N250TR

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 49,379 hrs · 28,885 cycles

DURING MAINTENANCE, FOUND RIGHT OVERWING EMERGENCY DOOR LIGHT OUT. REPLACED BATTERY PACK AND OPS CHECKED OK.

Part: FLOORBEAM — CORRODED (BS 947) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED CORROSION ON UPPER FLANGE OF BS 947.5 FLOORBEAM. REPLACED DAMAGED SECTION OF FLOORBEAM PER EA 53-120.

Part: FLOORBEAM — CORRODED (BS 986) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED CORROSION ON UPPER FLANGE OF BS 986.5 FLOORBEAM. REPLACED DAMAGED SECTION OF FLOORBEAM PER EA 53-115.

Part: FLOORBEAM — CORRODED (BS 967) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED CORROSION ON UPPER FLANGE OF BS 967.5 FLOORBEAM. REPLACED DAMAGED SECTION OF FLOORBEAM PER EA 53-122.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED A CRACK IN THE AFT UPPER CORNER OF THE AFT CARGO DOOR SKIN AT THE HANDLE ACCESS CUTOUT. REPLACED DOOR SKIN PER DWG 65-47952 AND SRM 51-30-02 AND 51-30-02 DUE TO PROXIMITY TO AN EXISTING REPAIR AND OTHER MULTIPLE DENTS AND SCRATCHES.

Part: STRUCTURE — CRACKED (CARGO DOOR) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED FORWARD AND AFT CORNERS OF THE AFT CARGO DOOR LOWER -T- CORD ARE CRACKED. REPLACED -T- CORD IN ACCORDANCE WITH DRAWING 65C80735 AND SRM 51-30-1.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED CRACK AT THE END OF STR 16RT AT BS 500B+2. REPAIRED PER SB 737-53-1145.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED STRINGER 18LT TIE CLIP CRACKED AT BS 277. REPLACED TIE CLIP PER SRM 51-30-02 AND DRAWING 65-73744.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED CORROSION ON THE UPPER CORD OF THE BS 344 FLOORBEAM FROM LBL 50 TO RBL 16. INSTALLED REPLACEMENT SECTION OF -T- CAP PER SRM 53-10-09.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, NOTED CORROSION ON UPPER CORD OF BS 294 FLOORBEAM FROM BL 0 TO LBL 12. REPLACED SECTION OF FLOORBEAM -T- CAP FROM LBL 12 TO THE RIGHT SERVICE DOOR PER SRM 53-10-9 FIGURE 5.

Part: FLOOR SUPPORT — CORRODED (BS 767) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING INSPECTION, NOTED CORROSION ON LOWER SURFACE OF THE OUTBOARD LONGITUDINAL FLOOR SUPPORT ANGLE IN THE AFT CARGO BIN AT BS 767 +6. REMOVED DAMAGED SECTION OF FLOOR SUPPORT AND REPAIRED PER SRM 53-10-5.

Part: FRAME — DAMAGED (BS 927) · airframe 49,122 hrs · 28,676 cycles

DURING INSPECTION, NOTED FIGURE 8 HOLE IN BS 927 FRAME AT STR 6LT. REPAIRED FRAME PER SRM 51-40-02, 51-40-05 AND 51-30-00 AND REPLACED STRINGER CLIP PER SRM 51-40-02 AND 51-40-03.

Part: FLOORBEAM — CORRODED (BS 312) · corrosion level 2 · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE CHECK, NOTED CORROSION ON UPPER CHORD OF BS 312 FLOORBEAM FROM BL 0 TO LBL 12. REPLACED SECTION OF TEE CAP PER SRM 53-10-9 FIGURE 5.

Part: STRINGER CLIP — CRACKED (BS 727A) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, FOUND STR 8LT TIE CLIP CRACKED AT BS 727A. REPLACED TIE CLIP PER SRM 51-10-1.

Part: STRINGER CLIP — CRACKED (BS 663 S11L) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, FOUND STR 11LT TIE CLIP CRACKED AT BS 663.17. REPLACED TIE CLIP PER SRM 51-30-0.

Part: STRINGER CLIP — CRACKED (BS 947) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, FOUND STR 2LT TIE CLIP CRACKED AT BS 947. REPLACED TIE CLIP PER SRM 51-30-0.

Part: STRINGER CLIP — CRACKED (BS 747) · airframe 49,122 hrs · 28,676 cycles

DURING MAINTENANCE, FOUND STR 7RT TIE CLIP CRACKED AT BS 747. REPLACED TIE CLIP PER SRM 51-10-1.

Part: TIRE — FLAT (NR 2 MLG) · airframe 49,050 hrs · 28,524 cycles

FLIGHT 210 LIH-HNL - ON LANDING, ATC OBSERVED SMOKE FROM THE LEFT MAIN LANDING GEAR. CREW FOUND NORMAL BRAKING AND NO LOSS OF CONTROL. CREW REQUESTED THE AIRPORT FIRE EQUIPMENT AND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE NR 2 MAIN TIRE FLAT. MAINTENANCE REMOVED AND REPLACED BOTH THE NR 1 AND NR 2 MAIN WHEEL ASSEMBLIES PER AMM 32-45-11. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONTROL PANEL — FAILED · airframe 48,731 hrs · 27,738 cycles

NON-ETOPS FLT 206 HNL-OGG: AS THE AIRCRAFT WAS TAXIING PRIOR TO TAKEOFF, THE (OVHT/DET) LIGHT ILLUMINATED ON THE MASTER CAUTION ANNUNCIATOR PANEL ALONG WITH THE AFT CARGO FAULT LIGHT AND AFT SMOKE LIGHT. THE CREW FOLLOWED QRH PROCEDURES AND RETURNED TO THE GATE. MX ACTION: MAINTENANCE REPLACED THE CARGO FIRE DETECTION/SUPPRESSION CONTROL PANEL. THE FORWARD AND AFT CONTROL ELECTRONIC UNITS WERE ALSO REPLACED FOR PRECAUTIONARY MEASURE. MAINTENANCE PERFORMED AN OPERATIONAL CHECK WITH BOTH ENGINES RUNNING. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE — CHAFED (CONTROL PANEL) · airframe 48,726 hrs · 27,726 cycles

NON-ETOPS FLT 242 HNL-ITO: DURING ENGINE START ON PUSH BACK, THE (OVHT/DET) LIGHT ILLUMINATED ON THE MASTER CAUTION ANNUNCIATOR PANEL ALONG WITH THE FIRE WARNING LIGHT. THE CREW FOLLOWED QRH PROCEDURES AND RETURNED TO THE GATE. MAINTENANCE FOUND AND REPAIRED CHAFED WIRES AT CONNECTOR PLUG D9500P. MAINTENANCE ALSO REMOVED AND REPLACED CARGO SMOKE DETECTION/SUPPRESSION CONTROL PANEL. PERFORMED OPERATIONAL TEST, GOOD IAW AMM 26-15-00. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ELECTRONIC UNIT — MALFUNCTIONED (CARGO BAY) · airframe 48,688 hrs · 27,650 cycles

DURING PUSH BACK, THE OVHT/DET LIGHT ILLUMINATED ON THE MASTER CAUTION ANNUNCIATOR PANEL ALONG WITH THE FORWARD CARGO FAULT LIGHT. THE CREW FOLLOWED QRH PROCEDURES AND RETURNED TO THE GATE. MAINTENANCE FOUND FAULT LIGHT ON FORWARD CARGO ELECTRONIC UNIT. PERFORMED TEST ON FORWARD CARGO ELECTRONIC UNIT. NO DEFECTS WERE FOUND. MAINTENANCE PLACED THE FORWARD CARGO COMPARTMENT FIRE DETECTION/SUPPRESSION SYSTEM ON MEL. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY) · airframe 48,687 hrs · 27,649 cycles

NON-ETOPS FLT 281 KOA-HNL: AFTER ENGINE START, (OVHT/DET) ANNUNCIATOR LIGHT AND MASTER CAUTION LIGHT ILLUMINATED. CREW WAS UNABLE TO RESET LIGHT AND RETURNED TO BLOCK. MX ACTION: MAINTENANCE PERFORMED OVERHEAT AND FIRE WARNING TEST ALONG WITH THE CARGO FIRE DETECTION SYSTEM TEST. NO FAULTS WERE NOTED. RESET POWER TO AIRCRAFT AND MASTER CAUTION RESET NORMALLY WITH THE (OVHT/DET) ANNUNCIATOR LIGHT EXTINGUISHED. AIRCRAFT WAS RETURNED TO SERVICE. DURING OVERNIGHT, MAINTENANCE REMOVED AND REPLACED THE NR 1 AFT CARGO SMOKE DETECTOR AS PRECAUTIONARY. AIRCRAFT WAS RETURNED TO SERVICE. SPECIFIC PART OR STRUCTURE CAUSING DIFFICULTY.

Part: WARNING LIGHT — FALSE INDICATION · airframe 48,680 hrs · 27,633 cycles

NON-ETOPS FLT 34 HNL-ITO: AFTER ENGINE START, OVHT/DET ANNUNCIATOR LIGHT ILLUMINATED WITH NO CORRELATED SYSTEM OVERHEAT INDICATION DURING RECALL CHECK. CREW WAS UNABLE TO RESET LIGHT AND ELECTED TO SHUTDOWN ENGINES AND RETURN TO BLOCK. AS THE ENGINES WERE SPOOLING DOWN, SMOKE ANNUNCIATOR LIGHTS ILLUMINATED WITH FAULT LIGHT ON THE AFT CARGO COMPARTMENT. MAINTENANCE INSPECTED AFT CARGO COMPARTMENT AND CONFIRMED THAT IT WAS A FALSE INDICATION. MAINTENANCE CLEANED AFT CARGO COMPARTMENT SMOKE DETECTOR. PERFORMED OPERATIONAL TEST GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONTROL PANEL — FAILED (SMOKE DETECTION) · airframe 48,679 hrs · 27,632 cycles

NON-ETOPS FLT 72 LIH-HNL: AFTER ENGINE START, ( OVHT/DET) ANNUNCIATOR LIGHT ILLUMINATED WITH NO CORRELATED SYSTEM OVERHEAT INDICATION DURING RECALL CHECK. CREW ELECTED TO SHUTDOWN ENGINES AND RETURN TO BLOCK. AS THE ENGINES WERE SPOOLING DOWN, (SMOKE) ANNUNCIATOR LIGHTS ILLUMINATED WITH FAULT LIGHT ON THE AFT CARGO COMPARTMENT. CREW COMPLIED WITH OPERATIONS ORDER 06-14 AND CONFIRMED THAT THERE WAS NO SMOKE IN CABIN. MX ACTION: MAINTENANCE INSPECTED AFT CARGO COMPARTMENT AND CONFIRMED THAT IT WAS A FALSE INDICATION. MAINTENANCE REMOVED AND REPLACED CARGO SMOKE DETECTION/SUPPRESSION CONTROL PANEL IAW AMM 26-20-13. PERFORMED OPERATIONAL TEST GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONTROL PANEL — FAILED (SMOKE DETECTION) · airframe 48,680 hrs · 27,633 cycles

NON-ETOPS FLT 34 HNL-ITO: AFTER ENGINE START, (OVHT/DET) ANNUNCIATOR LIGHT ILLUMINATED WITH NO CORRELATED SYSTEM OVERHEAT INDICATION DURING RECALL CHECK. CREW WAS UNABLE TO RESET LIGHT AND ELECTED TO SHUTDOWN ENGINES AND RETURN TO BLOCK. AS THE ENGINES WERE SPOOLING DOWN, (SMOKE) ANNUNCIATOR LIGHTS ILLUMINATED WITH FAULT LIGHT ON THE AFT CARGO COMPARTMENT. MAINTENANCE INSPECTED AFT CARGO COMPARTMENT AND CONFIRMED THAT IT WAS A FALSE INDICATION. MAINTENANCE REMOVED AND REPLACED CARGO SMOKE DETECTION/SUPPRESSION CONTROL PANEL IAW AMM 26-20-13. PERFORMED OPERATIONAL TEST GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FAN — ODOR (CABIN) · airframe 48,663 hrs · 27,600 cycles

NON-ETOPS FLT 269 KOA-HNL: SHORTLY AFTER LANDING, THE CREW AND FLIGHT MECHANIC NOTICED A BURNING SMELL COMING FROM THE GASPERS. THE CREW SWITCHED OFF THE GASPER FAN AND THE BURNING SMELL DISSIPATED SHORTLY AFTER. THE CREW CONTINUED TAXIING TO THE GATE WITHOUT FURTHER INCIDENT. MX ACTION: MAINTENANCE PLACED THE GASPER FAN ON MEL 21-24. AIRCRAFT WAS RETURNED TO SERVICE. MX ACTION: MAINTENANCE REMOVED AND REPLACED THE GASPER FAN IAW AMM 21-24-21. AIRCRAFT WAS RETURNED TO SERVICE.

Part: PANEL — CORRODED (LAV SERVICE) · corrosion level 2 · airframe 48,579 hrs · 27,432 cycles

DURING B-CHECK, INSPECTION NOTED FORWARD LAVATORY SERVICE PANEL CORRODED ON INBOARD SIDE. REMOVED MINOR SURFACE CORROSION FROM LAVATORY PAN PER SRM 51-10-6 AND REPLACED INTERNAL DOUBLER 65-55757-2 PER DWG 65-45802.

Part: CONTROL UNIT — MALFUNCTIONED (NR 1 ENGINE) · airframe 48,507 hrs · 27,396 cycles

TAKEOFF ABORTED DUE TO NR 1 GENERATOR TRIPPED OFF LINE. CHECKED NR 1 CSD OIL LEVEL, DP INDICATOR, FOUND NORMAL. CHECKED APU OIL QUANTITY. DISCONNECTED NR 1 CSD AND PLACED NR 1 GENERATOR ON MEL 24-1. REPLACED NR 1 ENGINE GENERATOR CONTROL UNIT PER MM 24-20 AND OPS CHECKED NORMAL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 48,364 hrs · 27,298 cycles

FORWARD AND AFT SECTIONS OF SEAT MOUNTED EMERGENCY LIGHTS INOP. REPLACED FWD AND AFT POWER SUPPLIES PER MM 33-50.

Part: CONTROL UNIT — OUT OF ADJUST (AUTO THROTTLES) · airframe 48,364 hrs · 27,298 cycles

AUTO THROTTLE ADVANCES THRUST LEVERS UNCOMMANDED. ADJUSTED RIGHT ENGINE LVDT PER MM 22-31-81.

Part: CONNECTOR — CORRODED (CABIN) · airframe 48,321 hrs · 27,267 cycles

RIGHT WING EGRESS LIGHTS OUT. CLEANED SLIGHT CORROSION FROM BULB CONNECTOR. OPS CHECKS GOOD.

Part: CONTROL UNIT — MALFUNCTIONED (YAW DAMPER) · airframe 48,131 hrs · 27,125 cycles

YAW DAMPER WILL NOT ENGAGE. PLACED ON MEL 22-3-B. 01/16/2006: REPLACED YAW DAMPER CONTROL UNIT. SYSTEM TESTS OK PER MM 22-12-01.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 48,070 hrs · 27,080 cycles

OVERHEAD EMERGENCY LIGHT INOP AT ROW 2. REPLACED BATTERY PACK. OPS CHECKS GOOD PER MM 25-60-10.

Part: CONTROL PANEL — MALFUNCTIONED · airframe 48,011 hrs · 27,026 cycles

MODE CONTROL PANEL INOP. REPLACED MODE CONTROL PANEL PER MM 22-11-01.

Part: YAW DAMPER — MALFUNCTIONED · airframe 47,997 hrs · 27,014 cycles

YAW DAMPER TRIPS OFF ON GROUND ONLY WHEN WIDE TURNS ARE MADE WITH TILLER OR RUDDER. PLACED ON MEL 22-3-1B.

Part: YAW DAMPER — FAILED · airframe 47,964 hrs · 26,990 cycles

YAW DAMPER WILL NOT ENGAGE. PLACED YAW DAMPER ON MEL 22-3-18.

Part: TRANSFORMER — FAILED (ELECTRICAL) · airframe 47,950 hrs · 26,979 cycles

AUTO THROTTLES WON'T ENGAGE. LOSS OF VALID AIR DATA SPEED SIGNAL PREVENTED AUTO THROTTLE ENGAGEMENT. REPLACED T98 TRANSFORMER IN J4 BOX PER WDM SPM CHAPTER 20 DUE TO SHORT. AUTO THROTTLES OPS CHECK GOOD PER MM 22-31-01.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,949 hrs · 26,978 cycles

RIGHT SIDE EMERGENCY LIGHT FOR OVERWING EXIT NOT ILLUMINATING. REPLACED RIGHT SIDE OVERWING EXIT LIGHT BATTERY PACK. LIGHT OPS CHECKS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,948 hrs · 26,978 cycles

EMERGENCY EXIT LIGHTS AT REAR EXIT DOORS AND AT FORWARD EXIT DOORS ARE NOT ILLUMINATING. REPLACED BATTERY PACK FOR REAR DOOR LIGHTS AND FORWARD DOOR LIGHTS AND OPS CHECKED PER MM 33-51-71.

Part: COMPASS — MALFUNCTIONED (COCKPIT) · airframe 47,687 hrs · 26,739 cycles

AFTER TAKEOFF, BOTH COMPASS HEADINGS ROLLED AWAY FROM RUNWAY HEADING. RETURNED TO FIELD. PERFORMED SYSTEM CHECKOUT PER MM 34-21-00. SYSTEM CHECKED NORMAL. PERFORMED VISUAL INSPECTION OF BOTH DIRECTIONAL GYROS, NO PROBLEMS NOTED.

Part: WIRE — DAMAGED (LT ENGINE) · airframe 47,623 hrs · 26,685 cycles

IN PREPARATION TO TAXI, LEFT ENGINE UNCOMMANDED SHUT DOWN AFTER START. FOUND BROKEN WIRES W368-011 AND 010 UNDER CLAMP SIX INCHES BEFORE FUEL SHUTOFF VALVE CONNECTOR 0788. PRECAUTIONARY, CHECKED RIGHT ENGINE AND DISCOVERED WIRES DAMAGED IN SAME LOCATION. REPAIRED LEFT AND RIGHT ENGINE WIRING PER SPM 24-20 AND WDM 28-21-01. INSPECTED FIVE OTHER 737-200 AIRCRAFT IN FLEET. NO OTHER DISCREPANCIES NOTED.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,534 hrs · 26,598 cycles

L-1, R-1, R-2 EXTERNAL EMERGENCY EXIT LIGHTS INOP. REPLACED LAMPS. OPS CHECKS GOOD PER MM 33-40-1.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

ATTACH ANGLE AT BS 663 BELOW WALL TO FLOOR TRANSITION ANGLE CRACKED, RIGHT SIDE. REPLACED ATTACH ANGLE PER SRM 51-10-2 AND SRM 53-10-2.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

INTERCOSTAL WEB FROM BS 500A TO BS 500B AT STR 26 LT IN FORWARD CARGO BIN IS CRACKED. REPLACED WEB AND ATTACH ANGLE PER BOEING DWG 69-41473 AND DWG 69-51411 AND SRM 51-30-0.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

CORROSION ON STR 27 RT JUST FORWARD OF BS 360. REPAIRED IAW EA NR 53-291 AND SRM 53-10-3.

Part: SUPPORT — CRACKED (RADAR) · airframe 47,483 hrs · 26,564 cycles

SUPPORT FOR RADAR TR RACK CRACKED. REPAIRED IAW SRM 51-40-3.

Part: SCUFF PLATE — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

FORWARD CARGO THRESHOLD FWD AND AFT CORNER SCUFF PLATES CRACKED. REPAIRED PER BOEING SPEC BAC5975.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

ATTACH ANGLE CRACKED UNDER THRESHOLD AT BS 480 AND STR26RT IN FORWARD CARGO BIN. REPLACED ANGLE IAW MFG DWG. 69-16784 AND SRM 51-30-0.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

FORWARD CARGO INTERCOSTAL WEB CRACKED UNDER THRESHOLD AT STR 26 RT AT BS 460+10. REPAIRED PER SRM 51-40-3 AND SRM 51-30-02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

CRACK AT FORWARD END OF OXYGEN SERVICE PANEL CUTOUT. REPAIRED PER EA 53-288 AND SRM 53-30-3.

Part: STRINGER — CORRODED (FUSLEAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

CORROSION OF STR 25 LT FROM BS 986 TO BS 1006. REPAIRED PER SRM 53-10-2.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

ATTACH ANGLE CRACKED UNDER THRESHOLD AT BS 460 AND STR 26 RT IN FORWARD CARGO BIN. REPLACED ANGLE PER BOEING DWG 69-16784 AND SRM 51-30-02.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

AFT SIDE OF TIE CLIP AT BS 1006 AND STR 27 LT HAS CORROSION. REPLACED TIE CLIP PER SRM 51-10-1.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 23,564 cycles

CORROSION UNDER NUT PLATE ON FRAME AT BS 1006 AT RBL 5. REPLACED FRAME SECTION PER SRM 51-10-1 AND SRM 51-30-0.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

CORROSION AROUND NUT PLATE IN STR 28 LT AT BS 500 IN FORWARD CARGO BIN. REPAIRED PER SRM 53-10-3.

Part: ANGLE — CRACKED (FUSLEAGE) · airframe 47,483 hrs · 26,564 cycles

DRAG ANGLE CRACKED UNDER LEFT FORWARD WING TO BODY FAIRING. REPAIRED PER EA 53-290.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

CORROSION ON INSIDE OF FUSELAGE SKIN BETWEEN STR 24 RT AND STR 25 RT AT BS 1016+4. REPAIRED PER EA 53-294.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

CORROSION ON STR 26 RT FROM BS 1006 TO BS 1016. REPLACED STRINGER SECTION PER SRM 51-10-1.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

INTERCOSTAL WEB ATTACH ANGLE CRACKED AFT SIDE OF FRAME AT BS 500 AT STR 28 RT IN FORWARD CARGO BIN. REPLACED ANGLE PER BOEING DWG 69-37261 AND SRM 51-30-2.

Part: SUPPORT CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

DRAIN MAST UPPER SUPPORT CHANNEL FROM BS 986 TO BS 1006 AT STR 25 LT HAS CORROSION. REPLACED SUPPORT CHANNEL IAW SRM 53-10-2.

Part: BEAM — DAMAGED (MLG) · airframe 47,483 hrs · 26,564 cycles

AFT LUG ON THE RIGHT MAIN GEAR BEAM ARM HAS AN INDICATION OF A DEFECT. REPLACED WALKING BEAM ARM PER 737 MM 32-11-00.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

CORROSION ON STR 26 LT BETWEEN BS 986 AND BS 1006. REPAIRED PER EA 53-292 AND SRM 53-10-1.

Part: CLIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

FRAME TO SKIN ATTACH CLIP HAS CORROSION AT BS 967 BETWEEN STR 26 LT AND STR 25 LT. REPLACES ATTACH CLIP PER SRM 51-10-1.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

INTERCOSTAL WEB ATTACH ANGLE CRACKED AFT SIDE OF FRAME AT BS 500 AT STR 28 RT IN FORWARD CARGO BIN. REPLACED ANGLE IAW MFG DWG. 69-37261 AND SRM 51-30-2.

Part: WEB — CRACKED (FUSELAGE) · airframe 47,483 hrs · 26,564 cycles

WEB FROM BS 490 TO BS 500 AT STR 26 RT IS CRACKED. REPLACED WEB IAW MFG DWG. 65-20726 AND SRM 51-30-2.

Part: SKIN — BULGED (FUSELAGE) · corrosion level 2 · airframe 47,483 hrs · 26,564 cycles

SKIN BULGING AROUND RIVETS AT SERVICE INTERPHONE JACK AT STR 23 LT AND BS 1040 AT THE AFT PRESSURE BULKHEAD DOOR. REPAIRED PER EA 53-287.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 47,419 hrs · 26,511 cycles

L-2 LOW LEVEL LIGHT DOOR IDENTIFIER INOP. REPAIRED WIRING AT LIGHT ASSY. OPS CHECKS NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,392 hrs · 26,488 cycles

EMERGENCY EXIT LIGHTS ON RIGHT EXTERIOR BELOW HATCH AND AFT OF WING INOP. REPLACED BATTERY PACK AND OPS CHECKED OK PER MM 33-51-81.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 37,385 hrs · 26,481 cycles

AFT DOORS EXTERIOR EMERGENCY LIGHTS INOP. REPLACED POWER SUPPLY BATTERY CHARGER FOR L2 AND R2 EXTERIOR EMERGENCY LIGHTS. OPS CHECKS GOOD PER MM 33-51-8P.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,270 hrs · 26,387 cycles

FWD CABIN AFT SECTION OF EMERGENCY LIGHTS INOP. REPLACED BATTERY. SYSTEM CHECKS NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,264 hrs · 26,382 cycles

FORWARD CABIN CENTER AISLE EMERGENCY LIGHT INOPERATIVE. REPLACED BATTERY PACK AND OPS CHECKED OK.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,240 hrs · 26,363 cycles

LOW LEVEL EMERGENCY LIGHTS INOP AT ROWS 5DEF, 11DEF, 20DEF. RELAMPED AND OPS CHECKS NORMAL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,237 hrs · 26,360 cycles

EMERGENCY PATH LIGHTING INOP. REPLACED POWER SUPPLY. OPS CHECKS NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,225 hrs · 26,353 cycles

CRACK IN THE FUSELAGE SKIN AT THE LEFT AFT ENTRY DOOR CUTOUT LOWER FORWARD CORNER. REPAIRED DAMAGE PER SRM 53-30-3 FIG. 24.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 46,884 hrs · 26,082 cycles

RIGHT HAND OVERWING & FLAP EMERGENCY EXIT LIGHTS INOP. REPLACED BATTERY PACK M193 AND REFLECTOR. OPS CHECKS GOOD PER MM 33-51-1.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 46,884 hrs · 26,082 cycles

RIGHT HAND OVERWING & FLAP EMERGENCY EXIT LIGHTS INOP. REPLACED BATTERY PACK M193 AND REFLECTOR. OPS CHECKS GOOD PER MM 33-51-1.

Part: COMPUTER — MALFUNCTIONED (NR 1 FCC) · airframe 46,884 hrs · 26,082 cycles

CAPTAIN'S FLIGHT DIRECTOR FLAG IN VIEW. REPLACED NR 1 FLIGHT CONTROL COMPUTER PER MM 22-11-331. OPS CHECKS GOOD.

Part: SKIN — DELAMINATED (NR 1 SLAT) · airframe 46,796 hrs · 26,003 cycles

NR 1 LEADING EDGE SLAT FOUND DELAMINATED. REPLACED NR 1 LEADING EDGE SLAT ASSY PER MM 27-81-21.

Part: COMPUTER — INOPERATIVE (FLT CNTRL) · airframe 46,773 hrs · 25,976 cycles

FIRST OFFICER'S FLIGHT DIRECTOR FLAG IN VIEW DURING FLIGHT. REPLACED NR 1 AND NR 2 FLIGHT CONTROL COMPUTER IAW MM 22-11-331.

Part: SWITCH — DAMAGED (AUTOTHROTTLE) · airframe 46,773 hrs · 25,976 cycles

AUTO THROTTLE WILL NOT ENGAGE. REPLACED BOTH AUTO THROTTLE DISCONNECT SWITCHES. OPS CHECKS OK PER MM 22-31-01.

Part: GYRO — MALFUNCTIONED (1 & 2 VERTICALS) · airframe 46,717 hrs · 25,926 cycles

B CHANNEL AUTO PILOT JERKS EXCESSIVELY IN RIGHT AND LEFT TURNS. PLACED B CHANNEL AUTO PILOT ON MEL 22-1. 8/15/2003: REPLACED NR 1 AND 3 VERTICAL GYROS PER MM34-22-1. AUTO PILOT BITE TEST NORMAL PER MM22-11-01.

Part: INDICATOR — FAULTY (COCKPIT) · airframe 46,702 hrs · 25,912 cycles

ADI ATTITUDE FLAG STICKS WHEN TEST SWITCH ACTUATED ON FIRST OFFICER'S SIDE. REPLACED FIRST OFFICER'S INDICATOR AND OPS CHECKED OK PER MM 34-22-0.

Part: COUPLER — FAILED (YAW DAMPER) · airframe 46,621 hrs · 25,842 cycles

YAW DAMPER INOPERATIVE. REPLACED YAW CAMPER COUPLER PER MM 22-12-01. OPS CHECKS NORMAL.

Part: BULB — BURNED OUT (EMERGENCY LIGHT) · airframe 46,569 hrs · 25,797 cycles

OVERWING EMERGENCY LIGHT INOP. RELAMPED OVERWING EMERGENCY LIGHT.

Part: INDICATOR — MALFUNCTIONED (COCKPIT) · airframe 46,553 hrs · 25,783 cycles

F/O'S ADI JUMPS & TURNS. REPLACED F/O'S ADI. OPERATIONAL TEST NORMAL PER MM 34-22-0.

Part: FRAME — CRACKED (FUSELAGE) · airframe 46,495 hrs · 23,732 cycles

CRACK IN FRAME AT BS 480 AT LEFT TRANSITION ANGLE (FORWARD CARGO BIN). REPAIRED PER SRM 51-40-3.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 46,495 hrs · 25,732 cycles

CORROSION ON LEFT TRANSITION ANGLE BS440 TO BS480 (FORWARD CARGO BIN). REPLACED CORRODED SECTION OF TRANSITION ANGLE PER EA53-114.

Part: CARGO TRACK — DAMAGED (FUSELAGE) · airframe 46,495 hrs · 25,732 cycles

RIGHT CARGO TIE DOWN TRACK CRACKED AT BS 460 (FORWARD CARGO BIN).REPAIRED PER SRM 51-40-4.

Part: STIFFENER — DAMAGED (FUSELAGE) · airframe 46,495 hrs · 25,732 cycles

HOLE IN STIFFENER AT STR 26RT BETWEEN BS420 AND BS440. FABRICATED NEW WEB PER DWG 65-20726 AND INSTALLED PER SRM 51-10-1.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 46,495 hrs · 25,732 cycles

HOLE IN NR 2 FLOOR PANEL IN FORWARD CARGO BIN. REPAIRED PER SRM 51-40-2 FIG 1.

Part: PANEL — CRACKED (FUSELAGE) · airframe 46,495 hrs · 25,732 cycles

WEB PANEL CRACKED LEFT SIDE UNDER TRANSITION ANGLE AT BS460 (FORWARD CARGO BIN). FABRICATED NEW WEB IAW DWG 69C41473 AND INSTALLED.

Part: WEB — CRACKED (FUSELAGE) · airframe 46,495 hrs · 25,732 cycles

WEB PANEL CRACKED BELOW LEFT TRANSITION ANGLE BS440 (FORWARD CARGO BIN). FABRICATED AND INSTALLED NEW WEB PER DWG 69C41473.

Part: COMPUTER — MALFUNCTIONED (AUTOPILOT) · airframe 46,495 hrs · 25,732 cycles

B-AUTO PILOT CREATES JERKING OF ELEVATORS WHILE AIRCRAFT BANKED; OK WITH -A- AUTO PILOT. SWAPPED FCC'S FOR FURTHER TROUBLESHOOTING.

Part: LIGHT — MALFUNCTIONED (CABIN) · airframe 46,458 hrs · 25,701 cycles

EMERGENCY EXIT LIGHT COMES ON WHEN POWER IS SWITCHED OFF AND EMERGENCY EXIT SWITCH IS IN OFF POSITION. REPLACED RT FWD EMERGENCY EXIT LIGHT ASSY AND OPS CHECK PER MM 33-51-11.

Part: TRANSMITTER — MALFUNCTIONED (AUTOTHROTTLE) · airframe 46,458 hrs · 25,701 cycles

AUTO THROTTLE KEEPS DISCONNECTING DURING FLIGHT. REPLACED LT. ENGINE THRUST LEVER POSITION TRANSMITTER PER MM 22-31-81. OPS CHECKED OK.

Part: COWLING · airframe 46,442 hrs · 25,689 cycles

#2 engine air inlet cowl has gouge at 1:30 position. Repaired damaged area per EA No. 54-045 dated 2/14/2003.

Part: COMPUTER · airframe 46,442 hrs · 25,689 cycles

Auto throttle would not engage. R&R auto throttle computer. Chks good per MM 22-31-01.

Part: WIRE — BROKEN (AUTOFLIGHT) · airframe 46,427 hrs · 25,680 cycles

A/T FAILS INTERFACE TEST 6.9 & 56.9 SUB.TEST 8 & 9. ITEM DEFERRED IAW 737-200 MEL 22-4 CONTROL NR 1221003. 01/10/2003. REPAIRED BROKEN WIRES AT SUMMING POINTS ON E1-3 SHELF PER WDM CHPT. 20 A/T OPS NORMAL PER BITE & A/P INTERFACE TESTS. CLEARED MEL 22-4, CONTROL # 1221003.

Part: POTENTIOMETER · airframe 46,266 hrs · 25,493 cycles

"A" Auto-pilot jerky in all modes. R&R stab trim potentiometer.

Part: AUTOTHRUST SYS · airframe 46,216 hrs · 25,441 cycles

Auto Throttles Inop.

Part: SWITCH — OUT OF ADJUST (AUTOTHRUST SYS) · airframe 46,158 hrs · 25,392 cycles

AUTO THROTTLES WILL SET TAKEOFF AND CLIMB POWER BUT WILL NOT RETARD THROTTLES TO MAINTAIN SPEED. DURING CRUISE PDC SPEED IS THE ONLY MODE THAT WORKS. MCP SPEED MODE WILL NOT WORK IN ANY REGIME. ADJUSTED AUTO THROTTLE SWITCH. OP'S CHECKS OK.

Part: RECEIVER · airframe 46,152 hrs · 25,386 cycles

MCP panel @ 7000`, engage PDC A/S bug goes to 310K. Speed mode would not engage. When flaps select to 5 auto pilots kick off, would not re-engage. R&R both radio altimeters.