Eastway Aviation, LLC.

Part: ACTUATOR — FAULTED (ZONE 300) · airframe 3,426 hrs · 2,201 cycles

UPON DEPARTURE FROM KHPN , THE PRIMARY STAB TRIM FAILED . CONTROL PRESSURE BECAME EXCESSIVE AS THE AIRCRAFT PITCHED UP. THE CREW SWITCHED TO SECONDARY TRIM , THE SECONDARY TRIM ALSO FAILED. THE PIC DECLARED AN EMERGENCY AND THE EMERGENCY /ABNORMAL CHECKLIST WAS UTILIZED. UNTIL AIRSPEED WAS REDUCED, IT TOOK BOTH CREW MEMBERS PUSHING ON THE CONTROL YOKE TO REMAIN IN CONTROL. THE AIRCRAFT LANDED AT KSWF. TEXTRON AVIATION PERFORMED REPLACEMENT OF THE STAB TRIM ACTUATOR AND SECONDARY TRIM MOTOR. A TEARDOWN REPORT OF THE STAB TRIM LINEAR ACTUATOR AND SECONDARY TRIM MOTOR IS IN PROCESS AT THIS TIME. IT WAS NOTED THAT THE STAB TRIM ACTUATOR TORQUE CHECK FAILED. THE TORQUE WAS FOUND ABOVE THE ALLOWABLE LIMIT. ALSO, THE AIRCRAFT WAS PAINTED 12 DAYS PRIOR. TEXTRON AVIATION REPORTED THAT EXCESSIVE PAINT ON THE INTERIOR OF THE STAB WIPER FAIRINGS WAS CAUSING UNDUE DRAG TO THE STAB MOVEMENT WHICH MAY OR MAY NOT HAVE BEEN A CONTRIBUTING FACTOR.

Part: HOSE — RUPTURED (HYD SYSTEM) · airframe 1,242 hrs · 883 cycles

SHORTLY AFTER TAKEOFF, THE CREW SELECTED LANDING GEAR UP, RECEIVED EICAS MESSAGES HYD. FLUID LOW AND HYD PRESSURE LOW. UNABLE TO RETRACT LANDING GEAR. PERFORMED AN EMERGENCY LANDING GEAR EXTENSION AND ELECTED TO DIVERT. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. ON INVESTIGATION, FOUND THE NOSE WHEEL CENTERING HYD HOSE RUPTURED BETWEEN THE 45 DEGREE FITTING LOCATED AT TOP OF NLG WHEEL WELL. RUPTURE OCCURRED BETWEEN SWAGED END OF HOSE FITTING AND HOSE DATA TAG. IT APPEARS THAT THE STAINLESS STEEL HOSE PART ID TAG LOCATION CLOSE TO THE SWAGED FITTING CAUSED THE HOSE TO BEND IN A REDUCED LENGTH DURING LANDING GEAR RETRACTION, CAUSING UNDUE STRAIN AND FRETTING ON THE HOSE AT THE BASE OF THE SWAGED SLEEVE.

Part: TUBE — BROKEN (FCU)

WHILE APPLYING POWER FOR TAKEOFF, THE LEFT ENGINE WOULD NOT RESPOND. INSPECTED AND FOUND THE PY LINE CRACKED AT THE FUEL CONTROL UNIT. (X)

Part: PUMP HOUSING — ERODED (RT ENGINE SCAV)

OIL WAS FOUND ON COWL. INVESTIGATION FOUND THE AFT EXTERNAL SCAVENGE PUMP HOUSING WAS LEAKING OIL. PUMP WAS DISASSEMBLED AND FOUND CAVITATION EROSION WHICH CAUSED A PIN HOLE THROUGH THE HOUSING.

Part: VALVE — STUCK OPEN (RT FUEL VENT)

CREW REPORTED IN-FLIGHT, FUEL STREAMING FROM RIGHT WING TIP. FOUND BOTH RIGHT WING FUEL VENT AIR INLET CHECK VALVES STUCK OPEN. REPLACED CHECK VALVES. NOTE: FUEL TANKS WERE FULL.

Part: VALVE — STUCK OPEN (RT FUEL VENT)

CREW REPORTED IN-FLIGHT, FUEL STREAMING FROM RIGHT WING TIP. FOUND BOTH RIGHT WING FUEL VENT AIR INLET CHECK VALVES STUCK OPEN. REPLACED CHECK VALVES. NOTE: FUEL TANKS WERE FULL.

Part: TORQUE LINK — FAILED (LT MLG)

LEFT MLG UPPER TORQUE LINK FAILED AT THE PIVOT POINT WITH THE LOWER TORQUE LINK. AN EMERGENCY LANDING WAS EXECUTED. AT TOUCH-DOWN, THE LEFT LOWER STRUT, WHEEL AND TIRE ASSY DEPARTED AIRCRAFT DAMAGING THE UPPER STRUT HOUSING, INBOARD FLAP, AND THE LEFT SIDE OF THE FUSELAGE AT STA 340.0. APPEARS THE TORQUE LINK FAILURE WAS AT THE GREASE FITTING HOLE. PART TOTAL TIME: 6,413 HOURS. PART TOTAL CYCLES, 7,300. TIME SINCE LAST 7,500 CYCLE/60 MONTH INSPECTION, 2,385 HOURS. CYCLES SINCE LAST 7,500 CYCLE/60 MONTH INSPECTION, 3,273. MONTHS SINCE LAST 7,500 CYCLE/60 MONTH INSPECTION, 50.