N18VV

Part: POTENTIOMETER — MALFUNCTIONED (MAP LIGHT) · airframe 27,353 hrs · 7,682 cycles

THE PILOT REPORTED AN ELECTRICAL SMELL IN THE COCKPIT DURING FLIGHT. MAINTENANCE INSPECTED AND FOUND THE POTENTIOMETER FOR THE PILOT OVERHEAD MAP LIGHT MALFUNCTIONING. THE MAP AND DIMMER ASSEMBLY WERE REMOVED AND REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: ENGINE — DAMAGED (RIGHT) · airframe 26,055 hrs · 6,591 cycles

PILOT REPORTED A SIGNIFICANT DROP IN OIL PRESSURE DURING FLIGHT, AND AFTER LANDING, OIL LEAKING FROM RIGHT ENGINE. MAINTENANCE INSPECTED AND FOUND METAL PARTICLES IN THE OIL FILTER AND PROPELLER GOVERNOR SCREEN AND IS CHANGING THE RIGHT ENGINE, PROPELLER, VAPC, TURBOCHARGER AND WASTEGATE.

Part: RESISTOR — BURNED (DIMMER ASSY) · airframe 24,419 hrs

PILOT REPORTED WHEN PANEL LIGHTING AND OVERHEAD LIGHTING IS ON, THERE IS AN ELECTRICAL BURNING SMELL. MAINTENANCE INSPECTED AND FOUND THE OVERHEAD FLOOD LIGHT DIMMER ASSEMBLY RIGHT RHEOSTAT RESISTER BURNT. THE ASSEMBLY WAS REPLACED WITH NO FURTHER DEFECTS.

Part: ENGINE — FAILED (LEFT) · airframe 24,184 hrs

PILOT REPORTED LEFT ENGINE STARTED VIBRATING IN FLIGHT, WHEN MANIFOLD PRESSURE WENT TO AMBIENT. THE ENGINE WAS SHUT DOWN IN FLIGHT AND WOULD NOT RESTART. UPON INITIAL INSPECTION THE CRANK CASE WAS FOUND TO BE PENETRATED AT THE REAR OF THE ENGINE IN THE VICINITY OF THE NR 1 CYLINDER. THE ENGINE IS BEING REPLACED, FURTHER DETAILS WILL BE PROVIDED UPON ENGINE TEAR-DOWN INVESTIGATION.

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 21,900 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 21,900 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 21,900 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 21,900 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 21,803 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 21,803 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: DOOR — OPEN (CABIN) · airframe 20,614 hrs · 1,413 cycles

PILOT REPORTED UPPER CLAM, PAX DOOR, OPENED IN FLIGHT. REMOVED UPPER CABIN DOOR TRIM PANEL, INSPECTED LATCH SPRINGS INTERNAL BEARING FOR PLAY & ALL OTHER INTERNAL COMPONENTS, NO DEFECTS NOTED. INSPECTED LATCH HOUSING FOR WEAR & DOOR WARNING SYS, NO DEFECTS NOTED. INSTALLED UPPER CABIN DOOR TRIM & INSPECTED DOOR FOR PROPER CLOSING, FOUND UPPER CABIN DOOR TO BE PROPERLY SECURED.

Part: ACTUATOR — FAILED (RT MLG) · airframe 19,241 hrs

PILOT SELECTED GEAR DOWN DURING FUNCTIONAL CHECK FLIGHT, GEAR INDICATED TWO GREEN FOR LT MAIN & NLG, RED UNSAFE FOR RT MLG. PILOT CYCLED LG SEVERAL TIMES, UNSAFE CONDITION REMAINED. PERFORMED EMERGENCY EXTENSION CHECKLIST & PULLED TEE HANDLE TO BLOW MLG DOWN. RT MLG DID NOT EXTEND, ACFT LANDED WITH LT MAIN & NLG EXTENDED.

Part: CHANNEL — CRACKED (LT ENGINE)

DURING COMPLIANCE WITH AD 2005-12-13 BY INSTALLATION OF SPAR MOD KIT SK402-47B IT WAS DISCOVERED THAT THE LT NACELLE OB ENGINE SUPPORT BEAM CHANNEL PN 56541111 HAD A 1.75 INCH CRACK RUNNING LONGITUDINALLY ON THE IB RADIUS. THE AREA OF THE CRACK IS IN A LOCATION WHERE THAT PORTION OF THE CHANNEL IS TO BE REMOVED AND NEW CHANNEL INSTALLED IAW SK402-47B. (K)