N1027P

ATA 7532

Part: PRESSURE SWITCH — FAILED (RT ENG BLEED) · airframe 4,411 hrs · 3,111 cycles

THE FLIGHT CREW REPORTED AN AMBER CAS MESSAGE "HP VALVE FAIL R" ILLUMINATED ON EICAS AFTER LANDING AND REMAINED ILLUMINATED UNTIL SHUTDOWN. THE MAINTENANCE PROVIDER TROUBLESHOT AND DETERMINED THE RIGHT ENGINE HP BLEED DIFFERENTIAL PRESSURE SWITCH HAD FAILED. THE FAILED PRESSURE SWITCH WAS REMOVED, AND A NEW SWITCH WAS INSTALLED. OPS CHECKS WERE GOOD, NO FAULTS NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 2721

Part: ACTUATOR — FAULTED (RUDDER TRIM) · airframe 4,395 hrs · 3,097 cycles

THE FLIGHT CREW REPORTED THAT THE RUDDER TRIM INDICATOR WAS NOT INDICATING FULL TRAVEL. THE MAINTENANCE PROVIDER FOUND THE TRIM INDICATOR WAS STOPPING OUTSIDE THE GREEN ARE WHEN MOVED TO THE RIGHT. THEY THEN CONFIRMED THAT THE TRIM ACTUATOR WAS NOT MOVING FULL TRAVEL. THE DEFECTIVE TRIM ACTUATOR WAS REMOVED, AND A REPLACEMENT ACTUATOR WAS INSTALLED. OPERATIONAL AND RIGGING CHECKS WERE COMPLETED WITH SATISFACTORY RESULTS. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 7200

Part: CARBON SEAL — FAULTED (RT ENGINE) · airframe 4,391 hrs · 3,090 cycles

FLIGHT CREW REPORTED THAT DURING FLIGHT OF OBSERVING SMOKE IN THE CABIN, THE CREW RAN THE CHECKLIST, DONNED OXYGEN MASKS AND ISOLATED THE BLEAD AIR SOURCE TO THE NO1 ENGINE. SMOKE DIMINISHED. APPROACH AND LANDING WAS UNEVENTFUL. THE MAINTENANCE PROVIDER TROUBLESHOT AND AFTER MULTIPLE ENGINE RUNS DETERMINED THE RIGHT ENGINE CARBON SEALS WERE AT FAULT. THIS REQUIRES THE ENGINE TO BE REMOVED FROM THE AIRCRAFT FOR REPAIRS. NO FURTHER INFORMATION ON FAILED CARBON SEALS AT THIS TIME.

ATA 2720

Part: ACTUATOR — DEFECTIVE · airframe 4,242 hrs · 2,972 cycles

CREW REPORTED RUDDER BIAS CHECK - UNSATISFACTORY, NO CHANGE IN RUDDER PEDAL WITH ENGINE POWER UP LEFT OR RIGHT. THE MAINTENANCE VENDOR DETERMINED THE RUDDER BIAS ACTUATOR WAS DEFECTIVE AND REQUIRED TO BE REPLACED WITH AN OVERHAULED UNIT. OPS CHECKS SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE. REF: CE680 AMM 27-20-10

ATA 2750

Part: DRIVE UNIT — FAULTED (FLAP SYSTEM) · airframe 4,120 hrs · 2,884 cycles

THE FLIGHT CREW REPORTED THAT DURING DESCENT FOR LANDING THE FLAP SYSTEM STOPPED EXTENSION BETWEEN THE 15 AND 35 POSITION. THE APPROACH AND LANDING WAS UNEVENTFUL. THE MAINTENANCE TEAM DETERMINED THE FLAP DRIVE WAS AT FAULT. THE FLAP DRIVE UNIT WAS REMOVED AND AN OVERHAULED UNIT WAS INSTALLED. ALL OPS CHECKS WERE SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE..

ATA 2824

Part: VALVE — FAULTED (MOTIVE FLOW) · airframe 4,018 hrs · 2,810 cycles

THE FLIGHT CREW REPORTED THE LOSS OF ENGINE OIL PRESSURE ON THE NO2 ENGINE DURING THE DOWNWIND LEG OF THE APPROACH FOR LANDING. THE FLIGHT CREW ACCOMPLISHED A PRECAUTIONARY SHUTDOWN OF THE NO2 ENGINE. THE APPROACH AND LANDING WAS UNEVENTFUL. NO PASSENGERS WERE ABOARD. THE MAINTENANCE TEAM TROUBLESHOT AND COMPLETED ENGINE AND FUEL TRANSFER OPERATIONAL CHECKS. ALL CHECKS WERE SATISFACTORY. ENGINE COMPUTER DATA WAS DOWNLOADED AND FORWARDED TO PRATT AND WHITNEY FOR EVALUATIONS. THE INVESTIGATION REPORT BY P&W DETERMINED THE CAUSE OF THE LOSS OF OIL PRESSURE TO BE ATTRIBUTED TO WHEN THE PILOT SELECTED THE LH TO RH TRANSFER, THE AIRFRAME BOOST PUMP CAME ON, MOTIVE FLOW VALVE WAS OFF. WHEN THE TRANSFER WAS DONE, THE BOOST PUMP WERE OFF AND THE MOTIVE FLOW VALVE KICKED BACK IN. THAT CAUSED A RIPPLE IN THE FUEL TO THE FUEL PUMP CAUSING A FLAMEOUT AND THUSLY A LOW OIL PRESSURE LIGHT. THIS SITUATION IS ADDRESS IN THE AIRCRAFT FLIGHT MANUAL. ANOTHER FAULT WAS FOUND IN THE ENGINE DATA FOR A DEFECTIVE MOTIVE FLOW VALVE ON THE NO1 ENGINE. THE VALVE WAS REMOVED AND A NEW VALVE WAS INSTALLED. OPS CHECKS WERE SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 3030

Part: SENSOR — FAULTED (PITOT HEAT) · airframe 3,924 hrs · 2,728 cycles

FLIGHT CREW A "PITOT/STATIC COLD - R" MESSAGE DISPLAYED. THE MAINTENANCE VENDOR TROUBLESHOT AND FOUND THE RIGHT PITOT HEAT CURRENT SENSOR FAULTY. THE SENSOR WAS REMOVED AND A NEW SENSOR INSTALLED. ALL WORK AND GROUND FUNCTIONAL CHECKS WERE SATISFACTORY. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 2600

Part: DETECTOR — FAILED (BLEED LEAK) · airframe 3,536 hrs · 2,427 cycles

THE FLIGHT CREW REPORTED THAT DURING PREFLIGHT CHECKS THE RIGHT WING BLEED CHECK FAILED DURING THE ROTARY TEST. THE MAINTENANCE VENDOR DETERMINED THAT THE RIGHT WING BLEED LEAK DETECTOR UNIT FAILED. THE DETECTOR UNIT WAS REMOVED AND REPLACED WITH NEW. OPS CHECKS GOOD AT THIS TIME. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 5311

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,600 hrs · 1,608 cycles

DURING A ROUTINE DOCUMENT INSPECTION THE MAINTENANCE VENDOR DISCOVERED A CRACKED FRAME AT FS 72 IN THE NOSE LANDING GEAR WHEEL WELL TUNNEL. DURING THE REMOVAL OF THE CRACKED FRAME SECTION, THEY IDENTIFIED OTHER CRACKS IN A DOUBLER ASSOCIATED WITH THE FS 72 SECTION WHICH REQUIRED REPAIRS.