N214EB
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
MGB REMOVED FOR OIL LEAKING FROM CRACK IN RING GEAR CASE. UPON DISASSEMBLY AT REPAIR STATION DISCOVERED A SECTION OF 13 SPLINE TEETH ON THE UPPER RING FRACTURED. 7 TEETH WERE COMPLETELY SEPARATED FROM THE CASE BUT HELD IN PLACE BY THE INNER RING GEAR ASSY. THERE WERE MULTIPLE CRACKS ORIGINATING FROM THE ROOT AREA OF THE FRACTURED SPLINES IN ADDITION TO THE CRACK THAT BREACHED THE OUTSIDE OF THE CASE AND LEAKED OIL.
TWO MAIN ROTOR TRANSMISSION MAST STUDS FOUND SHEARED OFF DURING 25 HOUR INSPECTION.
PILOT REPORTED MOMENTARY TAIL ROTOR GEAR BOX CHIP LIGHT ON MASTER CAUTION PANEL.
NUMBER 1 ENG FUEL FILTER MASTER CAUTION LIGHT CAME ON, INDICATING FUEL FLOW RESTRICTION.
DURING CRUISE FLIGHT IN A SHALLOW RIGHT HAND TURN, NR 2 ENG EXPERIENCED HIGH SIDE FAILURE IMMEDIATELY, FOLLOWED BY UNCOMMANDED SHUTDOWN. ACFT RECOVERED 26 MILES BACK TO BASE IN SINGLE ENG CONFIGURATION.
DURING PREFLIGHT OIL WAS NOTICED ON THE UPPER TRANSMISSION CASE. UPON FURTHER INVESTIGATION, PAINT WAS BUBBLED ON RING GEAR CASE. CLEANED PAINT & DYE PENETRANT WAS USED REVEALING A SUSPECTED CRACK. ACFT WAS RUN AT 100% NR & OIL WAS NOTICED COMING FROM A CRACK IN THE TRANSMISSION RING GEAR CASE.
TAIL BOOM, EMPENNAGE METALLIC SKIN, HONEYCOMB STRUCTURE ON RT SIDE JUST AFT OF THE FWD VOR ANTENNA MOUNT WL 74, BS 294 HAS DISBONDED. INSPECTION WAS PERFORMED IAW BHT ALL SRM 2-13. TAIL BOOM IS BEING REPLACED WITH REPAIRED SERVICE TAIL BOOM. DAMAGED TAIL BOOM IS BEING SENT TO REPAIR FACILITY.
ON APPROACH, CREW NOTICED LOW PRESS ON NR 2 HYD SYS & THE MASTER CAUTION LIGHT, CONSULTED THE EMER CHECKLIST & SHUTOFF NR 2 HYD SYS. LANDED THE ACFT AT ANOTHER LOCATION.
AFTER A ROUTINE MISSION AN ACCESS PANEL LOCATED ON THE AFT PYLON FAIRING ON THE RT SIDE, WAS FOUND NOT INSTALLED ON THE ACFT. THE PANEL IS SECURED AT THE TOP BY A HINGE TO THE AFT PYLON FAIRING. THE HINGE CONSISTS OF 8 SECTIONS ATTACHED TO THE FAIRING AND HAS A WIRE THROUGH EACH SECTION AS WELL AS THE SECTIONS OF THE PANEL. THE FIRST 5 SECTIONS FROM L/E OF THE DOOR FAILED. THE LAST 3 SECTIONS APPEAR TO BE INTACT. THE WIRE HINGE IS NOT INSTALLED DURING POST FLIGHT. ADDITIONAL DAMAGE WAS NOTED AT THE AFT END OF THE AFT PYLON FAIRING WHERE IT ATTACHES TO THE CENTER BEAM CENTER PANEL. THE METAL AROUND THE ATTACHING BOLTS FAILED. IT IS UNDETERMINED IF THIS FAILURE IS A RESULT OF THE AIR STREAM ENTERING THROUGH THE ACCESS NORMALLY COVERED BY THE ACCESS PANEL. THERE IS NO APPARENT STRUCTURAL DAMAGE, DENTS OR PAINT SCRATCH TO THE PYLON OR TAIL ROTOR ASSY.
INFLIGHT CREW NOTED NR 1 HYD SYS FAIL LIGHT ILLUMINATED & PROCEEDED TO SHUT DOWN NR 1 SYS. EXECUTED UNEVENTFUL LANDING. VISUALLY FOUND NR 1 HYD SYS PRESSURE LINE PN 70-060T000Y4B4 TO LT CYCLIC SERVO RUPTURED.
WHILE CONDUCTING A "POST FLIGHT" INSPECTION, MECHANICS NOTICED THAT ONE OF THE MAIN ROTOR BLADES WAS MISSING A TRIM TAB.
WHILE PERFORMING AN URELATED MX WALK-AROUND INSPECTION, NOTED A CRACK ON THE UPPER LT MAIN FUSELAGE TO TAILBOOM ATTACHMENT FITTING. THIS IS A KNOWN ISSUE.
THE TRANSMISSION WAS LIFTED TO FACILITATE CHANGING THE LT TRANSMISSION STOP FITTING. IT WAS NOTICED THAT THE LT NODAL BEAM WAS FREE TO ROTATE ON THE TRANSMISSION SPINDLE. IT WAS DISCOVERED THAT IT WAS NOT THE ELASTOMERIC, BUT THAT THE SPINDLE ASSY HAD CRACKED RADIALLY ALLOWING THE NODAL TO SWING. THERE WAS CORROSION INSIDE THE THREADS AT THE POINT WHERE IT CRACKED. IT WAS NOT DETERMINED IF CORROSION WAS PRESENT PRIOR TO THE FINDING. THERE WAS NO PRESENCE OF CRACKING ON THE RT SPINDLE HOWEVER, CORROSION WAS FOUND ON THE THREADS AT THE SAME LOCATION AS THE FAILURE ON THE LT . THE STRUCTURAL ANALYSIS OF THE PART IS PENDING.