Piper PA-31-310 Navajo

For unknown reasons, the twin engine airplane belly landed at Myrtle Beach and was damaged beyond as a result. The pilot, sole on board, escaped uninjured.

About two minutes after takeoff from San José-Tobías Bolaños Airport, while climbing, the twin engine aircraft went out of control and crashed in the district of Rohrmoser, about 3 km southeast of the airport. Both occupants were killed.

An aircraft mechanic working abeam of the point on the runway that the airplane lifted off was attracted by the sound of engine roughness, and observed black smoke trailing from the left engine. The airplane continued to climb to about 150 feet above ground level, entered a series of shallow left turns at about the airport's east boundary at a slow speed, and then entered a rapid left roll and pitched down. The pilot transmitted an unreadable call on FAA tower frequency, but the words, 'we got a..' and 'engine' were clearly discernable. The airplane crashed in dense brush about 1.25 miles northeast of the airport. Contamination was found in the left engine fuel system. Post crash testing of the left fuel servo revealed it would not sustain a steady state fuel flow above about one half throttle due to contamination.

The pilot stated he checked the fuel quantity in the inboard fuel tanks, but may have omitted the outboard tanks. He departed and climbed to 100 feet where the airplane yawed right. He believed it was a gust of wind which he attempted to correct. At 200 feet, the pilot stated the airplane rolled hard right and impacted trees in a 60 degree nose down attitude. There was no indication of a left engine discrepancy prior to impact. The right engine was examined with no fuel found in the fuel lines, and trace fuel was found in the fuel servo. According to the accident pilot, he regularly flew between Washington-Dulles and Southport, North Carolina using only the inboard tanks. Because of this, he did not check the location of the fuel selector, nor did he necessarily check the fuel quantity in the outboard fuel tanks. The cockpit fuel selector for the right engine was found in the outboard tank location. The right outboard tank on this airplane was not breached, and contained no fuel. The takeoff checklist states the fuel selector should be on the inboard fuel tank prior to takeoff.

The pilot was performing a night VOR/DME approach during which instrument meteorological conditions prevailed. The airplane was equipped with VOR, LORAN, and RNAV receivers. There were two step-downs fixes on the approach. At 13 DME the minimum altitude was 1,800 feet. At 10 DME the minimum altitude was 1,040 feet. The missed approach point was at 6 DME, and the VOR/DME transmitter was located 5.5 miles beyond the airport. Radar data revealed a descent profile based upon distances from the end of the runway, rather than DME from the VOR. The airplane reached an altitude of 1,000 feet when it was 13.52 miles from the VOR, and 7.58 miles from the approach end of the runway. It subsequently impacted rising terrain at an altitude of about 900 feet, about 11.5 miles from the VOR, and 5.5 miles from the approach end of the runway. Impact damage and a post-crash fire precluded a check of the radio set up at the time of the accident. According to FAR 135 a pilot-in-command was required to have 1,200 hours total time. The investigation documented the pilot's total time as about 1,057 hours.

The aircraft departed Grand Manan, New Brunswick, at 1938 Atlantic daylight time (ADT) on a charter flight to Yarmouth, Nova Scotia, with the pilot and five passengers on board. After dropping off the passengers at Yarmouth, the aircraft departed at 2106 ADT for a night visual flight to return to Grand Manan. The pilot was unable to land at Grand Manan off the first visual approach because of low weather conditions and conducted a second visual approach. During the second approach, he noticed that he required increasing right rudder to maintain direction, and that the left engine manifold pressure was low. The pilot feathered the left propeller and, despite the application of full power on the right engine, the aircraft would not accelerate or climb. The aircraft began a shallow descent into a fog layer, and the aircraft collided with some trees, pitched nose-down, and struck the ground. The aircraft was destroyed by the impact and a post-impact fire. The pilot suffered serious injuries, but managed to get out of the aircraft and make his way to a nearby cabin where he was found by a ground search team about three hours later.

The aircraft concluded an aerial survey and landed at Brown Field to clear U.S. Customs. On restart, as the left engine began running, a witness noticed two short, yellow flame bursts exit the exhaust. During taxi, the witness heard a popping sound coming from the aircraft. As power was applied to cross runway 26L, the sound went away. The aircraft stopped for a few seconds prior to pulling onto the runway; the witness did not observe or hear a run-up. Witnesses reported hearing a series of popping sounds similar to automatic gunfire and observed the aircraft between 600 and 1,000 feet above the ground with wings level and the landing gear up. The aircraft was observed to make an abrupt, 45-degree banked, left turn as the nose dipped down. Witnesses reported the nose of the aircraft then raised up toward the horizon. This was followed by the aircraft turning to the left and becoming inverted in an estimated 30-degree nose low attitude. With the nose still low, the aircraft continued around to an upright position and appeared to be in a shallow right bank. Witnesses then lost sight of the aircraft due to buildings and terrain. A May 20, 1997, work order indicated the left manifold pressure fluctuated in flight. Both wastegates were lubricated and a test flight revealed the left engine manifold pressure lagged behind the right engine manifold pressure. On June 18, 1997, the left engine differential pressure controller was noted to have been removed and replaced. This was the corrective action for a discrepancy write up that the left engine manifold pressure fluctuated up and down 2 inHg and the rpm varied by 100 in cruise. A test flight that afternoon by the accident pilot indicated the discrepancy still occurred at cruise power settings, but the engine operated normally at high and low power settings. Post accident functional checks were performed on various components. No discrepancies were noted for the left governor. The left engine differential pressure controller was damaged and results varied on each test. The left density controller was too damaged to test. The right engine density and differential pressure controllers tested satisfactory. The left and right fuel pumps operated within specifications. Both fuel servos were damaged. One injection nozzle on the left engine was partially plugged; all others flow tested within specifications.

Few minutes after takeoff from Reykjavik Airport, while cruising over Eyjafjallajökull, the pilote declared an emergency following the failure of the left engine. He was cleared to return to Reykjavik and was vectored for an approach to runway 14. On final, he encountered strong winds when the aircraft banked left then stalled and crashed 200 metres short of runway. The aircraft was damaged beyond repair and the pilot escaped uninjured. At the time of the accident, the wind was gusting from 100°-130° up to 35 knots.

En route from Nairobi to Mwanza, the pilot informed ATC about an engine failure and elected to return to Nairobi-Wilson Airport. Twenty minutes after takeoff, the aircraft went out of control and crashed in the Ngong Hills, near Ngong. All eight occupants were killed.

The parents of the pilot/owner stated that he arrived late in the afternoon prior to the accident. They stayed up with their son until approximately 0100 the morning of the accident. They stated that their son was a doctor and kept a busy schedule. The son told the parents that he had to fly back in order to have new fuel cells installed in the airplane and to work at his clinic. The pilot was airborne by 0700. The weather at his destination had low ceilings and fog restricting the visibility. The pilot was cleared by ATC to fly the localizer approach to the runway. The pilot called his position at the outer marker on the unicom frequency and no further transmissions were heard. Witnesses on the airport heard and saw the bottom of the airplane and stated that the airplane's engines sounded normal as it went overhead. Radar data showed that the airplane's altitude fluctuated and ground speed decreased significantly during the missed approach flight path. The airplane impacted the ground in approximately 40- degree nose-low, right wing down attitude. The toxicology report revealed 0.005 ug/ml Tetrahydrocannabinol (Marihuana) in the blood, and 0.013 ug/ml and 0.017 ug/ml Tetrahydrocannabinol Carboxylic Acid (Marihuana) in the blood and kidney fluid respectively.