NTSB Factual Report

History of the Flight

On October 20, 2004, about 0043 central daylight time, a Eurocopter Deutschland BO-105 CBS5, N916SH, call sign Airheart One, registered to and operated by Metro Aviation, Inc., as a Title 14 CFR Part 91 emergency medical services (EMS) positioning flight, from Santa Rosa Beach, Florida, to DeFuniak Springs, Florida, crashed in Choctawhatchee Bay, near Santa Rosa Beach. Instrument meteorological conditions prevailed in the accident area at the time and a company visual flight rules flight plan was filed. The helicopter was destroyed and the commercial-rated pilot, paramedic, and flight nurse were fatally injured. The flight originated from Santa Rosa Beach at 0041.

Personnel from the Walton County, Florida, Emergency Operations Center, stated that at 0021 they received a call from Healthmark Hospital in DeFuniak Springs, requesting the Airheart One helicopter to transport a patient to West Florida Hospital in Pensacola, Florida. The dispatcher then contacted the pilot of Airheart One and advised him of the request. The pilot stated he would have to check the weather and get back to him. At 0035, the pilot called back and stated they would take the flight. At 0041, the paramedic on Airheart One called via radio and reported they were airborne with three persons on board, 2 hours 20 minutes of fuel, and an estimated time en route to Healthmark Hospital of 10 minutes. At 0043, the paramedic reported that due to weather they were returning to base. The dispatcher did not talk with the flight after this. At 0050, the dispatcher cleared the Airheart One call, believing that they were back at base due to the short flight time. At 0610, the relief pilot that was coming on duty called the Emergency Operations Center and advised that Airheart One was not at base. Search and rescue operations were initiated and the wreckage of the helicopter was located in Choctawhatchee Bay about 0820.

A witness, who was fishing on the northwest side of the Highway 331 bridge reported that between 0030 and 0100, he observed a helicopter flying from south to north parallel to the bridge on the east side. The weather was lightning and thunder and it was just starting to drizzle and rain. He observed the helicopter either fly into a big cloud or fly behind the big cloud. He then saw lightning. He then saw the helicopter making a "U Turn" toward the east and then descend at a 45-degree angle to the water. He observed the helicopter by the red light on the belly. He left shortly after this because of the rain.

Recorded radar data from Eglin Air Force Base showed that the flight departed the Walton County Sheriff's Department heliport and was first observed on radar at 0040:37 while at 300 feet, 1/10 of a mile east-southeast of the heliport. The flight climbed to 900 feet, while proceeding north bound, across the bay, flying parallel to Highway 331 Bridge. The flight then descended to between 700 and 800 feet. At 0042:18, the flight initiated a turn to the east and at 0042:49, the last radar contact was recorded when the flight was at 700 feet, flying on an east-southeast heading. This position was about 3/4 mile to the east-northeast of the crash site.

Personnel Information

The pilot held a FAA Commercial Pilot Certificate, last issued on May 21, 1984, with airplane multiengine land, rotorcraft helicopter, instrument airplane, and instrument rotorcraft ratings. The certificate also had private privileges for airplane single engine land. The pilot held a FAA second class medical certificate last issued on February 5, 2004, with the limitations that the holder shall wear corrective lenses. Metro Aviation, Inc. personnel reported that at the time of the accident the pilot had accumulated 12,340 total flight hours with 6,950 total flight hours in rotorcraft. On November 20, 2003, the pilot reported to Metro Aviation, Inc. that he had 420 total instrument flight hours with 69 instrument flight hours in rotorcraft. Logbook records for the pilot were not located after the accident.

The pilot was hired by Metro Aviation, Inc. in November 2003. He became qualified as pilot-in-command on the BO-105 on November 14, 2003. The pilot received a recurrent check flight, as required by 14 CFR Part 135, on April 27, 2004. The pilot received instrument proficiency training in accordance with the Metro Aviation, Inc. training program on September 27, 2004. At the time of the accident the pilot was seated in the right front seat of the helicopter, the designated pilot's seat.

The paramedic was employed by the South Walton Fire District on September 17, 2001. He became a flight paramedic in March 2003. The paramedic was seated in the left front seat of the helicopter at the time of the accident. He conducted all communications between the accident flight and the Emergency Operations Center.

The flight nurse was employed by Sacred Heart Health System in March 2002 and became a flight nurse in January 2003. At the time of the accident the flight nurse was seated aft of the pilot in a side facing seat.

Helicopter Information

The helicopter was a Eurocopter Deutschland BO-105 CBS5, serial number S-769, manufactured in 1987. The helicopter was equipped with two Rolls-Royce/Allison 250-C20B, 420 shaft horsepower engines. At the time of the accident, the helicopter had accumulated 8,846 total flight hours. The helicopter was last inspected on September 11, 2004, 110 flight hours before the accident, when it received a 50-hour, 150-hour, and 30-day inspection in accordance with the Metro Aviation, Inc, FAA approved aircraft inspection program. NTSB records show the helicopter received substantial damage on November 13, 200, when it was involved in a landing accident at Parumph, Nevada. The aircraft had FAA registration number N911VH assigned to it at the time of that accident.

Meteorological Information

A meteorological study was performed by the NTSB Operational Factors Division. The study showed that at 2353 the Destin-Ft. Walton Beach Airport (KDTS), Destin, Florida, automated surface weather observation was winds 220 degrees at 7 knots, 200 degrees to 280 degrees variable, visibility 7 statute miles, ceiling 800 feet broken, temperature 79 degrees F., dew point temperature 75 degrees F., altimeter setting 29.94 inches of Hg., lightning distant north, ceiling 700 variable 1300. The airport is located 16.2 nautical miles west of the accident site. At 0053 the KDTS automated surface weather observation was winds variable at 6 knots, visibility 7 statute miles, ceiling 600 feet broken, 1,500 feet overcast, temperature 79 degrees F., dew point temperature 75 degrees F., altimeter setting 29.93 inches of Hg., lightning distant southeast.

The 2355 surface weather observation taken at the Valparaiso/Okaloosa-Eglin AFB (KVPS) was winds 210 at 5 knots, visibility 7 statute, clouds 800 feet scattered, ceiling 2,000 feet overcast with thunderstorm, temperature 77 degrees F., dew point temperature 77 degrees F., altimeter setting 29.94 inches Hg., thunderstorm northeast and east moving southeast. The airport is located 20 nautical miles west-northwest of the accident site. The 0055 surface weather at KVPS was winds 230 at 5 knots, visibility 7 statute, clouds at 800 feet scattered, ceiling 1,700 feet broken with thunderstorm, overcast at 4,000 feet, temperature 77 degrees F., dew point temperature 77 degrees F., altimeter setting 29.93 inches Hg., thunderstorm northwest and north moving southeast.

Weather radar data obtained from the Eglin AFB Doppler Weather Radar System show that weak weather echoes were present in the area of the accident at the time of the accident. Additionally, an intense to extreme weather echo was present about 10 nautical miles north of the accident site.

At the time of the accident Airmet IFR MIAS WA 200145 was in effect for the accident area. The Airmet called for occasional ceiling below 1,000 feet, visibility below 3 miles, precipitation, mist, and fog. The Airmet was issued at 2045 on October 19, 2004, and was valid until 0300 on October 20, 2004.

Communications

There were no reported problems with communications between the accident flightcrew and the Walton County Emergency Operations Center. The flightcrew was not in contact with any Air Traffic Control facilities.

Wreckage and Impact Information

The helicopter crashed into Choctawhatchee Bay at position 30 degrees, 24.65 minutes North Latitude, and 86 degrees, 08.510 minutes West Longitude, or about 1.5 miles east of the Highway 331 bridge and ¼ mile southwest of the mouth of the Mitchell River. The wreckage was located in about 10 feet of water. Divers from the Okaloosa County Sheriff's Department, who examined the wreckage under water, reported the main cabin was lying on a northeasterly heading. The engines, transmission, main rotor head, and portions of the main rotor blades were still attached to the main cabin. The skids were separated and one was located about 25 feet northwest of the main cabin. The forward portion of the tail boom was located about 25 feet northeast of the main cabin. The aft end of the tail boom, including the tail rotor gear box and portions of the tail rotor, was located about 50 feet northeast of the main cabin. A 300-foot by 1 mile long floating debris field extended to the southeast of the main wreckage. The water temperature was between 72 and 74 degrees F., and there was about a 3-4 foot deep silt layer on the bottom of the bay.

The wreckage was recovered and taken to the maintenance hangar at the Walton County Sheriff's Department heliport, Santa Rosa Beach, Florida. Damage to the helicopter's right front cabin floor was consistent with the helicopter impacting the water in a nose low, rolled right attitude. Impact damage was present on the left side of the fuselage. Impact forces separated the lower fuselage structure from the upper fuselage structure. The two remained attached by electrical wire bundles. The airframe fuel system was destroyed by impact forces. The smell of jet fuel was present throughout the wreckage. The separated right hand skid tube and step were recovered. The left skid tube and step were separated but not recovered. The cross tube assemblies remained loosely attached to the lower fuselage structure. The tail boom was separated immediately aft of the fuselage attach ring and was located in two pieces. The electrical system of the helicopter was destroyed by impact forces. There was no evidence of lightning strike on the helicopter.

Examination of the flight control system showed continuity was established for collective, longitudinal and lateral cyclic, and anti-torque. All separation points in the control system were consistent with overstress separation. All attaching hardware was found in place and safety wired.

The four main rotor blade attach points were in place on the rotor head. Portions of three blades were still attached. One blade had separated near the attach point at the rotor head and the intermediate section of the blade was not recovered. The outboard tip section for this blade was recovered. The tip sections for the remaining three blades were separated by impact forces but were not recovered.

The tail rotor had one of the two blades fractured and separated about one quarter span from the blade root. The separated portion was recovered. The tail rotor gearbox rotated freely and the input drive was observed to turn when the gearbox was rotated. The magnetic indicating plug was void of metal. The intermediate gearbox rotated freely and the magnetic indicating plug was void of metal. The tail rotor driveshaft from the main transmission to the first flexible coupling was in place. The first flexible coupling was attached and had signatures consistent with torsional distortion. The intermediate coupling and the long section of tail rotor driveshaft along with the hangar bearing had separated and were not recovered. The aft flexible coupling at the input to the intermediate gear box remained attached to the gearbox and had torsional distortion. The tail rotor driveshaft between the intermediate and tail rotor gear boxes was in place.

The main transmission, main rotor head, and both engines remained attached to the upper fuselage structure. The main transmission was manually rotated and continuity was established from the engine input quills to the rotor head. The freewheeling clutch units operated. The main transmission magnetic indicating plugs were found void of material. All components of the main rotor head operated normally when moved by hand.

The hydraulic power pack was in place and the automated switch over was positioned to the normal No. 1 system position. The power pack was removed from the helicopter and tested at Eurocopter Canada under Transportation Safety Board of Canada oversight. The power pack had sustained minimal damage to an electric wiring harness and some hydraulic lines. The power pack was functionally tested and no preaccident failures or malfunctions were noted. All pumps and actuators operated normally.

All three crew seats were separated from the cabin floor. The left front passenger seat displayed aft and right bending damage. The right front pilot's seat displayed forward bending of the seat support structure. The left facing passenger seat located aft of the pilot's seat displayed forward displacement damage to the seat structure.

The emergency locator transmitter was recovered and found to be full of water. The internal circuit board was covered with water and corrosion and the battery had discharged to 5.6 volts.

The instrument panel had impact damage and many instruments were not recovered. The radio panel was not recovered. The engine control panel was separated and the engine controls were in the forward fly position. The two logo light bulbs located on the horizontal stabilizer and the left navigation light bulb showed filament deformation. Multiple bulbs from the instrument lighting system were examined and did not show filament deformation.

The No. 1 engine and accessories were examined after removal from the helicopter. There was no visible external engine or control damage. The engine had been submerged in salt water. Both gearbox magnetic indicating plugs were found free of material. The N1 drive train rotated by the tachometer drive pad. The N2 drive train rotated by the tachometer drive pad and by hand through the exhaust collector. The engine fuel filter was found full of fuel. All pneumatic and fuel lines were found tight. The engine to transmission drive coupling was attached. Disassembly examination of the engine and accessories was performed at manufacturer facilities under NTSB oversight. No pre-accident failures or malfunctions were observed.

The No. 2 engine and accessories were examined after removal from the helicopter. There was no visible external engine or control damage. The engine had been submerged in salt water. Both gearbox magnetic indicating plugs were found free of material. The N1 drive train rotated by the tachometer drive pad. The N2 drive train rotated by the tachometer drive pad and by hand through the exhaust collector. The engine fuel filter was found full of fuel. All pneumatic and fuel lines were found tight. The engine to transmission drive coupling was found fractured and displayed rotational scoring. Disassembly examination of the engine and accessories was performed at manufacturer facilities under NTSB oversight. No pre-accident failures or malfunctions were observed.

Medical and Pathological Information

Postmortem examination of the pilot, paramedic, and flight nurse was performed by the District 1, Florida, Medical Examiners Office, Fort Walton Beach, Florida. The cause of death for the pilot was reported as traumatic head injuries due to helicopter crash. The cause of death for the paramedic was reported as drowning due to blunt impact head trauma due to helicopter crash. The cause of death of the flight nurse was reported as multiple traumatic injuries due to helicopter crash. No findings which could be considered causal to the accident were reported.

Postmortem toxicology testing on specimens from the pilot was performed by the FAA, Bioaeronautical Sciences Research Labora

NTSB Probable Cause

The pilot's spatial disorientation and in-flight loss of control of the helicopter after encountering night instrument meteorological conditions resulting in collision with water during the resultant uncontrolled descent. A factor in the accident was the pilot's decision to attempt the flight when instrument meteorological conditions were forecasted for the area.