N128AM

Part: NONE — NONE · airframe 9,979 hrs · 1,232 cycles

DURING TRANSIT CHECK, IT WAS DETECTED SEVERAL LIGHTNING STRIKE ON RIGHT ENGINE THRUST REVERSER AND FUSELAGE SKIN. MAINTENANCE PERSONNEL PERFORMED A LIGHTNING STRIKE CONDITIONAL INSPECTION PHASE 1A, LEVEL EXAMINATION AND PHASE 1B AND II, GENERAL VISUAL INSPECTION AND SYSTEM COMPONENTS IAW AMM DMC-B-787-A-05-51-19-00A-311A-A, DETECTING SEVERAL LIGHTNING STRIKES ON RIGHT ENGINE THRUST REVERSER AFT FAIRING AT AFT EDGE; ON SEVERAL FUSELAGE SKIN FASTENERS WITH LOOS OF MATERIAL. THE WO´S 7738255, 7738258, 7738264, 7738302, 7738303, 7738304, 7738305, 7738308, 7738310, 7738312, 7738329, 7738333, 7738334, 7738335, 7738338, 7738339, 7738345, 7738346, 7738347, 7738348 AND 7738374 WERE ISSUED TO REPAIR THE DAMAGES DETECTED; THE THRUST REVERSER AFT FAIRINGS WERE REMOVED IAW AMM DMC-B787-G787-A-G78-31-21-00A-520A-A; DVI AND ULTRASONIC INSPECTIONS WERE PERFORMED AT AFFECTED AND SURROUNDING AREA IAW B787 NDTM PART 4, 51-00-03; ULTRASONIC INSPECTIONS WERE PERFORMED IAW B787 NDTM PART 4, 51-00-02/-03/-05 AND DOCUMENT COLLINS AEROSPACE NUMBER CV21-09697; TEMPORARY SEAL WERE PERFORMED IAW DOCUMENT COLLINS AEROSPACE NUMBER CV21-09697 REPAIR INSTRUCTIONS; RH ENGINE THRUST HALF REVERSER AFT FAIRING ACCESS PANEL WAS INSTALLED IAW DMC-B787-A-G78-31-21-00A-720A-A; DAMAGES WERE REMOVED IAW SRM B787-A-51-13-02-01A-280A-A; FASTENERS SHOULD BE REPLACE WITHIN 2000 FLIGHT CYCLES IAW SRM B787-A-53-30-01-04A-661A-A, TABLE 1, NOTE 25, ALL CORRECT.

Part: NONE — NONE · airframe 9,245 hrs · 1,134 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A LIGHTNING STRIKE ON EXTERIOR TIP TRAILING EDGE RIGHT ELEVATOR LOWER. MAINTENANCE PERSONNEL PERFORMED A LIGHTNING STRIKE CONDITIONAL INSPECTION PHASE 1A, LEVEL EXAMINATION AND PHASE 1B AND II, GENERAL VISUAL INSPECTION AND SYSTEM COMPONENTS IAW DMC-B787-A-05-51-19-00A-311A-A, DETECTING LIGHTNING STRIKE ON EXTERIOR TIP TRAILING EDGE RIGHT ELEVATOR LOWER LIGHTNING PROTECTION FRAME WITH DISBOND; FASTENERS WERE REMOVED IAW SRM B787-A-51-40-02-01A-010A-A, PARAGRAPH 7; STRIP FRAME WAS BONDED IN TRAILING EDGE IAW DWG BOEING NUMBER 323Z2000-1507; FASTENERS WERE INSTALLED IAW DWG BOEING NUMBER 323Z2000-1507 AND SRM B787-A-51-40-02-01A-010A-A, PARAGRAPH 7, ALL CORRECT.

Part: THRUST REVERSER — DAMAGED (RIGHT) · airframe 7,140 hrs · 825 cycles

DURING OVERNIGHT CHECK AT MEX, IT WAS DETECTED DAMAGE ON RIGHT ENGINE REVERSER. MAINTENANCE PERSONNEL PERFORMED GROUND HANDLING EQUIPMENT HITS AIRPLANE CONDITIONAL INSPECTION, IAW AMM 05-51-58. DETECTING LOSS OF SEALANT ON RIGHT ENGINE INBOARD THRUST REVERSER NOISE SUPPRESSOR. SO THE RIGHT ENGINE INBOARD THRUST REVERSER NOISE SUPPRESSOR P/N GENX1B76AP2G01, S/N 958314 WITH TSN 9853, CSN 1079, MANUFACTURER GENERAL ELECTRIC COMPANY WAS SEALED IAW AMM B787-A-54-61-01-00A-721B-A, ALL CORRECT.

Part: ENGINE — DAMAGED (RIGHT) · airframe 5,609 hrs · 639 cycles

IAW CNR 20200621005706014 OF REMOTE DIAGNOSTIC GE/CFM SYSTEM AT MEX STATION, THE RT ENG INCREASE OF PARTICLES IN THE DMS SENSOR, BEING NECESSARY TO PERFORM PROCEDURE IAW AMM DMC-B787-A-G79-00-00-07B-343A-A. VERIFY IF A MESSAGE EXISTS RELATED TO THE DMS SENSOR IN THE CMCF AND ATTEND ACCORDING TO THE MESSAGE FOUND. REMOVAL OF THE DMS SENSOR, IAW AMM DMC-B787-A-G79-21-12-01A-520A-A DEBRIS MONITORING SYSTEM SENSOR REMOVAL. PERFORMED THE GVI OF THE DMS SENSOR IAW AMM DMC-B787-A-G79-00-00-03B-311A-A. IF MAGNETIC PARTICLES ARE FOUND IN THE DMS SENSOR, APPLY THE CORRESPONDING CONDITION FOR 5 OR LESS PARTICLES AND/OR 6 OR MORE PARTICLES. IF PARTICLES ARE FOUND, SEND THEM TO THE LABORATORY FOR THEIR CORRESPONDING ANALYSIS; INSTALL THE DMS SENSOR IAW AMM DMC- B787-A-G79-21-12-01A-720A-A DEBRIS MONITORING SYSTEM SENSOR INSTALLATION IAW AMM DMC-B787-A-G71-00-00-44B-320A-A TEST 17 DEBRIS MONITORING SYSTEM OPERATIONAL TEST. THE VERIFICATION OF DMS SENSOR MESSAGES WAS PERFORMED IAW DMC-B787-A-G79-00-00-07B-343A-A, NO MESSAGES FOUND. REMOVAL THE GVI AND INSTALL OF DMS SENSOR WERE PERFORMED IAW AMM DMC-B787-A-G79-21-12-01A-520A-A, DMC-B787-A-G79-00-00-03B-311A-A AND DMC-B787-A-G79-21-12-01A-720A-A, FUZZ WERE FOUND AND SENT FOR ANALYSIS; THE DEBRIS MONITORING SYSTEM TEST 17 WAS PERFORMED IAW AMM DMC-B787-A-G71-00-00-44B-320A-A, TESTED CORRECT.

Part: HEAT EXCHANGER — FAILED (RIGHT) · airframe 4,493 hrs · 511 cycles

CAPTAIN REPORTED THAT DURING LANDING, THE LIGHT ELEC GEN OFF R2 LIGHT TURNED ON. MAINTENANCE PERSONNEL PERFORMED VISUAL INSPECTION DETECTING OIL AND FUEL OVER VARIABLE FREQUENCY STARTER GENERATOR. VFSG FUEL AND OIL HEAT EXCHANGER R2 RT ENGINE WAS REPLACED IAW DMC-B787-A24-11-12-00B-520A-A AND 720A-A, TEST CORRECT.

Part: ANTENNA — FAILED (ZONE 500) · airframe 3,254 hrs · 375 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXING BEFORE START THE TAKEOFF, THE TCAS LT AND TCAS RT MESSAGES WERE SHOWN, SO MAINTENANCE PERSONNEL PERFORMED RESET CONTINUING FAILURE. THE ANTENNA WAS REPLACED IAW AMM DMC-B787-A-34-42-05-00A-720-A, ALL CORRECT.

Part: SLEEVE — MISSING (BRAKE) · airframe 2,180 hrs · 256 cycles

DURING WHEEL BRAKE NUMBER 7 OF THE RIGHT MLG, IT WAS DETECTED THE BRAKE SLEEVE MISSING. MAINTENANCE PERSONNEL PERFORMED INSPECTION TO THE WHEEL BRAKE SLEEVE NUMBER 7 AND MLG AXLE IAW DMC-B787-A-32-11-26-00A-280A-A, NO DAMAGES WAS FOUND AND THE BRAKE SLEEVE WAS INSTALLED AND MESSAGE BOEING NUMBER AMX-AMX-190525-02B WAS ATTENDED AND NO DAMAGE WAS FOUND.

Part: CONNECTORS — DIRTY (PACK VALVES)

BOTH PACKS BLOW VERY HOT AIR IN ALL MODES. RETURNED TO FIELD. CLEANED CONNECTORS ON PACK VALVES RAN BOTH PACKS. CHECKS GOOD ON GROUND

Part: FCU — FAILED (TE FLAPS)

OUTBOARD FLAPS CONTROL FAULT AND WILL NOT RESET. RETURNED TO PDX. REPLACED FLAP CONTROL UNIT IAW MM 27.

Part: CONNECTOR — LOOSE (T6 HARNESS)

FAR - FIRE BOTTLE 'B' WILL NOT TEST AND T6 FLUCUTATE IN FLIGHT. MAINTENANCE CORRECTED A POOR GROUND CONNECTION AND TIGHTENED TERMINAL BLOCK OF THE T6 HARNESS. (M)

Part: FLAP SELECTOR — FAILED (COCKPIT)

ORD - FLAPS WILL NOT GO PAST 25 DEGREES WHEN FLAPS 45 DEGREES SELECTED. MAINTENANCE REPLACED FLAP SELECTOR. (M)

Part: ACTUATOR — OUT OF ADJUST (LT/RT MLG)

ORD - LEFT MAIN LANDING GEAR WILL NOT RETRACT. BOTH A AND B RED LIGHTS REMAIN ON AFTER GEAR SELECTED UP. MAINTENANCE ADJUSTED LEFT AND RIGHT MLG ACTUATORS AND UPLOCK INDICATOR SWITCHES. TEST FLIGHT SATISFACTORY. (M)

Part: RETRACT MECH — DIRTY (TE FLAPS)

RDU - FLAP DISAGREEMENT AFTER TAKEOFF. MAINTENANCE CLEANED FLAP TRACKS AND COULD NOT DUPLICATE DISAGREEMENT. (X)

Part: TRACKS — DIRTY (TE FLAPS)

RDU - FLAP DISAGREEMENT AFTER TAKEOFF ROLL. MAINTENANCE CLEANED FLAP TRACKS AS REQUIRED AND PERFORMED BITE TEST IAW EMB120 MM. SYSTEM OPERATES GOOD. (M)

Part: FILTERS — CLOGGED (FUEL SYSTEM)

RDU - FUEL FILTER LIGHT ILLUMINATED ON POWER UP FOR DEPARTURE. REMOVED ADN REPLACED FUEL PUMP OUTLET FILTER AND FUEL HEATER FILTER. AIRCRAFT RETURNED TO SERVICE. REFERENCE: OPERATOR CONTROL NR 96ZZZX3648. (X)

Part: FILTERS — CLOGGED (FUEL SYSTEM)

RDU - FUEL FILTER LIGHT ILLUMINATED ON POWER UP FOR DEPARTURE. REMOVED AND REPLACED FUEL PUMP OUTLET FILTER AND FUEL HEATER FILTER. AIRCRAFT RETURNED TO SERVICE. REFERENCE: OPERATOR CONTROL NR GLBA96114.

Part: FLAP ACTUATOR — FAILED (RT TE FLAP)

RDU - FLAP DISAGREEMENT, OUTBOARD FLAPS HANG AT ABOUT 10 DEGREES WHEN SELECTED FROM 15 DEGREES TO ZERO DEGREES. REMOVED AND REPLACED RIGHT OUTBOARD FLAP ACTUATOR, OPS CHECKS GOOD. (X)

Part: ACTUATOR — FAILED (LT TE FLAP)

MYR - CREW REPORTED A FLAP DISAGREEMENT FAULT AFTER TAKEOFF. THEY MADE AN AIR TURN-BACK AND LANDED UNEVENTFULLY. MAINTENANCE REPLACED LEFT OUTBOARD FLAP ACTUATOR. OPS CHECK WAS GOOD. (X)

Part: SWITCH — OUT OF ADJUST (SERVICE DOOR)

RDU - CREW REPORTED SERVICE DOOR ANNUNCIATOR ILLUMINATED AND THEY RETURNED TO THE GATE. MAINTENANCE ADJUSTED SERVICE DOOR MICROSWITCHES. SYSTEM OPS CHECK WAS GOOD. (M)

Part: FAULT INDICATION — ACTIVATED (TE FLAPS)

RDU - ON MAY 9 AND MAY 12, CREW REPORTED A FLAP ASYMMETRY FAULT FOLLOWING TAKEOFF. THEY MADE AIR TURNBACKS AND UNEVENTFUL LANDINGS ON BOTH DATES. MAINTENANCE CLEANED FLAP TRACKS AND PERFORMED BIT TESTS, BUT COULD NOT DUPLICATE DISCREPANCY. (X)

Part: PROX SENSOR — FAILED (LT STAB TRIM)

MYR - CREW REPORTED AURAL WARNING INDICATING UNSAFE TRIM SETTING ON TAKEOFF. ELECTED AN AIR TURN BACK AND MADE AN UNEVENTFUL LANDING. MX REMOVED AND REPLACED LEFT TRIM PROX SENSOR. SYSTEM OPS CHECK GOOD. (M)

Part: CURRENT LIMITOR — BURNT (RT WINDSHIELD)

STL - FLT 7151 - INSULATION BURNING TYPE SMELL WHEN RT WINDSHIELD HEAT IS TURNED ON. MAINTENANCE REPLACED WIRE AND WINDSHIELD HEAT CURRENT LIMITOR. (W)

Part: TRANSDUCER — MOISTURE (MLG)

STL - FLT 7458 - BRAKES ARE EXTREMELY WEAK EXCEPT AT VERY LOW SPEEDS, OK WITH ANTI-SKID OFF. MAINTENANCE CLEANED ALL FOUR ANTI-SKID TRANSDUCERS. TAXI CHECK REVEALED NORMAL OPERATION. (W)

Part: EEL BATTERY — DISCHARGED (CABIN)

STL - EMERGENCY LIGHTS ARE INOP. MAINTENANCE REPLACED EMERGENCY LIGHTING BATTERY. (W)

Part: CONTROL UNIT — MALFUNCTIONED (TE FLAPS)

STL - FLT 7495 - FLAP DISAGREEMENT WAS EXPERIENCED AFTER TAKEOFF. MAINTENANCE RERACKED FLAP CONTROL UNIT. SYSTEM TEST GOOD. (X)

Part: DEICE MONITOR — FAILED (AVIONICS BAY)

STL - FLT 7459 - DE-ICE MONITOR FAILED. MAINTENANCE RESET DE-ICE TIMER UNIT. TEST OF DE-ICING SYSTEM REVEALED NORMAL OPERATION. (X)