N546DH

ATA 7500

Part: WARNING MESSAGE — ILLUMINATED (BLEED SYS) · airframe 8,197 hrs · 5,869 cycles

THE FLIGHT CREW REPORTED A RED LEFT ENGINE BLEED LEAK MASSAGE WHILE CLIMBING THROUGH 11K FEET. THE FLIGHT CREW RAN THE CHECKLIST AND ELECTED TO RETURN TO THE AIRPORT FOR LANDING AND EVALUATION. THE BASE MAINTENANCE TEAM FOUND A BLEED AIR FITTING ON THE LEFT LOW PRESSURE SUPPLY TUBE TO BE LEAKING ABOVE THE BAGGAGE PANEL. REMOVED AND REPLACED SEALS ON LEAKING BLEED AIR FITTING WITH NEW PER LEAR 45 AMM 20-31-02. PERFORMED LEAK CHECK OF BLEED AIR FITTING, NO LEAKS NOTICED AT THIS TIME. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 3445

Part: TCAS SYSTEM — FAILED · airframe 8,025 hrs · 5,740 cycles

THE FLIGHT CREW REPORTED THAT THE TCAS SYSTEM FAILED PREFLIGHT CHECKS. OPERATIONS WERE CONTINUED PER MEL 34-45-02 CAT C. AT CORRECTIVE ACTION THE MAINTENANCE TEAM REMOVED AND REPLACED THE TCAS PROCESSOR WITH REPAIRED UNIT. OPS CHECKS WERE SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE

ATA 2760

Part: COMPUTER — FAULTED (SPOILERS) · airframe 7,651 hrs · 5,469 cycles

FLIGHT CREW REPORTED THAT AN AMBER SPOILER FAIL ANNUNCIATOR ILLUMINATOR ON POWER UP FOR EACH FLIGHT FLIGHT LEG. THE CREW WAS ABLE TO PULL AND RESET BREAKERS TO RESET SYSTEM. THE MAINTENANCE VENDOR TROUBLE SHOT AND SUSPECTED A FAULTY SPOILERON COMPUTER. THE VENDOR REMOVED THE DEFECTIVE COMPUTER AND INSTALLED A REPAIRED UNIT. PERFORMED FUNCTIONAL CHECKS WITH NO FAULTS REPORTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 2740

Part: CONTROL BOX — FAILED (PITCH TRIM) · airframe 6,426 hrs · 4,569 cycles

AFTER DEPARTURE, THE CREW WAS WAS ALERTED TO AN ANNUNCIATOR INDICATING THAT THE PRIMARY PITCH TRIM HAD FAILED. ELECTED TO RETURN TO DEPARTURE. TROUBLESHOT AND DETERMINED THAT THE PRIMARY PITCH TRIM ACTUATOR CONTROL BOX HAD FAILED. THE CONTROL BOX WAS REPLACED, AND FUNCTIONAL CHECKS WERE SATISFACTORY.

ATA 7297

Part: WIRE HARNESS — FAULTY (ENGINE) · airframe 6,347 hrs · 4,502 cycles

DURING FLIGHT, THE FLIGHT CREW HAD REPORTED SEVERAL TIMES THAT THE RIGHT ENGINE N2 INDICATIONS WERE ERRATIC AND FLUCTUATING. ATTEMPTS WERE MADE AFTER EACH REPORT TO CORRECT THIS DISCREPANCY. AFTER THE THIRD WRITE-UP TROUBLESHOOTING IDENTIFIED THAT THE ENGINE WIRING HARNESS WAS FAULTY. THE HARNESS WAS REMOVED AND REPLACED WITH NEW. FUNCTIONAL CHECKS WERE SATISFACTORY AND

ATA 3097

Part: WIRE — DAMAGED · airframe 5,880 hrs · 4,158 cycles

DURING THE INITIAL DESCENT FOR LANDING, THE CREW REPORTED THAT THE STAB/WING HEAT CIRCUIT BREAKER TRIPPED. FOLLOWING THE FLIGHT AIRCRAFT MAINTENANCE CREW TROUBLESHOT AND FOUND WIRE PAR204SA WAS CHAFING EXTERNALLY ON THE P40 RELAY BOX. THE WIRE WAS REPAIRED WITH AN ENVIRONMENTAL SPLICE. THE WIRE AND WIRE BUNDLE WAS RE-POSITIONED AND PROTECTED TO PREVENT FURTHER DAMAGE. OPERATIONAL CHECKS WERE SATISFACTORY. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 2742

Part: CONTROLLER — FAILED (HORIZ STAB) · airframe 5,288 hrs · 3,758 cycles

HORIZONTAL STAB ACTUATOR CONTROL WAS REPORTED TO BE DEFECTIVE BY THE FLIGHT CREW. TROUBLESHOOTING DISCOVERED THAT THE HORIZONTAL STAB TRIM ACTUATOR CONTROLLER WAS DEFECTIVE, PN 6627401000-003. A REPAIRED UNIT WAS INSTALLED. OPERATIONS CHECKED OK.

ATA 2421

Part: ALTERNATOR — FAILED (RT ENGINE) · airframe 5,188 hrs · 3,695 cycles

DURING FLIGHT THE RT WINDSHIELD HEAT FAILED. TROUBLESHOOTING FOUND THAT THE RT ALTERNATOR HAD PREMATURELY FAILED. TOTAL TIME ON UNIT AFTER OVERHAUL 695.2 HRS. THE DEFECTIVE UNIT WAS REMOVED & AN OVERHAULED UNIT INSTALLED. OPERATIONS CHECKED OK.

ATA 2400

Part: UNKNOWN — DEFECTIVE (ELECTRICAL SYS) · airframe 4,962 hrs · 3,571 cycles

ATTEMPTED TO START THE APU AFTER LANDING WHILE TAXIING & RECEIVED A RT ESS BUSS FAULT CAS & AN APU FAIL CAS, AFTER ENG SHUTDOWN. THE RT BATTERY COULD NOT BE SHUTOFF. FORCED TO DISCONNECT THE BATTERY CABLES. TROUBLESHOOTING FOUND THE RT AFT PDP DEFECTIVE & REPLACED IT WITH REPAIRED UNIT. OPERATIONS CHECKS SATISFACTORY.

ATA 7830

Part: CONTROL QUADRANT — FAULTY (THRUST REVERSER) · airframe 4,861 hrs · 3,471 cycles

CREW REPORTED THE THE LT THRUST REVERSER WAS INTERMITTENT OR SLOW TO DEPLOY. TROUBLESHOOTING WAS ABLE TO DUPLICATE THE DISCREPANCY BY APPLYING A SIDE LOAD TO THE ENG POWER LEVER. IT WAS FOUND THAT THE DEPLOY SWITCH IN THE THROTTLE QUADRANT TO BE DEFECTIVE. THE THROTTLE QUADRANT PN 6676101000-021, SN 171 WAS REMOVED & A MODIFIED CONDITION QUADRANT WAS INSTALLED. OPERATIONS CHECKED SATISFACTORY.