Beechcraft E18

The airplane was observed to depart normally for a positioning flight conducted during night visual meteorological conditions. In addition, the landing gear was observed to retract after takeoff. A witness who lived near the accident site heard a "loud" engine noise and observed the airplane just above the trees. The airplane then pitched down, impacted the ground, and exploded. The airplane impacted in a soybean field about a 1/2 mile from the departure end of the runway. Two pairs of ground scars were observed at the beginning of the debris path. The initial pair of ground scars were about 2 to 3 feet in length and were located about 380 feet south of the main wreckage. A pair of 10 to 12 foot long ground scars were located about 10 feet forward of the initial ground scars and they contained portions of the left and right engines; respectively. There was no impact damage observed to the portion of the soy bean field located in-between the second ground scar and the main wreckage. Prior to the flight, maintenance personnel replaced a frayed elevator trim cable. The work was supervised and checked by the accident pilot. Examination of the airplane did not reveal any evidence of a preimpact failure; however, a significant portion of the airplane was consumed in a post crash fire. Examination of the propellers revealed damage consistent with engine operation at the time of impact. The pilot reported 22,500 hours of total flight experience, with over 17,00 flight hours in make and model.

The pilot lost control of the airplane following the loss of engine power from the right engine during takeoff. The pilot stated that the engine power loss was not sudden, but rather a slow continued reduction of power. The pilot further stated that the loss of power occurred after he placed the landing gear selector in the retract position. He added that his airspeed at the time of the power loss was between Vmc (86 mph) and Vy (120 mph). The airplane started to roll towards the right (dead) engine as the pilot reduced the power on the left engine. The outboard portion of the right wing impacted the ground short of a taxiway. Examination of the wreckage revealed that the right engine propeller was in the feather position and the left engine was torn from the airframe. The reason for the loss of engine power was not determined.

The pilot reported that the airplane lifted off at 70 knots. After accelerating in ground effect the airplane became 'unstable in the roll axis' so he added power. He reported that the left wing tip contacted the runway approximately 3/4 the way down the runway. The pilot then added additional power at which point the left wing contacted the grass off the left side of the departure end of the runway. The pilot then reduced the power to idle and landed the airplane in the grass collapsing the landing gear. The pilot reported that the engines sounded normal throughout the accident sequence. Investigation revealed another Beech 18 had taken off on the same runway, but in the opposite direction of N916TM less than one minute prior to the accident.

The flight had been delayed due to severe weather over the departure airport. The preflight weather briefing received by the pilot included AIRMETS and SIGMETS for icing and severe thunderstorms, possible tornadoes, hail to 2 inches, and wind gusts to 70 knots near the ground. The Beech 18 was not equipped with a storm scope or weather radar. Prior to takeoff, a passenger stated to a witness that the weather was 'really really bad,' and that they would have to 'do some deviating to get around it.' After takeoff, the airplane cruised at 10,000 feet uneventfully for 1 hour and 50 minutes, when a center controller advised that radar contact was lost, which the pilot acknowledged. The next and last transmission occurred 13 minutes later when the controller received a 'Mayday' radio transmission that the airplane was 'going down.' The last radar target revealed a 6,000 foot per minute rate of descent. Training records revealed the pilot, also the company chief pilot, had flown solo 6.3 hours in the Beech 18 and credited it as dual flight instruction. He then passed a Part 135 evaluation with the FAA Principal Operations Inspector (POI), which lasted 1.6 hours. The next day the POI issued the pilot check airmen authorization for the Beech 18, all models. According to the POI, the airplane was not approved for Part 135 operations; however, the company had a bogus approval for the airplane, signed by the POI, that allowed the company to apply to Canadian Authorities for authorization to operate in Canada. The bogus approval had been used to justify the accident flight.

On August 28, 1995, about 1331 eastern daylight time, a Beech E18S, N171LG, registered to Caribbean Leasing Company, and operated by Avmac Air, Inc., as a 14 CFR Part 135 nonscheduled international cargo flight, from Orlando, Florida, to Freeport, Bahamas, crashed into the Atlantic Ocean, about 45 miles northwest of Freeport. Instrument meteorological conditions prevailed at the time and an instrument flight rules flight plan was filed. The aircraft was destroyed. The airline transport-rated pilot has not been located and is presumed to have been fatally injured. The flight originated from Orlando, on August 28, 1995, about 1229. A person identifying himself as the pilot of N171LG contacted the FAA Miami Flight Service Station by radio at 1328:33. The pilot reported he was 46 miles northwest of Freeport and requested information on the weather at Freeport. The pilot was given the weather. At 1330:15 the pilot reported he had an emergency. The controller asked what is the emergency and the pilot reported "fire onboard." No further transmissions from the flight were received and attempts to contact the flight were unsuccessful. See the transcript of communications. Search and rescue efforts were initiated and at 1600, a oil slick, the left main landing gear from N171LG, and personal effects of the pilot and debris from the cabin contents were found floating on the ocean surface, 40 miles northwest of Freeport. Examination of the recovered debris showed no evidence of fire damage. The main wreckage of N171LG was not located and recovered.

Following a wrong approach configuration, the twin engine aircraft landed too far down the runway at Walker's Cay Airfield. After touchdown, the pilot realized his mistake and initiated a go-around procedure. He asked the passenger seating on the right seat (a pilot rated passenger) to retract the flaps. Mistakenly, the passenger raised the landing gear instead. The aircraft sank on its belly, causing both propellers to struck the runway surface. The aircraft caught fire and the pilot elected to continue. During initial climb, he eventually ditched the airplane few dozen metres offshore. Both occupants were seriously injured and the aircraft was destroyed.

While performing an ILS approach at night and in IMC, the airplane collided with trees in mountainous terrain prior to the IAF. The MDA prior to the IAF is 10,600 feet. The descent altitude at the outer marker is 7,713 feet. The wreckage was located under the localizer path at an elevation of 7,600 feet. Damage to tree tops along the wreckage distribution path indicates that the airplane travelled through the trees on a level plane until contact with the ground approximately 300 feet into the path. Light snow was falling at the time of the accident and visibility was deteriorating due to fog. During the post crash investigation, there was no evidence found to indicate a mechanical failure or malfunction.

During arrival at night in fog and drizzle, the pilot was cleared for an ILS runway 1l approach. While on the approach, she reported encountering moderate rime ice. Radar data showed that the airplane continued inbound on the localizer until it neared the middle marker, then it deviated about 20° left and collided with the ground, about 300 feet short and 300 feet left of the threshold. According to witnesses, the airplane stopped its descent and slowed down, shortly before entering a steep descent and a spin. An on-scene investigation revealed no preimpact airframe, control system, or powerplant anomalies. The wings had 1/4 inch of ice on the leading edge and a 1/2 inch high ridge of ice, parallel to the deicing boots, about 3 inches aft of the boots. The cockpit and windshield heating system were found in the 'off' position. The pilot's logbook was not available for inspection. Company records showed she had passed a 14 cfr part 135 checkride on may 20, 1994. The faa checkride form was administered and signed by the chief pilot. However, other records/information showed the chief pilot would not have been able to have given the checkride on that date.

The pilot was conducting his initial revenue and solo flight for this company, in this type of airplane. The weather for takeoff included fog and low ceilings. The airplane was equipped with a primary (left) attitude indicator which was electrically operated via an independent switch. This aircraft was the only such airplane operated by this company, with an independent switch configuration for the primary attitude indicator. The airplane collided with the terrain on the airport, just after takeoff. Subsequent examination revealed no anomalies with the engines or airframe. The primary attitude indicator was located. On examination it was found to have a malfunctioning on/off flag which gave the indication of being operative regardless of power to the unit. No rotational damage was noted within the gyro housing. The pilot, sole on board, was killed.

The pilot of a twin-engine cargo airplane shut down the left engine and feathered the propeller due to a loss of engine oil. The FAA ARTCC handling the flight vectored the airplane toward a VOR. Due to the airplane's altitude and distance from the center's radar, the pilot of the airplane had to perform a full instrument approach procedure. The airplane maintained its enroute assigned altitude until passing the VOR outbound. Ntap readouts show the airplane descending throughout the procedure turn and inbound leg of the approach. The airplane's last radar contact was 300 feet below the inbound altitude for the approach while outside the final approach fix. The airplane collided with trees and terrain approximately 2 1/4 miles from the airport. The VOR is 5.5 miles from the airport. The on-scene investigation revealed the left engine's propeller had been feathered, its number nine cylinder mounting studs on the engine's case were crushed downward or were broken off at the case's surface, and the landing gear had been extended. The pilot, sole on board, was killed.