Eurocopter AS 350 BA N141MK

Summary

On 5 January 2009 at about 20:45 local time, a Eurocopter AS 350 BA registered N141MK, operated by Schuman Aviation Company Ltd, was involved in an accident near Honolulu, Hawaii, United States. 2 people were on board and nobody was injured. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

5 January 2009 at 20:45

Classification

Accident

Location

Honolulu, Hawaii, United States

Coordinates

21.3275, -157.7533

Aircraft

Eurocopter AS 350 BA

Registration

N141MK

Category

Helicopter

Engines

1

Operator

Schuman Aviation Company Ltd

Operating rule

Part 135: Air Taxi & Commuter

Phase of flight

Not recorded

Route

Honolulu → Honolulu

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

WPR09FA072

Nobody was injured.

The partial loss of engine power during landing for an undetermined reason.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

The purpose of the flight was to transport a worker to an antenna located on a ridge top at an elevation of about 2,400 feet. The pilot reported that the flight to the location was uneventful and that he completed his prelanding checklist and noted nothing abnormal. Just prior to landing, there was a loss of engine power. According to the pilot, “the engine felt and sounded like it was winding down and rotor RPM was starting to bleed off.” At this point the helicopter was less than 10 feet from the landing site and was not holding altitude. The pilot maneuvered the helicopter so that it touched down and rolled over onto its right side, which prevented the helicopter from falling down the steep slope of the ridge. After the helicopter came to rest, the pilot shut down the engine. Examination of the helicopter revealed no discrepancies with the fuel system. Engine continuity was established. A pneumatic leak check was performed and leaks were identified at the temperature compensator and at the PX acceleration bellows. A test cell run of the engine was completed without tightening any of the pneumatic fittings. During the test cell run, the engine achieved maximum continuous, takeoff, and thermodynamic shaft horsepower. The engine did not surge during transient deceleration and acceleration runs, and was responsive to commanded throttle inputs. No preexisting condition was identified on the engine that would have interfered with normal operation or explain the reported loss of engine power.

Quoted verbatim from the NTSB record.