HELIFLITE SHARES LLC

Part: ACTUATOR — MALFUNCTIONED (COLLECTIVE SERVO)

INCREASED COLLECTIVE FORCES WERE REQUIRED TO CONTROL AIRCRAFT. AN INSPECTION OF THE ENTIRE FLIGHT CONTROL SYSTEM WAS PERFORMED WITH NO ANOMALIES. IT WASN`T UNTIL THE ENTIRE FLIGHT CONTROL SYSTEM WAS PERFORMED WITH NO ANOMALIES. IT WASN`T UNTIL THE COLLECTIVE SERVO ACTUATOR WAS REPLACED THAT THE DISCREPANCY CLEARED. THIS SERVO WAS INSTALLED ON 7/25/12 AS "MODIFIED" AFTER SDB 430-11-46, REV A HAD BEEN COMPLIED WITH. SERVIO ACTUATOR WAS CONVERTED FROM 222-382-001-107 TO 222-382-001-111FM DURING SAME VISIT TO THE REPAIR STATION. THIS PART ACCUMULATED 1063.0 HOURS SINCE INSTALLED ON THIS ACFT.

Part: ACTUATOR — MALFUNCTIONED (COLLECTIVE SERVO)

INCREASED COLLECTIVE FORCES WERE REQUIRED TO CONTROL AIRCRAFT. AN INSPECTION OF THE ENTIRE FLIGHT CONTROL SYS WAS PERFORMED WITH NO ANOMALIES. IT WASN`T UNTIL THE COLLECTIVE SERVO ACTUATOR WAS REPLACED THAT THE DISCREPANCY CLEARED. THIS SERVO WAS INSTALLED ON 7/25/12 AS "MODIFIED" AFTER MFG ASB 430-11-46, REV A HAD BEEN COMPLIED WITH AT REPAIR STATION. SERVO ACTUATOR WAS CONVERTED FROM 222-382-001-107 TO 222-382-001-111FM. DURING SAME VISIT TO THE REPAIR STATION. THIS PART ACCUMULATED 1063.0 HOUR SINCE INSTALLED ON THIS ACFT.

Part: FITTING — LOOSE (NR 1 ENGINE) · airframe 6,310 hrs · 16,664 cycles

ON OCTOBER 26, 2012 THE NR 1 ENGINE FUEL NOZZLE WAS REMOVED AND RESHIMMED FOR AN INTERMITTENT STARTING PROBLEM. THE MAINTENANCE ACTION WAS COMPLETED AND SIGNED OFF IN THE AIRCRAFT LOGBOOK, HOWEVER NO SUBSEQUENT CHECK RUN WAS ACCOMPLISHED ON THE ENGINE PRIOR TO RETURN TO SERVICE, AS REQUIRED IN THE ROLLS ROYCE M250-C40B OPERATION AND MAINTENANCE MANUAL. THE AIRCRAFT WAS LAUNCHED ON THE FOLLOWING DAY, OF WHICH THE AIRCRAFT FEW 2.7 FLIGHT HOURS AND 3 ENGINE STARTS (CYCLES). UPON LAST LANDING OF THE DAY, THE FLIGHT CREW NOTICED FUEL DRIPPING FROM THE NR 1 ENGINE DECK DRAIN. UPON FURTHER INVESTIGATION IT WAS DETERMINED THAT THE FUEL LINE FITTING LEADING TO THE FUEL NOZZLE WAS NOT TIGHT, DESPITE HAVING BEEN SAFTIED DURING THE PREVIOUS MAINTENANCE ACTION. THE FUEL LINE FITTING WAS TIGHTENED (1/4 TURN), THE ENGINE WAS LEAKED CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THIS ISSUE COULD HAVE BEEN ALLEVIATED IF THE ESTABLISHED COMPANY PROCEDURE FOR APPLYING THE RED OUT-OF-SERVICE COVER OVER THE CYCLIC CONTROL STICK HAD BEEN FOLLOWED AFTER THE INITIAL FUEL SYSTEM MAINTENANCE WAS PERFORMED.

Part: BLADE — CRACKED (MAIN ROTOR) · airframe 7,606 hrs · 17,125 cycles

DURING INDUCTION, INSPECTION INTO A ROTOR BLADE REPAIR FACILITY, MAIN ROTOR BLADE SPAR WAS FOUND CRACKED (INTERNAL ROOT END). CRACK ORIGINATES FROM LEADING EDGE, OB LOWER ATTACHMENT BOLT HOLE. PHENOLIC BLOCK WAS REMOVED AND DYE PENETRANT INSPECTION WAS PERFORMED TO CONFIRM PRESENCE OF CRACK.