURE 103, DETAIL C. DENTS WERE REPAIRED IAW COLLINS MESSAGE NUMBER CV20-11065 AND SRM 54-10-01, REPAIR 14 PART 4. DENTS WERE ACCEPTABLE AS PERMANENT REPAIR, IAW COLLINS MESSAGE NUMBER CV20-11065. NICK WAS REMOVED IAW SRM 51-10-02 THE INNER BARREL ACOUSTIC PANEL WAS REPAIRED, IAW SRM 54-10-01 REPAIR 7 PART 4. ALUMINIZED EPOXY WAS APPLIED, IAW SRM 54-10-01-2R-7/14 ON LEFT ENGINE INNER BARREL ACOUSTIC PANEL INLET COWL, ALL CORRECT.

Part: SWITCH — FAILED (SPEED BRAKE) · airframe 48,282 hrs · 21,149 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXIING, WHEN PRESS TOGA FOR TAKEOFF SOUNDS THE ALARM OF TAKEOFF CONFIGURE WITH FLAPS 1 AND STAB TRIM 6.1. MAINTENANCE PERSONNEL PERFORMED BITE TO PSEU, IAW FIM 32-09 TASK 801 PROCEDURE AND FIM 27-62 TASK 808 PROCEDURE STEP F (2). THE SPEED BRAKE TAKEOFF WARNING SWITCH S651, P/N 65C10042-2 MANUFACTURER BOEING COMPANY WAS REPLACED, IAW AMM TASK 31-51-03-000/-400-801. A SPEED BRAKE INSTALLATION TEST WAS PERFORMED, IAW AMM TASK 31-51-03-840-002. THE SPEED BRAKE REJECTED TAKE OFF SWITCH P/N V3L2228, MANUFACTURER HONEYWELL INTERNATIONAL INC WAS REPLACED, IAW TASK 27-63-32-000/-400-801, TESTED CORRECT.

Part: PACKING — DAMAGED (HYD SYSTEM) · airframe 48,275 hrs · 21,145 cycles

DURING TRANSIT CHECK, A HYDRAULIC LEAKAGE WAS DETECTED ON FLAP CONTROL VALVE. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING PACKING´S OF HYDRAULIC LINES OF FLAP CONTROL VALVE WITH LEAKAGE. SO THE PACKING´S OF HYDRAULIC LINES P/N NAS1612-8A, MANUFACTURER BOEING COMPANY WAS REPLACED, IAW AMM 27-51-65/400, TESTED CORRECT.

Part: SKIN — DAMAGED (TE FLAP) · airframe 48,221 hrs · 21,106 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A DISBONDED AND ERODED OF LT OUTBOARD AFTER FLAP. MAINTENANCE PERSONNEL PERFORMED REVISION TO DISBONDED AND ERODED 2 AT UPPER AND LOWER SKIN ON TRAILING EDGE INBOARD CORNER OF LT OUTBOARD AFTER FLAP, FROM OTEF STA 88.2 TO OTEF STA 97.2. THE BOND TEST AND CTTU INSPECTIONS WERE PERFORMED DELIMITED LOWER SKIN DAMAGED AREAS IAW NDTM PART 4, 51-00-02 05. THE INNER AND UPPER SKIN ON TRAILING EDGE OF LT OUTBOARD AFTER FLAP WERE REPAIRED IAW SRM 57-53-01-2R-4 FIGURE 201. THE BOND TEST AND CTTU INSPECTIONS AT UPPER AND LOWER SKIN WERE PERFORMED ON REPAIRED AND SURROUNDING AREA WITH NO DISBONDS FOUND IAW NDTM PART 4, 51-00-02 05. THE OUTBOARD AFT FLAP WAS REMOVED AND INSTALLED IAW AMM 27-51-22-400-801, ALL CORRECT.

Part: WINDOW — CRACKED (COCKPIT) · airframe 45,334 hrs · 19,981 cycles

AIRCRAFT RETURN TO PLATFORM AS A CONSEQUENCE OF THE RT WINDOW NR 2 WAS CRACKED FRM 56102042; SO MAINTENANCE PERSONNEL REPLACED THE RT WINDOW P/N: 141A4810-39, S/N: 01269H9011 NR 2 IAW AMM56-12-11-400-801; IT WAS PERFORMED CABIN PRESSURE LEAK TEST IAW AMM 05-51-91-790-801, TEST CORRECT.

Part: IDG — FAILED (RIGHT) · airframe 44,051 hrs · 19,507 cycles

AIRCRAFT PERFORMED AN UNSCHEDULED LANDING AT MID DUE TO DURING CRUISE, THE APU SHUTDOWN AND RIGHT IDG WAS PREVIOUS DEFERRED. MAINTENANCE PERSONNEL PERFORMED REVIEW TO SYSTEM, DETECTING APU LOW OIL PRESSURE LIGHT TURNED ON WITH LIGHTEN AND APU WAS HAD PROTECTIVE SHUTDOWN; THE FIM 49-90 TASK 803 PROCEDURE AND LOW OIL PRESSURE PROCEDURE WERE PERFORMED AND THE RIGHT ENGINE INTEGRATED DRIVE GENERATOR (IDG) WAS REPLACED IAW AMM 24-11-11, TESTED CORRECT AND THE REPORT WAS CLOSED. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE AIRCRAFT LANDED WITH 61,900 KILOGRAMS AND THE MAXIMUM ALLOWABLE LANDING WEIGHT IS 65,317 KILOGRAMS.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 43,970 hrs · 19,479 cycles

DURING TRANSIT CHECK, A HYDRAULIC LEAK WAS DETECTED IN THE HYDRAULIC SYSTEM B OF THE ENGINE DRIVEN PUMP. MAINTENANCE PERSONNEL PERFORMED REVISION DETECTING HYDRAULIC LEAK AT HYDRAULIC SYSTEM B IN PLUG OF RETURN FILTER MODULE; SO THE RETURN FILTER MODULE PLUG P/N MS21902-W12 IN SYSTEM B WAS REPLACED IAW AMM 29-11-61, TESTED CORRECT.

Part: MOUNT — FAILED (WEATHER RADAR) · airframe 42,715 hrs · 18,980 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXING, THE EICAS MESSAGE WXR FAIL WAS SHOWN; MAINTENANCE PERSONNEL PERFORMED INSPECTION DETECTING MBA 4A MOUNTING TRAY FAILED IAW AMM 34-42; SO THE WEATHER RADAR R/T MOUNT WAS REPLACED P/N: 2041213-0413 S/N: MBA4A-08195 IAW AMM 34-43, TESTED CORRECT.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 42,473 hrs · 18,892 cycles

AIRCRAFT RETURN TO PLATFORM DUE TO BEFORE TO TAKEOFF, THE TAKEOFF CONFIGURATION ALARM AND LIGHT, PSEU LIGHT TURNED ON. MAINTENANCE PERSONNEL PERFORMED BITE TO PSEU IAW AMM 31-51-00, SHOWING MESSAGES AND FAILURE CODES STAB TRM NOT GRN, STAB TRM GREEN AND TAKEOFF WARN INHIBIT, 31-55006, 31-55007 AND 31-55008; SO THE TAKEOFF WARNING BITE TEST WAS PERFORMED IAW FIM 31-51 TASK 801 PROCEDURE, TESTED CORRECT.

Part: SEAL — LEAKING (OIL DRAIN) · airframe 41,887 hrs · 18,675 cycles

DURING OVERNIGHT CHECK, IT WAS DETECTED AN OIL LEAK IN THE LH ENGINE. MAINTENANCE PERSONNEL PERFORMED ENGINE 3A IDLE-POWER LEAKING TEST, DETECTING AN OIL LEAK ON N2 PAD DRAIN SEAL OF 60 DROPS PER MINUTE, BEING OUT OF LIMITS IAW AMM 71-71-00; SO THE MAGNETIC SEAL P/N 340-155-305-0 WAS REPLACED IAW AMM 72-63-00, TESTED CORRECT.

Part: SHUTOFF VALVE — LEAKING (RT ENG BLEED) · airframe 39,739 hrs · 17,804 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DUCT PRESSURE LOW INDICATION IN THE RIGHT ENGINE, SHOWING 18 PSI. MAINTENANCE PERFORMED REVISION IAW 36-11-00, DETECTING A PNEUMATIC LEAK IN THE RIGHT ENGINE PRSOV. THE RIGHT ENGINE PRSOV AND THE RIGHT ENGINE BLEED AIR REGULATOR WERE REPLACED IAW AMM 36-11-04 AND AMM 36-12-03, TESTED CORRECT.

Part: CONNECTOR — LOOSE (STAB) · airframe 36,037 hrs · 16,516 cycles

DURING TRANSIT CHECK, IT WAS DETECTED THE STABILIZER TRIM WITHOUT MOVEMENT. MAINTENANCE PERSONNEL PERFORMED REVISION DETECTING THE CONNECTOR D381 LOOSE, THEREFORE THE CONNECTOR WAS TIGHTENED IAW AMM 27-41-00,TESTED CORRECT. AS A PRECAUTIONARY ACTION, THE STAB TRIM STAB TRIM MOTOR WAS REPLACED IAW AMM 27-41-71, TESTED CORRECT.

Part: SLIDE — OUT OF LIMITS (ENTRY DOOR) · airframe 35,298 hrs · 16,198 cycles

DURING THE TRANSIT CHECK, THE ESCAPE SLIDE PACK FROM FWD ENTRY DOOR WAS FOUND OUT OF RANGE OF PRESSURE. MAINTENANCE PERSONNEL REPLACED THE ESCAPE SLIDE PACK IAW AMM 25-65-01, TESTED CORRECT.

Part: B-NUT — LOOSE (HYD LINE) · airframe 34,590 hrs · 15,933 cycles

DURING TRANSIT CHECK, DETECTED A HYDRAULIC LEAK IN THE RIGHT MAIN LANDING GEAR WW. MAINTENANCE PERFORMED FOUND THE HYDRAULIC LEAK IN THE HYDRAULIC SYSTEM B OF THE ENGINE DRIVEN PUMP HYDRAULIC PRESSURE LINE NUT. THE HYDRAULIC PRESSURE LINE WAS TIGHTENED IAW AMM 29-11-21 AND THE HYDRAULIC SYSTEM B WAS HYDRAULIC SERVICED IAW AMM 12-12-00, TESTED CORRECT.

Part: SHUTOFF VALVE — MALFUNCTIONED (FUEL SYSTEM) · airframe 34,397 hrs · 15,860 cycles

DURING FUELING, A FUEL SPILLAGE IN THE LEFT TANK WAS DETECTED DUE TO THE SHUTOFF VALVE DID NOT CLOSE. THE PLATFORM WAS CLEANED BY FIREMEN AND MAINTENANCE PERSONNEL CLOSED THE VALVE MANUALLY AND THE REFUELING SHUTOFF VALVE WAS DEFERRED BY MEL 28-10-2 CAT C. AT MEX, DURING OVERNIGHT CHECK, THE PRESSURE FUELLING SYSTEM TEST WAS PERFORMED IAW AMM 28-21-00, NOT LEAK WERE DETECTED AND SHUTOFF VALVE WORKED CORRECT.

Part: PUMP — FAILED (LEFT) · airframe 33,526 hrs · 15,487 cycles

AIRCRAFT RETURNED OF FLIGHT DUE TO DURING CLIMB AT FL 170´, THE LEFT ENGINE EXPERIENCED THRUST DETERIORATION AT A SHOW RATE, THE LEFT ENGINE THRUST LEVER WAS ADVANCED TO THE FULL THRUST POSITION WITHIN INDICATION OF THRUST INCREASING AT ALL PARAMETERS. AIRCRAFT WAS SENT TO THE HANGAR AND THE NRC´S A0241280 AND A0241281 WERE ISSUED TO REPAIR THE DAMAGES. MAINTENANCE PERSONNEL PERFORMED LEFT ENGINE BORESCOPE INSPECTION OF THE HIGH PRESSURE TURBINE IAW AMM TASK 72-00-00-200-807-F00, NO DAMAGES WERE FOUND AND FUEL PUMP PACKAGE INSPECTION WAS PERFORMED IAW FIM 73-31 TASK 803 AND TASK 73-11-01-200-801-F00, SHOWING FAILURE CODE 73-11551; SO THE FUEL PUMP PACKAGE, HMU AND FUEL NOZZLE FILTER WERE REPLACED I.A.W. AMM 73-11-01, AMM 73-21-10 AND AMM 73-11-03 AND OPERATIONAL TESTS 12-13, 3A AND 13A WERE PERFORMED IAW AMM 73-00-00, TESTED CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE AIRCRAFT LANDED WITH 49,700 KILOGRAMS AND THE MAXIMUM ALLOWABLE LANDING WEIGHT IS 65,317 KILOGRAMS.

Part: PUMP — FAILED (LT ENGINE) · airframe 33,526 hrs · 15,487 cycles

AIRCRAFT RETURNED DURING CLIMB AT FL 170´, THE LEFT ENGINE EXPERIENCED THRUST DETERIORATION AT A SHOW RATE, THE LEFT ENGINE THRUST LEVER WAS ADVANCED TO THE FULL THRUST POSITION WITHIN INDICATION OF THRUST INCREASING AT ALL PARAMETERS. AIRCRAFT WAS SENT TO THE HANGAR AND THE NRC´S A0241280 AND A0241281 WERE ISSUED TO REPAIR THE DAMAGES. MAINTENANCE PERSONNEL PERFORMED LEFT ENGINE BORESCOPE INSPECTION OF THE HIGH PRESSURE TURBINE IAW AMM TASK 72-00-00-200-807-F00, NO DAMAGES WERE FOUND AND FUEL PUMP PACKAGE INSPECTION WAS PERFORMED IAW FIM 73-31 TASK 803 AND TASK 73-11-01-200-801-F00, SHOWING FAILURE CODE 73-11551; SO THE FUEL PUMP PACKAGE, HMU AND FUEL NOZZLE FILTER WERE REPLACED I.A.W. AMM 73-11-01, AMM 73-21-10 AND AMM 73-11-03 AND OPERATIONAL TESTS 12-13, 3A AND 13A WERE PERFORMED IAW AMM 73-00-00, TESTED CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE AIRCRAFT LANDED WITH 49,700 KILOGRAMS AND THE MAXIMUM ALLOWABLE LANDING WEIGHT IS 65,317 KILOGRAMS.

Part: ACTUATOR — FAILED (LEFT) · airframe 32,627 hrs · 15,136 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING ENGINES START, THE LEFT ENGINE CONTROL LIGHT TURNED ON. MAINTENANCE PERSONNEL PERFORMED BITE TO LEFT EEC IAW FIM 73-10 TASK 801 PROCEDURE, SHOWING THE MESSAGES L REVERSER SLEEVE POSITION SIGNAL OUT OF RANGE; SO THE LEFT ENGINE UPPER LOCKING HYDRAULIC ACTUATOR OF THE SLEEVE REVERSE IAW AMM 78-31-03, TESTED CORRECT. AFTER, DURING PREFLIGHT CHECK, IT WAS DETECTED HYDRAULIC LEAK IN THE MAIN LANDING GEAR PIT. MAINTENANCE PERSONNEL PERFORMED REVISION DETECTING HYDRAULIC LEAK IN THE HYDRAULIC PUMP ACMP SYSTEM A; SO THE HYDRAULIC PUMP ACMP SYSTEM A WAS REPLACED IAW AMM 29-11-21, TESTED CORRECT.

Part: RELAY — FAILED (RIGHT) · airframe 27,207 hrs · 12,971 cycles

AIRCRAFT REJECTED TAKE OFF AT 80 KNOTS DUE TO MASTER CAUTION & RT AFT OVERWING DOOR LIGHTS TURNED ON. THE FLIGHT CREW PERFORMED THE QRH 1.8 PROCEDURE, CONFIRMING THE FAILURE. PERFORMED REMOVAL & INSTALLATION OF THE RT EMER EXIT DOOR IAW AMM 52-22-00 & IT PERFORMED BITE TO PSEU IAW FIM 32-09 TASK 801 PROCEDURE, SHOWING FAILURE CODES 52-72008, D10988 PIN 2. THE DOOR WARNING LIGHT SYS OVERWING WAS DEFERRED IAW MEL 52-3-2 CAT C. THE HIGH ENERGY STOP INSPECTION WAS PERFORMED IAW MM 05-51-07, NO DAMAGES WERE FOUND. THE RT RELAY R743 WAS REPLACED IAW AMM 52-41-14, THE RT AFT OVERWING LOCK SOLENOID M2221 WAS REPLACED IAW AMM 52-22-41 & RT AFT OVERWING EMER EXIT DOOR WAS CHECKED IAW AMM 52-22-00, TESTED CORRECT.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 27,196 hrs · 12,964 cycles

AIRCRAFT REJECTED TAKE OFF AT 60 KNOTS DUE TO MASTER CAUTION & RT AFT OVERWING DOOR LIGHTS TURNED ON. THE FLIGHT CREW PERFORMED THE QRH 1.8 PROCEDURE, CONFIRMING THE FAILURE. PERFORMED BITE TO PSEU & THE CB`S WERE RESEATED IAW FIM 32-09 TASK 801 PROCEDURE, NO CONFIRMING FAILURE, TESTED CORRECT. THE HIGH ENERGY STOP INSPECTION WAS NOT NECESSARY DUE TO THE MAXIMUM GROSS WEIGHT 67 317 KG & BRAKES ON SPEED 110 KNOTS WERE NOT EXCEEDED IAW MM 05-51-07.

Part: BATTERY PACK — DAMAGED (CABIN) · airframe 26,973 hrs · 12,874 cycles

AIRCRAFT RETURNED FROM FLIGHT DUE TO DURING CLIMB, ALL EMER LIGHTS TURNED ON & BURNED ODOR WITH NO EVIDENCE OF SMOKE WAS DETECTED. PERFORMED REVISION DETECTING IN THE M1671 BATTERY PACK THE CB P18-3 B-10 POPPED. O THE BATTERY PACK NR M1671 WAS DEFERRED IAW MEL 33-15-2 CAT C. THE BATTERY PACK NR M1671 WAS REPLACED IAW AMM 33-51-06, TESTED CORRECT & THE REPORT WAS CLOSED.

Part: SOLENOID — MALFUNCTIONED (DOOR) · airframe 26,889 hrs · 12,838 cycles

AIRCRAFT REJECTED TAKE OFF AT 60 KNOTS, DUE TO RT AFT OVERWING LIGHT TURNED ON. PERFORMED A REVISION AT THE AFT OVERWING DOOR IAW AMM 52-20-00 & BITE TO PSEU IAW FIM 52-20 TASK 801 PROCEDURE, SHOWING FAILURE MSG. R FL SW FAULT, & DETECTING FAILURE OF FLIGHT LOCK SOLENOID. THE FLIGHT LOCK SOLENOID WAS DEFERRED IAW MEL 52-15 CAT C. THE HIGH ENERGY STOP INSPECTION WAS NOT NECESSARY DUE TO THE MAXIMUM GROSS WEIGHT 65 317 KG & THE BRAKES ON SPEED 110 KNOTS WERE NOT EXCEEDED IAW MM 05-51-07. THE FIM 52-20 TASK 808 PROCEDURE WAS PERFORMED, NO FAILURE WAS FOUND & THE REPORT WAS CLOSED.

Part: WIRE HARNESS — DAMAGED (LT ENGINE) · airframe 26,618 hrs · 12,715 cycles

CAPTAIN REPORTED THAT DURING CRUISE, THE BLEED TRIP OFF LIGHT TURNED ON. ACCOMPLISHED THE QRH 2.6 PROCEDURE, CONFIRMING THE FAILURE & CONTINUING TO DESTINATION. PERFORMED THE FIM 36-10 TASK 801 DETECTING WIRING HARNESS DAMAGE. MW0311 LT ENG WIRING HARNESS WAS REPLACED IAW AMM 36-10-00 & LT ENG BLEED CROSSOVER TEST WAS PERFORMED IAW AMM 36-11-00, ALL CORRECT.

Part: BRAKE ASSY — DAMAGED (LT MLG) · airframe 26,411 hrs · 12,619 cycles

AIRCRAFT REJECTED TAKEOFF AT 120 KNOTS, DUE TO AN ABNORMAL VIBRATION IN THE LT MLG. PERFORMED HIGH ENERGY STOP INSPECTION & AIRFRAME VIBRATION CONDITION INSPECTION IAW AMM 05-51-07 & AMM 05-51-67, DETECTED LT MLG BRAKES & WHEELS NRS 1 & 2 DAMAGED, LT MLG AXLE DAMAGED & LT CTR & INNER MAIN GEAR DOORS MISSING. LT MLG & WHEELS NRS 1 & 2 REPLACED IAW AMM 32-41-41 & AMM 32-45-11, LT MLG AXLE REPLACED IAW AMM 32-11-85. THE MLG LOWER SIDE STRUT WAS FOUND WITH LIGHT TWIST, SO THE LOWER SIDE STRUT WAS REPLACED IAW AMM 32-11-61.

Part: OVEN — CONTAMINATED (GALLEY) · airframe 22,556 hrs · 10,900 cycles

ACFT RETURNED TO PLATFORM, F/A REPORTED THAT A WIRE BURNED ODOR AFTER AFT GALLEY OVENS TURNED ON. MAINTENANCE PERFORMED SMOKE OR FUMES IN CABIN CONDITIONAL INSPECTION IAW MM 05-51-56, DETECTING PAPER BURNED PROPERTY OF CATERING; THE PAPER WAS REMOVED AND AFT GALLEY OVENS TESTED IAW CMM 25-35-03, ALL CORRECT.

Part: UNKNOWN — UNKNOWN · airframe 22,455 hrs · 10,856 cycles

CAPTAIN REPORTED THAT DURING DESCENT, A STRONG NOISE IN COCKPIT FWD COMPARTMENT WAS HEARD. MX PERFORMED A PRESSURIZATION VALVE AND OUTFLOW VALVE EXTERIOR VISUAL INSPECTION AND BITE TO CONTROLLER NR 2 IAW AMM 21-31-00, ALL CORRECT.

Part: SKIN — DAMAGED (BS 480) · airframe 21,346 hrs · 10,354 cycles

CAPTAIN REPORTED A LIGHTNING STRIKE DURING APPROACH IN THE FUSELAGE SKIN. MX PERSONNEL PERFORMED A LIGHTNING STRIKE INSPECTION IAW MM 05-51-19 DETECTING A PERFORATION OUT OF LIMITS OF .1250" DIAMETER AT BS 480. FUSELAGE SKIN AT BS 480 WAS REPAIRED IAW SRM 53-00-01, FIG 204-13, ALL CORRECT.