N390AL

Part: ELBOW — WORN (HYDRAULIC SYS) · airframe 11,247 hrs

OIL COOLER CAUTION PANEL LIGHT CAME ON DURING FLIGHT. ENGAGED SECONDARY OIL COOLER SYS & RETURNED TO BASE IAW EMER PROCEDURES IN ROTOR FLIGHT CRAFT MANUAL.

Part: SKIN — CRACKED (RT ELEVATOR) · airframe 12,210 hrs · 23,553 cycles

FOUND CRACK IN SKIN OF RT ELEVATOR. CRACK IS LOCATED AT THE AFT INBD BOTTOM SIDE OF THE ELEVATOR, JUST FWD OF THE RIVETS ATTACHING THE TAB.

Part: FITTING — CRACKED (TAILBOOM) · airframe 11,967 hrs · 22,848 cycles

CRACK ON THE VERTICAL SPAR OF THE TAIL IT IS LOCATED IN THE COLD WORK AREA JUST ABOVE THE OUTPUT QUILL OF THE 42 DEG GEARBOX. LOCATED ON THE LEFT SIDE AT BS 569.689, WL 95 ON FIN STATION 32. CRACK IS .040 DEEP AND 1.1 INCHES LONG.

Part: LINE — LEAKING (NR 1 HYD SYS)

ENROUTE, A HOWLING NOISE STARTED AND BECAME LOUDER, THE PILOT NOTICED NR 1 HYD PRESSURE FLUCTUATED BETWEEN 200-300 PSI. THE PILOT TURNED OFF NR 1 HYD NOISE WENT AWAY. UPON LANDING THE MECHANIC FOUND NR 1 PRESSURE LINE TO THE COLLECTIVE SERVO IS LEAKING. HE TIGHTENED THE LINE AND REPLACED THE HYD PUMP ASSY AND THE AC WAS RETURNED TO SERVICE UPON COMPLETION OF FUNCTION CHECKS IAW MM. (K)

Part: STARTER — BROKEN (ENGINE) · airframe 8,432 hrs

REPAIR DUE TO THE STARTER WOULD NOT ENGAGE.

Part: AMPLIFIER — WILL NOT TEST · airframe 8,418 hrs

NR 2 ELEVATOR WILL NOT TEST AND ALSO KICKS OFF.

Part: GEARBOX — WORN (TAIL ROTOR) · airframe 8,142 hrs

TAIL ROTOR GEARBOX MOUNT HOLE ELONGATED AND WORN AT CONTACT POINT.

Part: GEARBOX — WORN (TAIL ROTOR) · airframe 8,142 hrs

MOUNT HOLE ON GEARBOX ELONGATED AND WORN AT CONTACT POINT.

Part: SENSING ELEMENT — INOPERATIVE (NR 1 ENGINE)

DURING RUN-UP CHECKS. NR 1 ENGINE FIRE DETECTION SYSTEM WOULD NOT TEST.

Part: BEARING — WORN (TAIL ROTOR) · airframe 7,911 hrs

TAIL ROTOR BEARING WORN.

Part: BLOWER — FAILED (NR 1 ENGINE)

NR 1 ENGINE PARTICLE SEPARATOR FAILED ON TAKEOFF. FOUND PARTICLE SEPARATOR BLOWER SHAFT SHEARED.

Part: LONGERON — CRACKED (LT T/B ATTACH)

DAILY INSPECTION FOUND CRACK AT UPPER LEFT TAIL BOOM ATTACH POINT, AIRFRAME SIDE. THIS LONGERON BASE IS ONE OF ONLY FOUR ATTACH POINTS. THE UPPER LEFT CARRIES HIGHEST LOADS.

Part: LONGERON — CRACKED (UPPER TAILBOOM)

UPPER TAILBOOM ATTACHMENT LONGERON CRACKED THROUGH ATTACHMENT FITTING. CRACK WAS DISCOVERED DURING THE DAILY VISUAL INSPECTION. PART WAS TAGGED AND SHIPPED TO BELL HELICOPTER IN FORT WORTH, TEXAS.

Part: SUPPORT ANGLE — CRACKED (TAILBOOM AFT LT)

PHASE INSPECTION FOUND ANGLE CRACKED ON FORWARD END APPROXIMATELY 2 INCHES FROM END OF ANGLE. THE SUSPECT CAUSE WAS VIBRATION.

Part: EROSION SHIELD — SEPARATED (M/R BLADE)

IN CRUISE FLIGHT OVER THE GULF OF MEXICO, THE AIRCRAFT DEVELOPED A SEVERE VIBRATION. THE PILOT MADE AN IMMEDIATE PRECAUTIONARY LANDING TO AN OFFSHORE DRILLING PLATFORM. EXAMINATION OF THE AIRCRAFT REVEALED THE LOWER EROSION SHIELD ON A MAIN ROTOR BLADE HAD SEPARATED FROM THE BLADE.

Part: BEARING — FRACTURED (OUTER RACE)

WHILE HANGER ASSY WAS REMOVED TO LUBRICATE FLEX-COUPLINGS. HANGER BEARING FELT ROUGH WHEN ROTATED BY HAND WITH HANGER ASSY REMOVED. OUTER RACE OF BEARING WAS FOUND FRACTURED WHEN REMOVED FROM THE HOUSING. CAUSE UNKNOWN.