737 MAX
Incident Reports

FWD ENTRY DOOR LT AT 85KIAS DURING TAKEOFF. COMPLIED WITH HIGH ENERGY STOP INPECTION IN REFERENCE TO AMM TASK 05-51-07-210-801 STEP 2.NO DAMAGE OR DEFECTS FOUND. PSEU LOGGED MAINTENANCE MESSAGE 52-71111. ENTRY DOOR INDICATION SENSOR TEST GOOD PER AMM TASK 52-71-11-710-801. THE OMF SHOWS NOT ACTIVE FOR THE MAINTENANCE MESSAGE. REQUESTING TO PLACE FWD ENTRY DOOR WARNING ON MEL 5271E. .APPROVED COMPLIED WITH STEPS (M) A. 1. AND D. OF MEL 5271E. *DM* DUE TO 52-71111, SUGGEST FIM 52-20 TASK 801, SEE M/L FOR FWD ENTRY DR SENSOR.

20C EMERGENCY EXIT LIGHT DANGLING. FOUND GREEN CABLE FOR BLUE IFE LIGHT ROUTED INCORRECTLY CAUSING THE RED EMERGENCY LIGHT HOUSING MOUNTING HARDWARE TO SEPERATE FROM CASE. INSTALLED A SERVICABLE PART FROM STOCK MAN PN 1044199-301BTB M&E PN 42-2521-3-0084. HOUSING IS SECURE AND LIGHT OPERATES NORMALLY. ITEM CLOSED. PARTS USED: 42-2521-3-0084, QTY :1

PASSING 16;000; FLIGHT ATTENDANTS IN BACK OF AIRCRAFT REPORTED VIBRATION AND AR NOISE. EAR WERE POPPING AND FELT PRESSRE.

ON BLEEDS OFF TAKEOFF UNABLE TO PRESSURISE ACFT WITH ENG BLEEDS. UNABLETO RESET PER FLT CREW, THE ONLY WAY TO REGAIN BOTH ENG BLEEDS WAS TO PUSH BLEED TRIP RESET BUTTON EVEN THOUGH THERE WERE NO BLEED TRIP LIGHTS. AFTER RESET, BLEEDS OPERATED NORMALLY. BITE CHECKED BOTH CPC, CPC 1 NO FAULTS FOUND , CPC 2 SHOULD FAULT LO INFL/HI LEAKAGE, NO MAINTENANCE MESSAGE DISPLAYED , RESET FAULTS ON CPC2. FOLLOWED FIM 21-31 TASK 802, 21-31 TASK 808 CORRECTION FIM 21-31 TASK 839. BITE CPC 2 AFTER RESET NO FAULTS SHOWN REF AMMTASK 21-31-00-740-801. PLEASE NOTE TAKE OFF REPORT (UIO-IAH) "B44B" PACK 1 = HIGH, PACK 2 = HIGH, ISO VALVE = OPEN, NOT CONFIG. PER FLIGHT MANUAL SEC. 5.20.3, SUGGEST PERFORMING ENGINE START, AND PRESSURIZE A/C WITH APU BLEED LEFT PACK ONLY AND THEN WITH ENGINE BLEEDS TO VERIFY NO FAILURES. PEFORMED ENGINE IDLE SYSTEM TEST PER AMM TASK 71-00-00-700-808-G00 AND WHILE ENGINES WERE RUNNING PERFORMED MULTIPLE PRESSURIZATION PER AMM TASK 21-31-00-710-801 WITH BOTH ENGINES AND APU IN MULTIPLE CONFIGS AND PRESSUIZED IN NO ENGINE BLEED TAKEOFF CONFIG WITH NO ISSUES.

LE FLAPS TRANSIT ILLUMINATED AFTER FLAP RETRACTIONSDR STARTED PER FIM 27-81 TASK 830 REPLACE THE FSEU M1746 IF ALL MESSAGE ARE NOT ACTIVE. INSTALLED NEW FSEU PER AMM 27-51-01-400-801 , COMPLETED UP TO F(1) PER AMM 27-51-01-400-801. ROTOABLE PARTS HAS BEEN COMPLETED. NEED TO COMPLETE ALL TEST PER AMM ADD EMP:U102091 27-51-01-400-801. SEE ELOTO FOR OPEN CBS. PARTS USED: 43-2751-9-0013,QTY :1 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1522772 SN OFF 9004 UNIT, FLAP SLAT OFF 43-2751-9-0013 9004 ON 43-2751-9-0013 9162 AHM SHOWED FAULTS 27-81214 "LE SLAT 8 OUTBOARD SENSOR SIGANL DOES NOT AGREE WITH OTHER LE SLAT OUTBOARD SENSOR SIGNALS" AND 27-81215 "LE SLAT 8 INBOARD SENSOR SIGNAL DOES NOT AGREE WITH OTHER LE SLAT INBOARD SIGNALS" FSEU REPLACMENT WAS NO HELP WHILE PERFORMED A LEADING EDGE CRUISE DEPRESSURIZATION TEST IN REFERENCE TO B737 AMM 27-81-00-730-801 NOTICED THE NUMBER 8 SLAT LAGGED BEHIND THE REST OF THE SLATS ON EXTENTION DURING TEST WHEN SLAT WHERE RETRACTED NUMBER 8 SLAT RETRACTED QUICKER THE THE REST AND SLATS LOCKED OUT DUE TO ASSYMETREY MAINT LIGHT ILLUMINATED AND AND BOTH SMYDS SHOWED MESSAGES FOR LEADING EDGE SLAT ASYM SUSPECT NUMBER 8 SLAT ACTUATOR OR RIG REFERENCE B737 FIM 27-81 TASK 820 ADDED PICTURES OF DIFFERENCE BETWEEN NUMBER 7 AND 8 SLAT AS WELL AS NUMBER 1 AND 2 SLAT ON THE OPPPOSITE WING FOR COMPARISON AFTER VERIFIED #8 SLAT ACTUATOR ROD END TORQUE AND FINAL INSTALLATIONLEAK CK AND OPERATION OF #8 SLAT, NO LIMITING DEFECTS NOTED PER GMM 09-10-05

CB FOR FWD GALLEY COFFEE MAKER POPPED WAS NOT IN USE MAKER NUMBE R 105REMOVED C/M 105 AND C/M 106. INSPECTED VISIBLE WIRING, CONNECTORS, GROUNDS FOR SHORTS OR DEFECTS, NONE NOTED. REMOVED POWER PANEL ASSY IN FWD GALLEY NEXT TO C/MAKERS. INSPECTED WIRING, CONNECTORS AND CLAPS FOR DAMAGE OR SHORTS, NO DEFECTS NOTED. REMOVED POWER PANEL NEXT TO FORWARD OVEN. INSPECTED WIRING, CONNECTOR AND GROUNDS. NO DEFECTS NOTED. OPERATED BOTH FORWARD OVENS FOR 20 MINUTES, NO DEFECTS. CONTINUED... RAN SEVERAL BREW CYCLES ON BOTH FWD C/MAKERS. NO DEFECTS. VERIFIED BOTH HOTPLATE DRAINS DRAIN PROPERLY. CREW REPORTED THAT INTO PBI THE PRIOR FLIGHT, THEY NOTICED AN ELECTRICAL SMELL BUT NO SMELL WAS IN GALLEY. SUSPECT POSSIBLE SHORT OR DEFECT BETWEEN FWD GALLEY POWER SOURCE AND THE 2 FORWARD GALLEY MODULES. NEEDS FURTHER TROUBLESHOOTING TO DETERMINE CAUSE. T/S PER WDM 25-31-11 AND CMM 25-31-147. FOUND LOOSE SCREWS ON TERMINAL LUGS OF CB101 AND CB102. TIGHTENED SCREWS. MEASURED CURRENT ON ALL 3 PHASES WITH CLAMP METER. MEASURED 0 AMPS WITH BOTH COFFEE MAKERS AT REST AND 6.6 AMPS FOR EACH COFFEE MAKERS WHEN THEY WERE BREWING. ISOLATED CIRCUIT BY PULLING CB C914 AND REMOVING GALLEY PWR IND LIGHT. MEGGED WIRES AT RECEPTACLES OF COFFEE MAKERS 105 & 106. EACH PHASES TO NEUTURAL AND GND & TO EACH OTHER. NON DEFECTS NOTED. RE-INSTALLED ALL BACK TO THEIR ORIGINAL POSIPOSITIONS. PERFORMED OPS CHECK OF COFFEE MAKERS 105 & 106 IAW AMM 25-32-01. OPS CHECK GOOD. CB102 AND CB103 REMAINED IN AFTER NUMUROUS TESTS.

FOUND LH FWD OVERWING EXTERIOR EMERGENCY LIGHT INOP WHILE PERFORMING TC 33-010-00. GROUNDED - YES. RELAMPED REF AMM 33-51-04. OPS NML. LENS ASSY HAS DAMAGED SCREW, REQ'S REPLACEMENT. INSTALLED SERVICEABLE SCREW REF AMM 33-51-04.

#1 ENGINE AFT FAIRING LOWER HEAT SHEILD HAS A LARGE CRACK IN THE LOWER PAN

REF TTG8Q00VTMYX; #2 ENGINE PYLON AFT FAIRING CRACK DAMAGE

STRONG ELEC SMELL IN CABIN ROWS 22-27 QRH RAN AT FL350 THEN DI VERT TO DENFLIGHT AND CABIN CREWS COMPLIED WITH SMOKE ODOR QUESTIONAIRE SEE PICS FIM 21-00- TASK 830 NEEDS COMPLIED WITH REMOVED AND REPLACED RELAY R560 REF SWPM 20-81-11 AND AIPC 24-21-21-61A. REMOVED CEILING PANELS AROUND ROWS 21-27, NO DEFECTS NOTED IN ANY WIRING. INSTALLED CEILING PANELS PER AMM 25-21-45. TURNED ON PED OUTLETS AND PLUGGED INTO SEVERAL, NO SMELL COMING FROM ANY OUTLETS. TURNED ON BOTH LEFT AND RIGHT PACKS, SET EACH TEMPERATURE CONTROL TO COLD, NO SMELL. SET TEMP TO AUTO, NOTICED HEAVY ELECTRICAL/BURNING SMELL IN ROWS 21-27. PER FIM 21-00 TASK 830 STEP Q(3) INSPECTED AIR RECIRC FAN FILTERS. BOTH FANS AIR FILTERS SMELLED OF BURNING SIMILAR TO CABIN. REPLACED LEFT AND RIGHT AIR RECIRC FANS FILTERS PER AMM 21-25-01-400-801. PARTS USED: 29-2124-3-0006,QTY :1 OPERATED BOTH PACKS ON AUTO TEMP FOR 10 MINUTES. SMELL IN CABIN IS LESS BUT STILL PRESENT IN SAME ROWS. REMOVED AND REPLACED LEFT RECIRCULATION FAN. AMM 21-25-03-400-801. UP TO AND INCLUDING, STEP 3. C. (2) (A). STILL REQUIRES LEAK CHECK. PARTS USED: 29-2125-9-0001,QTY :1 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1368631 SN OFF 7825 FAN, AIR, DISTR OFF 29-2125-9-0001 7825 ON 29-2125-9-0001 4365 REMOVED & REPLACED RIGHT RECIRC FANREF AMM 21-25-03-400-801 UP TO AND INCLUDING STEP 3. C. (2) REF FIM 21-00 TASK 830. REPLACED BOTH L/R RECERT FANS PERCATIONAATY. PACKS RUNNING,FANS RUNNING, UNABLE TO DUPLICATE ELCT SMELL. ADD EMP:U411446

AFT GALLEY; FO SIDE; FA FLASHLIGHT WILL NOT TEST. OK TO CONTINUE PER MEL 25-64-02A;SP1B 218184

EMERGENCY LIGHTS OPERATIONAL CHECK EMERGENCY LIGHTS OPERATIONAL CHECK - SEAT ROWS 1-5 AND R1 EXTERIOR EMERGECY LIGHTS INOP PERFORMED FIM 33-51 TASK 806. REMOVED AND REPLACED M2816 BATTERY PACK. NO HELP. REMOVED AND REPLACED ALL 4 FUSES REF AMM 33-51-06. OPS CHECK GOOD. FUSES CORRECTED THE FAULT. RE-INSTALLED ORIGONAL BATTERY PACK. OPS CHECK GOOD

ON TAKEOFF WITH AUTO THROTTLE ENGAGED ENG #1 N1 FLUCTUATED RAPIDLY FROM 85-89% FLUCTUATIONS CEASED AFTER 3 MINUTES/ CLIMB THRUST SELECTED COMMANDED N1 WAS 87.0%

ANTI-SKID INOP LIGHT ILLUMINATED. BRAKE ENERGY ON LANDING 28.6M FT-LB. BRAKE COOLING TIME 52 MIN

FWD CABIN LT & RT EMERGENCY LIGHTS INOP

EMERGENCY EXIT LIGHTS FROM ROW 38 TO 32 INOP TESTED AFT LEFT POWER SUPPLY (PLUG D10746) REF WDM 33-51-22 PER AMM 33-51-06, LIGHTS REMAIN INOP. R/R ALL 4 FUSES ON AFT LEFT POWER SUPPLY PER AMM 33-51-06, NO HELP. SWAPPED MID POWER SUPPLY (PLUG D10716) WITH LEFT AFT POWER SUPPLY (PLUG D10746), NO HELP. SUSPECT WIRING HARNESS ON ONE OF THE SEAT FROM ROWS 32-38 OR WIRING FROM AFT LEFT POWER SUPPLY (PLUG 10746). REQUIRE AVIONICS SUPPORT. REF L/P 9475240 CLOSED IN ERROR ALL GALLEY AND LAV MODULE LIGHTS WERE WORKING. DISCONNECTED THE PIGTAIL FROM ROW 38 AND THE REST OF THE LIGHTS TESTED GOOD. RECONNECTED PIGTAIL AND ALL LIGHTS NOW WORKED NORMALLY. OK TO CONTINUE.

CABIN EMER LIGHTS BREAKER POPPED. GROUNDED - YES. VERIFIED OPEN C/B AT P6-5 ROW B18. OPEN P6-5 ACCOMP GVI OF C/B NO DEFECTS NOTED. CLOSED P6-5. ACCOMP EMERGENCY LIGHTS TEST FROM FLT DECK, TEST PASS. CLOSED C/B AT P6-5 ROW B18. ACCOMP EMERGENCY LIGHTS TEST FROM AFT ATTENDANT PNL, TEST PASS & C/B STAYED CLOSED. REF AMM 33-*51-00-720-801 & AMM 20-60-01-860-005 & WDM 33-51-11-2.

#2 ENG AFT FAIRING HEAT SHIELD LOWER SUPPRESSOR SKIN IS CRACKED SEE ATTACHED PICTURE FOR REFERENCE

EMERGENCY LIGHTS OPERATIONAL CHECK EMERGENCY LIGHTS OPERATIONAL CHECK - RIGHT AFT EMERGENCY EIXT LOWER LIGHT INOP ROW 21 FOUND RIGHT AFT EMERGENCY EXIT DOOR LIGHT L1188 CONNECTED TO WIRING FOR AFT OVERWING DOOR FWD TRIM HEATER M2202. SWAPPED CONNECTION, R/R DAMAGED EMERGENCY EXIT SIGN IAW AMM 33-51-01. OPS CHECK FOR EMERGENCY EXIT LIGHT GOOD IAW AMM 33-51-00. OPS CHECK FOR RIGHT AFT OVERWING EXIT DOOR HEAT GOOD IAW AMM 21-45-00. PARTS USED: 29-3351-3-0022,QTY :1

L/H FWD CABIN EMERGENCY LIGHTS INOP.

AFT ENTRY EMERGENCY LIGHTS INOP.

R/H FWD CABIN EMERGENCY LIGHTS INOP.

FWD SERVICE EMERGENCY LIGHTS INOP.

TAT AT 99 LOST LNAV/VNAV AT T/O LOST N1 LIMITS AND ENG 1/2 AIR DATA REPLACED TAT PROBE REF AMM TASK 34-21-06-000-801, OP CHECKS GOOD

STATIC OVER ALL COMMS 1- 3. ON CLIMB COULDN/T HEAR AT ALL. DISSI PATED IN DESCENT. DURING CREW BRIEFING NOTICED FLIGHT CREW HAD OWN HEADSETS PLUGGED IN. THEY WHERE NOT THE GOOD BOSE HEADSETS. UNLESS COMPANY PROVIDED HEADSETS OR ONE PARTICULAR BOSE HEADSET IS USED THERE MAY BE VERY LOUD STATIC OR BACKGROUND NOISE ON VHF SYSTEM ON 737 AIRCRAFT. PER AMM 23-11-00 USED COMPANY PROVIDED HEADSETS AND OPS CHECK OF ALL THREE RADIOS. ALL THREE RADIOS ARE VERY LOUD AND CLEAR. ALSO ACCOMPLISHED NOSE RADOME STATIC GROUND CHECK. NOSE RADOME GROUND POINTS FOR STATIC BUILDUP ALL CHECK GOOD. FOUND HEADSET JACK TIP INSIDE FLIGHT INTERPHONE JACK IN NOSE WHEELWELL. SEE PIC. REMOVED SAME, OP CHECK OF JACK NORMAL REF AMM 23-51-00

PER FLIGHT SAFETY REQUEST PULL AND COLLAR CVR AND FDR C/B'S PULLED 5 EA BREAKERS. ON P 18-2 PANEL. VOICE RECORDER RIPS, VOICE RECORDER RELAY, FR AC, FR DC, FR POSITION SENSOR TOMC LOCKING LOG UNTIL APPROVAL TO RESET C/B'S OR REPLACE CVR/FDR FLIGHT SAFETY CONTACTED AND DO NOT WANT THE CVR OR FDR PULLED. OK TO RESTORE THE SYSTEMS AND RETURN THE A/C TO SERVICE RESET AND SECURED ALL FIVE BREAKERS PER TOM C

STAB TRIM INOP AFTER LANDING. STAB TRIM ACTUATOR CIRCUIT BREAKER IS POPPED. REMOVED AND REPLACED STABILIZER TRIM MOTOR IAW AMM 27-41-71-700-801 AND AMM 27-41-71-400-801. OPERATIONAL CHK GOOD. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1515090 SN OFF 1093 MOTOR, STABILIZ OFF 42-2741-9-0003 1093 ON 42-2741-9-0003 1025 ACCOMPLISHED RII INSPECTION CHAPTER 27 FLIGHT CONTROLS THS ACTUATOR . CREW WAS USING CONTROL COLUMN TRIM SWITCHES DURING LANDING, AFTER LANDING STAB TRIM ACTUATOR BREAKER POPPED, MANUAL TRIM WAS JAMMED REQUIRING HIGH FORCE WITH NO SIGNIFICANT MOVEMENT, ALSO SEE LP 9382131, TRIED FIM 27-41 TASK 809 NO HELP, REPLACED STAB TRIM MOTOR OPS CHECKED NORMAL

FOUND WATER LEAK IN AFT GALLEY. FROM STATION 887 TO 1016 AND STRINGER 17L TO 17R 887 TO BS 1016 BETWEEN LEFT BUTT LINE (LBL) 64 AND (RIGHT) RBL ARMENTA TOMC 64 AS REQUIRED PER ECRA 2011-01000, GALLEY SPILL, SECTION 2.B. ECRA 2011-0100, GALLEY SPILL, SECTION 2.B., IN-DEPTH CLEAN UP, THE THE APROXIMATE AREA OKAY TO CARRY FORWARD WITH A NON-HAZARDOUS GALLEY SPILL DUE TO TOMC-APPROVAL FROM SC1ELBYC COMMENT SERVICING WATER OVERFLOW AN IMMEDIATE CLEANUP OF GALLEY SPILL UP TO STEP 2. (10) ECRA 2011-01000. WITHIN SEVEN (7) CALENDAR DAYS, ACCOMPLISH AN IN-DEPTH CLEANUP, FROM BS 887 TO BS 1016 BETWEEN LBL 64 AND RBL 64 AS REQUIRED PER ECRA 2011-01000, GALLEY SPILL, SECTION 2.B. NO WATER FOUND IN CARGO PITS OR ANY ELECTRONICS. WATER CONTAINED DURING H2O SANITATION, HOSE WAS HOOKED UP INCORRECTLY AND CAUSED PREFORMED IMMEDIATE CLEANUP OF GALLY SPILL UP TO STEP 2. (10) OF UPDATE FOR BUTT LINE INFORMATION, FROM LBL 64 TO RBL 64.

DURING TOWING OPERATION, APPROX 15 MIN AFTER AC LANDED, TAIL PIP E FIRE INDICATED VISUALLY IN #1 ENGINE, INSP ENGINE FOR POSSIBLE HEAT DAMAGE. *UPDATE TO SHOW SDR REPORTABLE*

ON DESCENT WE NOTICE A DIRTYSOX SMELL I (CAPTAIN) NOTICED IT AS WE BEGAN DESCENT. F.O. NOTICED IT BEFORE. INTENSITY WAS LEVEL 1-2 WEAK TO MODERATE INTENSITY FA "D" ALSO NOTICED THE ODOR IN THE BACK OF AIRCRAFT. F.O. REPORTED FEELING A HEADACHE. I (CAPTAIN) EYES FELT IRRITATED ODOR APPEARED TO BE COMMING FROM VENTS. GROUNDED - YES. ON DEFERRAL.

A/C DIVERTED TO PHX DUE TO POSSIBLE CABIN AIR CONTAMINATION . SUSPECT CARBON MONOXIDE DUE TO FLIGHT CREW REPORTING DIZZY/LIGHT HEADED LOCKING LOG PAGE TO COMPLY WITH CONDITIONAL INSPECTION 05-51-56. ADDED SFR REQUIREMENT UNLOCKING TO UPDATE AND CLOSE LOG T/S FUMES IN FWD GALLEY AREA FOUND GALLEY 1 NO POWER, C/B C914 POPPED , RESET BREAKER AND OPS CHECKED GALLEY COMPONETS. BREAKER REMAINED CLOSE,SSM 25-31-11-101. REPLACED HEPA FILTERS REF 21-25-01 BEFORE AND AFTER HIGH POWER ENGINES RUN. NO FUMES OR SMOKE NOTED, NO SYMPTOMS OF DIZZINESS NOTED BY ANY OF THE 4 TECHNICIANS ONBOARD DURING HIGH POWER RUN REF 71-00-00, 21-00 TASK 830,05-51-56-200-801 TOMC REVIEW AND AGREES WITH CORRECTIVE ACTIONS.

PASSENGER CABIN EMERGENCY PROXIMITY LIGHTING SHOWS SIGNS OF WATER/HUMIDITY DAMAGE NEAR PASSENGER CABIN SEAT 30C.

FLIGHT ATTENDANT REPORTS BURNING PLASTIC COMING FROM AFT COFFEE MAKER 2B

AFT WING EMERGENCY EXIT LIGHT INOP

EMERGENCY LIGHT BATTERY PACK (M2335) FAILS TO CHARGE (STA 500C+7 LBL 67)

FWD ENTRY FOOR SLIDE EMERGENCY LIGHT INOP

#2 ENGINE STRUT AFT HEAT SHIELD SKIN HAS A LARGE CRACK #2 ENGINE STRUT AFT HEAT SHIELD SKIN HAS A LARGE CRACK REF. SRM 54-50-70-1A-3 ALLOWABLE DAMAGE LIMITS 4(B)

DURING EXTERNAL INSPECTION FOUND #2 ENGINE PYLON CRACK LOWER SKIN AFT. CRACK IS APPROX. 8.5 INCHES LONG.

ON DESCENT LE FLAPS TRANSIT LIGHT ILLUMINATED. PERFORMED FIM 27-81 TASK 821. OPS CHECKED LE FLAPS. LE FLAPS TRANSIT LIGHT REMAINS EXTINGUISHED. NO PREVIOUS HISTORY. OK FOR SERVICE. PERFORMED FIM 27-81 TASK 821. OPS CHECKED LE FLAPS. LE FLAPS TRANSIT LIGHT REMAINS EXTINGUISHED. NO PREVIOUS HISTORY. OK FOR SERVICE.

DURING ETOPS PDSC WALK AROUND; FOUND SEVERAL CRACKS AND DELAMINATED DIVETS ON RADOME SURFACE.

ROLL AUTHORITY ON FINAL 7NM 1500FT PER DFCS BITE SEE PHOTOS. REF AMM 22-11-00 PER FIM 22-11 TASK D79. PER AMM22-11-25-710-801 TEST PASS NO FAULTS . ADD EMP:U102168 NEED TO CONTINUE WITH FIM 22-11-D79. PERFORMED AMM 27-11-00-710-801, OPS CHECK IS GOOD. PERFORMED AMM 27-61-00-710-801, OPS CHECK IS GOOD. BOTH REQUIRED PER FIM 22-11 D 79. AMM TASKS 22-11-25-710-801, 22-23-00-710-802, 27-11-00-730-801, 27-21-00-700-805 & 27-21-00-700-807 STILL NEED TO BE ACCOMPLISHED PER FIM 22-11 D 79. ATTEMPTED TO PERFORM LAND VERIFY TEST TO NARROW DOWN TROUBLESHOOTING. ACFT IS FAILING DUAL STAB AND SUBSEQUENTLY MACH TRIM TESTS AND GIVING HARD FAULT OF 22-11191 MT CMD MON. ADDING FCC PART PRECAUTIONARY. ABOVE UPDATE FOR MESSAGE 22-11191 TRANSCRIBED TO LOGPAGE 9215536 SEE REFERENCED LOGPAGE FOR DISPOSITION PERFORMED AUTOPILOT AILERON ACTUATOR TEST IN REFERENCE TO B737 AMM 22-11-25-710-801 TEST PASSED PERFORMED YAW DAMPER SYSTEM TEST IN REFERENCE TO B737 AMM 22-23-00-710-802 SYSTEM TEST PASSED UPDATED FOR SDR PERFORMED AILERON TRIM RESPONSE TEST IN REFERENCE TO B737 AMM 27-11-00-730-801 TEST PASSED ADD EMP:U388284, PERFORMED RUDDER TRIM SYSTEM TEST IN REFERENCE TO B737 AMM 27-21-00-700-807 TEST PASSED PERFORMED RUDDER TRAVEL TEST IN REFERENCE TO B737 AMM 27-21-00-700-805 TEST PASSED ALL TESTS IN B737 FIM 22-11 TASK D79 HAVE BEEN COMPLETED WITH NO FAULTS FOUND ADD EMP:U388284, COMPLETED B737 FIM 22-11-D79 WITH NO FAULTS FOUND SPOKE WITH TOMC OK TO CLEAR FCC A REPLACED ON LOGPAGE 9204147

FA'S REPORT THAT R1 DOOR IS DIFFICULT TO CLOSE FULLY. CLOSES WITH HANDLE IN CORRECT POSITION, BUT CAN LEAVE OPEN GAP AT UPPER RIGHT CORNER. REQUIRES MULTIPLE ATTEMPTS TO ENSURE IT CLOSES COMPLETELY. GROUNDED - YES. VERIFIED R1 DOOR CLOSED W/ AN OPEN GAP AT UPPER R/H CORNER INTERMITTENTLY. FOUND GUIDE ARM ADJUSTMENT JAMNUT LOOSE. ADJUSTED GUIDE ARM REF AMM 52-41-00 STEP 2.(I). OPS CHECK GOOD DOOR OPERATES AS INTENDED. SKIN CLEARANCE AND FLUSHNESS CHECK GOOD. ACCOMPLISHED GALLEY SERVICED DOOR SYSTEM TEST REF AMM 52-41-00-700-801. TEST PASSED. VERIFIED GUIDE ARM ADJUSTMENT JAMNUT IS TIGHTENED.

WHILE IN CRUISE FL380 A SLIGHT BURNING SMELL BECAME PRESENT IN COCKPIT AND CABIN. SMELL QUICKLY BECAME VERY INTENSE IN CABIN AND COCKPIT. BOTH QRC AND QRH COMPLETED FOR SMOKE/FIRE OR FUMES. 02 MASKS CONT...DONNED SMELL DISSIPATED SHORTLY BEFORE LANDING AND DID NOT RETURN. NO VISIBLE SMOKE INDICATIONS WERE EVER PRESENT. NO 30DH - CH21/CH36

11C EMERGENCY EXIT LIGHT INOP. WIRE BROKEN PLACING 11C EMERGENCY LIGHT ON MEL 3351A. VERIFIED THAT THE ADJACENT EMERGENCY LIGHT IS OPERATIVE. TOMC APPROVED ,OK TO DEFER PER MEL 3351A APPLIED MEL 3351A. PLACED INOP PLACARD ON EMERG LIGHT SWITCH T/S PER MERIDIAN 1072994 CMM REF 25-21-65. FOUND RECEPTACLE ON HARNESS PART NUMBER BR9631-28 MISSING, REQUIRES NEW HARNESS. ADD EMP:U393350 HARNESS IS NIS @ EWR. ALSO MISSING ARE FLOOR PROXIMITY EMERGENCY LIGHT MISSING, PART NUMBER BR9644-21FS, OUTBOARD SHROUD ASSY MISSING, PART NUMBER 1078850-305BWC, AND INNER SHROUD ASSY MISSING, PART NUMBER 1044199-301BTD. *DM* ASSIST: {HRNSS/29-2542-3-0042, EPL CLOSEOUT/42-2521-3-0084, RACEWAY SHROUD/42-2521-3-0092, & LT MODULE/99-3350-3-0008 PREV ORDERED (MODULE DUPED M&E+MFG: I CANXD MFG#BR9644-21FS)}.INCREASED M/H TO MATCH GRND TIME @ 3 REMOVED AND REPLACED EMERGENCY PROXIMATELY LIGHT AND WIRE HARNNESS AT SEAT ROW 11ABC PER AMM 33-51-11-960-801.PARTS USED: 29-2542-3-0042,QTY :1 99-3350-3-0008,QTY :1

L1 DOOR LOWER HINGE COVER BINDING UP DOOR ON OPENING. GROUNDED - YES. PERFORMED GVI OF L1 DOOR, FRAME, SURROUNDING AREA. OPS CK'D DOOR FROM INSIDE AND OUT MULTIPLE TIMES. NO DEFECTS FOUND. OPERATES AS IT SHOULD.

STAB TRIM UNCOMMANDED NOSE DOWN TRIM DURING LANDING ROLLOUT. MAI N ELEC TRIM NOT APPLIEDTALKED TO PILOTS. STAB ON LAND ROLLOUT WITH AUTO PILOT OFF TRIM STARTED TO GO FULL DOWN. PILOT MADE SURE HAND WAS OFF ELECTRIC TRIM. WHEN NOTICED WAS OFF THEY HOT TRIM CUT OUT AMD THE TRIM STOPPED. NO FUALTS IN HISTORY AND NO FULTS IN EXSITING OR INBOUND. UPDATED TO REPORT SDR FOUND NO FAULTS IN INBOUND FLIGHT DECK EFFECTS OR FAULT HISTORY PEROFORMED STABALIZER TRIM MOTOR TEST IN REFERENCE TO B737 AMM 27-41-71-700-801 TEST PASSED AWAITING ESC TO REVIEW QAR DATA FOR FURTHER DIRECTION PERFORMED DIGITAL FLIGHT CONTROL SYSTEM SPEED TRIM/STAB TRIM DISCRETE BITE TEST IN REFERENCE TO B737 AMM 22-11-00-740-815 TEST PASSED STILL AWAITING ESC RESPONSE FOR FURTHER DIRECTION AFTER QAR DATA REVIEW VERIFIED BOTH FCC'S IN GROUND MODE 28 VOLTS ON BOTH FCC A AND B ON PIN B3. PER ESC REQUEST PERFORMED AN ANGLE OF ATTACK SENSOR SYSTEM TEST IN REFERENCE TO B737 AMM 34-21-05-730-801 TEST PASSED PERFORMED DFCS BITE FOR THE ADIRU AND SMYD IN REFERENCE TO B737 AMM 22-11-00-740-801 TEST PASSED PERFORMED AN OPERATIONAL TEST OF THE STALL WARNING SYSTEM IN REFERENCE TO B737 AMM 27-32-00-710-802 OPERATIONAL TEST PASSED NO FAULTS FOUND CONFIRMED BOTH FCCS INSTALLED ARE 822-1604-102 REFERENCE B737 IPC 22-11-33-03 AS REQUESTED REPLACED FCC A IN REFERENCE TO B737 AMM 22-11-33-400-801 CONFIRMED CORRECT SOFTALL ABOVE ACTIONS COMPLIED WITH PER ESC INSTRUCTIONS. REPLACED BOTH FCCS ALL OPERATIONAL TESTS PASSED OK TO CLOSE ITEM

PER INBOUND CAPTAIN, AT ALTITUDE IN CRUISE, EXPERIENCED UN COMMANDED ROLL RIGHT. MAX ROLL AUTHORITY LIMIT STOP WAS REACHED. AIRCRAFT WAS AT FL 340, 255KTS ON ARRIVAL. THEY WERE APPROACHING A WAYPOINT THAT REQUIRED A SLIGHT RT TURN. AUTOPILOT STARTED THE RIGHT TURN AND CONTINUED UNTIL AIRCRAFT REACHED 33 DEGREES OF BANK. THE AUTOPILOT THEN COMMANDED YOKE TO LEFT TO CORRECT BUT THE PLANE CONTINUED TURNING RIGHT. AT THIS POINT "ROLL AUTHORITY" WAS ANNUCIATED. PILOTS THEM DISCONNECTED AUTOPILOT AND MADE EXCESSIVE LEFT ON YOKE TO REGAIN WINGS LEVEL. PILOTS STATED THEY EXPERIENCED BUFFETING/SHUDDERING THROUGH THE AIRFRAME. THEY STATED IT SEEMED LIKE A SPOLIER WAS UP. THEY DONT THINK IT WAS WAKE TURBULENCE OR MOUNTAIN WAVE TURBULENCE. ACCESSED MY BOEING FLEET TO FIND MAINTENANCE MESSAGES. NONE FOUND. ACCOMPLISHED SEVERE OR UNUSUAL TURBULENCE, EXCESSIVE MANEUVER CONDITIONAL INSPECTION ON LOG PAGE 9133363 FOLLOWED FIM 22-11 TASK D79. PREFORMED ALL OPS CHECKS LISTED. ALL OPS CHECKS GOOD, FOUND NO DISCREPANCIES. ACCOMPLISHED DFCS BITE TESTS REF AMM 22-11-00-740-814 AND LAND VERIFY TEST PASSED. HOWEVER A RELATED FAULT WAS FOUND IN LEG 01. FAULT MSG 22-11715, "ROLL AUTHORITY" MATCHES THE DATE AND FLIGHT PARAMETERS. NEED TO ACCOMPLISH FIM TASK 22-11 TDUE TO UNCOMMANDED ROLE WE HAVE C/W FIM TASK 22-11-C37, AND 22-11-D79. REF LOG PAGE 9133363 FOR SEVER TURBULANCE INSPECTION C/W. A/C HAS BEEN RETURNED TO SERVICE AND READY FOR T-HOP.

UPPER FWD DOOR STOP FITTING ON L2 DOOR REQUIRES REPLACEMENT DUE TO BEING OUT OF LIMIT PER SRM 52-10-90-1A1 AD1. REMOVED FITTING FOR REPLACEMENT. HOLES AND COUNTERSINKS FOR HOLES COMMON TO FITTING REQUIRE INSPECTION. HOLES AND COUNTERSINKS FOR HOLES COMMON TO FITTING REQUIRE INSPECTION. VERIFIED RII REQUIREMENTS, PERFORMED HOLE PROBE INSPECTION REF NDTM PART 6 51-00-00 PROCEDURE 16. NO DEFECTS NOTED. DRILLED FITTING OFF OF DOOR, CLEANED AND DEBURRED FITTING. REQUEST OK TO INSTALL FITTING. DRILLED FITTING OFF OF DOOR, CLEANED AND DEBURRED FITTING. REQUEST OK TO INSTALL FITTING. VERIFIED RII REQUIREMENTS OK TO INSTALL FITTING

TWO AFT GALLEY FLASHLIGHTS WILL NOT TEST

#1 ENG FILTER BYPASS INFLIGHT, INFLIGHT SHUTDOWN. GROUNDED - YES. ACCOMPLISHED TSR 716465 UP TO STEP 7. FOUND MAGNETIC METAL MATERIAL IN THE SCAVENGE FILTER AND ON THE ODMS SENSOR. ODMS POD WAS USED AND THE SCAVENGE FILTER ROUTED TO AOG ENGINEERING FOR ANALYSIS. ALL SCAVENGE SCREENS WERE REMOVED AND FOUND NO DEBRIS. INSTALLED ALL SCAVENGE SCREENS AND SCAVENGE FILTERS IAW TSR. MAINTENANCE MESSAGE:79-42890 DESCENT, OIL FILTER IMPENDING BYPASS FAULT CODE: 79330251. REQUIRES TROUBLESHOOTING. COMPLETED 70 PERCENT RUN FOR 10 MINUTES INSPECTED ODMS AND SCAVENGE SCREENS, NO PARTICLES FOUND. INSTALLED ODMS REF AMM 79-21-12-400-801-G00 AND SCAVENGE SCREEN PLUGS REF AMM 79-21-04-400-801-G00. LEAK CHK GOOD. ACCOMPLISHED INFLIGHT WINDMILLING INSPECTION REF AMM 71-00-00-200-807-G00. TSR 716465 COMPLETE. FINDINGS REPORTED TO AOG ENGINEERING CONSULTED AND ADVISED RETURN TO SERVICE. REF LOGPAGE 60787795 FOR SIGNIFICANT EVENT PROCESS COMPLETED AND AIRCRAFT RETURN TO SERVICE AUTHORIZATION BY SEAMC.

IAS DISAGREE AT 100KTS F/O 100KTS.CA 70 KTS RTO.RETURNING TO GAT E ACCOMPLISHED PITOT STATIC SYSTEM FLUSHING REF AMM34-11-00-170-802. FOUND TO DEBRIS DURING FLUSHING PROCESS. FOUND MAINT MESSAGE 31-03120. REPLACED #2 ADM NO HELP. LATER FOUND MAINT MESSAGE 31-03120 SWAPPED #1 & #2 ADIRS. FAULT DID ADD EMP:344425 NOT FOLLOW. RETURNED ADIRS TO ORIGINAL POSITIOMS. FOUND NO DEBRIS DURING FLUSH PROCESS. REF FIM 31-65 TASK B70 & FIM 31-65 TASK B74. UPDATED LABOR HOURS REMOVED AND REPLACED RH AOA SENSOR IAW B737 AMM 34-21-05. OPS CHECK GOOD. REMOVED AND REINSTALLED ORIGINAL RH ADM IAW B737 AMM 34-21-04. OPS CHECK GOOD.PARTS USED: 29-3412-9-0001,QTY :1 ADD EMP:U348571 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1460359 SN OFF 6558 SENSOR, ANGLE O OFF 29-3412-9-0001 6558 ON 29-3412-9-0001 9256 VERIFIED ALL PITOT AND STATIC PORTS COVERS REMOVED, AND QDS RECONNECTED. OPS CHECK NORMAL. UPDATE ROTABLE PART CHANGED ROTABLE PARTS CHANGE WAS INDICATED - TT # 1325600 SN OFF 3217 MODULE, AIR DAT OFF 42-3413-9-0001 3217 ON 42-3413-9-0001 7799

FOUND DENT REF LP 8972873, AVO13111A HAS BEEN COMPLETED. INSPECTION HAS EMAILED ENGINEERING OF THEIR FINDING STRINGER INSPECTED NO DAMAGE NOTED. VERIFIED ALL STEPS OF AVO COMPLETE ACCOMPLISHED DETAILED VISUAL INSPECTION OF REPAIR AREA REF AVO13111 STEP 15 AND 16 STEPS WORKED ON PER AVO13111 REV. B - ACCOMPLISHED STEP 17, WILL NOT BE REPLACING S-29 AS ADVISED IN STEP 18. ACCOMPLISHED GVI OF S-29 AND FOUND NO DAMAGE. ALL STEPS OF AVO13111 REV. B HAVE BEEN COMPLIED WITH SENT ALL FINDINGS TO ESC FOR FURTHER REPAIR 2 DENTS, DENT 1 IS LOCATED FWD OF E & E DOOR, AT BS 316 AND O/B OF S29-C. DENT 2 IS LOCATED BS 314 AND 8" O/B OF S-29-C. PERFORMED STEP 14-A-C AND E-K OF AVO 13111 REV B. CUT DAMAGE OUT AT 2 LOCATIONS. PERFORMED INSURANCE CUTS ON BOTH DAMAGE CUT OUTS, REF AVO 1311 REVB, STEP 14-D. COMPLIED WITH INSPECTION OF AVO13111 STEP 14. NO DISCREPANCIES NOTED,INCLUDING STEP 14.D. HFEC, INCLUDING INSURANCE CUT. NO LIMITING DEFECTS NOTED DURING INSPECTION REF AVO13111 STEPS 15 AND 16 INSTALLED TCAS ANTENNA IAW EC/RA 5330-07331 STEP 28 AND 34-45-02-400-801. REQ INSP. BONDING MEASURES 0.82 MILLI OHM. PREV ABOVE STATEMENT REQUIRES INSPECTION VERIFIED THE ECRA 5330-073371 REV ORIGINAL. ARE COMPLETED SIGN OFF UP TO AND INCLUDED SPET 30. INSTALLED INTERIM REPAIR DOUBLER/TRIPLER REF EC/RA 5330-07331.

ENG 2 HYD LOW PRESS LT WAS FIRST INDICATION OF LOSSZOF ALL QTY I N SYS B. CREW REPORTED THAT FIRST INDICATION WAS ENGINE 2 HYDRAULIC ENGINE DRIVEN PUMP LOW PRESSURE LIGHT ON. CREW RAN QRH SHUT DOWN NUMBER 2 EDP THEN RAN ALTERNATE PROCEDURES. WHEN CREW COMPLETED QRH THEY FOUND SYSTEM B HYDRAULIC RESERVOIR WAS AT 0. CREW REPORTED THAT NUMBER2 ELECTRIC DRIVEN PUMP WAS ON FOR SOMETIME AFTER RESERVOIR WAS EMPTY. ATTEMPTED TO FILL HYD SYST B RESERVOIR BY HAND PUMP METHOD. FLUID STARTED LEAKING FROM ENG 2 FWD DRAIN MAST. CLOSED ENG 2 PYLON VALVES WITH FIRE HANDLE IN FLIGHT DECK. TAGGED FIRE HANDLE WITH LOTO TAG

FMC 2 PGM FAULT 34-62001 FAULT WAS 34-62001 FMC-2 PGM FAULT DETECTED BY: FLIGHT MANAGEMENT COMPUTER (FMC)-1. REF TSM 34-61-882, DUE TO FMC DISAGREE MESSAGE REPLACED FMC-2 REF AMM TASK 34-61-02-000-801 & TASK 34-61-02-000-801. PICTURE INCLUDED OF INSTALLED FMC. FMC REMOVED WAS PN 176200-01-01 SN 019415. OPS CHECKED OK.

EMERGENCY LIGHT BATTERY PACK M1671 WILL NOT HOLD A CHARGE

L1 DOOR EMERGENCY SLIDE LIGHT INOP THE IMAGES ATTACHED ARE OF THE BACKSIDE OF THE FORWARD GALLEY/WINDSCREEN ON THE LEFT SIDE OF AIRCRAFT. THE RED SQUARE INDICATES THE AREA WHERE THE CHAFFED WIRE WAS FOUND. THE VERTICAL RECTANGLE IS THE LOCATION OF AN ALUMINUM BRACKET THAT SUPPORTS THE FRONT EDGE OF THE KICK PANEL. IT HAS A TAB WITH A SCREW SLOT AT THE TOP OF THE BRACKET THAT ATTACHES IT TO THE GALLEY WALL. THIS TAB WAS RUBBING AGAINST THE WIRING FOR THE SLIDE LIGHT.

EMERGENCY LIGHT BATTERY PACK M1676 WILL NOT HOLD A CHARGE

EMERGENCY LIGHT BATTERY PACK M2816 WILL NOT HOLD A CHARGE

EMERGENCY LIGHT BATTERY PACK M2335 WILL NOT HOLD A CHARGE

EMERGENCY LIGHT BATTERY PACK M1675 WILL NOT HOLD A CHARGE

EMERGENCY LIGHT BATTERY PACK M1695 WILL NOT HOLD A CHARGE

EMERGENCY LIGHT BATTERY PACK M1670 WILL NOT HOLD A CHARGE

FORWARD CARGO COMPARTMENT STA. 500I AFT BULKHEAD LOWER CENTER SUPPORT IS CORRODED. GROUNDED - YES. EVALUATED CORROSION OF SUPPORT, FOUND TO BE CORRODED MULTIPLE AREAS THAT EXCEED 10% WIDTH OF LOWER FLANGE, FOUND TO BE OUT OF LIMITS IAW B737-MAX SRM 53-00-53-1A-2 FIG. 103 SHEET 2 DETAIL A&B. REMOVED AND REPLACED LOWER CENTER SUPPORT IAW B737-MAX SRM 51-40-02 AND BAC DWG 143A9481 REV. A. REMOVED AND REINSTALLED FLOOR PANEL 120EF IAW B737-MAX AMM 5110-04. LOWER CENTER SUPPORT P/N 143A9485-35 P.O.# 1096478.2.

M1673 EMERGENCY EXIT LIGHT BATT PACK AT STA 952 WL 290 LBL 14 WILL NOT CHARGE.

M1672 EMERGENCY EXIT LIGHT BATT PACK AT STA 952 WL 291 RBL 14 WILL NOT CHARGE.

R/H HORIZONTAL STABILIZER UPPER FORWARD SLIDING SEAL HAS A VERTICAL CRACK ON THE FORWARD SIDE.

DOT A24-7 RH WING #12 SPOILER UPPER SKIN IS DELAMINATED ABOUT 2 INCHES O/B OF I/B EDGE AND 2 THROUGH 10 INCHES FWD OF AFT EDGE.

PROCEDURE - LIFE VEST SEAL WRONG SECURITY SEALS INSTALLED 6 EACH REMOVED 6 EACH FOUND WRONG TAGS SECURITY. INSTALLED SEALS ME 29-2521-3-0030.

LH HORIZONTAL STABILIZER-TO-BODY UPPER FRONT SPAR SLIDING SEAL IS CRACKED.

AFT ENTRY LIGHT ILLUMINATED ON TAKEOFF ROLL DID NOT EXCEED 80 KTS, REJECTED TAKEOFF. OPENED AND CLOSED L2 DOOR IAW AMM 52-13-00, NO DEFECTS NOTED AT THIS TIME. DOOR SECURED CLOSED, LIGHT EXTINGUISHED. PERFORMED HIGH SPEED ENERGY STOP INSPECTION IAW AMM 05-51-07, NO DEFECTS NOTED. SPEED AT 80 KTS NO DAMAGE NOTED. REF LP 737-002-9548. PER COMPANY REQUEST ADJUSTED L2 DOOR PROX SWITCH SENSOR IAW AMM 52-71-11 PERFORMED OPS CHECK OF DOOR WARNING SYSTEM IAW AMM 52-71-00 OPS CHECK GOOD AT THIS TIME.

THROUGHOUT THE PASSENGER CABIN THERE ARE SEVERAL FLOOR PROXIMITY GLOW STRIPS THAT HAVE THE PART NUMBER TAGS STILL ATTACHED TO THE UPPER SURFACES.

NEITHER AUTOPILOT WILL ENGAGE AFTER SEVERAL ATTEMPTS DURING CLIM B AND CRUISE ACCOMPLISHED FIM TASK 22-11 TASK 933 FOR MAINT MSG 22-11176 UP TO STEP F.2. REMOVED AND REPLACED MAIN ELEC STAB TRIM RELAY R1193, REQUIRES LAND VERIFY. PERFORMED SPD/STB TRIM TEST LAND VERIFY TEST PER AMM 22-11-00-700-801. OPS CHK GOOD. ALL TEST PAASED WITH NO FAULTS

UPON LANDING, R2 EMERGENCY LIGHT ILLUMINATED AND EXIT LIGHT ILLUMINATED. BOTH LIGHTS WENT OUT AFTER APPROXIMATELY 15 SECONDS NO PRESSURIZATION ISSUES NOTED AND NO COCKPIT INDICATION PRESENT. GROUNDED - YES. R2 DOOR INSPED, NO DEFECTS NOTED.OPENED & CLOSED INSIDE & OUTSIDE HANDLES PRFM'D EMERGENCY LIGHT TEST IAW AMM 33-51-00-720-801. CHIK'D COCKPIT DEFECTS FOR DOOR & LIGHT INDITCATIONS NO DEFECTS NOTED.

2 MIN AFTE TAKEOFF AFT FA REPORTED A VERY LOUD VIBRATION AND NOI SE FOR 5 MIN. HISSING AFTEWARDS UPON INITIAL EVALUATION, FOUND DAMAGE TO UPPER RIGHT DOOR STOP AND HARDWARE. THREADED INSERT RETAINING CLIP/PIN IS MISSING, INSERT IS LOOSE. PHOTOS ATTACHED. LOCATION IS L2 DOOR AS REPORTED BY FA. ADJUSTED GUIDE ARM IN REFERENCE TO AMM 52-13-00-820-801. THE DOOR NO LONGER CONTACTS THE STOP FITTING IN TRANSITION. UPPER FOWARD STOP PIN ADJUSTED AND NEW STOP PIN CLIP INSTALLED IN REFERENCE TO AMM 52-13-00-820-801. INSPECTED AND VERIFIED GUIDE ARM ADJUSTED AND STOP PIN CLIP INSTALLED PER AMM 52-13-00-820-801. OK TO CONTINUE. ADJUSTED DOOR PER AMM 52-13-00-820-801 PERFORMED LEAK CHECK AND VERIFIED NO LEAKS, QC VERIFIED THAT NO WHISTELING OR HISSING NOTED DURING PRESSURIZATION LEAK CHECK.

STAB OUT OF TRIM LIGHT ILLUMINATED DURING CLIMB. ELECTRIC TRIM INOPERATIVE. MANUAL TRIM WORKED NORMALLY. NO CIRCUIT BREAKERS POPPED.

DOT#06 A-043 AFT CARGO COMPARTMENT RH FWD SHIELD CORRODED AT NUTPLATE HOLES TOP AND BOTTOM SIDES STA 767 TO 787 RBL 22 WL 156

DOT#07 A-043 AFT CARGO COMPARTMENT LH Z ANGLE CORRODED STA 727E+10' TO 747 LBL 22 WL 156

DOT#08 A-043 AFT CARGO COMPARTMENT FLOOR 'T' SPLICE PLATE CORRODED STA 767+5' BL 0 TO RBL 21 WL 156

DOT#09 A-043 AFT CARGO COMPARTMENT RH Z ANGLE CORRODED AT STA 727B+10' TO 767 RBL 22 WL 156

FWD CARGO COMPARTMENT FLOOR PANEL 120AF IS CORRODED AT FASTENER HOLES

FWD CARGO COMPARTMENT FLOOR PANEL 120DF IS CORRODED AT FASTENER HOLES

IRS-R FAULT LIGHT IS ON CHECKED FAULT MASSAGE: ADIRU-R INTERNAL FAULT. ADDED PARTS USED. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1522004 SN OFF 1048 UNIT, ADIRU, AI OFF 42-3421-9-0001 1048 ON 42-3421-9-0001 5385 REMOVED & REPLACED RT ADIRU (M1752) REF AMM 34-21-01, PERFORMED OPS TEST REF AMM 34-21-00-710-801 TESTS OK.

FWD CARGO COMPARTMENT FLOOR PANEL 120CF IS CORRODED AT FASTENER HOLES

NUMBER 2 ENG FAIL ON T/O ROLL...EGT WENT RED AT STABILIZED NO N1 N2...REJECT 60 KTS ENGINE #2 REMOVED AND REPLACED IAW ETASK 41-7100-1-0006. ALL CKS GOOD. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1579351 SN OFF 3315 ENGINE, BASIC, OFF 42-7200-9-0001 3315 ON 42-7200-9-0001 3248 JOBCARD COMPLETED

EMERGENCY LIGHTS UNABLE TO ILLUMINATE WHEN IN THE "ON" POSITION. GROUNDED - YES. REMOVED/REPLACED EMERGENCY EXIT LIGHT SWITCH IAW SYSTEM SCHEMATIC MANUAL 33-51-11-103. OPS CHECK GOOD.

ENGINE NUMBER ONE ENG ANTI ICE LIGHT ILLUMINATED IN FLIGHT. FOUND E1 PI SENSOR FAULT 36-21010. PLACED ON MEL IAW CARD 36070. REMOVED AND REPLACE PRSOV IAW 36-11-04. NO HELP WITH ISSUE. FURTHER TROUBLE SHOOTING REQ.

SMOKE AND FUMES IN THE CABIN AND COCKPIT DURING DEPARTURE. NO ENGINE ABNORMALITIES

LE FLAP TRANSIT LIGHT ILLUMINATED IN FLIGHT - DID NOT RESET AFTE R QRH PROCEDUREBEGAN TROUBESHOOTING PROCEDURE. FAULT SHOWS ON #1 LEADING EDGE FLAP WITH ASSOCIATED MTC MESSAGE 27-81216. UNABLE TO CLEAR FAULT THROUGH FSEU INTERROGATION. REF FIM TASK 27-81 822. FAULT REMAINS. PERFORMED UP TO STEP D3 (FSEU REPLACEMENT) WHILE INSPECTING LE FLAP RETRACT SENSOR 1, FOUND SPLICES HAD SLIGHTLY PULLED APART DUE TO WIRE BUNDLE SECURED TOO TIGHTLY. SUSPECT THAT COULD BE POSSIBLE ISSUE. REMOVED AND RESPLICED WIRES FOR LE FLAP RETRACT SENSOR 1 (S168) REF SWPM 20-30-12. DURING TESTING IT WAS A NO FIX. LEFT LE FLAP 1 IN TRANSIT LIGHT STILL ILLUMINATED AND FAULT STILL EXISTS. MAY NEED NEW FSEU OR FURTHER WIRING CHECKS ACCOMPLISHED. SUSPECT SWITCH S-168 IS BAD, MOVED FLAPS TO A POSITION WHERE ALL SENSORS WERE OFF THEIR TARGETS, USED A SCALE ON OTHER 3 RETRACT SENSORS TO SIMULATE THE TARGET, ALL THEIR RESPECTIVE LIGHTS WENT OUT, DID THE SAME THING TO S -168 NO CHANGE STILL SHOWED IN TRANSIT. REMOVED LE FLAP 1 RETRACT SENSOR S168 REF AMM 27-88-11/401, RESISTANCE CKS OF WIRES FROM S168 TO THE FSEU GOOD REF WDM 27-81-11-1, INSTALLED NEW SENSOR S168 NO FIX, T/S FURTHER AND FOUND BAD GROUND AT GD614AC. VERIFIED GROUND GD614-AC IS BAD. BRACKET NOT GROUNDED TO THE AC. PERFORMED WIRING CHECKS FROM SWITCH S168, TO. FSEU REF WDM 27-81-11, SWITCH CHECKS GOOD. REBITE CK OF FSEU GOOD IAW AMM 27-51-01/401.

ON CLIMB OUT; STRONG SMELL OF BURNING OIL

REJECT T/O 100-105KTS AIRSPEED DISAGREE CREW REPORTS FO AIRSPEED STOPPED ACCELERATING. CAPT AIRSPEED KEPT CLIMBING. THEN THEY REJECTED TAKEOFF. APPROX 20 KNOT DIFFERENCE. PERFORMED DETAILED INSPECTION OF THE PITOT AND STATIC DRAINS AS REQUIRED, FOUND NO EVIDENCE OF MOISTURE AND OR DEBRI REF AMM 34-11-00-210-801 AND AMM 34-11-00-210-802 MIANTENANCE MESSAGE 31-03120 " IAS DISAGREE", NO OTHER RELATED MESSAGES FOUND, PER FIM 31-65 TASK B70, REQUIRES PITOT STATIC SYSTEM FLUSHING ACP FIM 31-65 TASK B70 PITOT SYSTEM FLUSH. NO DEBRIS FOUND. RPL PITOT ADM IAW AMM34-21-04-400-801. ACP R/H PITOT SYSTEM LEAK TEST REF AMM34-11-11-790-807. LEAK CHECK OK. ALL OPS CHECK NORMAL.PARTS USED: 42-3413-9-0001,QTY :1 PARTS USED: ADD EMP:U330401 42-3413-9-0001,QTY :1 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1722908 SN OFF 4122 IPC REFERENCE # IPC 34-11 COMPLIED WITH INSPECTIONS REF GMM 09-10-05. MODULE, AIR DAT OFF 42-3413-9-0001 2412 ON 42-3413-9-0001 8156

AT TOP OF DECENT F/A REPORTED SMOKE IN CABIN. IDENTIFIED SOURCE AS PAX CELL PHONE BATTERY. EXTINGUISHED IN CONTAINMENT BAG. DIVERTED TO PBI AS PRECAUTION. NO OVERWEIGHT LANDING.

(A125) CABIN; EMERGENCY LIGHTS INOP AT CEILING - ROW 2; ROW 4; LH ROW 9; LH ROW 12; AND R1 DOOR - EXIT SIGN AND OVERHEAD LIGHT

#1 ENGINE FLUCTUATING 1.3 % N1 AT CLIMB THRUST; ALSO EGT AND FUEL FLOW ALSO FLUCTUATING

FOUND EMERGENCY BATTERY PACK M1695 WILL NOT CHARGE

FOUND EMERGENCY BATTERY PACK M1671 WILL NOT CHARGE

CRACK ON BAFFLE CLIP AT FCB; BS460 AFT FRAME; LBL23; WL153

FOUND EMERGENCY BATTERY PACK M1673 WILL NOT CHARGE

CRACK ON BAFFLE CLIP FWD FRAME BS 460; LBL 23 AND WL 153

CRACK ON BAFFLE CLIP AT FCB; BS500A; AFTER FRAME RBL23; WL153.

CRACK ON BAFFLE; AT FCB; BS500B; FWD FRAME; RBL23; WL153 CRACK ON BAFFLE CLIP AT FCB BS500B FWD FRAME RBL23 WL153