N239WA

Part: FUEL CONTROL — MALFUNCTIONED (NR 2 ENGINE) · airframe 49,582 hrs · 38,047 cycles

AT APPROX 9800 FT DURING MANUAL POWER ADVANCE NR 2 ENGINE COMPRESSOR STALLED. REPLACED FUEL CONTROL.

Part: SKIN — FATIGUED (FUSELAGE) · airframe 47,778 hrs · 36,683 cycles

CRACK INDICATIONS WERE NOTED DURING MFEC INSPECTION OF THE S4R LAP. DURING REPAIR ACCOMPLISHMENT PER SRM 53-30-3, FIG 42, 12 MORE ADDITIONAL CRACK INDICATIONS WERE NOTED. CRACK INDICATIONS WERE REMOVED, ADDITIONAL INSPECTIONS ACCOMPLISHED AS PER ERA 386164-14AD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,778 hrs · 36,683 cycles

DAMAGED HOLES FOUND IN STR 20R LAP SPLICE FASTENER ROWS. DURING REPLACEMENT OF UPPER SKIN PANEL BETWEEN STA 916-990. REPAIRED PER ERA 386177-14.

Part: FLOOR SUPPORT — FATIGUED (FUSELAGE) · airframe 47,778 hrs · 36,683 cycles

A CRACKED WAS NOTED IN THE BBL 0.07 LONGITUDINAL FLOOR SUPPORT AT BS 715. CRACKED REMOVED AND FLOOR SUPPORT REPAIRED PER ERA 386095-14AD.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 47,778 hrs · 36,683 cycles

CORROSION WAS NOTED ON THE LUGS OF THE HORIZONTAL STABILIZER CENTER SECTION REAR SPAR HINGE AND HOUSING FITTING. CORROSION REMOVED AND FITTINGS REWORKED IAW ERA 386232-14.

Part: SKIN — CORRODED (FUSELAGE) · airframe 47,778 hrs · 36,683 cycles

CORROSION WAS FOUND ON THE KEEL BEAM LOWER SKIN PANEL. LOWER SKIN PANEL WAS REPLACED PER ERA 386233-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,775 hrs · 36,683 cycles

A TIME LIMITED REPAIR WAS REMOVED FROM BS 1025 NEAR S25R, NEARBY ADDITIONAL DAMAGE WAS NOTED (EG, DENTS AND GOUGES). DENTS AND GOUGES WERE CUTOUT AND A PERMANENT REPAIR INSTALLED PER ERA 386109-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,775 hrs · 36,683 cycles

SCRIBE MARKS WERE NOTED BETWEEN BS 360 TO BS 540 AT THE S26R LAP JOINT. LAP WAS REWORKED PER INSTRUCTIONS CONTAINED IN ERA 386165-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,775 hrs · 36,683 cycles

SCRIBE MARKS WERE NOTED BETWEEN BS 360 AND BS 540 ALONG S26L LAP JOINT IN THE LOWER SKIN. LAP JOINT WAS REWORKED PER INSTRUCTIONS CONTAINED IN ERA 386161-14.

Part: ATTACH FITTING — CORRODED (VERTICAL STAB) · airframe 47,775 hrs · 36,683 cycles

CORROSION WAS NOTED ON THE VERT STAB ATTACH LUGS, ON THE AFT FACE OF THE NR 6 FIN LUG. CORROSION REMOVED AND LUG REWORKED PER ERA 386225-14.

Part: WIRE — BROKEN (CABIN) · airframe 47,496 hrs · 36,566 cycles

EMERGENCY LIGHT INOP AT 16D. REPAIRED BROKEN WIRE.

Part: ACM — SEIZED (A/C BAY) · airframe 46,479 hrs · 36,129 cycles

A/C DIVERTED INTO JAX WITH SMOKE/FUMES IN THE CABIN AND COCKPIT. PASSENGERS IN SEAT 10ABC FELT AND HEARD RUMBLING UNDER FLOOR INDICATING A PACK PROBLEM. UPON FURTHER INVESTIGATION FOUND THE LEFT PACK ACM HAD SEIZED UP CAUSING THE FUMES AND SMOKE. LEFT PACK WAS PUT ON MCO AND POSITION FERRIED BACK TO ORLANDO.

Part: FITTING — CORRODED (FUSELAGE) · airframe 44,680 hrs · 35,354 cycles

THE LT MAIN LANDING GEAR SIDE STRUT SUPPORT FITTING AT FS 685 WAS FOUND WITH CORROSION IN THE MAIN LUG BORE. THE BORE WAS OVERSIZED TO REMOVE ALL CORROSION AND AN OVERSIZE REPAIR BUSHING INSTALLED. THE REPAIR WAS ACCOMPLISHED PER ER/A 379223-14.

Part: FITTING — CORRODED (FUSELAGE) · airframe 44,680 hrs · 35,354 cycles

THE RT MAIN LANDING GEAR SIDE STRUT SUPPORT FITTING AT FS 685 WAS FOUND WITH CORROSION IN THE MAIN LUG BORE. THE BORE WAS OVERSIZED TO REMOVE ALL CORROSION AND AN OVERSIZE REPAIR BUSHING INSTALLED. THE REPAIR WAS ACCOMPLISHED PER ER/A 379224-14.

Part: HYDRAULIC LINE — RUPTURED (NOSE WHEEL WELL) · airframe 44,469 hrs · 35,262 cycles

SHIP 363 FLIGHT 2131 ARRIVED EWR AT 2353E. DURING TAXI TO TERMINAL CREW NOTICED A SYSTEM HYDRAULIC QUANTITY DEPLETED. FOUND BRAIDED HYDRAULIC LINE WITH PINHOLE LEAK. LINE IS LOCATED IN AFT SECTION OF NOSE WHEEL WELL. REPLACED HYDRAULIC LINE.

Part: TIRE — FAILED (MLG) · airframe 44,460 hrs · 35,257 cycles

NR 1 TIRE BLEW ON LANDING. SPEED 142 KTS, AUTOBRAKES MEDIUM. AUTOBRAKE DISARM LIGHT W/OUT CREW INTERVENTION. REPLACED NR 1 AND NR 2 WHEEL ASSYS PER M/M. INSPECTED BRAKE, GEAR AND AIRCRAFT. NO DAMAGE FOUND. DEFERRED ANTI SKID SYSTEM.

Part: FRAME — CORRODED (FUSELAGE) · airframe 43,023 hrs · 34,635 cycles

THE FWD FRAME OF THE C2 DOOR OPENING (FS 794) WAS FOUND WITH AN AREA OF CORROSION IN THE FRAME WEB UNDER THE LOWER LATCH FITTING. THE CORROSION WAS REMOVED WITH 1.5 X .75 CUTOUT IN THE FRAME WEB AND REPAIRED WITH A FORMED ALUMINUM DOUBLER PER B737 SRM 51-40-3 AND ER/A 377331-14AD.

Part: O RING — DEFORMED (NR 1 ENGINE CSD)

AT 30 KTS ON TAKEOFF ROLL HAD NR 1 ENG GENERATOR LOW OIL PRESS LIGHT FLICKER FOLLOWED BY GENERATOR KICKING OFF-LINE. AN ABORT WAS ACCOMPLISHED AND TAXI BACK TO THE GATE. MTC SERVICED NR 1 ENG CSD. PERFORMED ENGINE RUN AND FOUND OIL LEAKING FROM CHARGE FILTER AREA ON CSD. REPLACED O-RING ON CHARGE FILTER HOUSING COVER, P/N 012206891. PERFORMED ENG RUN/LEAK CHECK. GENERATOR OPN WAS GOOD. ACFT WAS RETURNED TO SERVICE.

Part: MASK — FAILED (COCKPIT)

OBSERVERS 02 MASK FAILED. REPLACED OBSERVERS 02 MASK.

Part: PUMP — MALFUNCTIONED (A HYD SYST)

ON DESCENT INTO MCO, LOST BOTH A SYSTEM ENGINE DRIVEN HYDRAULIC PUMPS, LOW PRESSURE LIGHT ILLUMINATED. CHECKED AND REPLACED ALL CASE DRAIN AND RETURN FILTERS, NO METAL. REPLACED COCKPIT OVERHEAD HYDRAULIC PANEL AND BOTH ENGINE DRIVEN HYDRAULIC PUMPS AS PRECAUTION. RAN ENGINES AND ALL FLIGHT CONTROLS, ALL OPERATION NORMAL.

Part: TIRE — FAILED (RT MLG)

AFTER TAKEOFF FROM BDL, TOWER NOTIFIED US OF RUBBER DEBRIS ON THE RUNWAY. ON APPROACH TO MCO, AT GEAR EXTENTION HAD A RIGHT MAIN GEAR UNSAFE LIGHT ON AND GREEN LIGHT OFF. FOLLOWED ABNORMAL PROCEDURE. FOUND NR 3 MAIN TIRE LOST CAP AND DAMAGED INBD BRAKE LINE AND HOLDER AND AFT FLAP AND MID FLAP AND GEAR DOWN AND LOCK PROX TARGET. REPLACED NR 3 AND 4 MAIN WHEEL ASSYS. REPLACED BRAKE LINE AND HOLDER, AFT INBOARD FLAP ASSY, MID FLAP BELLCRANK MECHANISM, AND ACCESS PNL.

Part: SIGN — INOP (DOOR 2L)

EXIT SIGN AT DOOR 2L WILL NOT TEST.

Part: SKIN — DAMAGED (CARGO DOORWAY)

DURING INSP OF THE C1 DOOR CUTOUT PER RTN OPN 8706, AN EXISTING DOUBLER WAS REMOVED TO ACCOMMODATE THE INSPECTION. UPON REMOVING THE DOUBLER, ADDITIONAL SKIN DAMAGE WAS FOUND. REPAIRED PER ERA 332066-14.

Part: SKIN — GOUGED (CARGO DOORWAY)

THE UPPER AFT PORTION OF THE C1 DOOR CUTOUT WAS FOUND TO HAVE A GOUGE APPROX 10.5 BY 2.5. REPAIRED PER ERA 332098-14.

Part: DOUBLER — CRACKED (BS 682)

DURING RTN INSP PER SI3-56673-12 OF THE LH AND RH LONGITUDINAL OVERWING FLOORBEAMS, CRACKS WERE FOUND IN THE WEB DOUBLERS. THE CRACKS ARE LOCATED IN THE DOUBLERS IN THE UPPER AFT CORNER OF THE AILERON CONTROL QUADRANT CUTOUTS AT THE LBL/RBL 24.82 AND APPROX STA 682. AT BOTH LOCATIONS THE CRACKS EXTEND FROM THE UPPER EDGE OF THE DOUBLER TO THE CONTROL QUAD OPENING AND SEPARATE THE WEB INTO TWO PIECES. REWORKED PER ERA 332082-14AD.

Part: GENERATOR — TRIPPED (NR 1 ENGINE)

ON CLIMB-OUT OF 23,000 FEET, CTR FUEL PUMPS WERE TURNED ON AND WE LOST THE NR 1 GEN IN ABOUT 2-3 SECONDS, THE NR 1 BUS OFF AND GEN OFF BUS LIGHTS ILLUM FOLLOWING POM PROCEDURES WE WERE UNABLE TO POWER NR 1 BUS BY LT GEN OR APU. GEN NR 1 VOLTS AND FREQS PEGGED TO THE LOW SIDE. CHECKED NR 1 CSD OIL SVC CHECKED GOOD, HAD MT AND LV FAULTS CLEARED FAULTS APU POWERED BOTH LT/RT BUSSES NML. RESET NR 1 GEN, RAN BOTH ENG GEN SYS XFERS POWER SEVERAL TIMES, CKS NML LT GEN AND BUS OPN CKS NML.

Part: SEAL — TORN (CARGO DOOR)

CLIMBING THROUGH FL242 CABIN ALT WARN HORN. CABIN ALT OBSERV CLIMB THROUGH 10000 AND AIRCRAFT LEVELED. DESCENT BEGAN AND CABIN ALT CLIMBED TO 13500, NO HELP IN STBY OR MAN, PRESS MODE OUTFLW VLV FULLY CLOSED AND FWD VALVE CLOSED LIGHT ON ENTIRE TIME. CHECKED ENTRY SERVICE CARGO DOOR SEALS. FOUND WORN FWD CARGO DOOR SEAL. REPLACED FWD CARGO DOOR SEAL. PRESSURIZED A/C, ALL IND GOOD, NO LEAKS.

Part: DUCT — COLLAPSED (RT PACK)

ON TAKEOFF AFTER RETRACTING L/GEAR, LOUD BANG FOLLOWED BY SMOKE IN CABIN. A/C RETURNED TO GATE. FOUND DUCT FROM RT PACK HOT AIR SIDE OF MIX VALVE DISCONNECTED AND COLLAPSED (P/N 65-54474-1). MUFFLER 21-20-0-46A REF G COLLAPSED(P/N 65-78947-10) AND MIX CHAMBER REF 360 (P/N 65-54472-8) PARTIALLY COLLAPSED. DUCTS REPLACED AND SYS CHKS OK.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING INSPECTION, 2 CRACKS WERE DISCOVERED ON THE FWD FACE OF BS 178 BULKHEAD WEB. CRACKS WERE LOCATED UNDER THE LBL 5.7 AND RBL 5.7 VERTICAL STRAPS. IN ACCORDANCE WITH FAA/DER FORM 8110-3, DER DESIGNATION SO-957, DATED 9 AUG 1996, THE CRACKS WERE TRIMMED OUT AND A REPAIR DOUBLER WAS INSTALLED.

Part: SKIN — CRACKED (BS 379)

SKIN AT THE COOLING DUCT CUTOUT BS 379 BL 2 WAS FOUND CRACKED AT THE AFT EDGE OF THE CUTOUT INTO A FASTENER HOLE. THE CRACK IS APPROXIMATELY .6 IN LENGTH AND IS TYPICAL OF CRACKS DESCRIBED IN BACO S/B 737-53-1117 R1 IN ACCORDANCE WITH THE ABOVE S/B, THE SKIN WAS REPAIRED.

Part: AOA SENSOR — BROKEN (LEFT)

ON LIFT-OFF, THE STICK SHAKER ACTIVATED AND DID NOT STOP UNTIL TOUCHDOWN. FOUND LEFT AOA SENSOR BROKEN OFF FROM A/C. REPLACED LEFT AOA, OPS CKS GOOD.