Enstrom F-28A N9235

Summary

On 22 November 2004 at about 00:11 local time, a Enstrom F-28A registered N9235 was involved in an accident near Smyrna, Tennessee, United States. One person was 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

22 November 2004 at 00:11

Classification

Accident

Location

Smyrna, Tennessee, United States

Nearest airport

Smyrna Airport (KMQY)

Coordinates

36.0089, -86.5200

Aircraft

Enstrom F-28A

Registration

N9235

Category

Helicopter

Engines

1

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Personal

Phase of flight

Not recorded

Route

Lexington → Smyrna

Aircraft damage

Substantial

Weather

VMC

Light

Night

NTSB number

ATL05CA028

Nobody was injured.

The loss of engine power for undetermined reasons, and the pilot's improper flare during forced landing, which resulted in an inflight collision into an open field.

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

Read the full NTSB narrative

The pilot stated he reduced the collective from 23 inches of manifold pressure to 21 inches of manifold pressure to initiate a descent for landing, and it "felt like the engine was shuddering." He stated he increased the manifold pressure to 23 inches, and the engine "seemed to smooth out." He stated he entered a left base, then turned final and reduced the manifold pressure. On final approach, the pilot slowed the helicopter to approximately 10 miles per hour, and when he added more collective, he saw the "rpm drop to the bottom of the green." He stated he "dropped collective and added throttle." He stated the helicopter would not maintain altitude, and he attempted a run-on landing in the grass; the left skid contacted the ground and collapsed, and the helicopter rolled over onto its left side. Examination revealed the forward and aft left skid struts were bent inboard approximately 135 degrees. Two main rotor blades were bent downward and were delaminated near the root and on the trailing edge of the blades. The third main rotor blade was bent upward near the tip, and trailing edge and upper skin deformation was observed. Continuity for the tail rotor, cyclic, collective, over-running clutch, throttle, and mixture controls was established. Examination of the drive belt revealed a shaved area in the vicinity of the clutch assembly, and the over-running clutch operated. The fan shroud displayed circumferential scoring. An engine start was attempted by utilizing the cockpit engine controls. The engine started, then idled smoothly. Higher rpm settings were not attempted.

Quoted verbatim from the NTSB record.