Washington

Shortly after takeoff, the copilot reported that the flight was returning with the right engine shut down. Seconds later, the tower controller saw a fire. The airplane collided with level terrain, 3,450 feet from the end of runway 21 in a 75° to 80° nose down attitude. The right engine propeller was found in the feathered position. The left engine indicated evidence that it was producing power at the time of impact. A fatigue crack was found that separated the head from the barrel on the number eight cylinder of the right engine. No other evidence was found to indicate a mechanical failure or malfunction. Both pilots were killed.

After departure, the airplane intercepted airway V-2, and appeared to climb normally until reaching 8,300 feet (9,000 assigned) while tracking approximately 110° magnetic. Radar analysis showed the airplane at 128 kias when it abruptly turned left 30° and then appeared to recover. Voice communication during this event was normal with no change in the pilot's level of anxiety. Immediately thereafter, the heading changed over 90° to the left (northbound), and a maximum 6,750 fpm rate of descent developed before the heading stabilized and the descent slowed. The airplane's ground impact site was approximately 1 nm southwest of the last radar target. Wreckage distribution was roughly parallel to V-2. The airplane impacted the mountainside in a steep nose low, left wing down attitude. The engines, propellers/governors were disassembled and inspected with no evidence of mechanical malfunction. Exam of the left propeller indicated low power on impact. There was no evidence of significant icing/turbulence. The pilot, sole on board, was killed.

While climbing in moderate icing conditions after takeoff, pilot was cleared to 17,000' feet. Radar data showed aircraft climbed at an indicated airspeed (IAS) of 82 to 123 knots. A Beech safety info booklet stated that a minimum airspeed of 140 knots must be maintained in icing conditions. Climbing at reduced airspeed would have increased angle of attack and allowed ice to accumulate under the wings and aft of the de-icing boots. Aircraft climbed to 13,500 feet, descended momentarily to 13,300 feet, then continued climbing as airspeed decreased abruptly. After slowing to 60 knots ias at 13,700 feet, the aircraft entered a steep descending turn and accelerated to high speed (above VNE). An emergency was declared, stating the aircraft 'lost an engine.' Soon thereafter, radar contact was lost and the aircraft crashed. Pieces of empennage surfaces separated in flight and were found at remote location from the main wreckage. Both counterweights separated from the elevators. Post crash tests disclosed no mechanical evidence of engine malfunction. Low ceiling, fog, light rain, snow and icing conditions were reported in area. All six occupants were killed.

The crew was completing a local training mission at Yakima-Vagabond AAF. On final approach, the crew shut down the left engine to simulate a failure when the aircraft rolled to the left, lost height and crashed about 500 yards short of runway threshold. Both pilots were injured.

As the flight was approaching the destination, at night, the pilot obtained vectors for a descent over mountainous terrain. During the approach, he cancelled the IFR flight plan and the aircraft descended below radar coverage. Subsequently, the aircraft crashed in mountainous terrain, northwest of the destination airport. Impact occurred in a wooded area at an elevation of about 2,700 feet. The ELT did not activate during the accident. A search was initiated on 12/1/90, but the aircraft and surviving passenger were not found until the next day. The Canadian ATP pilot and other four passengers were fatally injured. After initial impact with trees, the main portion of the fuselage traveled about 1,000 feet before coming to rest. No preimpact mechanical problem was found.

During a cross country flight, the pilot failed to plan for the effects of known adverse weather, including strong winds aloft and mountain wave activity. The pilot overflew several possible fuel stops, continuing on toward the destination until the fuel was exhausted. The airplane collided with heavily wooded terrain after the loss of power to both engines.

A Cessna 172N registered N738AQ crashed in the Olympic National Forest earlier that day and a fire erupted. The crew was dispatched in the region of Lake Wynoochee to proceed in a fire fighting mission. After the retardant was dropped, the crew initiated a climb when control was lost and the aircraft crashed in a wooded area located near the Wynoochee Dam. Both pilots were killed.

During arrival for an ILS runway 21R approach, the aircraft encountered icing conditions for about 9-1/2 minutes. As the aircraft was vectored for the approach, the Seattle ARTCC controller used an expanded radar range and did not provide precise positioning of the aircraft to the final approach course. The flight crew attempted to continue on a steep, unstabilized approach for a landing. Recorded radar data showed that the aircraft was well to the right of the ILS course line and well above the glide slope as it passed the outer marker/final approach fix (faf). It did not intercept the localizer course until it was about 1.5 mile inside the faf. Also, it was still well above the ILS glide slope were recorded altitude data was lost when the aircraft was abt 2.5 miles from the airport. The tower had closed, but the controller saw the aircraft in a higher than normal rate of descent in a wings level attitude. Before reaching the runway, the aircraft nosed over and crashed in a steep descent. There was evidence that ice had accumulated on the airframe, including the horizontal stabilizers, which may have resulted in a tail plane stall. All six occupants were killed.

For unknown reasons, the aircraft landed hard at Whidbey Island NAS and was considered as damaged beyond repair. There were no casualties.

Shortly after takeoff from Seattle-Tacoma Intl Airport, the crew noted a right engine power loss and decided to return for a precautionary landing. After lowering the landing gear, a massive fire was discovered in the right engine nacelle. After landing, directional control and all braking were lost. The aircraft departed the left side of the runway 16L after the left power lever was moved to flight idle. The f/o advised tower that the aircraft was out of control. The aircraft rolled onto the ramp area where it struck a runway designator sign, ground equipment, and jetways B7 and B9. The aircraft was subsequently destroyed by fire. Investigation revealed that during overhaul the high pressure fuel filter cover was improperly installed on the engine and the improper installation was not discovered drg company installation of the engine on the aircraft. This led to a massive fuel leak and the nacelle fire. The fire/explosion caused the loss of the engine panels, reducing the effectiveness of the fire suppression system and allowing other systems to be damaged.