Hughes 269A N62269

Summary

On 1 June 2005 at about 15:00 local time, a Hughes 269A registered N62269 was involved in an accident near Sherman, Texas, United States. 2 people were on board and one had minor injuries. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

1 June 2005 at 15:00

Classification

Accident

Location

Sherman, Texas, United States

Coordinates

33.7083, -96.6700

Aircraft

Hughes 269A

Registration

N62269

Category

Helicopter

Engines

1

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Instructional

Phase of flight

Not recorded

Route

Sherman → Sherman

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

DFW05CA144

1 person had minor injuries.

The applicant's failure to maintain directional control of the helicopter during a simulated power failure from a hover and the FAA inspector's delayed remedial action resulted in a dynamic rollover.

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

Read the full NTSB narrative

A pilot applicant was demonstrating a simulated power failure from a two-foot hover to an FAA inspector when he lost control of the helicopter. The helicopter drifted aft and to the left before it impacted the ground and rolled on its left side. The FAA inspector's attempts to recover the helicopter were unsuccessful. According to the FAA Rotorcraft Flying Handbook, common errors when executing a power failure in a hover are; failing to use sufficient proper antitorque pedal when power is reduced, failing to stop all sideward and backward movement prior to touchdown, failing to apply up-collective pitch properly, resulting in a hard touchdown, failing to touch down at a level attitude, and not rolling the throttle completely to idle. In addition, "A helicopter is susceptible to a lateral rolling tendency, called dynamic rollover, when lifting off of the surface. For dynamic rollover to occur, some factor has to first cause the helicopter to roll or pivot around a skid, or landing gear wheel, until its critical rollover angle is reached. Then, beyond this point, main rotor thrust continues the roll and recovery is impossible. If the critical angle is exceeded, the helicopter rolls on its side regardless of the cyclic corrections made."

Quoted verbatim from the NTSB record.