N2310

Part: FITTING — CORRODED (FUSELAGE) · airframe 46,668 hrs · 31,939 cycles

CORROSION WAS FOUND IN THE LUG BORE AND AFT LUG FACE OF THE LT MLG SIDE STRUT FITTING AT FS 685. THE BORE WAS OVERSIZED AND THE FACE SPOTFACED TO REMOVE ALL CORROSION. A REPAIR BUSHING WAS INSTALLED IN THE BORE AND A WASHER INSTALLED TO FILL THE SPOTFACE. THE REPAIR WAS ACCOMPLISHED PER ER/A 385080-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 46,666 hrs · 31,938 cycles

FUSELAGE / SKIN / DENTING AND CREASE AT STA 380 BETWEEN STRINGERS 17L AND 18L. DENTED AND CREASED SKIN WAS CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER AND TRIPLER PER ER/A 384851-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 46,666 hrs · 31,938 cycles

FUSELAGE / COCKPIT FLOOR STRUCTURE / CRACKED WEB AND INTERCOSTAL / STA 178, WL 207, RBL 28, THE INTERCOSTAL OUTBOARD STRUCTURE AND HORIZONTAL WEB WERE FOUND CRACKED. BOTH ARE LOCATED IMMEDIATELY AFT OF THE STA 178 BULKHEAD. THE CRACK WAS TRIMMED OUT OF THE STRUCTURE AND A NEW BULKHEAD ATTACH CLIP WAS INSTALLED WHICH PICKS UP ADDITIONAL FASTENERS ON THE CHORD AND WEB. THE WEB WAS REPLACED. ALL WORK WAS ACCOMPLISHED PER ER/A 384917-14AD.

Part: SMOKE DETECTOR — FAULTY (LAVATORY) · airframe 44,971 hrs · 30,962 cycles

LAV SMOKE AMBER LIGHT AND CHIME CAME ON DURING CRUISE FLIGHT. ALL LAVS CHECKED WITH NO SIGN OF SMOKE, FUMES, EXCESSIVE HEAT. CIRCUIT BREAKER PULLED TO SILENCE CHIME. FOUND AFT RT DETECTOR INOP. REPLACED DETECTOR, OPS CHECKS GOOD.

Part: ENGINE — OVERTEMP (NR 1) · airframe 44,965 hrs · 30,958 cycles

ON TAKEOFF (NORMAL POWER) CLIMBOUT BOTH ENGINE INDICATIONS SHOWED RED LIGHT ILLUMINATED ON DIGITAL READOUT AT 970 DEGREES (C) PLUS ON BOTH ENGINES AT LEAST 5 SECONDS. N1 INDICATES AT ABOUT 96.6. PULLED BACK THROTTLES, RED LIGHT EXTINGUISHED. REMOVED AND REPLACED BOTH ENGINES DUE TO OVERTEMP.

Part: TRANSMITTER — MALFUNCTIONED (T/E FLAP) · airframe 44,965 hrs · 30,958 cycles

DURING FLAP EXTENSION RIGHT FLAP IND REMAINED NEAR ZERO AND LEFT INDICATED NEAR ONE DEGREE. L/E INDICATIONS NORMAL. FOLLOWED QRH PROCEDURES AND LANDED AT 170 KIAS. REPLACED RIGHT T/E FLAP POSITION TRANSMITTER, OPS NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 41,822 hrs · 28,991 cycles

THE FUSELAGE SKIN AT THE AFT EDGE OF THE C2 DOOR CUTOUT WAS FOUND WITH A SMALL CRACK AT STRINGER 22R. THE CRACK WAS REMOVED WITH A 1.1 IN X .85 IN EDGE TRIM AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 380703-14, REV A.

Part: BATTERY — INOPERATIVE (CABIN) · airframe 39,983 hrs · 27,817 cycles

1L DOOR AND 1R EXIT SIGN EMERGENCY LIGHT INOP. REPLACED BATTERY.

Part: WIRE — FAILED (APU) · airframe 39,931 hrs · 27,784 cycles

AFTER LANDING WITH APU RUNNING AND POWER ON RT ENG ON APU GEN, SHUT DOWN RT ENG AND APU GEN IMMEDIATELY DROPPED OFF LINE. RECONNECTED APU GEN TO RT SIDE SIMULTANEOUSLY. F/A IN AFT NOTED SPARKS IN CEILING. CRACK IN CEILING ON CAPT SIDE WHERE AISLE MEETS GALLEY WALL. ALSO NOTICED ELECTRICAL BURNING SMELL WHICH DISSIPATED QUICKLY. SPARKS LASTED ONLY AN INSTANT. NO C/B POPPED. FOUND APU GEN FEEDER CABLES ARC''D IN CEILING FWD OF AFT GALLEY.

Part: ATTACH FITTING — CORRODED (NR 2 PYLON) · airframe 39,865 hrs · 27,742 cycles

REMOVAL OF A MIGRATED SPHERICAL BEARING ON THE AFT LUG FITTING OF THE NR 2 ENGINE STRUT CROWN BEAM REVEALED CORROSION IN THE LUG BORE. THE LUG BORE WAS OVERSIZED BY .10 INCHES TO REMOVE THE CORROSION, A 15-5 STEEL BUSHING INSTALLED, AND A NEW SPHERICAL BEARING INSTALLED. THE REPAIR WAS ACCOMPLISHED PER ER/A 377570-14, REV C.

Part: ACTUATOR — FAILED (AUTOPILOT) · airframe 39,427 hrs · 27,482 cycles

AT FL 270, BEGINNING DESCENT, EXPERIENCED UNCOMMANDED ABRUPT ROLL APPROX 35-40 DEGREES TO THE LEFT. AUTOPILOT REVERTED TO CWS PITCH AND ROLL. YAW DAMPER IND SHOWED NO ABNORMAL INDICATIONS. NO TURBULENCE IN AREA. A/C IN CLEAN CONFIG. A AUTOPILOT ENGAGED AT THE TIME OF OCCURANCE. REPLACED THE A SYSTEM AUTOPILOT ACTUATOR PER MM. ALSO, REPLACED A CHANNEL FCC.

Part: VALVE — OPEN (STARTER) · airframe 39,276 hrs · 27,383 cycles

START VALVE CAME OPEN DURING TAXI ON NUMBER 2 ENGINE. STARTER DESTROYED. REPLACED STARTER AND START VALVE.

Part: SKIN — CRACKED (LT COCKPIT)

A .75 INCH CRACK WAS FOUND IN THE SKIN AND UNDERLYING CORNER GUSSET AT UPPER OUTBD CORNER OF THE L1 COCKPIT WINDOW (C-D WINDOW POST LOCATION). THE CRACK WAS ROUTED OUT AND REPAIRED WITH AN EXTERNAL STEEL REPAIR DOUBLER AND AN ALUMINUM REPAIR TRIPLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 365209-14, REV B.

Part: BRAKES — FAILED (NR 4)

NR 4 BRAKE FAILED. FOUND PARTS OF STATORS AND PADS IN WHEEL ASSY. REPLACED BRAKE AND WHEEL ASSY.

Part: HYD HOSE — RUPTURES (NLG)

NOSE GEAR WOULD NOT RETRACT. FOUND RUPTURED HYD HOSE ON NOSE GEAR UPLOCK ACTUATOR. REPLACED HOSE, SWUNG GEAR AND OPERATIONAL CHECK GOOD.

Part: SKIN — DENTED (FS 765)

DURING HMV INSPECTION, THE SKIN WAS FOUND DENTED AT FS 765 JUST BELOW THE STRINGER 20R LAP SPLICE. IN ACCORDANCE WITH B737-300 SRM 53-00-01, FIG 202, THE DAMAGED SECTION WILL BE CUT OUT AND AN EXTERNAL REPAIR DOUBLER WILL BE INSTALLED.

Part: SKIN — WORN (NR 2 PYLON)

AT HMV, INSP FOUND THE O/B SIDE OF NR 2 PYLON WORN AT WING L/E AREA. ACCOMPLISHED REPAIRS PER SRM 54-50-01 PG 219.

Part: ANGLE — CRACKED (BS 807)

FLOOR SUPPORT ANGLE CRACKED ABOVE STR 27L AT STA 807. REMOVED DAMAGED SECTION OF ANGLE, MADE REPAIR PARTS, AND INSTALLED PER SRM 53-00 -53, FIG 201.

Part: APU DOOR — DAMAGED (APU COMPARTMENT)

DURING LETTER CHECK, FOUND LOWER APU SHROUD RUBBING ON THE APU DOOR CAUSING DAMAGE WHICH REQUIRED REPAIRS PER SRM 52-40-01 FIG 204.