N379DL

Part: AUTOTHROTTLE SYS — FAILED (NR 1 ENGINE) · airframe 43,040 hrs · 33,831 cycles

ON T/O ROLL AFTER TOGA THROTTLES REQUIRED MANUAL SET WITH NORMAL FD/AP/AT. F/O TURNED THROTTLE OVER TO CAPT NR 1 AND 2 THROTTLES SPLIT WITH AN INCREASE ON 1. EGT WENT UP TO 630 ON NR 1 WITH A 2.12 SETTING 2.1 AT SET. NR 2 WAS AT 2.04. EVENED THROTTLES AT 2.10 W/STD OPS. 630 IN EXCESS FOR T/O LIMIT. INSPECTED NR 1 ENG PER M/M FOR EGT, NO ACTION REQUIRED M/M. AUTO THROTTLES FWD TO MCO AND PLAC PER MEL 22-00-04. PULLED AND SECURED AUTO THROTTLE AC AND DC C/BS PER MEL.

Part: SENSE LINE — LOOSE (LT ENGINE) · airframe 42,512 hrs · 33,392 cycles

A/C WOULD NOT PRESSURIZE DURING CLIMBOUT. POM PROCEDURE WERE FOLLOWED AS WELL AS MULTIPLE BLEED CONFIGURATIONS WERE TRIED INCLUDING USING APU BLEED AND STBY AND MANUAL AC/DC MODES ON CONTROLLER. MAIN AND FWD OUTFLOW VLVS WERE CLOSED. SECURED LOOSE SENSE LINE TO LEFT ENGINE BLEED.

Part: DUCT — DAMAGED (NR 2 ENGINE) · airframe 42,429 hrs · 33,325 cycles

NR 2 ENGINE OVERHEAT LIGHT ILLUM SHORTLY AFTER T/O EGT APPROX 620 FULL T/O POWER SETTING. RETARDED THROTTLE, LIGHT WENT OUT APPROACHING IDLE. REPLACED FLEX DUCT AND TWO LOWER FIRE LOOPS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 41,613 hrs · 32,889 cycles

THE FUSELAGE SKIN AT FS 480 WAS GOUGED AND CRACKED BY GROUND EQUIPMENT JUST BELOW THE STRINGER 26R SKIN LAP JOINT. THE DAMAGE WAS REMOVED WITH A CUTOUT IN THE SKIN. THE SKIN CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER ER/A 384498-14.

Part: BLADE — DAMAGED (NR 2 ENGINE) · airframe 41,396 hrs · 32,797 cycles

ON CLIMBOUT FROM BDL PASSING THROUGH FL6000 HEARD AND FELT A LOUD EXPLOSION FROM AREA OF THE FORWARD CARGO NR 2 ENG. DIVERTED TO JFK, THE STALL NOISE WAS AUDIBLE FROM COCKPIT BUT ENGINE INST WERE NORMAL ON BOTH ENGINES. FOUND 5 FAN BLADES CURLED AT TIP. BLENDED ALL BLADES AS REQUIRED, PER AMM 72-00. ALL BLADES ARE WITHIN CONTINUE IN SVC LIMITS EXCEPT FOR 2. THE 2 BLADES ARE WITHIN THE 5 CYC LIMITS. PERFORMED BORESCOPE PER AMM 72-00. CLOSED COWLS. PERFORMED T/O PWR R/U. NO VIBS FELT. ALL OPS.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 37,769 hrs · 31,280 cycles

ON TAXI OUT, F/A NOTED STRONG ELECT SMELL FROM MID OF ACFT ROW 1-15 NIGHT PORTION OF LIGHTS INOP. RETURNED TO GATE. MAINT FOUND NO ELECT SMELL WHEN BACK AT GATE. SUSPECT NIGHT LIGHT TRANSFORMER. PULLED AND CLAMPED C/B FOR LIGHTS AND DEF PER MEL 33-00-02.

Part: SKIN — CRACKED (FS 727B, S-18R) · airframe 37,756 hrs · 31,274 cycles

FUSELAGE / SKIN / FS 727B / STRG. 18R : CRACK REPAIR INSPECTION OF THE FUSELAGE SKIN REVEALED A 1" AT FS 727B JUST ABOVE THE WAFFLE DOUBLER LINE AT STRINGER 18R. THE CRACK WAS REMOVED WITH A CUTOUT AT THE STRINGER. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 381960-14.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 36,494 hrs · 30,617 cycles

1L EXTERIOR EMERGENCY LIGHT INOP. RELAMPED SAME.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 36,410 hrs · 30,541 cycles

DURING AD 2000-05-29 INSPECTIONS, CRACKS WERE FOUND IN THE CENTER WEB AND LT AND RT SIDE CHORDS OF THE FS 178 BULKHEAD. A COMPLETE MODIFICATION PER SECTION XI OF S/B 737-53A1173 WAS ACCOMPLISHED.

Part: OIL PRESS SW — FAILED (APU)

CLIMBING THRU 13,000 FT, APU SHUT DOWN WITH LOW OIL PRESSURE LIGHT, (RT GENERATOR ALREADY ON MCO.) REPLACED LOW OIL PRESSURE SW AND LOW SEQ SW APU, CKS NORMAL.

Part: BULKHEAD WEB — CRACKED (BS 178)

THREE CRACKS WERE DISCOVERED ON THE FWD FACE OF THE FS 178 BULKHEAD WEB. TRIMMED OUT CRACKS; 0.050 2024-T3 DOUBER, FILLER AND SHIMS AS REQUIRED; DTA ANALYSIS AT 60,000 CYCLES.

Part: FLOORBEAM — CRACKED (BS 520)

STA 520 HAS DAMAGE ON THE FLOORBEAM, 1.5 CRACK ON BOTH THE LEFT INBD AND RT INBD SEAT TRACK LOCATION. BOTH THE CRACKS ARE IN THE RADIUS AND EXTEND INBD AND OUTBD. THIS IS A GROUP 3 A/C PER S/B 737-53-1120, REV 1. INSPECT FOR CRACKS, REPAIR SIMILAR TO S/B 737-53-1120, REV 1.

Part: BATTERY PACK — DISCHARGED (CABIN)

ON LAYOVER, FOUND NR 1 SERVICE DOOR SLIDE EMERGENCY LIGHT INOP. REPLACED BATTERY PACK, OP CK GOOD.

Part: ANTI-ICE DUCT — BLOWN (NR 2 ENGINE)

RIGHT ENGINE OVERHEAT LIGHT CAME ON ABOUT 1 MIN AFTER TAKEOFF. RETARDED THROTTLE TO IDLE AND LIGHT WENT OUT. RETURNED TO ABE. FOUND RT ANTI-ICE DUCT BLOWN AT 13TH STAGE TAPOFF. REPLACED DUCT, RAN ENG AND LEAK CHECKED.

Part: AIR DATA COMP — INOPERATIVE (NR 2)

ON TAKEOFF ROLL, F/O'S AIRSPEED VSI AND ALTIMETER OFF FLAGS CAME ON, RETURNED TO THE GATE. C/A INSTALLED NEW NR 2 ADC, ALL INDICATIONS ARE NORMAL.

Part: SOCKET — SHORTED (CABIN)

DURING SVC CK, FOUND LAST SECTION OF CABIN EMERGENCY FLOOR TRACK ESCAPE LIGHTS INOP. PROBLEM CAUSED BY FARTHEST AFT LIGHT SOCKET WAS SHORTED AND FUSE BLOWN IN POWER SUPPLY. REPLACED SHORTED LIGHT SOCKET AND POWER SUPPLY.