Robinson R44 N25VH

Summary

On 19 July 2009 at about 12:40 local time, a Robinson R44 registered N25VH, operated by Advanced Helicopter Concepts, was involved in an accident near Silver Spring, Pennsylvania, 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

19 July 2009 at 12:40

Classification

Accident

Location

Silver Spring, Pennsylvania, United States

Nearest airport

Lancaster (LNS)

Coordinates

40.0719, -76.4319

Aircraft

Robinson R44

Registration

N25VH

Category

Helicopter

Engines

1

Operator

Advanced Helicopter Concepts

Operating rule

Part 91: General Aviation

Purpose of flight

Instructional

Phase of flight

Not recorded

Route

Frederick → Lancaster

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

ERA09LA410

Nobody was injured.

The student pilot's inability to fully control the helicopter, during cruise and the resultant off-field hard landing.

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

Read the full NTSB narrative

The student helicopter pilot was at the end of the cruise portion of a solo cross-country flight. When she was about to begin her descent to the destination airport, she noticed that the vertical speed indicator was indicating a descent of approximately 1,000 feet per minute and that the airspeed had increased about 10 knots. The pilot "raised the collective" control in an effort to reduce or stop the descent, but the helicopter did not respond as she expected and the descent continued. She then determined that she would not be able to reach the airport, and selected a field suitable for a landing. The helicopter landed hard in the field, and sustained substantial damage to the skids and portions of the engine mount and fuselage. On-scene examination did not reveal any preimpact failures or anomalies and postaccident testing, including runs at the engine manufacturer's factory, indicated that the engine performed normally and was capable of developing its rated power. The helicopter was equipped with hydraulically boosted main rotor flight controls which were to be used for all phases of flight. The pilot's control for activating or deactivating the hydraulic system was a 1/4 inch unguarded toggle switch located on the pilot’s cyclic control stick. The accident helicopter was not equipped with any visual or audio annunciations to alert the pilot that the hydraulic system had either failed or was selected off in flight, and no such option was available from the manufacturer. According to the helicopter manufacturer's pilot operating handbook, "Hydraulic system failure is indicated by heavy or stiff cyclic and collective controls," and that in the event that the hydraulic system failed or was turned off, "control will be normal except for the increase in stick forces." Although some control symptoms experienced by the pilot were consistent with an inoperative hydraulic system, some were not, and no physical evidence of an inoperative hydraulic system was noted.

Quoted verbatim from the NTSB record.