N604AR
Registered owner: CONSTRUCTION HELICOPTERS LLC, MI (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| CONSTRUCTION HELICOPTERS, LLC (JTAA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
TORQUE SENSOR ASSEMBLY [PN: 3101726-3, SN: P-8423, TSO: 3,059.5] HEXAGON PLAIN NUT [PN: 867349-1] BACKED OFF DURING FLIGHT.
DURING DESCENT, #2 ENGINE FLAMED OUT @ 7000 FOOT MSL, THROTTLES @ F.I. ENGINE NTS SURGING, EGT 428, RPM 38%, FEATHERED ENGINE. SINGLE ENGINE LDG UNEVENTFUL. CAUSE TBD
DURING DESCENT, ENGINE FLAMED OUT @ 7000 FT MSL. THROTTLES @ FLIGHT IDLE, ENGINE NTS SURGING, EGT 428, RPM DROPPED TO 38%, INITIATED FEATHER OF ENGINE. SINGLE ENGINE LANDING UNEVENTFUL. CAUSE TBD.
WHILE INVESTIGATING HORIZONTAL FITTINGS ON FUSELAGE SIDE DUE TO CRACKS IN FITTINGS, FOUND MATING FITTINGS ATTACHED TO HORIZONTAL STABILIZERS CRACKED AS WELL WHEN INSPECTED POST STABILIZER REMOVAL FROM EMPENNAGE. R/H STABILIZER AFT SPAR ATTACH FITTING P/N 212-31123-05.1 & L/H STABILIZER FWD SPAR ATTACH FITTING P/N 212-31122-03.1 FOUND TO BE CRACKED.
DURING A 1Y, 2Y, 4Y CPCP INSPECTION OF THE EMPENNAGE OF S/N 289 IT WAS FOUND 6 OUT OF 8 OF THE HORIZONTAL STABILIZER FITTINGS CRACKED. THE CRACKS WERE FOUND IN THE RADIUS OF ONE OF THE FITTINGS & FROM FASTNER TO FASTNER ON OTHERS.
DURING A 1Y, 2Y, 4Y CPCP INSPECTION OF THE EMPENNAGE OF S/N 289 IT WAS FOUND 6 OUT OF 8 OF THE HORIZONTAL STABILIZER FITTINGS CRACKED. THE CRACKS WERE FOUND IN THE RADIUS OF ONE OF THE FITTINGS & FROM FASTNER TO FASTNER ON OTHERS.
DURING A 1Y, 2Y, 4Y CPCP INSPECTION OF THE EMPENNAGE OF S/N 289 IT WAS FOUND 6 OUT OF 8 OF THE HORIZONTAL STABILIZER FITTINGS CRACKED. THE CRACKS WERE FOUND IN THE RADIUS OF ONE OF THE FITTINGS & FROM FASTNER TO FASTNER ON OTHERS.
DURING CRUISE FLIGHT, 50 MILES FROM HK01, #1 ENGINE FAILED. CREW PERFORMED APPROPRIATE EMERGENCY PROCEDURE, ANALYZED PERFORMANCE OF AIRCRAFT WITH ONE ENGINE AND ENTERED DESCENT, APPROACH, AND LANDING PHASES FOR SINGLE ENGINE LANDING. AIR RESTART WAS ATTEMPTED WITH NO SUCCESS. AIRCRAFT WAS LANDED ON ONE ENGINE, NO DAMAGE OR INJURIES. INVESTIGATION REVEALED THE ACCESSORY GEAR BOX SUFFERED INTERNAL FAILURE AND FUEL PUMP / FUEL CONTROL INPUT DRIVE WAS INOPERATIVE. NO OTHER DAMAGE OR MECHANICAL FAILURES WERE NOTED. ENGINE WILL BE SENT TO OVERHAUL FACILITY.
AT CRUISE FLIGHT DURING NIGHT VISION GOGGLE TRAINING THERE WAS AN ORDER OF SMOKE IN THE FLIGHT DECK. THE COPILOTS SIDE OF THE OVERHEAD PANEL WAS HOT TO THE TOUCH IN THE VICINITY OF THE LIGHT SWITCHES & RHEOSTATS. FLIGHT DECK LIGHTING WAS EXTINGUISHED & THE OVERHEAD PANEL DECREASED IN TEMPERATURE. THE DECISION WAS MADE TO RETURN TO AIRPORT & A NORMAL LANDING WAS ACCOMPLISHED WITHOUT FURTHER INCIDENT. REPAIRED POST LIGHT ON MONITOR PANEL, COPILOT SIDE IAW DWG C212-289-012.