N312WA

Part: SKIN — CRACKED (FUSELAGE) · airframe 49,895 hrs · 33,844 cycles

INSPECTION OF THE FUSELAGE SKIN PER AD 2004-18-06 REVEALED A 3 INCH CRACK ALONG THE BONDED DOUBLER MILL LINE JUST BELOW STRINGER 15R AT FS 500D+7. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737 SRM AND PER ER/A 095736-14AD.

Part: ENGINE — OVERTEMP (NR 1 ENGINE) · airframe 47,220 hrs · 32,369 cycles

ON TAKEOFF ROLL, NR 1 ENGINE EGT WAS INCREASING TO 954 DEGREE CELSIUS. THROTTLES (AUTO THROTTLES) HAD TO BE DISCONNECTED TO KEEP ENGINE EGT FROM CLIMBING HIGHER. N1 WAS 91 PERCENT, N2 WAS 102 PERCENT AND INCREASING. FUEL FLOW NORMAL ON T/O ROLL. REPLACED ENGINE.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,033 hrs · 32,264 cycles

FUSELAGE/SKIN/FS430-460, S23R TO S27R - DENTS AND WEAR. THE SUBJECT DAMAGE IS CUT OUT FROM THE FUSELAGE SKIN AND REPAIRED WITH EXTERNAL ALUMINUM DOUBLER, TRIPLER AND STRUCTURAL FILLER IN ACCORDANCE WITH ER/A 385699-14. DAMAGE DUE TO CONTACT WITH GROUND EQUIPMENT.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,033 hrs · 32,264 cycles

FUSELAGE/SKIN/STA 500D - STA 520/STR 12R - REPAIR OF CRACK. THE CRACK IS CUT OUT OF THE FUSELAGE SKIN AND AN EXTERNAL ALUMINUM DOUBLER AND TRIPLER ARE INSTALLED IN ACCORDANCE WITH ER/A 381822-14 REV C.

Part: BEAM — CORRODED (NR 1 PYLON) · airframe 47,033 hrs · 32,264 cycles

CORROSION WAS FOUND IN THE AFT LUG BORE OF THE NR 1 PYLON CROWN BEAM FITTING AT NAC STA 257.25. THE BORE WAS OVERSIZED TO REMOVE THE CORROSION, HFEC INSPECTED, AND STEEL REPAIR BUSHINGS INSTALLED. THE REPAIR WAS ACCOMPLISHED PER ER/A 385679-14.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 47,033 hrs · 32,264 cycles

MODIFICATION OF THE FS 178 BULKHEAD REVEALED A CRACK IN THE LBL & RBL 28 COCKPIT FLOOR INTERCOSTAL WEB AND CHORD AT WL 107. THE CRACKED CHORD AND WEB WERE REMOVED AT BOTH LOCATIONS AND PARTS INSTALLED PER ER/A 385678-14AD.

Part: IRU — FAULTY (LEFT) · airframe 46,745 hrs · 32,089 cycles

LOST LEFT IRU IN FLIGHT. UNABLE TO GET HEADING IN ATT. BOTH AUTOPILOTS INOP. REPLACED LEFT INERTIAL REFERENCE UNIT PER M/M.

Part: SPAR — DAMAGED (LT WING TE FLAP) · airframe 46,503 hrs · 31,941 cycles

NR 2 INBOARD MID FLAP FRONT SPAR ASSEMBLY WAS FOUND DAMAGED. A REPLACEMENT WEB SECTION AND SPLICE DOUBLER WAS INSTALLED PER ER/A 423065-14.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 45,787 hrs · 31,553 cycles

EMERGENCY EXIT LIGHTING INOP AT ROW 22 AND 25. REPLACED LIGHT SOCKET AT ROW 22 AND REATTACHED WIRES AT ROW 25. BOTH EMERGENCY EXIT LIGHTS NOW CHECK NORMAL.

Part: SKIN — DENTED (FUSELAGE) · airframe 44,062 hrs · 30,511 cycles

TWO LARGE DENTS WERE FOUND IN FUSELAGE SKIN BETWEEN STA 907 AND 957 AND S-20R AND 25R. THERE WAS ALSO AN EXISTING REPAIR IN THE AREA. THE DAMAGED SKIN AREA WAS TRIMMED AWAY AND EXISTING REPAIR REMOVED. A NEW SECTION OF SKIN WAS SPLICED IN AT FS 957 FORWARD TO END OF PANEL.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 44,062 hrs · 30,511 cycles

A NEW SECTION OF SKIN WAS SPLICED IN FROM FS 907 TO 957 AND S-20R TO 25R PER ER/A 383228-14. A SECTION OF THE LOWER SKIN WAS FOUND TO BE ROUTED OUT IN THE LAP SPLICE AREA AT APPROXIMATELY FS 935 AND S-25R. AFTER INSTALLATION OF THE NEW UPPER SKIN, THE LOWER SKIN WAS REPAIRED PER SRM 53-00-01, FIGURE 210 WITH MINOR DEVIATIONS.

Part: COMPRESSOR — STALLED (NR 2 ENGINE) · airframe 43,087 hrs · 29,932 cycles

ON CLIMBOUT, LOUD THUMP FOLLOWED BY COMP STALL WITH RED EGT LIGHT AND ZERO OIL QTY ON NR 2 ENGINE. REPLACED ENGINE.

Part: INDICATOR — FAILED (COCKPIT) · airframe 41,033 hrs · 28,620 cycles

STANDBY ATTITUDE INDICATOR FAILED ENROUTE. REPLACED STBY ATT INDICATOR. OPS NML

Part: SKIN — DAMAGED (FUSELAGE) · airframe 40,722 hrs · 28,410 cycles

DIMPLES IN FUSELAGE AT WINDOW LINE IN FRONT OF WINGS BOTH SIDES. FOUND WAVINESS 3 PLACES ON EACH SIDE OF FUSELAGE BETWEEN WINDOWS AT BS 500 - 520 WITHIN LIMITS PER SRM 51-10-01 PG 10 FIG 4 SHT 1.

Part: OVERHEAT LOOP — WORN (WING TO BODY) · airframe 40,486 hrs · 28,250 cycles

AIR RETURN FOR LT WING BODY OVERHEAT HISTORY - REPLACED OVERHEAT DETECTION LOOP

Part: WIRE — FAILED (COCKPIT) · airframe 38,677 hrs · 27,009 cycles

SHORTLY AFTER LIFTOFF FROM SJC, WHEEL WELLS CIRCUIT BREAKER POPPED. CIRCUIT BREAKER WAS CHECKED JUST PRIOR TO DEPARTURE FROM SJC BY AMERICAN AIRLINES CONTRACT MAINT. NO PROBLEMS WERE NOTED. ALSO HAD PREVIOUS WRITEUP IN SLC. REPAIRS WERE MADE TO WIRING AT FWD NOSE W/W LIGHT ASSY. SLC MAINTENANCE FOUND DAMAGED AND BURNED WIRING BEHIND P18-3 CIRCUIT BREAKER PANEL. SUSPECTED SHORT CAUSED C/B TO POP AND WIRE BUNDLE TO BE DAMAGED (APPROX 20 WIRES). BURNT ELECTRICAL SMELL IN COCKPIT. REPAIRED WIRING.

Part: HARNESS — BROKEN (SEAT 14) · airframe 38,512 hrs · 26,892 cycles

SEAT 14 DEF EMERGENCY LIGHT INOP. REPLACED HARNESS, OPS NOW OK.

Part: BULKHEAD WEB — CRACKED (BS 178)

THE FS 178 BULKHEAD WEB WAS FOUND CRACKED AT THREE LOCATIONS DURING A MV VISIT IN ATL. THE DAMAGE WAS REPAIRED PER ERA 333565 14.

Part: FITTING — CRACKED (RT MLG)

THE RT MAIN LANDING GEAR BEAM ATTACH FITTING WAS FOUND CRACKED AT MV. ERA 333585-14 REPAIRED THE DAMAGE.

Part: FITTING — CRACKED (LT MLG)

THE LT MAIN LANDING GEAR BEAM ATTACH FITTING WAS FOUND CRACKED AT MV IN ATLANTA. ERA 333578-14 REPAIRED THE DAMAGE.

Part: STRINGER — CRACKED (BS 727)

STRINGER 18AR WAS FOUND CRACKED AT FS 727. THE DAMAGE WAS REPAIRED PER ERA 333593-14 AT HMV.

Part: STRINGER — CRACKED (BS 727)

A CRACK WAS FOUND IN THE WEB OF STRINGER 18A AT FS 727. THE DAMAGE WAS REPAIRED PER ERA 333598-14 AT MV.

Part: WIRE — LOOSE (ROW 15 20 22 23)

IN-SEAT EMERGENCY PATH LIGHTS INOP IN SEATS 15, 20, 22, 23. FOUND WIRES PULLED FROM CONNECTOR AT EACH LOCATION UNDER SEAT NEXT TO LIGHT ASSY. SECURED SAME, CHECKS OK.

Part: POWER SUPPLY — INOP (ROW 18-27)

ON INSPECTION, FOUND EMERGENCY PATH LIGHTS FROM ROWS 18 TO 27 INOP. REPLACED POWER SUPPLY AT BATTERY PACK M1136. ALL LIGHTS OPERATE NORMAL.

Part: BATTERY PACK — DISCHARGED (GALLEY)

ON PREFLIGHT FOUND LAST SECTION OF EMERGENCY TRACK LIGHTING INOP. FOUND BATTERY PACK BAD AND WIRE SHORTED ABOVE AFT GALLEY. REPLACED PACK AND SECTION OF WIRE CHECKS GOOD. ALSO, REPLACED BATTERY.

Part: OVEN — OVERHEATED (AFT GALLEY)

ON TAXI FLIGHT, ATTENDANT REPORTED SMOKE COMING FROM AFT GALLEY OVENS ON CAPTS SIDE. SMOKE STOPPED WHEN OVEN POWER WAS TURNED OFF. RETURNED TO GATE. FOUND AFT LEFT IB OVEN AND AFT RT OB OVENS WITH PANEL FAIL LIGHTS. INSPECTED REAR GALLEY AND OVEN AREAS FOR FIRE AND SMOKE DAMAGE, NONE DETECTED. FOUND BOTH OVEN CONTROL PANELS VERY HOT TO TOUCH. FWD BOTH OVENS TO MCO PER MEL 25-00-10.

Part: O-RING — LEAKING (NR 2 ENGINE)

NR 2 ENGINE SHUT-DOWN IN CRUISE AFTER OIL PRESSURE DROP AND OIL QUANTITY LOSS. FOUND OIL LEAKING FROM N2 GEAR BOX MANUAL CRANK PAD. REPLACED O-RING AND INSTALLED CRANK PAD COVER.

Part: INTERCOSTAL — CRACKED (R1 DOOR FRAME)

AT HMV IN ATL, THE R1 DOOR FRAME INTERCOSTAL WAS FOUND CRACKED IN THE TYPICAL MANNER SHOWN IN S/B 737-53A1108, REV. 5. THIS REPAIR WAS ACCOMPLISHED IN PER AND IN ACCORDANCE WITH S/B 737-53A1108, REV. 5.