Monday, January 15, 2018

Spirit Launching New Jamaica Flights



Spirit Airlines is expanding its route network in the Caribbean with new service between Baltimore/Washington and Montego Bay, Jamaica.

The new service, which will begin March 22, will operate daily, year round, according to the Miramar, Fla.-based company.

“We are excited to celebrate our growth in these key markets and offer even more ultra-low fares to some of our guests’ favorite destinations,” said Mark Kopczak, Spirit Airlines’  Vice President of Network Planning. “We know these new, nonstop flights will bring more friends together and allow more families to go on vacation.”

Spirit also recently announced the planned launch of new service between Fort Lauderdale-Hollywood and Cap-Haitien, Haiti in April.

Original article can be found here ➤ https://www.caribjournal.com

Norwegian Air to end service to Connecticut



WINDSOR LOCKS — Norwegian Air, one of two foreign airlines serving Bradley International Airport, announced Monday it is ending service to Connecticut.

Service between Edinburgh Airport and Bradley — New England’s second busiest airport after Boston’s Logan International Airport — will end as of March 25, said Anders Lindstrom, a U.S.-based spokesman for the airline. He said the decision by Norwegian Air was motivated by an ongoing tax dispute with the Scottish government.

“The decision to pull the route, along with decreasing service to Edinburgh from other United States airports, is due to the Scottish Government’s postponement of a reduction to air passenger taxes,” Lindstrom said. “Following Norwegian’s launch of affordable trans-atlantic routes from the U.S. to Edinburgh last year, the prospect of a reduction in air passenger taxes meant we had been planning for continued future growth to Scotland.”

Norwegian Air has “seen great potential” in providing service out of Bradley and “is continuously reviewing other future opportunities in Hartford,” he said..

Lindstrom said all passengers who have been affected by the decision have been informed and offered alternative flights, or full refunds, if they chose to cancel their booking.

Norwegian Air’s decision leaves Aer Lingus as the only foreign-based airline providing international service to Bradley. It also leaves the airport at a distinct disadvantage in its efforts to keep Connecticut residents from choosing other airports in neighboring states.

For example, Rhode Island’s T.F. Green Airport, located in Warwick, is often an attractive travel alternative for residents of eastern Connecticut because of its proximity to the region. T.F. Green is seeing service to Scotland reduced, but not eliminated, according to the Providence Journal.



Bradley is operated by the Connecticut Airport Authority. Kevin Dillon, executive director of the state agency, said airport officials are “disappointed by the discontinuation of Norwegian’s nonstop service.”

“Unfortunately, despite the strength of the Bradley business case for continuing the service, external factors have deteriorated the service’s viability at this time,” Dillon said in a statement. “The United Kingdom’s Air Passenger Duty, which is levied on passengers who utilize Edinburgh Airport, has had a debilitating effect on Norwegian’s business model. For an airline that prides itself on serving as an ultra-low cost option for travelers, the APD incurred by passengers at Edinburgh Airport often essentially doubles the passenger’s total flight costs and undercuts the attractiveness of Norwegian’s low fares.”

Bradley is not the only airport with Norwegian service to Edinburgh that is being impacted by these dynamics, he said.

“We knew from the start that the lack of connecting options at Edinburgh Airport would make the Norwegian service a challenge to maintain,” Dillon said. “However, we were pleased to see that Norwegian’s performance was in line with expectations for a new airline entrant starting operations at Bradley.”

Dillon said Aer Lingus’ route between Dublin and Bradley has shown promising growth, and, after recent discussions, “we are confident that the Bradley route is currently in line for an aircraft upgrade in 2019.”

“This investment is indicative of the strong partnership between Bradley and Aer Lingus, and we look forward to growing together to continue meeting the region’s transatlantic travel needs,” he said.

Original article can be found here ➤ https://www.nhregister.com

Akron-Canton Regional (KCAK) director bleeds ‘airport blue’

Rick McQueen


GREEN Although he’s announced retirement plans, Rick McQueen isn’t done working as president and chief executive officer at Akron-Canton Airport.

Later this year he hopes see ground broken for several new gates, the last of 10 projects in CAK 2018. He also expects to spend time helping the next CEO transition to the job.

“I will always bleed airport blue,” McQueen said, referring to the color used in the Akron-Canton Airport’s logo.

Deciding to retire hasn’t been an easy decision, but the Akron-Canton staff is a close-knit team that cares about the airport and has made it a success, McQueen said. “I could do none of this by myself,” he said.

McQueen, 58, joined Akron-Canton’s staff as an accountant in 1982. “It’s home to me,” he said. He climbed the ranks and served as assistant airport director before taking the helm after Fred Krum retired as director.

He’s seen and directed plenty of changes over the past 35 years. The CAK 2018 projects — $118 million of capital improvements — started in 2008 as McQueen moved into the lead role. The projects include extending a runway, improving the entrance road and parking lots, new facilities for rescue and fire fighting equipment, and numerous improvements and renovations to the terminal.

When McQueen joined the airport staff, Krum had been director for two years. McQueen said he had the good fortune to spent 26 years working with Krum, who is credited with sparking the string of changes that have transformed the facility. Krum set a course and direction that McQueen followed, making tweaks to adjust with changes in the commercial airline industry.

Because of several factors, the biggest being airline consolidation, Akron-Canton has seen passenger use numbers fall over the past few years. McQueen believes the trend will bottom out and cited the decision by United Airlines to add service to Houston as a sign the situation is changing. McQueen said he hopes the airport’s next CEO will be able to lead the facility to the next level.

The airport’s eight-member board, which is appointed by officials in Stark and Summit counties, plans a nationwide search. McQueen anticipates someone will be hired before the year ends. He hopes to help the next CEO get to know the operation and the community. “I’m committed to making sure we can have a smooth transition,” he said.

Read more here ➤ http://www.cantonrep.com

Vacation Express Expands Flights to Cozumel, Grand Bahama



Sunwing’s Vacation Express is launching new flights from Cincinnati-Northern Kentucky International Airport to a pair of Caribbean destinations.

The carrier is slated to launch new nonstop flights from CVG to both Grand Bahama and Cozumel, Mexico.

“We are excited about adding these additional flights from CVG and to return with our Grand Bahama Island program, and we know Cozumel will become a popular destination for us this summer,” said Kevin Hernandez, VP Marketing and Sales at Vacation Express. “We have had requests from many passengers and travel agents looking for great deals on quick and easy four-night packages with non-stop flights to exciting destinations and we are here to deliver.”

The Cozumel flights will operate between May 24 and Aug. 23, while the Grand Bahama flights will operate between May 30 and Aug. 18.

“The addition of Cozumel, Mexico and return of Grand Bahama Island to Vacation Express’ existing service to Punta Cana, Dominican Republic; Montego Bay, Jamaica and Cancun, Mexico provides CVG passengers the most nonstop flight options in the Vacation Express network,” said Candace McGraw, chief executive officer, CVG. “We’re pleased that local travelers now have the opportunity to travel with Vacation Express to five different exotic destinations.”

The flights to Grand Bahama and Cozumel will be operated by Swift Air on Boeing 737-300 aircraft.

Original article can be found here ➤ https://www.caribjournal.com

Loss of Engine Power (Total): Hughes 369HM, N4QX, fatal accident occurred January 15, 2018 in Perrysburg, Wood County, Ohio

Video Screen Shot

Video Screen Shot

Main Wreckage

Main Wreckage and Utility Towers

Main Wreckage and Main Rotor

Tail Boom and Tail Rotor

Belly and Skids

Cabin and Forward Fuselage

Main Rotor Blades

Tail Boom and Tail Rotor

Engine and Exhaust

Instrument Panel

Instrument Panel and Cabin
Boeing

Pilot Seat

The National Transportation Safety Board traveled to the scene of this accident.

Additional Participating Entities:

Federal Aviation Administration / Flight Standards District Office; Cleveland, Ohio
Boeing; Mesa, Arizona
MD Helicopters Inc; Mesa, Arizona
Rolls-Royce; Indianapolis, Indiana

Aviation Accident Final Report - National Transportation Safety Board: https://app.ntsb.gov/pdf


Investigation Docket - National Transportation Safety Board: https://dms.ntsb.gov/pubdms 
 
http://registry.faa.gov/N4QX


Location: Perrysburg, OH
Accident Number: CEN18FA074
Date & Time: 01/15/2018, 1136 EST
Registration: N4QX
Aircraft: MD HELICOPTERS INC 369HM
Aircraft Damage: Substantial
Defining Event: Loss of engine power (total)
Injuries: 2 Fatal
Flight Conducted Under: Part 91: General Aviation - Aerial Observation

Analysis

The commercial pilot and the crewmember departed on a power line aerial observation flight. Security video showed the helicopter sat on the ramp, in falling snow, for over an hour before departing for the accident flight. While two people were seen in the video walking around the helicopter before the flight, the distance was too great to ascertain how much snow or ice may have accumulated in the engine inlet area or what, if any, preflight snow or ice removal actions were taken by either the pilot or the crewmember.

One witness in the area observed the helicopter descend at an angle before it impacted the ground. Recovered GPS data indicated that the helicopter was operating in right turns consistent with the slow, hover flight (line inspection operations) with at an altitude between 180 ft and 220 ft agl and an airspeed of less than 10 knots.

Satellite, radar, and weather observations near the accident site supported low clouds and visibility with light to moderate snow fall at the time of the accident. Weather models and advisories support the probability of structural icing in the area at the time of the accident. In addition, witnesses described the snowfall as moderate at the time of departure from the airport and at the time of the accident. Photographs taken by law enforcement following the accident further illustrate falling snow and flat light and or white out conditions at the time of the accident.

Ground scars and damage to the helicopter were consistent with the helicopter impacting the ground in a vertical and level pitch attitude. Further, the damage to the main rotor hub and main rotor blades was consistent with excessive coning and downward flapping of the main rotor blades. These characteristics are consistent with a loss of engine power or thrust on the main rotor system.

The RE-IGN bulb stretch signatures are consistent with activation of the engine ignition system, indicating that power turbine speed was low. The lack of stretch signatures on the flashing engine out caution panel light is likely due to the light's cycle stage at the time of the impact.

There were no mechanical anomalies with the helicopter, engine, or fuel system that would have precluded normal operations. There was no damage to the compressor, compressor front support vanes, or first-stages rotor blades that was consistent with hard body ingestion.

Investigators were not able to determine how much snow or ice accumulated on the helicopter while it sat on the ramp or how much snow or ice was removed before the helicopter departed. The helicopter was operating at a slow forward airspeed and in hover for most of the flight increasing the likelihood of snow and or ice accumulation in the engine inlet area during the hover inspection operations. According to the engine manufacturer, snow ingestion cannot be ruled out as it does not always produce visible damage to the compressor.

The helicopter was not equipped to prevent or mitigate the accumulation of snow in the inlet; only to prevent snow and ice from entering the engine through the fuel system. The manufacturer required the installation of the auto-reignition system in order to operate in snow and ice; however, the low altitude where the loss of engine power occurred was likely insufficient for a successful auto-relight and recovery of engine power.

Performance charts indicate the helicopter was operating within an airspeed and altitude combination which would make a successful autorotation difficult to perform. The flat light and/or white out conditions would increase the difficulty of judging altitude, depth, and distance during an autorotation. 

Probable Cause and Findings

The National Transportation Safety Board determines the probable cause(s) of this accident to be:
A loss of engine power due to snow or ice ingestion at an altitude that was insufficient to allow for engine re-ignition. Contributing to the accident were conditions, including altitude and flat light conditions, that precluded a successful autorotation to the field.

Findings

Aircraft
Air inlet section (core eng) - Related operating info (Cause)
Engine out capability - Capability exceeded (Factor)

Environmental issues
Snow - Effect on equipment (Cause)
Flat light - Ability to respond/compensate (Factor)

Factual Information

History of Flight

Maneuvering-hover
Loss of engine power (total) (Defining event)

Autorotation
Other weather encounter

Uncontrolled descent
Collision with terr/obj (non-CFIT) 

On January 15, 2018, about 1136 eastern standard time, a MD Helicopters Inc. 369HM helicopter, N4QX, was substantially damaged when it impacted terrain near Perrysburg, Ohio. The commercial pilot and crewmember were fatally injured. The helicopter was owned and operated by Vista One Inc., under the provisions of Title 14 Code of Federal Regulations (CFR) Part 91 as an aerial observation flight. Instrument meteorological conditions prevailed and no Federal Aviation Administration (FAA) flight was filed for the flight. The local flight departed Wood County Airport (1G0), Bowling Green, Ohio, at 1024.

According to the owner of Vista One Inc., the pilot departed from the company base at the Wayne County Airport (BJJ), Wooster, Ohio, on the morning of the accident. The pilot landed at 1G0 to pick up the powerline inspector. The pilot fueled the helicopter with 20.68 gallons of Jet A fuel at 1G0. The accident flight was the first leg of aerial inspections on the transmission towers for the Toledo Edison power grid. The team was scheduled to conduct aerial inspections from Bowling Green to the Indiana/Ohio border over the following 4 weeks.

A security camera at the Bowling Green Flight Center (1G0), located about ¼ mile from the fuel pumps, captured the arrival and departure of the helicopter. The helicopter arrived at 0920:56 and departed at 1023:53. About 1013, two people exited the building and moved towards the helicopter. They walked back and forth between the helicopter and the building and then walked around the helicopter for several minutes. Due to the distance of the helicopter from the camera, it is not clear what the specific preflight activities were. It appears that both people boarded the helicopter before the helicopter departed.

A witness, located just south of the accident site, observed the helicopter descend "at an angle" before it impacted terrain. The witness was indoors at the time and did not hear the helicopter.

A search of radar facilities did not find any primary or secondary radar targets consistent with the accident helicopter. Data recovered from a handheld global positioning system unit (GPS), located in the wreckage, started at 1017:14 at 1G0 and terminated at 1136:34, at the accident location. Track data illustrated the helicopter in multiple right turns consistent with line inspection operations. The last few minutes of the track data showed the helicopter at an altitude between 800 ft and 840 ft mean sea level (msl) or between 180 ft and 220 ft above ground level (agl) and at an airspeed of less than 10 knots. 



Tyson Snyder

Pilot Information

Certificate: Flight Instructor; Commercial
Age: 32, Male
Airplane Rating(s): None
Seat Occupied: Right
Other Aircraft Rating(s): Helicopter
Restraint Used:
Instrument Rating(s): Helicopter
Second Pilot Present: No
Instructor Rating(s): Helicopter
Toxicology Performed: Yes
Medical Certification: Class 2 With Waivers/Limitations
Last FAA Medical Exam: 04/24/2017
Occupational Pilot:Yes 
Last Flight Review or Equivalent: 06/26/2017
Flight Time:  (Estimated) 1219.4 hours (Total, all aircraft), 212.7 hours (Total, this make and model), 183.6 hours (Last 90 days, all aircraft), 31.4 hours (Last 30 days, all aircraft), 1.2 hours (Last 24 hours, all aircraft) 

At the time of his most recent medical certificate application, the pilot reported no chronic medical conditions and no medications. The medical certificate contained the limitation "Must wear corrective lenses."

The pilot's flight logbook contained entries dated between May 27, 2013, and December 28, 2017. The pilot had logged no less than 1,219.4 hours in helicopters; 212.7 hours of which were logged in the make and model of the accident helicopter. The pilot had logged 97.9 hours of simulated instrument flight time, and no flight time in actual instrument conditions. The last simulated instrument flight (0.4 hours dual received) was conducted September 30, 2015, in a Robinson R44 II helicopter.

The pilot started work at Vista One Inc. on September 6, 2017, and recorded a flight in his logbook, dated 9/6/17, of .5 hours with the note "Vista 1 First Day." The pilot had logged 309.3 hours of flight time in company helicopters between September 6, 2017, and December 28, 2017.

The company did not provide any training records for the pilot. The owner recalled conducting a training flight with the pilot the week before the accident but did not provide any specifics for that flight. This flight was not logged in the pilot's flight logbook. The owner mentioned that the pilot had difficulty recalling how to clear the GPS track just before the accident flight. He also stated that the pilot did not recall how to operate the throttle past the detent. He did not report any other concerns with the pilot's performance.



Jeffrey Lysle Fluharty

Crewmember

The powerline inspector worked for Vista One Inc. for 2 to 3 years. He lived in West Virginia and would drive to Ohio when it was time to work. According to the crewmember's family, he had been flying from platforms for line inspection and maintenance since 2004. The owner of Vista One Inc. stated that the crewmember drove from his home West Virginia the evening before the accident and met the pilot at 1G0 for work on the day of the accident. 

Aircraft and Owner/Operator Information

Aircraft Make: MD HELICOPTERS INC
Registration: N4QX
Model/Series: 369HM
Aircraft Category: Helicopter
Year of Manufacture: 1971
Amateur Built: No
Airworthiness Certificate: Normal
Serial Number: 610209M
Landing Gear Type: High Skid
Seats: 3
Date/Type of Last Inspection: 10/25/2017, Annual
Certified Max Gross Wt.: 2550 lbs
Time Since Last Inspection: 62 Hours
Engines: 1 Turbo Shaft
Airframe Total Time: 10373.1 Hours at time of accident
Engine Manufacturer: Rolls-Royce
ELT: C91A installed, not activated
Engine Model/Series: M250-C20B
Registered Owner: VISTA One INC
Rated Power: 317 hp
Operator: VISTA One INC
Operating Certificate(s) Held: Rotorcraft External Load (133) 

According to the MD 500 Rotorcraft Flight Manual (RFM) the helicopter was certificated in the normal helicopter category for day and night visual flight rules (VFR) operations.

The helicopter was not equipped, nor was it required to be equipped, with either a radar altimeter or emergency locator transmitter.

The RFM stated that flight into known icing is prohibited. "Flight operation is permitted in falling and/or blowing snow only when the Automatic engine Reignition Kit and Engine Failure Warning System are installed and operable."

The helicopter was equipped with the late configuration warning and caution indicators which included a "flashing red engine out warning indicator" in addition to an "audible warning tone in headset." These indicators annunciate when gas generator speed (N1) falls below 55%.

The helicopter was equipped with the automatic engine reignition kit, a later modified system (250-C18 or C20). According to the RFM, this kit arms the automatic reignition system whenever there is transmission oil pressure and the ARMED (lower light) light is illuminated. Rotor speeds less than 98 +/- 1% of the power turbine speed (N2) or N1 speed is below 55%, the RE-IGN (upper light) is illuminated and the igniter is activated. The RE-IGN light only goes out when manually reset by the pilot.

The helicopter was also equipped with the anti-ice airframe fuel filter. This filter is designed to filter out ice particles and other solid contaminates from the fuel before it enters the engine fuel system. The RFM stated that use of this filter removes the requirement for using fuel containing anti-ice additives.



Rolls-Royce Engine

The Rolls-Royce M250-C20 Operations and Maintenance Manual contained several warnings regarding operations in snow and ice: "AT AMBIENT TEMPERATURES BELOW 4°C (40°F). SOME TYPE OF ANTI-ICE PROTECTION IS REQUIRED, SUCH AS AN ANTI-ICE ADDITIVE OR A MEANS OF AIRFRAME FUEL ICE ELIMINATION. ENGINE FLAMEOUT COULD RESULT FROM FAILURE TO USE ANTI-ICE PROTECTION."

It further notes that, "SNOW OR ICE SLUGS CAN CAUSE THE ENGINE TO FLAME OUT. BE SURE AVAILABLE PREVENTATIVE EQUIPMENT IS INSTALLED AND IN PROPER WORKING ORDER WHEN FLYING IN CONDITIONS WHERE SNOW OR ICE BUILD UP MIGHT OCCUR."

According to Rolls-Royce, a 1968 study showed that as little as 30 grams of snow/slush ingested in the engine inlet can induce a flameout in the Allison 250-series engines.

Meteorological Information and Flight Plan

Conditions at Accident Site: Instrument Conditions
Condition of Light: Day
Observation Facility, Elevation: KTDZ, 623 ft msl
Distance from Accident Site: 4 Nautical Miles
Observation Time: 1130 EST
Direction from Accident Site:
Lowest Cloud Condition: Few / 1400 ft agl
Visibility:  2 Miles
Lowest Ceiling: Broken / 3200 ft agl
Visibility (RVR):
Wind Speed/Gusts: 9 knots /
Turbulence Type Forecast/Actual: None / None
Wind Direction: 130°
Turbulence Severity Forecast/Actual: N/A / N/A
Altimeter Setting: 30.3 inches Hg
Temperature/Dew Point: -7°C / -9°C
Precipitation and Obscuration: Light - Snow
Departure Point: Bowling Green, OH (1G0)
Type of Flight Plan Filed: None
Destination: Bowling Green, OH (1G0)
Type of Clearance: None
Departure Time: 1024 EST
Type of Airspace: Class G 

A weather study was conducted by the National Transportation Safety Board (NTSB) in support of this accident investigation and the detailed weather study is available in the public docket.

The National Weather Service (NWS) Surface Analysis Chart for 1000 local depicted a low-pressure system located over southern Wisconsin with its associated frontal boundary stretching northward into Canada and southward into Illinois, Indiana, and Missouri. A high-pressure system was located over central Virginia. The accident site was located in between the high- and low-pressure systems. The station models around the accident site depicted air temperatures in the mid to high teens (Fahrenheit (F)), dew point temperatures in the low teens, with temperature-dew point spreads of 5° F or less, an east-southeast wind of 5 to 10 knots, overcast sky cover, and light snow.

The Geostationary Operational Environmental Satellite-16 depicted abundant cloud cover above the accident site at the time of the accident, with that cloud cover moving from southwest to northeast. Infrared imagery indicated cloud tops at 13,000 ft msl.

There was a meteorological impact statement valid for the accident site at the time of the accident for areas of marginal visual flight rules and instrument flight rules with light snow spreading from west to east in addition to light to patchy moderate ice between 1,500 ft and 10,000 ft msl spreading from west to east. There were Airmen's Meteorological Information (AIRMET) Sierra and Zulu valid for the accident site at the accident time for IFR conditions due to precipitation and mist and moderate icing conditions below 15,000 ft msl.

A search of official weather briefing sources, such as contract Automated Flight Service Station (AFSS) provider Leidos weather briefings and the Direct User Access Terminal Service (DUATS), was done and the accident pilot did not request a weather briefing through Leidos or DUATS.

A search of archived ForeFlight information indicated that ForeFlight did not have any record of the accident pilot requesting a weather briefing before or during the accident flight. ForeFlight did record that the accident pilot accessed the Central Great Lakes NOAA Doppler radar loop weather Imagery at 0958:07. With no internet access while in flight, ForeFlight is still able to access weather information directly from the FAA but leaves no remote record of such access. It is unknown if the accident pilot checked or received additional weather information before or during the accident flight.

The weather conditions at 1G0 were visible in the security camera video. The visibility was reduced, and it was snowing. Witnesses at the airport characterized the weather at 1 ¼ to 1 ½ miles visibility, with moderate snow, and unknown ceilings. Photographs taken by law enforcement following the accident further illustrate falling snow and flat light and or white out conditions at the time of the accident.

The general manager of the Bowling Green Flight Center reported that it was snowing when the accident helicopter arrived at the 1G0 fuel pump area around 0920. It was still snowing when the accident flight departed around 1024 with 1 to 1 ½ miles visibility. The flight support manager recalled 1 ¼ miles visibility and the accident helicopter departed into instrument meteorological conditions with moderate snow.

The Current Icing Potential (CIP) product created by the National Weather Service and valid for the accident site indicated between a 20% to 50% probability of icing at 1,000 ft and 2,000 ft at 1200 at the accident site. The CIP indicated that the icing near the accident site would likely be trace to moderate intensity. The CIP also indicated an unknown chance of supercooled large droplets (SLD) near the accident site around the accident time.



Wreckage and Impact Information

Crew Injuries: 2 Fatal
Aircraft Damage: Substantial
Passenger Injuries: N/A
Aircraft Fire: None
Ground Injuries: N/A
Aircraft Explosion: None
Total Injuries: 2 Fatal
Latitude, Longitude: 41.501667, -83.445278 (est) 

The accident site was in a dormant corn/bean field at an elevation of 620 ft msl. The wreckage came to rest about 120 ft west of power lines. There was no evidence that the helicopter impacted either the power lines or the transmission towers. There was no evidence of a postcrash fire. There were no ground scars leading up to the wreckage. The ground was frozen, and it had snowed before, during, and after the accident. Photographs provided by first responders illustrated extensive debris and disturbed ground immediately adjacent to the belly of the helicopter. The helicopter came to rest on its left side with the nose oriented on a heading of 256°.

The main wreckage included the fuselage, tail boom, and main rotor system. Two main rotor blades came to rest on the ground and two main rotor blades were extended in the air. The tail boom was partially separated, and the left skid was separated, fractured into multiple pieces, and located about 20 ft south of the main wreckage.

The wreckage was recovered from the scene and relocated to a secure facility for further examination.



Wreckage Examination

The wreckage of the helicopter was examined under the auspices of the NTSB investigator in charge. The extensive details of the wreckage examination are contained in the docket for this accident.

The lower fuselage exhibited extensive upward crushing along the entire span of the fuselage. The cabin of the fuselage was crushed up from the floor/belly of the helicopter. The left side of the helicopter exhibited more upward and sideways crush as compared to the right side. The upper and lower windscreens on the left and right side were impact damaged and fragmented.

The collective control, cyclic control, and anti-torque pedals were impact damaged but were otherwise continuous and correct. The tail rotor driveshaft was continuous from the main rotor transmission aft to the separation point at the tail boom. The tail rotor controls were continuous from the break at the center seat box area aft to the separation point at the tail boom.

The main rotor hub exhibited varying degrees of damage to the feathering bearings, droop stops, and upper hub areas consistent with excessive coning and downward flapping of the main rotor blades. The main rotor rotating controls from the rotating swashplate up to each respective pitch horn were intact.

The tail boom was partially separated about 25 inches forward of the aft frame assembly and remained attached at the electrical cables. The tail rotor driveshaft was impact separated at that point. The tail rotor control rod was impact separated. The tail rotor was rotated by hand and driveshaft continuity was confirmed up to its separation point. Both tail rotor blades were wrinkled and bent several inches outboard from the blade root. The tail rotor pitch control was actuated by hand and functioned as designed; control rod continuity was confirmed forward to the tail boom fracture location. There was no evidence of main rotor strike at the tail boom.

The horizontal and upper vertical fin were unremarkable. The lower vertical fin was impact damaged and crushed to the left.

The blue main rotor blade remained attached to the hub and was bent and wrinkled at the trailing edge along the entire span of the blade. The white main rotor blade remained attached to the hub and was bent down about 90° at the root of the blade. The blade was bent and wrinkled at the trailing edge along the entire span of the blade. The red main rotor blade remained attached to the hub and was bent up about 45° at the root of the blade. The blade was wrinkled at the trailing edge along the entire span of the blade. The yellow main rotor blade remained attached to the hub and was bent and wrinkled at the trailing edge along the entire span of the blade.

Both the governor and the fuel control cables were continuous but distorted and both related bell cranks were impact damaged. The anti-ice cable was continuous and distorted. The positions of these controls at the engine were unreliable. There was drive continuity from the engine to the main rotor and the overrunning clutch was actuated by hand and functioned as designed.

The instrument panel was impact damaged. The airspeed read zero knots; the Kollsman Window was set at 30.44; the vertical speed indicator indicated 100 ft down.

The fuel bladder was impact damaged. The fuel line at the fuel shut off valve contained about a quarter cup of fuel. There was residual evidence of fuel in the bladder. The start pump was impact separated from its mounting plate. The float arm on the fuel sending unit was bent. No visual contamination was noted in the sump area.

The airframe fuel filter contained fuel and the fuel was unremarkable. The fuel was smoky in appearance with a small amount of black particulate matter and water at the bottom. The airframe fuel filter element was unremarkable.

The engine and its accessories were removed for further examination. The engine was intact, and external damage was noted to the outer combustion case. The fuel pump, fuel control unit, and the N1 turned freely when rotated by hand. The N2 did not rotate. Neither the upper nor the lower chip detectors displayed ferrous particles. The compressor inlet and first stage blades were free of any foreign object debris damage. The fourth stage turbine wheel was unremarkable and normal in appearance. All the external fuel, oil, and air line connections were at least finger tight. The fuel pump filter element was free of debris and normal in appearance. Fuel was present in the engine mounted fuel lines.

The following fuel system components were removed, and cursory inspections conducted: fuel nozzle, fuel control unit, power turbine governor, and fuel pump. The driveshafts for the fuel pump and starter generator were fractured consistent with impact damage. The fuel control unit housing was impact damaged.

Engine Examination

A NTSB Powerplants Group was convened following the initial wreckage examination. The engine was evaluated at Keystone Turbine Services under the auspices of the NTSB Powerplants Group Chairman and at the direction of the powerplants group. The examination of the engine and related systems revealed no mechanical anomalies that would have precluded normal operations. The details of the examination are contained in the Powerplants Group Chairman's factual report available in the public docket for this investigation.

The examination of the engine did not reveal soft or hard body damage on the first stage compressor blades. According to the engine manufacturer, they had 9 events on record involving a loss of engine power due to water, snow, or ice ingestion. The manufacturer stated that ingestion of snow does not always result in visible damage to the blades.

Garmin GPSMAP

A handheld Garmin GPSMAP 496 was recovered from the wreckage and sent to the NTSB's Recorders Laboratory for data recovery. Two tracks were recovered; the second track being consistent with the accident flight. The details of this data are contained in the public docket for this investigation.

Switch and Panel Examination

The auto re-ignition indicator panel and the "Warning and Caution" panel were submitted to the NTSB Materials Laboratory for examination. The radiographs for the re-ignition panel bulbs showed that the RE-IGN light bulb filaments were intact and stretched. The ARMED light bulb filaments were broken and stretched. The radiographs for all the light bulbs in the "Warning and Caution" panel were intact and not stretched.

Medical And Pathological Information

The Lucas County Coroner's Office, Toledo, Ohio, performed the autopsy on the pilot on January 16, 2018. The autopsy concluded that the cause of death was "multiple blunt force trauma" and the report listed the specific injuries.

The FAA Forensic Sciences Laboratory, Oklahoma City, Oklahoma, performed toxicological tests on specimens that were collected during the pilot's autopsy. Results were negative for all tests conducted. 

Organizational And Management Information

Vista One Inc held a 14 CFR Part 133 Rotorcraft External Load certificate. The company conducted powerline inspections under 14 CFR Part 91 and in the past had conducted 14 CFR Part 91 sightseeing operations. Before the accident there were only two pilots employed, the accident pilot and the company owner. The owner stated that there were no operations or company manuals outlining operations procedures or company policies.

According to the owner of the company, line inspection flights, such as the accident flight, involved the helicopter flying along the powerline, circling the tower, and then continuing along the line. It was the responsibility of the crewmember, using binoculars and a camera, to inspect the towers and lines for the security of cotter keys, nuts, bolts, and so on. The pilot would position the helicopter skids above the static line, about 20 ft, during these flights. He stated that it was typical for the helicopter to cover between 2 and 3 miles in an hour. In the accident report form, the owner stated that it was not normal to inspect the lines in snow and blowing snow due to the poor visibility and wind gusts.

According to several interviews with family members, both the pilot and the crewmember had expressed concerns about the maintenance of the helicopter. The crewmember expressed separately to his wife that the maintenance on the helicopters was a concern for him.

Both the pilot and the crewmember also expressed pressure from management to complete the missions in a very timely manner, regardless of the weather. The wife of the crewmember recalled multiple conversations between the crewmember and the owner regarding the weather – it was "horrible with cold and snow in the forecast." According to the crewmember's wife, the owner placed a lot of pressure on taking and completing the flights as they only had a short time to complete the work.

Additional Information

An estimated weight and balance calculation showed that the helicopter had a takeoff weight of 1,900 pounds. According to the RFM and based on the weather at the time of the accident, there was enough power available for the planned flight. According to the Height-Velocity Diagram in the RFM, the helicopter was operating within the cross-hatched regions of the diagram. The RFM stated in part:

"…These areas represent hazardous airspeed/altitude combinations from which a successful autorotation landing may be difficult to perform. Operation within the cross-hatched area is not prohibited, but should be undertaken only with extreme caution."

Title 14 CFR Part 91.155 Basic VFR weather minimums states that helicopters operating in class G airspace at 1,200 ft or less above the surface during day operations must have ½ statute mile visibility and remain clear of clouds.

In November 2013, the FAA issued Special Airworthiness Information Bulletin (SAIB SW-08-03R4) – Recommendations for Rotorcraft During Icing/Snowy Conditions. The SAIB describes the "procedures to reduce the probability of an engine in-flight shutdown due to ice and/or snow ingestion. MOST helicopters are not approved or equipped for flight into icing conditions." "Snow and ice can build up in the engine intakes and plenums when the rotorcraft is on the ground with the engine(s) not operating or are operating at a low power settings for extended periods." The SAIB went on to state that "Snow may accumulate on or in the engine inlet area during hover…"

In addition, the FAA safety pamphlet "Flying in Flat Flight and White Out Conditions" addressed the dangers associated with these weather conditions. These dangers include the lack of reference points to be used in determined depth perception while landing.

The Helicopter Association International (HAI) Utilities, Patrol and Construction Committee Safety Guide for Helicopter Operators stated that detailed power line patrols, such as the accident flight, "require the aircraft to spend extended periods in hovering flight out-of-ground effect or in slow flight."

Preventing Similar Accidents 

Understanding Flat Light and Whiteout Conditions

Flight operations in geographic areas that are susceptible to flat light and whiteout conditions can lead to accidents, as visual references are greatly reduced for pilots.

Flat light occurs when the sky is overcast, especially over snow-covered terrain and large bodies of water. In flat light conditions, no shadows are cast and terrain features and other visual cues are masked, making it difficult for pilots operating under visual flight rules (VFR) to perceive depth, distance, or altitude. These conditions combine to create an environment where it is difficult, if not impossible, to distinguish the sky from the ground.
Similarly, whiteout conditions can occur in areas with snow cover. Pilots can experience a loss of depth perception and become spatially disoriented, unable to maintain visual reference with the ground and unaware of their actual altitude.

What Can Pilots Do?

If possible, look for, use, and don’t lose sight of multiple visual reference points.

Obtain an instrument rating and become proficient and comfortable with operating in instrument meteorological conditions (IMC). Trust the cockpit instruments and develop good cross-check practices.

Understand that the ability to judge the height and determine the contour of terrain is difficult in conditions where the sky and ground (or water) are similar in color. When landing on snow-covered terrain, conduct an overflight and consider using weighted flags or other markers that can be dropped from an aircraft and provide contrast. Shorelines may also provide needed contrast.

If you regularly fly in snowy conditions, become proficient and comfortable with taxiing, taking off, landing, and conducting en route maneuvers and go-arounds in areas with snow. If visibility drops, use your instruments and land at the nearest suitable airport.

Install instruments that can enhance situational awareness (for example, radar altimeters, ground proximity warning systems, onboard weather systems, and GPS displays).

Check all available weather sources before and during a flight. Study the flight routes and avoid potentially hazardous areas (such as rapidly rising terrain, towers/wires, and large open water areas), particularly if the weather is conducive to flat light or whiteout conditions.

Set and use personal minimums, taking into account your skill level and the demands of a situation. Sticking to your personal minimums helps manage risk.

Use other sources of information during a flight to determine the weather conditions (for example: company dispatch, other pilots operating in the area, or weather cameras that may be in place, particularly in Alaska).

Interested In More Information?

Federal Aviation Administration (FAA) Pamphlet AM-400-00/1, “Spatial Disorientation Visual Illusions,” explains both phenomena and how to avoid them during flight operations.

The FAA pamphlet, “Flying in Flat Light and White Out Conditions,” provides information about how to safely operate in these conditions.

FAA Pamphlet P-8740-24, “Winter Flying Tips,” provides information to remind pilots about winter weather operating procedures.

The FAA Safety Team provides access to online training courses, seminars, and webinars. The course “Weather Wise: VFR into IMC” and many others can be accessed from www.faasafety.gov.

FAA Advisory Circular 60-22, “Aeronautical Decision Making” provides information about how to implement the various aspects of aeronautical decision-making into flight operations.

FAA Advisory Circular 61-134, “General Aviation Controlled Flight into Terrain Awareness,” provides information about controlled flight into terrain and mitigation strategies.

The NTSB issued Safety Recommendations A-02-33 through -35 and A-79-75 to improve, respectively, the safety of helicopter operations in flat light and whiteout conditions and GA safety in Alaska and other regions with similar environmental conditions.

NTSB Safety Alert SA-020, “Reduced Visual References Require Vigilance,” provides information about operating in reduced visibility conditions and historical accident information.

The NTSB’s Aviation Information Resources web page, www.ntsb.gov/air, provides convenient access to NTSB aviation safety products.

The NTSB presents this information to prevent recurrence of similar accidents. Note that this should not be considered guidance from the regulator, nor does this supersede existing FAA Regulations (FARs).
The National Transportation Safety Board traveled to the scene of this accident.


Additional Participating Entities:

Federal Aviation Administration / Flight Standards District Office; Cleveland, Ohio
Boeing; Mesa, Arizona
MD Helicopters Inc; Mesa, Arizona
Rolls-Royce; Indianapolis, Indiana 

Aviation Accident Factual Report - National Transportation Safety Board: https://app.ntsb.gov/pdf


http://registry.faa.gov/N4QX


Location: Perrysburg, OH
Accident Number: CEN18FA074
Date & Time: 01/15/2018, 1136 EST
Registration: N4QX
Aircraft: MD HELICOPTERS INC 369HM
Aircraft Damage: Substantial
Defining Event: Loss of engine power (total)
Injuries: 2 Fatal
Flight Conducted Under: Part 91: General Aviation - Aerial Observation 

On January 15, 2018, about 1136 eastern standard time, a MD Helicopters Inc. 369HM helicopter, N4QX, was substantially damaged when it impacted terrain near Perrysburg, Ohio. The commercial pilot and crewmember were fatally injured. The helicopter was owned and operated by Vista One Inc., under the provisions of Title 14 Code of Federal Regulations (CFR) Part 91 as an aerial observation flight. Instrument meteorological conditions prevailed and no Federal Aviation Administration (FAA) flight was filed for the flight. The local flight departed Wood County Airport (1G0), Bowling Green, Ohio, at 1024.

According to the owner of Vista One Inc., the pilot departed from the company base at the Wayne County Airport (BJJ), Wooster, Ohio, on the morning of the accident. The pilot landed at 1G0 to pick up the powerline inspector. The pilot fueled the helicopter with 20.68 gallons of Jet A fuel at 1G0. The accident flight was the first leg of aerial inspections on the transmission towers for the Toledo Edison power grid. The team was scheduled to conduct aerial inspections from Bowling Green to the Indiana/Ohio border over the following 4 weeks.

A security camera at the Bowling Green Flight Center (1G0), located about ¼ mile from the fuel pumps, captured the arrival and departure of the helicopter. The helicopter arrived at 0920:56 and departed at 1023:53. About 1013, two people exited the building and moved towards the helicopter. They walked back and forth between the helicopter and the building and then walked around the helicopter for several minutes. Due to the distance of the helicopter from the camera, it is not clear what the specific preflight activities were. It appears that both people boarded the helicopter before the helicopter departed.

A witness, located just south of the accident site, observed the helicopter descend "at an angle" before it impacted terrain. The witness was indoors at the time and did not hear the helicopter.

A search of radar facilities did not find any primary or secondary radar targets consistent with the accident helicopter. Data recovered from a handheld global positioning system unit (GPS), located in the wreckage, started at 1017:14 at 1G0 and terminated at 1136:34, at the accident location. Track data illustrated the helicopter in multiple right turns consistent with line inspection operations. The last few minutes of the track data showed the helicopter at an altitude between 800 ft and 840 ft mean sea level (msl) or between 180 ft and 220 ft above ground level (agl) and at an airspeed of less than 10 knots. 

Pilot Information

Certificate: Flight Instructor; Commercial
Age: 32, Male
Airplane Rating(s): None
Seat Occupied: Right
Other Aircraft Rating(s): Helicopter
Restraint Used: 4-point
Instrument Rating(s): Helicopter
Second Pilot Present: No
Instructor Rating(s): Helicopter
Toxicology Performed: Yes
Medical Certification: Class 2 With Waivers/Limitations
Last FAA Medical Exam: 04/24/2017
Occupational Pilot: Yes
Last Flight Review or Equivalent: 06/26/2017
Flight Time:  (Estimated) 1219.4 hours (Total, all aircraft), 212.7 hours (Total, this make and model), 183.6 hours (Last 90 days, all aircraft), 31.4 hours (Last 30 days, all aircraft), 1.2 hours (Last 24 hours, all aircraft) 

At the time of his most recent medical certificate application, the pilot reported no chronic medical conditions and no medications. The medical certificate contained the limitation "Must wear corrective lenses."

The pilot's flight logbook contained entries dated between May 27, 2013, and December 28, 2017. The pilot had logged no less than 1,219.4 hours in helicopters; 212.7 hours of which were logged in the make and model of the accident helicopter. The pilot had logged 97.9 hours of simulated instrument flight time, and no flight time in actual instrument conditions. The last simulated instrument flight (0.4 hours dual received) was conducted September 30, 2015, in a Robinson R44 II helicopter.

The pilot started work at Vista One Inc. on September 6, 2017, and recorded a flight in his logbook, dated 9/6/17, of .5 hours with the note "Vista 1 First Day." The pilot had logged 309.3 hours of flight time in company helicopters between September 6, 2017, and December 28, 2017.

The company did not provide any training records for the pilot. The owner recalled conducting a training flight with the pilot the week before the accident but did not provide any specifics for that flight. This flight was not logged in the pilot's flight logbook. The owner mentioned that the pilot had difficulty recalling how to clear the GPS track just before the accident flight. He also stated that the pilot did not recall how to operate the throttle past the detent. He did not report any other concerns with the pilot's performance.

Crewmember

The powerline inspector worked for Vista One Inc. for 2 to 3 years. He lived in West Virginia and would drive to Ohio when it was time to work. According to the crewmember's family, he had been flying from platforms for line inspection and maintenance since 2004. The owner of Vista One Inc. stated that the crewmember drove from his home West Virginia the evening before the accident and met the pilot at 1G0 for work on the day of the accident. 

Aircraft and Owner/Operator Information

Aircraft Make: MD HELICOPTERS INC
Registration: N4QX
Model/Series: 369HM
Aircraft Category: Helicopter
Year of Manufacture: 1971
Amateur Built: No
Airworthiness Certificate: Normal
Serial Number: 610209M
Landing Gear Type: High Skid
Seats: 3
Date/Type of Last Inspection: 10/25/2017, Annual
Certified Max Gross Wt.: 2550 lbs
Time Since Last Inspection: 62 Hours
Engines: 1 Turbo Shaft
Airframe Total Time: 10373.1 Hours at time of accident
Engine Manufacturer: Rolls-Royce
ELT: C91A installed, not activated
Engine Model/Series: M250-C20B
Registered Owner: VISTA One INC
Rated Power: 317 hp
Operator: VISTA One INC
Operating Certificate(s) Held: Rotorcraft External Load (133) 

According to the MD 500 Rotorcraft Flight Manual (RFM) the helicopter was certificated in the normal helicopter category for day and night visual flight rules (VFR) operations.

The helicopter was not equipped, nor was it required to be equipped, with either a radar altimeter or emergency locator transmitter.

The RFM stated that flight into known icing is prohibited. "Flight operation is permitted in falling and/or blowing snow only when the Automatic engine Reignition Kit and Engine Failure Warning System are installed and operable."

The helicopter was equipped with the late configuration warning and caution indicators which included a "flashing red engine out warning indicator" in addition to an "audible warning tone in headset." These indicators annunciate when gas generator speed (N1) falls below 55%.

The helicopter was equipped with the automatic engine reignition kit, a later modified system (250-C18 or C20). According to the RFM, this kit arms the automatic reignition system whenever there is transmission oil pressure and the ARMED (lower light) light is illuminated. Rotor speeds less than 98 +/- 1% of the power turbine speed (N2) or N1 speed is below 55%, the RE-IGN (upper light) is illuminated and the igniter is activated. The RE-IGN light only goes out when manually reset by the pilot.

The helicopter was also equipped with the anti-ice airframe fuel filter. This filter is designed to filter out ice particles and other solid contaminates from the fuel before it enters the engine fuel system. The RFM stated that use of this filter removes the requirement for using fuel containing anti-ice additives.

Rolls-Royce Engine

The Rolls-Royce M250-C20 Operations and Maintenance Manual contained several warnings regarding operations in snow and ice: "AT AMBIENT TEMPERATURES BELOW 4°C (40°F). SOME TYPE OF ANTI-ICE PROTECTION IS REQUIRED, SUCH AS AN ANTI-ICE ADDITIVE OR A MEANS OF AIRFRAME FUEL ICE ELIMINATION. ENGINE FLAMEOUT COULD RESULT FROM FAILURE TO USE ANTI-ICE PROTECTION."

It further notes that, "SNOW OR ICE SLUGS CAN CAUSE THE ENGINE TO FLAME OUT. BE SURE AVAILABLE PREVENTATIVE EQUIPMENT IS INSTALLED AND IN PROPER WORKING ORDER WHEN FLYING IN CONDITIONS WHERE SNOW OR ICE BUILD UP MIGHT OCCUR."

According to Rolls-Royce, a 1968 study showed that as little as 30 grams of snow/slush ingested in the engine inlet can induce a flameout in the Allison 250-series engines.

Meteorological Information and Flight Plan

Conditions at Accident Site: Instrument Conditions
Condition of Light: Day
Observation Facility, Elevation: KTDZ, 623 ft msl
Distance from Accident Site: 4 Nautical Miles
Observation Time: 1130 EST
Direction from Accident Site:
Lowest Cloud Condition: Few / 1400 ft agl
Visibility:  2 Miles
Lowest Ceiling: Broken / 3200 ft agl
Visibility (RVR):
Wind Speed/Gusts: 9 knots /
Turbulence Type Forecast/Actual: None / None
Wind Direction: 130°
Turbulence Severity Forecast/Actual: N/A / N/A
Altimeter Setting: 30.3 inches Hg
Temperature/Dew Point: -7°C / -9°C
Precipitation and Obscuration: Light - Snow
Departure Point: Bowling Green, OH (1G0)
Type of Flight Plan Filed: None
Destination: Bowling Green, OH (1G0)
Type of Clearance: None
Departure Time: 1024 EST
Type of Airspace: Class G 

A weather study was conducted by the National Transportation Safety Board (NTSB) in support of this accident investigation and the detailed weather study is available in the public docket.

The National Weather Service (NWS) Surface Analysis Chart for 1000 local depicted a low-pressure system located over southern Wisconsin with its associated frontal boundary stretching northward into Canada and southward into Illinois, Indiana, and Missouri. A high-pressure system was located over central Virginia. The accident site was located in between the high- and low-pressure systems. The station models around the accident site depicted air temperatures in the mid to high teens (Fahrenheit (F)), dew point temperatures in the low teens, with temperature-dew point spreads of 5° F or less, an east-southeast wind of 5 to 10 knots, overcast sky cover, and light snow.

The Geostationary Operational Environmental Satellite-16 depicted abundant cloud cover above the accident site at the time of the accident, with that cloud cover moving from southwest to northeast. Infrared imagery indicated cloud tops at 13,000 ft msl.

There was a meteorological impact statement valid for the accident site at the time of the accident for areas of marginal visual flight rules and instrument flight rules with light snow spreading from west to east in addition to light to patchy moderate ice between 1,500 ft and 10,000 ft msl spreading from west to east. There were Airmen's Meteorological Information (AIRMET) Sierra and Zulu valid for the accident site at the accident time for IFR conditions due to precipitation and mist and moderate icing conditions below 15,000 ft msl.

A search of official weather briefing sources, such as contract Automated Flight Service Station (AFSS) provider Leidos weather briefings and the Direct User Access Terminal Service (DUATS), was done and the accident pilot did not request a weather briefing through Leidos or DUATS.

A search of archived ForeFlight information indicated that ForeFlight did not have any record of the accident pilot requesting a weather briefing before or during the accident flight. ForeFlight did record that the accident pilot accessed the Central Great Lakes NOAA Doppler radar loop weather Imagery at 0958:07. With no internet access while in flight, ForeFlight is still able to access weather information directly from the FAA but leaves no remote record of such access. It is unknown if the accident pilot checked or received additional weather information before or during the accident flight.

The weather conditions at 1G0 were visible in the security camera video. The visibility was reduced, and it was snowing. Witnesses at the airport characterized the weather at 1 ¼ to 1 ½ miles visibility, with moderate snow, and unknown ceilings. Photographs taken by law enforcement following the accident further illustrate falling snow and flat light and or white out conditions at the time of the accident.

The general manager of the Bowling Green Flight Center reported that it was snowing when the accident helicopter arrived at the 1G0 fuel pump area around 0920. It was still snowing when the accident flight departed around 1024 with 1 to 1 ½ miles visibility. The flight support manager recalled 1 ¼ miles visibility and the accident helicopter departed into instrument meteorological conditions with moderate snow.

The Current Icing Potential (CIP) product created by the National Weather Service and valid for the accident site indicated between a 20% to 50% probability of icing at 1,000 ft and 2,000 ft at 1200 at the accident site. The CIP indicated that the icing near the accident site would likely be trace to moderate intensity. The CIP also indicated an unknown chance of supercooled large droplets (SLD) near the accident site around the accident time. 

Wreckage and Impact Information

Crew Injuries: 2 Fatal
Aircraft Damage: Substantial
Passenger Injuries: N/A
Aircraft Fire: None
Ground Injuries: N/A
Aircraft Explosion: None
Total Injuries: 2 Fatal
Latitude, Longitude: 41.501667, -83.445278 (est) 

The accident site was in a dormant corn/bean field at an elevation of 620 ft msl. The wreckage came to rest about 120 ft west of power lines. There was no evidence that the helicopter impacted either the power lines or the transmission towers. There was no evidence of a postcrash fire. There were no ground scars leading up to the wreckage. The ground was frozen, and it had snowed before, during, and after the accident. Photographs provided by first responders illustrated extensive debris and disturbed ground immediately adjacent to the belly of the helicopter. The helicopter came to rest on its left side with the nose oriented on a heading of 256°.

The main wreckage included the fuselage, tail boom, and main rotor system. Two main rotor blades came to rest on the ground and two main rotor blades were extended in the air. The tail boom was partially separated, and the left skid was separated, fractured into multiple pieces, and located about 20 ft south of the main wreckage.

The wreckage was recovered from the scene and relocated to a secure facility for further examination.

Wreckage Examination

The wreckage of the helicopter was examined under the auspices of the NTSB investigator in charge. The extensive details of the wreckage examination are contained in the docket for this accident.

The lower fuselage exhibited extensive upward crushing along the entire span of the fuselage. The cabin of the fuselage was crushed up from the floor/belly of the helicopter. The left side of the helicopter exhibited more upward and sideways crush as compared to the right side. The upper and lower windscreens on the left and right side were impact damaged and fragmented.

The collective control, cyclic control, and anti-torque pedals were impact damaged but were otherwise continuous and correct. The tail rotor driveshaft was continuous from the main rotor transmission aft to the separation point at the tail boom. The tail rotor controls were continuous from the break at the center seat box area aft to the separation point at the tail boom.

The main rotor hub exhibited varying degrees of damage to the feathering bearings, droop stops, and upper hub areas consistent with excessive coning and downward flapping of the main rotor blades. The main rotor rotating controls from the rotating swashplate up to each respective pitch horn were intact.

The tail boom was partially separated about 25 inches forward of the aft frame assembly and remained attached at the electrical cables. The tail rotor driveshaft was impact separated at that point. The tail rotor control rod was impact separated. The tail rotor was rotated by hand and driveshaft continuity was confirmed up to its separation point. Both tail rotor blades were wrinkled and bent several inches outboard from the blade root. The tail rotor pitch control was actuated by hand and functioned as designed; control rod continuity was confirmed forward to the tail boom fracture location. There was no evidence of main rotor strike at the tail boom.

The horizontal and upper vertical fin were unremarkable. The lower vertical fin was impact damaged and crushed to the left.

The blue main rotor blade remained attached to the hub and was bent and wrinkled at the trailing edge along the entire span of the blade. The white main rotor blade remained attached to the hub and was bent down about 90° at the root of the blade. The blade was bent and wrinkled at the trailing edge along the entire span of the blade. The red main rotor blade remained attached to the hub and was bent up about 45° at the root of the blade. The blade was wrinkled at the trailing edge along the entire span of the blade. The yellow main rotor blade remained attached to the hub and was bent and wrinkled at the trailing edge along the entire span of the blade.

Both the governor and the fuel control cables were continuous but distorted and both related bell cranks were impact damaged. The anti-ice cable was continuous and distorted. The positions of these controls at the engine were unreliable. There was drive continuity from the engine to the main rotor and the overrunning clutch was actuated by hand and functioned as designed.

The instrument panel was impact damaged. The airspeed read zero knots; the Kollsman Window was set at 30.44; the vertical speed indicator indicated 100 ft down.

The fuel bladder was impact damaged. The fuel line at the fuel shut off valve contained about a quarter cup of fuel. There was residual evidence of fuel in the bladder. The start pump was impact separated from its mounting plate. The float arm on the fuel sending unit was bent. No visual contamination was noted in the sump area.

The airframe fuel filter contained fuel and the fuel was unremarkable. The fuel was smoky in appearance with a small amount of black particulate matter and water at the bottom. The airframe fuel filter element was unremarkable.

The engine and its accessories were removed for further examination. The engine was intact, and external damage was noted to the outer combustion case. The fuel pump, fuel control unit, and the N1 turned freely when rotated by hand. The N2 did not rotate. Neither the upper nor the lower chip detectors displayed ferrous particles. The compressor inlet and first stage blades were free of any foreign object debris damage. The fourth stage turbine wheel was unremarkable and normal in appearance. All the external fuel, oil, and air line connections were at least finger tight. The fuel pump filter element was free of debris and normal in appearance. Fuel was present in the engine mounted fuel lines.

The following fuel system components were removed, and cursory inspections conducted: fuel nozzle, fuel control unit, power turbine governor, and fuel pump. The driveshafts for the fuel pump and starter generator were fractured consistent with impact damage. The fuel control unit housing was impact damaged.

Engine Examination

A NTSB Powerplants Group was convened following the initial wreckage examination. The engine was evaluated at Keystone Turbine Services under the auspices of the NTSB Powerplants Group Chairman and at the direction of the powerplants group. The examination of the engine and related systems revealed no mechanical anomalies that would have precluded normal operations. The details of the examination are contained in the Powerplants Group Chairman's factual report available in the public docket for this investigation.

The examination of the engine did not reveal soft or hard body damage on the first stage compressor blades. According to the engine manufacturer, they had 9 events on record involving a loss of engine power due to water, snow, or ice ingestion. The manufacturer stated that ingestion of snow does not always result in visible damage to the blades.

Garmin GPSMAP

A handheld Garmin GPSMAP 496 was recovered from the wreckage and sent to the NTSB's Recorders Laboratory for data recovery. Two tracks were recovered; the second track being consistent with the accident flight. The details of this data are contained in the public docket for this investigation.

Switch and Panel Examination

The auto re-ignition indicator panel and the "Warning and Caution" panel were submitted to the NTSB Materials Laboratory for examination. The radiographs for the re-ignition panel bulbs showed that the RE-IGN light bulb filaments were intact and stretched. The ARMED light bulb filaments were broken and stretched. The radiographs for all the light bulbs in the "Warning and Caution" panel were intact and not stretched. 

Medical And Pathological Information

The Lucas County Coroner's Office, Toledo, Ohio, performed the autopsy on the pilot on January 16, 2018. The autopsy concluded that the cause of death was "multiple blunt force trauma" and the report listed the specific injuries.

The FAA Forensic Sciences Laboratory, Oklahoma City, Oklahoma, performed toxicological tests on specimens that were collected during the pilot's autopsy. Results were negative for all tests conducted.

Organizational And Management Information

Vista One Inc held a 14 CFR Part 133 Rotorcraft External Load certificate. The company conducted powerline inspections under 14 CFR Part 91 and in the past had conducted 14 CFR Part 91 sightseeing operations. Before the accident there were only two pilots employed, the accident pilot and the company owner. The owner stated that there were no operations or company manuals outlining operations procedures or company policies.

According to the owner of the company, line inspection flights, such as the accident flight, involved the helicopter flying along the powerline, circling the tower, and then continuing along the line. It was the responsibility of the crewmember, using binoculars and a camera, to inspect the towers and lines for the security of cotter keys, nuts, bolts, and so on. The pilot would position the helicopter skids above the static line, about 20 ft, during these flights. He stated that it was typical for the helicopter to cover between 2 and 3 miles in an hour. In the accident report form, the owner stated that it was not normal to inspect the lines in snow and blowing snow due to the poor visibility and wind gusts.

According to several interviews with family members, both the pilot and the crewmember had expressed concerns about the maintenance of the helicopter. The crewmember expressed separately to his wife that the maintenance on the helicopters was a concern for him.

Both the pilot and the crewmember also expressed pressure from management to complete the missions in a very timely manner, regardless of the weather. The wife of the crewmember recalled multiple conversations between the crewmember and the owner regarding the weather – it was "horrible with cold and snow in the forecast." According to the crewmember's wife, the owner placed a lot of pressure on taking and completing the flights as they only had a short time to complete the work.

Additional Information

An estimated weight and balance calculation showed that the helicopter had a takeoff weight of 1,900 pounds. According to the RFM and based on the weather at the time of the accident, there was enough power available for the planned flight. According to the Height-Velocity Diagram in the RFM, the helicopter was operating within the cross-hatched regions of the diagram. The RFM stated in part:

"…These areas represent hazardous airspeed/altitude combinations from which a successful autorotation landing may be difficult to perform. Operation within the cross-hatched area is not prohibited, but should be undertaken only with extreme caution."

Title 14 CFR Part 91.155 Basic VFR weather minimums states that helicopters operating in class G airspace at 1,200 ft or less above the surface during day operations must have ½ statute mile visibility and remain clear of clouds.

In November 2013, the FAA issued Special Airworthiness Information Bulletin (SAIB SW-08-03R4) – Recommendations for Rotorcraft During Icing/Snowy Conditions. The SAIB describes the "procedures to reduce the probability of an engine in-flight shutdown due to ice and/or snow ingestion. MOST helicopters are not approved or equipped for flight into icing conditions." "Snow and ice can build up in the engine intakes and plenums when the rotorcraft is on the ground with the engine(s) not operating or are operating at a low power settings for extended periods." The SAIB went on to state that "Snow may accumulate on or in the engine inlet area during hover…"

In addition, the FAA safety pamphlet "Flying in Flat Flight and White Out Conditions" addressed the dangers associated with these weather conditions. These dangers include the lack of reference points to be used in determined depth perception while landing.

The Helicopter Association International (HAI) Utilities, Patrol and Construction Committee Safety Guide for Helicopter Operators stated that detailed power line patrols, such as the accident flight, "require the aircraft to spend extended periods in hovering flight out-of-ground effect or in slow flight."



WOOSTER, OH - As federal authorities try to determine the cause of a deadly helicopter crash outside Toledo, the family of the pilot says their only solace is that the Wooster native was doing exactly what he always wanted to do.

The mother of 32-year-old Tyson Snyder told Fox 8, "He wanted to try anything dangerous from a very young age and he lived up to that with his choices in vocation and in the military."

According to Julie Snyder, her son loved the challenge of his job as a helicopter pilot inspecting power lines. “He really loved it and he was good at his job, he was good at flying helicopters. It was his passion and he got to fulfill his passion," said Mrs, Snyder.

Tyson Snyder and a colleague, 62-year-old Jeff Fluharty, were killed on Monday, when their chopper crashed in a farm field, just south of the Ohio Turnpike in Wood County. First Energy says Tyson Snyder and Jeff Fluharty were contractors, inspecting the utility company’s transmission lines at the time of the crash. The FAA and the NTSB are now trying to determine the cause of the crash.

Tyson Snyder was a 2004 graduate of Wooster High School. His parents say he had been deeply affected by the events of 9/11, and that's why they were not surprised when he decided to enlist in the Marine Corps after graduating.

During his eight years as a Marine, Sgt. Tyson Snyder served in Iraq and Afghanistan, but his heart was never far from home. His sister, Ashley Escola told Fox 8, “I'll never forget the day, I was pregnant with my daughter and he called me on Mother's Day from Afghanistan and he said he was waiting to make those calls to me and my mom."

After completing his service to the country, Tyson Snyder began training to become a helicopter pilot and then got his dream job inspecting power lines.

"I think the adrenaline rush, he loved the challenge and he loved being in the air and he loved the difficulty of it, but he loved that he was good at it, I mean he worked so hard," said Tyson’s girlfriend, Kalli Hugus.

Tyson Snyder's parents says that after Tyson made it home safely after fighting in the War on Terror, they never suspected that they would get the knock on the door that every parent dreads. His father, Jeff Snyder, told us, “One thing that I would like to say is 'hug your kids, tell them that you love them because you never know, it may be the last time, so hug your kids and tell them that you love them.’"

Story and video ➤  http://fox8.com


STONY RIDGE, Ohio — The National Transportation Safety Board is investigating a helicopter crash in Wood County that killed two people Monday, and plans to release a preliminary report in about a week.

Helicopter pilot Tyson Snyder, 32, of Wooster, Ohio, and passenger Jeffery Fluharty, 62, of West Virginia, both died at the scene of the crash, which was reported just before noon Monday. Both were contracted to do utility work for Toledo Edison. 

The helicopter crashed into a field near State Rt. 163 and Pemberville Road in Troy Township.

The NTSB will recover the helicopter later Tuesday evening, and its full investigation could take up to a year, Jennifer Rodi, a senior air safety investigator with the safety board, said Tuesday during a news conference at the scene.

“We do not rush our process,” Ms. Rodi said. 

A preliminary report should be issued within five to seven days, she said, at which point an advisory could be issued for other helicopter pilots, if necessary. She did not speculate on any potential cause for the crash.

She said the pilot had between 1 and 1.5 miles of visibility at the time of the crash, and there was noticeable fuel at the scene of the crash. 

The helicopter, manufactured in 1971, was owned by Vista I, Inc., a Smithville, Ohio, company that has five other aircraft registered with the Federal Aviation Administration. A call to the company was not immediately returned on Tuesday.

Story and video ➤ https://www.toledoblade.com

"The two men who were tragically killed today in a helicopter crash were FirstEnergy contractors doing transmission line inspection work. Their employer is still in the process of notifying family members. FirstEnergy would like to express our sincere condolences to their families and fellow workers."


WOOD COUNTY, Ohio (WTVG) - Two people are dead after a helicopter crash in Wood County.

The crash happened just before noon near Bradner Road, just south of the Ohio Turnpike in Genoa.

Wood County Sheriff Mark Wasylyshyn tells 13abc that the helicopter is affiliated with a utility company. They were out doing survey work on lines in the area. Two people were on board, and both of them died. The company is said to not be based in Toledo, and the two killed were not from northwest Ohio.

Investigators with the National Transportation Safety Board are expected on the scene Tuesday morning to being an investigation.

Some people living near Monday’s deadly helicopter crash scene heard the crash, not realizing exactly what they heard until they saw the wreckage.

The sound of a low flying helicopter is something residents living off Pemberville and Bradner roads hear quite often. Monday though they heard a sound they're not familiar with hearing.

"All I heard was a big boom. I thought it was a tire that blew off a truck on the turnpike," said Sandra Minarik who lives near the crash scene.

Unfortunately that's not what Minarik heard after she got a phone call from another neighbor.

"A neighbor called and said a plane had crashed in my woods. And I ran out into the woods and I didn't see anything," said Minarik.

She eventually found the wreckage in another person's yard. Another neighbor says they heard what they now believe was this helicopter while in flight this morning.

"The helicopter going back and forth but it's not unusual out here," said Ken Reeves who lives near the crash site.

Reeves and others say they see if a few times a month, inspecting the power lines.

"You see the helicopter buzzing up and down. They follow the high tension lines as afar as you can see in both directions," said Reeves.

"It's very sad. Very sad. I feel bad for all the families involved," said Minarik.

Minarik flies her own plane in this area. While it's far too early to tell how this crash occurred, she is always cautious around one part of these lines.

"The one thing that scares us is that there are these stabilizing wires along the line and they're very, very difficult to see. When we take off we go left or right to get over them. With these snowy conditions it would be hard to see those lines," said Minarik.

Those neighbors say the helicopters do fly pretty low in this area looking at the lines but they're not sure exactly how low the pilot was flying Monday.

Story and video ➤  http://www.13abc.com



GENOA, OH (WTOL) -  Two people are dead after a helicopter crash in Wood County Monday.

Deputies were called to the scene of the crash a little before noon Monday near the Turnpike on Bradner Road. The call said that the helicopter went down suddenly.

The Sheriff's deputies and the Troy Township Fire Department responded to the crash. The two men were pronounced dead at the scene.

The Sheriff's Office says the helicopter was contracted to patrol the power lines by. 

Statement sent from FirstEnergy said both the pilot and the passenger who died in the crash, were FirstEnergy contractors doing transmission line inspection work.

"The two men who were tragically killed today in a helicopter crash were FirstEnergy contractors doing transmission line inspection work. Their employer is still in the process of notifying family members. FirstEnergy would like to express our sincere condolences to their families and fellow workers."

Police say neither pilot or the passenger were from our areal. 

Sheriff Mark Wasylyshyn says the helicopter never caught fire but the damage was extensive.

The NTSB will come to investigate the scene and inspect every inch of the commercial helicopter. 

Sheriff Wasylyshyn says the coroner will remove the bodies by Monday evening and the helicopter will remain until the NTSB shows up Tuesday. He says his department will do whatever it takes to preserve the scene so investigators can determine a cause. 

"As least one deputy on scene 24/7 until they come and remove the helicopter," Sheriff Wasylyshyn explained. "They will take it into a building somewhere and completely disect it and try to find out if it was human error or mechanical failure but it will be many months before we know the actual cause of the crash."

Sheriff Wasylyshyn says the names of the two men won't be released until family have been notified.  The crash is under investigation.

Story and audio ➤ http://www.wtol.com 



STONY RIDGE, Ohio — Two men doing work for FirstEnergy were killed Monday when their helicopter crashed into a field near State Rt. 163 and Pemberville Road in Troy Township.

The helicopter crashed about 11:40 a.m. in a large, harvested, snow-covered field east of Pemberville Road, between Route 163 and Recker Road, Wood County Sheriff Mark Wasylyshyn said on scene. 

Doug Calafella, a spokesman for FirstEnergy, said the crash victims were employees of a contractor for the utility. He said they were inspecting high-voltage transmission lines.

The company that employed the men were in the process of notifying family members, he added.

Sheriff Wasylyshyn said there was no obvious cause of the crash: no signs of fire or flames, and no indication the aircraft struck any utility lines. The crash was reported by a person in a nearby house who was looking out a window “and just saw the helicopter come down out of the sky and hit the ground,” he said.

The sheriff said his office was told by the National Transportation Safety Board that investigators from the agency will be on the scene on Tuesday, and the Federal Aviation Administration also had been notified.

"We will secure the scene. We are taking initial measurements. The NTSB will haul off the helicopter and do their dissecting to try to determine the cause," he said.

Tony Molinaro, an FAA spokesman, said in an email the helicopter was an MD-369 and the agency is sending investigators to the scene.

NTSB spokesman Christopher O'Neil said Monday afternoon an investigator was en route to the crash scene.

Story, video and slideshow ➤ http://www.toledoblade.com

  




 TROY TOWNSHIP, Ohio (WNWO) —  Wood County authorities are investigating a helicopter crash that killed two men today.

Sheriff Mark Wasylyshyn tells NBC24 two men died when their helicopter went down in a field just before noon in the vicinity Pemberville and Bradner Roads in Troy Township.

Wasylyshyn said the pair were working as independent contractors for Toledo Edison and were observing power lines throughout the area.

The men will be identified pending notification. No other details are available at this time.

Original article can be found here ➤ http://nbc24.com