N374PA

Part: CIRCUIT BREAKER — FAILED (WARNING SYSTEM) · airframe 18,165 hrs · 12,497 cycles

AUTO PILOT DISENGAGES BY ITSELF AND AURAL WARNING CIRCUIT BREAKER KEEPS POPPING OUT AFFECTING AUTO PILOT DISCONNECT HORN. REPLACED AURAL WARNING CIRCUIT BREAKER PER MM 31-26-00 AND OPS CHECKED. PERFORMED SELF TEST OF AUTO PILOT SYSTEM PER MM 22-02-10 AND 22-03-10. NO DEFECTS NOTED.

Part: LINE — LOOSE (BLEED VALVE) · airframe 18,158 hrs · 12,492 cycles

RIGHT ENGINE DOESN'T SPOOL UP. ADJUSTED GROUND IDLE PER MM. ADJUSTED SPECIFIC GRAVITY PER MM. TIGHTENED LINE AT BLEED REGULATOR. BOTH ENGINES OPERATE NORMAL PER MM.

Part: SKIN — DENTED (FUSELAGE) · airframe 17,612 hrs · 12,224 cycles

DENT IN FUSELAGE SKIN AFT OF L1 DOOR AT STA 400 BETWEEN STR 17 LT AND STR 18 LT. REPAIRED AREA PER SRM 53-00-01 AND EA 53-120.

Part: SKIN — DENTED (FUSELAGE) · airframe 17,612 hrs · 12,224 cycles

DENT AT RIGHT SIDE OF AIRCRAFT AT BS 312 AND STR 20. REPAIRED PER SRM 53-00-01 AND EA 53-121.

Part: THRESHOLD — CRACKED (FUSELAGE) · airframe 17,612 hrs · 12,224 cycles

AFT CARGO DOOR CENTER SECTION OF THRESHOLD CRACKED. WELDED PER BAC 5975.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 17,612 hrs · 12,224 cycles

CORROSION ON LT TRANSITION ANGLE IN AFT CARGO BIN FROM BS 727E TO AFT END. FABRICATED AND INSTALLED REPLACEMENT TRANSITION ANGLE IAW SRM 53-60-53.

Part: BOLT — LOOSE (RUDDER) · airframe 17,301 hrs · 28,333 cycles

FOUND FIVE BOLTS LOOSE DURING INSPECTION OF RUDDER FLANGE BOLTS PER PARA (A) & (B) OF AD 2003-26-01 AND BOEING SB 737-55A1087. REPLACED HARDWARE AT LOCATIONS F1, F2, F3, F4, F10 PER BOEING SERVICE BULLETIN.

Part: WARNING HORN — FALSE ACTIVATION (COCKPIT) · airframe 17,098 hrs · 11,963 cycles

WARNING HORN ON TAKEOFF ROLL. NO LEADING EDGE FLAP/SLAT INDICATION. RESET LEADING EDGE POSITION INDICATOR CIRCUIT BREAKER. SYSTEM OPS CHECKS GOOD PER MM 27-88-00.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 16,890 hrs · 11,846 cycles

FUSELAGE DAMAGED LEFT SIDE FROM BS 907 TO BS 927 AT STR 16 LT, AT BS 907 BETWEEN STR 21 LT AND 22 LT AND FRAME SHEAR TIE DAMAGED AT BS 908 BETWEEN STR 21 LT AND STR 22 LT. REPAIRED DAMAGE PER EA NOS 53-327, 53-331, AND 53-332.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 16,798 hrs · 11,785 cycles

RT EMERGENCY OVERWING EXIT SIGN LOCATOR LIGHT INOPERATIVE. RE-LAMPED LOCATOR LIGHT IAW MM 33-51-11. OPS CHECKS NORMAL.

Part: COUPLER — FAILED (YAW DAMPER) · airframe 16,397 hrs · 11,564 cycles

YAW DAMPER OFF LIGHT ILLUMINATED (YAW DAMPER DC CIRCUIT BREAKER POPPED). REPLACED YAW DAMPER COUPLER PER MM 22-13-00. OPS CHECKS GOOD.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 15,245 hrs · 10,959 cycles

FWD FLIGHT ATTENDANT JUMPSEAT OUTBOARD EMERGENCY FLASHLIGHT LED WILL NOT FLASH. ITEM DEFERRED PER MEL 25-12, CONTROL NR 0112001. 1/15/2003. R & R BATTERY POWER UNIT AS REQUIRED. OPS CHECK NORMAL. CLEARED MEL 25-12, CONTROL NR 0112001

Part: SENSOR — FAILED (LE FLAP) · airframe 14,785 hrs · 10,706 cycles

TAKEOFF WARNING HORN ACTIVATED DURING T/O ROLL, OBSERVED LE FLAPS TRANSIT LIGHT ILLUMINATED, PERFORMED RTO. FOUND NR 1 KRUGER FLAP POSITION SENSOR BAD. R&R PROXIMITY SENSOR PER MM 27-88-11, OPS CHECKED. GOOD.

Part: SENSOR · airframe 14,785 hrs · 10,706 cycles

Takeoff warning horn activated during T/O roll, observed LE flaps transit light illuminated, performed RTO. R&R #1&2 tires and brakes, R&R #3&4 brakes per 32-41 & 32-45; insp anti-skid system per 32-42-00 OK; performed T/O warning test per AD 88-22-09 OK; brake seizure insp per 05-51-04 OK; high energy insp per 05-51-07 no damage found. R&R #1 kruger flap proximity sensor per MM 27-88-11, Ops chk. good.