N603CF

ATA 2612

Part: FIRE LOOP — CHAFED (ENGINE BAY) · airframe 8,424 hrs · 22,630 cycles

DURING FLIGHT BACK TO BASE THE FIRE DETECT LIGHT ILLUMINATED, REPLACED FIRE DETECTOR LOOP AFTER FINDING A CHAFE

ATA 2430

Part: GCU — FAILED (LT ENGINE) · airframe 7,991 hrs · 21,543 cycles

WHILE IN CRUISE FLIGHT OVER AN APPROXIMATE TWO MINUTE PERIOD THE FOLLOWING SYSTEMS FAILED. EACH FAILURE WAS INDICATED ON EDU 1 HOWEVER THE MASTER CAUTION NEVER ILLUMINATED. FAILURES LISTED IN APPROXIMATE CHRONOLOGICAL ORDER: -INVERTER 1 -INVERTER 2 (THIS INITIALLY APPEARED TO BE A SIMPLE INDICATION ISSUE AS INVERTER POWERED SYSTEMS WERE STILL ON-LINE) -SAS 1 -SAS 2 THIS WAS AN ACTUAL FAILURE AS THE AIRCRAFT'S ATTITUDE BECAME LESS STABLE -FUEL PUMP 1 -FUEL PUMP 2 -INDICATIONS OF A GENERATOR FAILURE -EDU 1 COMPLETE FAILURE -EDU 2 COMPLETE FAILURE -COMM 1 COMPLETE FAILURE -DIGITAL CDI COMPLETE FAILURE WAS ABLE TO RECEIVE ON COMM 2 BUT UNABLE TO TRANSMIT. DIVERTED TO KHII. AFTER COMPLETING THE APPROPRIATE EMERGENCY PROCEDURES ATTEMPTED TO CONTACT AIRCOMM VIA SAT PHONE- WAS ABLE TO DIAL AIR COMM AND HEAR THEIR RESPONSE BUT WAS UNABLE TO TRANSMIT. ACTIVATED THE "EMERGENCY" BUTTON ON THE SAT TRACKING SYSTEM. COMPLETED AN UNEVENTFUL LANDING AT KHII. GENERATOR CONTROL UNIT PN GCSG505-28-1 WAS REPLACED AS REQUIRED. AFTER GROUND RUNS AND AN OPERATIONAL CHECK FLIGHT, NO FURTHER DEFECTS WERE NOTED.

ATA 7720

Part: MODULE — MALFUNCTIONED (ENGINE) · airframe 7,975 hrs · 21,511 cycles

AIRCRAFT DEPARTED, SHORTY AFTER TAKEOFF, DURING CLIMB TO CRUISING ALTITUDE, NOTICED THE ENGINE ITT INDICATION WAS READING ERRATICALLY. THE TEMPERATURE WAS DROPPING FROM THE NORMAL 660, TO 605 AND EVEN DIPPED TO 590 AT ONE POINT. THIS HAPPENED SEVERAL TIMES AND IT OCCURRED VERY QUICKLY, USUALLY DIPPING THAN RISING AGAIN WITHIN A SECOND OR TWO. INFORMED THE CREW OF THE MALFUNCTION AND NOTED THE OTHER ENGINE GAUGES AND LISTENED FOR ANY ABNORMAL SOUNDS OR RPM CHANGES. EVERYTHING ELSE WAS OPERATING NORMALLY. ABORTED THE FLIGHT AND RETURNED TO DEPARTURE. LANDED WITHOUT INCIDENT. THE ENGINE ITT TRIM MODULE WAS REPLACED AND ADJUSTED IAW AMM 71-21-8 AND EMM 71-00-00, NO FURTHER DEFECTS NOTED.

ATA 3597

Part: GROUND WIRE — DISCONNECTED (CABIN) · airframe 7,692 hrs · 20,736 cycles

THE CELESTIAL ILLUMINATION WAS DIMINISHING AND THE CREW ASKED FOR THE CABIN LIGHTING. TURNING ON THE LIGHTING, THE REAR CABIN LIGHTING DIMMED, FLICKERED, AND BRIGHTENED BEFORE GOING OUT. THE CABIN LIGHTING SWITCH RESET TO OFF. REPORT OF SMOKE AND FUMES IN THE CABIN. PREPARED FOR A PRECAUTIONARY LANDING. SMOKE DISSIPATED. THE ODOR REMAINED, THE ODOR WAS DISSIPATING. REMAINED IN FLIGHT, WHILE REMAINING AT A LOWER ALTITUDE AND TO DIVERTED. LANDED WITHOUT FURTHER INCIDENT. A MECHANIC TROUBLESHOT THE ISSUE. DETERMINED THAT A GROUND WIRE HAD BECOME DISCONNECTED FROM THE MEDICAL O2 INDICATOR, IN THE LT OVERHEAD PANEL. THE GROUND WIRE THAT WAS DISLODGED FROM THE DIGITAL DISPLAY, HAD TOUCHED ANOTHER GROUNDING POINT CONTACTING IT SEVERAL TIMES, THUS BURNING THE INSULATION AND INTERNAL WIRE. THE WIRE WAS REPLACED AND RECONNECTED IAW AMM WITH NO FURTHER DEFECTS NOTED.

ATA 3421

Part: VERTICAL GYRO — UNSERVICEABLE · airframe 7,310 hrs

DURING CRUISE FLIGHT, APPROX 30 MINS INTO THE RETURN LEG, EXPERIENCED A SINGLE & SEVERE JERK & BUMP THROUGH THE ACFT. THE PILOT CONSIDERED THE BUMP SEVERE ENOUGH TO WARRANT CHANGING COURSE TOWARDS THE NEAREST SUITABLE LANDING AREA. AFTER 3 MINS OF FLIGHT THE PILOT FELT THE SAME JERK & BUMP AGAIN. PERFORMED A PRECAUTIONARY LANDING, APPROX 2 MINS LATER, THE PILOT FELT THE SAME SINGLE SEVERE BUMP ONCE MORE. THE PILOT SHUT THE ACFT DOWN WITH NO FURTHER INCIDENT. MECHANIC ON SITE DETERMINED THAT VERTICAL GYRO HAD A BURNT ELEC SMELL COMING FROM THE CASE, INTERNALLY. REPLACED VERTICAL GYRO AS REQUIRED & PERFORMED A SUCCESSFUL OPERATIONAL CHECK FLIGHT. NO FURTHER DEFECTS NOTED.