N390AL
Registered owner: BANK OF UTAH TRUSTEE, UT (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| ERICKSON HELICOPTERS, INC. (9EKA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING SCHEDULED INSPECTION, FOUND BROKEN STUD FROM FORWARD RIGHT HAND OUTBOARD COMBINING GEARBOX MOUNT.
FUSELAGE LOWER PANEL BELOW LEFT FUEL BLADDER HAS A 30 INCHES LONGITUDINAL CRACK.
DURING A POST FLIGHT INSPECTION, FUSELAGE LOWER PANEL, BELOW LT FUEL BLADDER FOUND TO HAVE A 30" LONGITUDINAL CRACK.
ENGINE 1 INDICATED EXCESSIVE TORQUE SPLIT WITH YAW MOTION OF THE ACFT. ENG 1 THROTTLE WAS MANUALLY BROUGHT DOWN TO 10% BELOW NR 2 & SAFELY RETURNED TO BASE.
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.
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.
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.
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)
REPAIR DUE TO THE STARTER WOULD NOT ENGAGE.
NR 2 ELEVATOR WILL NOT TEST AND ALSO KICKS OFF.
TAIL ROTOR GEARBOX MOUNT HOLE ELONGATED AND WORN AT CONTACT POINT.
MOUNT HOLE ON GEARBOX ELONGATED AND WORN AT CONTACT POINT.
DURING RUN-UP CHECKS. NR 1 ENGINE FIRE DETECTION SYSTEM WOULD NOT TEST.
TAIL ROTOR BEARING WORN.
NR 1 ENGINE PARTICLE SEPARATOR FAILED ON TAKEOFF. FOUND PARTICLE SEPARATOR BLOWER SHAFT SHEARED.
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.
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.
PHASE INSPECTION FOUND ANGLE CRACKED ON FORWARD END APPROXIMATELY 2 INCHES FROM END OF ANGLE. THE SUSPECT CAUSE WAS VIBRATION.
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.
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.