Agusta A109C N109MX

Summary

On 29 January 2003 at about 02:53 local time, a Agusta A109C registered N109MX, operated by Air Angels, Inc., was involved in an accident near West Chicago, Illinois, United States. One person was on board and one died. The aircraft was destroyed. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

29 January 2003 at 02:53

Classification

Accident

Location

West Chicago, Illinois, United States

Nearest airport

DuPage Airport (DPA)

Coordinates

41.8722, -88.2544

Aircraft

Agusta A109C

Registration

N109MX

Category

Helicopter

Engines

2

Operator

Air Angels, Inc.

Operating rule

Part 91: General Aviation

Purpose of flight

Positioning

Phase of flight

Not recorded

Route

West Chicago → West Chicago

Aircraft damage

Destroyed

Weather

VMC

Light

Night

NTSB number

CHI03FA060

1 person died.

The pilot's failure to maintain control of the helicopter while maneuvering, resulting in the excessive descent rate and impact with terrain. Factors to the accident included the dark night, low ceiling and reduced visibility at the time of the accident.

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

Read the full NTSB narrative

The helicopter was destroyed when it impacted terrain about 2.0 nautical miles (nm) south of the departure airport during a positioning flight. Night marginal visual flight rules (MVFR) conditions prevailed with reduced visibilities and low clouds. After refueling the helicopter, the pilot requested to depart to the south in order to "status check a couple pieces of equipment" and then return to the heliplex located on the southeast perimeter of the airport. Aircraft radar track data showed the helicopter traveling south about 1.7 nm before turning to the south-southwest. While traveling to the south, the helicopter climbed to about 500 feet above ground level (agl) while accelerating from 95 knots to about 125 knots airspeed. The helicopter then entered an 18 second period where the climb rate increased from 500 feet/min to 2,000 feet/min and the helicopter reached a maximum altitude of about 1,000 feet agl. The helicopter decelerated from 125 to 100 knots airspeed during this climb. Based on the last two radar returns, the helicopter descended about 200 feet which resulted in a 1,350 feet/min descent rate. Further examination of the data showed the helicopter decelerating from 85 to 35 knots airspeed during the descent. The last radar return was at 800 feet agl and 425 feet east of the initial ground impact. The pilot was appropriately certificated to fly the helicopter and was employed as a pilot for an on-demand air ambulance service. The pilot was working his final shift as an employee with the company when the accident occurred. All primary airframe structural components, flight control systems, rotor systems, transmissions, and powerplant components were recovered at the accident site. Inspection of the recovered components did not exhibit any evidence of pre-impact malfunction. A review of the daily usage logs for the helicopter failed to reveal any unresolved maintenance discrepancies. The pilot who flew the helicopter prior to the accident flight did not report any malfunctions with the helicopter. A fuel sample was obtained from the source used to service the helicopter prior to the accident flight. The fuel sample was tested and met or exceeded the specifications for Aviation Turbine Fuel (Jet-A).

Quoted verbatim from the NTSB record.