N7YL

HISTORY OF FLIGHT

On October 7, 2005, at 2342 eastern daylight time, an Agusta 109E, N7YL, operated by CJ Systems Aviation Group Inc., was destroyed when it impacted trees and terrain in Smethport, Pennsylvania, while performing an instrument approach to Bradford Regional Airport (BFD), Bradford, Pennsylvania. The certificated commercial pilot was fatally injured. Night instrument meteorological conditions (IMC) prevailed, and an instrument flight rules (IFR) flight plan was filed for the flight that originated from Kane Community Hospital (PA91), Kane, Pennsylvania, at 2324. The positioning flight was conducted under 14 CFR Part 91.

In an interview, a mission flight nurse stated that he and another nurse were onboard the helicopter during a positioning flight from their base in Harborcreek, Pennsylvania, to Kane Community Hospital. Upon arrival at the hospital, he and the other nurse deplaned to prepare a patient for transport to Pittsburgh, Pennsylvania, while the helicopter departed for Bradford Airport to refuel.

Examination of radar and voice communication data provided by the Federal Aviation Administration (FAA) revealed that the helicopter departed Kane Hospital helipad and tracked the Copter GPS 246 Departure procedure course. The pilot contacted air traffic control (ATC), at 2324:47, stated that he had departed the hospital, and was "VFR to uh Bradford three thousand two hundred climbing to five."

Over the next 4 minutes, the pilot requested the instrument landing system (ILS) runway 32 approach to Bradford Regional Airport, and he and the controller discussed whether the helicopter would be vectored to the final approach course or if the full approach procedure would be flown.

The controller stated, "say your heading I've got you heading the wrong way for Bradford." The pilot replied that he was heading 246 degrees, which was prescribed in the procedure, but the controller questioned the response. The pilot reaffirmed his intention to fly to Bradford, and the controller assigned a 040-degree heading.

The pilot acknowledged the instructions; the helicopter then reversed direction, and assumed a northeasterly track. About 3 minutes later, the controller stated, "fly heading of zero eight five radar vectors runway three two I-L-S."

The pilot acknowledged the radio call, and the helicopter assumed an easterly track.

At 2339:01, the controller stated, "seven yankee lima fly heading of three four zero join the localizer report established please." At that time, the helicopter was at 5,000 feet, on an easterly track, about 1 mile west of the runway extended centerline, about 150 knots groundspeed. The pilot acknowledged the instructions.

The radar track depicted the helicopter on an easterly heading as it flew through the 322-degree final approach course, about 4 miles outside of the outer marker.

At 2340:03, the controller advised the pilot that the helicopter was "on the right side of the I-L-S," and the pilot acknowledged the call. At 2341:09, the controller asked if the pilot was established on the ILS. The pilot responded that he was "recapturing." The controller then asked if the pilot had said "affirmative," and the pilot replied "affirmative." At 0341:19, the controller transmitted, "Lifeguard seven yankee lima roger cleared I-L-S three two uh runway at Bradford uh maintain four thousand feet and uh report cancellation on this frequency..." The pilot read back the clearance at 0341:33. There were no further transmissions from the helicopter.

When the pilot replied "recapturing" the controller insisted the pilot respond "affirmative," which the pilot subsequently did.

At the time the controller advised that the helicopter was right of the localizer course, the radar track depicted the helicopter about midway through a left turn to about a 310-degree heading, at 5,000 feet, and about 1 mile east of the runway centerline.

The helicopter's track approached the localizer course centerline, and then turned sharply away from, and to the right of the inbound course. The radar target showed an approximate track of 100 degrees, when the target disappeared. During the 1 minute and 10 seconds following the pilot's acknowledgement of the 4,000-foot altitude assignment, the helicopter descended only 300 feet, slowed to approximately 65 knots groundspeed, and turned 140 degrees right of course.

The final three plots of the radar track showed a sharp left turn back towards the localizer course, and an approximate ground speed of 55 knots. The last radar plot was approximately over the crash site at 4,300 feet, about 1 mile east of the extended runway centerline, and 4 miles from the airport.

In an interview, a witness that lived approximately 1 mile from the crash site said that he did not see the helicopter, but heard it pass overhead. He said he was familiar with the sound, as he had lived close to the final approach course for runway 32 for many years.

The witness said the sound was louder than usual, and he felt the helicopter was closer to his home and lower than usual. The witness described the sound as smooth and continuous, with no change in aircraft noise. After the helicopter over flew his position, he heard the sound of an explosion.

On October 8, 2005, the FAA generated an alert notice at 0101, and a ground search for the helicopter began in the early morning hours of October 8, 2005. A search by air was not conducted due to weather. The helicopter wreckage was found on October 9, 2005, and was examined at the site on October 10, 2005.

The accident occurred during the hours of darkness approximately 40 degrees, 53 minutes north latitude, and 78 degrees, 06 minutes west longitude.

PERSONNEL INFORMATION

The pilot held a commercial pilot certificate with ratings for rotorcraft helicopter and instrument helicopter. The commercial certificate was issued February 10, 1979, and the instrument rating was added June 18, 1997. His most recent FAA second-class medical certificate was issued on October 19, 2004, and he reported 9,616 total hours of flight experience on that date.

The pilot's logbook was not recovered; however, some flight times were extracted from company records. In the 90 days prior to the accident, the pilot logged 56 hours, all of which was in the Augusta 109E. In this time period, he logged 25 hours of flight experience at night, 3 hours of simulated instrument experience, and 3 hours of actual instrument flight experience.

The company reported that the pilot had 110 total hours of instrument flight experience, and estimated that of this 70 hours were simulated instrument flight experience, and 40 hours were actual instrument flight experience. Later, the company reported that the pilot had accrued 100 hours of instrument flying experience, 10 hours of which was simulated.

AIRCRAFT INFORMATION

The helicopter was manufactured in 2001, and had accrued 1,905 total airframe hours. It was maintained under an Approved Aircraft Inspection Program (AAIP), and its most recent inspection was completed August 5, 2005.

The helicopter was equipped with an Integrated Flight Control System (IFCS). The system provided attitude automatic stabilization and automatic path control. Both stabilization and automatic path computation were actuated through the helipilot (autopilot) system and the flight director system.

A review of maintenance records revealed numerous entries related to autopilot malfunctions and failures. The malfunctions included erratic command bars on pilot and copilot displays, and uncommanded pitch and roll oscillations that occurred during preflight checks and also in flight. Over a 2-year span, 10 autopilot computers were changed on the accident helicopter due to their exposure to "high vibration levels."

A service bulletin (109EP-51) was released February 9, 2005, to address the vibration issues with the installation of shock-isolating mounts on the mounting trays for the autopilot computers. According to the site mechanic where the helicopter was based, he didn't recall having to change any computers once the service bulletin was applied.

METEOROLOGICAL INFORMATION

At 2337, the weather reported at Bradford Regional Airport included an overcast ceiling at 600 feet, with 2 1/2 miles of visibility in mist. The temperature was 50 degrees Fahrenheit, and the dew point was 48 degrees Fahrenheit.

WRECKAGE AND IMPACT INFORMATION

The helicopter impacted heavily wooded terrain about 2,000 feet elevation and all major components were accounted for at the scene. The initial impact point was in a treetop about 50 feet above the ground on level terrain. The wreckage path was about 180 feet long, and oriented about 100 degrees. The helicopter was fragmented, burned, and melted along the entire path. There were several pieces of angularly cut wood along the wreckage path, and several trees with fire damage and long angular slices along their trunks.

The wreckage path was documented at 1-foot increments called wreckage points (WP). At WP 33, a large tree, about 15 inches in diameter, was broken off about 25 feet above the ground. Sheets of composite material were embedded vertically into the trunk fracture.

The vertical fin was at WP 41. The tailboom was abeam the vertical fin, about 30 feet right of the wreckage path centerline. Structure that contained the number 1 hanger bearing was also at WP 41, 25 feet left of centerline. Both the left and the right antenna from the accident helicopter were destroyed by impact and postcrash fire.

The main wreckage, which consisted mostly of the main transmission with the mast and rotor head attached, was entangled at the base of three trees at WP 66. The cockpit and cabin area were consumed by fire, and all the flight and system instruments had been destroyed.

Because of impact and fire damage, control continuity could not be established. All flight controls, tubes, and bellcranks...