United States of America

While receiving radar vectors for an approach to land, the airplane (a Cessna 421C) departed controlled flight and impacted the terrain. Witnesses reported that they heard the engines operating before the plane crashed. During an investigation, no mechanical anomalies of the airplane were found. The pilot of a Boeing 727 reported that his airplane accumulated a 'quick load' of ice during his descent to land at the same airport within an hour of the accident.

While descending from 5,000 feet to 3,000 feet, the pilot informed ATC that the left engine had failed and the engine cowling was open. The crew said that after feathering the left propeller, and with the right engine at full power, they could not arrest a 300-500 fpm rate of descent. The crew informed ATC that they would be landing in the water. All the occupants exited the airplane from the left front pilot's emergency door. The victims were in the water for approximately 30 minutes before being rescued. One of the passengers was in cardiac arrest when he was retrieved from the water. Examination of the left engine revealed that the #2 cylinder had separated from the engine in flight as a result of high stress fatigue cracking of the cylinder hold down studs and the #3 main bearing thru-studs. The fatigue in the studs occurred as a result of the cylinder fastener preload forces either initially inadequate or lost during service. Maintenance records indicated that the thru-stud was replaced 80 service hours prior to the accident. Examination of the cylinder hold down studs and the #3 main bearing thru-studs revealed that they were improperly torqued, resulting in low initial preload on the fasteners. Incorrect installation of the oversize thru-studs, per existing service information, could have also been a factor in the improper torquing of the studs. The locations of the fatigue origins and the edge worn into the deck indicate that the upper studs were probably the first to fail, allowing the cylinder to rock on the lower rear corner of the cylinder flange.

Witnesses observed the aircraft approximately 250 feet above the ground heading towards the southwest. As the aircraft passed overhead, the 'engines were sputtering.' Approximately 3/4 mile from the witnesses, the aircraft made a 'sharp' right turn, nosed down, and impacted the ground. The engines 'quit' prior to the aircraft turning right. According to the operator, the flight was in preparation for a flight evaluation for the pilot-in-command by an FAA inspector. The pilot reported to Departure Control that he would be 'working on stalls and steep turns,' and the pilot was instructed to 'maintain VFR at or above five thousand five hundred.' The pilot-in-command had accumulated approximately 500 hours in the B-26. Prior to the accident flight, he had flown the B-26 once since October 8, 1993. That flight was on September 26, 1995, for a duration of 30 minutes. Prior to the flight the fuel tanks were 'sticked' and the total fuel was approximately 720 gallons of 100 octane low lead avgas. Examination of the airplane and engines did not disclose any pre mishap discrepancies. Due to the extent of damage, flight control continuity could not be established.

The aircraft was dispatched out from Elmendorf AFB on an AWACS survey mission under call sign Yukla 27, carrying 20 passengers and four crew members. Shortly after takeoff from runway 05, while in initial climb, the aircraft collided with a flock of Canada geese that struck both left engines n°1 and 2. The aircraft climbed to a maximum height of about 250 feet when the engine n°1 failed and the engine n°2 exploded. The aircraft entered an uncontrolled left roll, causing the left wing to struck trees. Out of control, it crashed in a huge explosion in a wooded area located about a mile from the runway end. The aircraft disintegrated on impact and all 24 occupants were killed. Numerous dead geese were found at the crash site.

The pilot obtained a preflight briefing and indicated that he would obtain an IFR clearance after becoming airborne; however, he took off and did not activate a flight plan. Witnesses observed the airplane flying north (away from the destination) about 200 to 300 feet above the ground below a low overcast sky condition. One witness said the airplane was flying very slow; he said he was almost able to keep up with it in his vehicle. The witnesses said they saw the airplane roll rapidly to the right and descend toward the ground. It collided with the ground in an approximate 50 degree pitch down attitude. An on-scene examination did not reveal any airframe or control anomaly that would have resulted in the accident. The engines and propellers were disassembled for inspection. Examination of the engines revealed they were capable of producing power. Examination of the propellers revealed both were operating at low pitch settings. About 25 miles north-northwest at Battle Creek, MI, the 1145 edt weather was, in part: 500 feet overcast, visibility 2 miles with fog, wind from 050 degrees at 10 knots.

A witness stated he observed the airplane on climbout from runway 32. The airplane started a right turn estimated at about 30 to 45° angle of bank. The airplane stopped climbing and began descending. Subsequently, it collided with a tree line, while in a right bank, and then it impacted the ground. Weather conditions at the time of accident were described by the witness as very dark, with no ambient light or visible horizon. Examination of the airframe, flight control system, engine assembly, and propeller assembly revealed no evidence of a precrash failure or malfunction. The autopilot was found in the off position, and the autopilot circuit breakers were not tripped. The pilot and passenger were seriously injured and had no memory of the flight. A radio transcript revealed that after taking off, the flight had made one radio transmission to request an ifr clearance.

During arrival at dawn, the pilot contacted Approach Control about 22 miles from the airport at 8,500 feet and requested an ILS runway 26 approach. The ATIS was reporting 1/8 mile visibility with fog; the minimum published visibility for the ILS landing was 3/4 mile. The controller vectored the aircraft so that it intercepted the ILS localizer at the outer marker at an intercept angle that was 5 degrees greater than the maximum allowable intercept of 30 degrees. The intercept point should have been at least 3 miles further away from the airport. The aircraft was 650 feet above the ILS glideslope at the outer marker (which was outside the ILS glideslope parameter). Instead of making a missed approach, the pilot elected to continue the ILS. As he attempted to intercept the glideslope from above, the airplane entered a high rate of descent and passed through the glideslope. The pilot was arresting the descent, when the airplane collided with level terrain about 1,000 feet short of the runway. After the accident, at 0646 edt, the visibility was 1/16 mile with fog.

The airplane was loaded with 10 sport parachutists and one pilot. Later, investigators calculated that the maximum gross weight was exceeded by 149.6 pounds, and the center of gravity was 2.87 inches aft of the aft limit. The cabin door had been removed for parachuting operations; however, an altered Flight Manual Supplement had been used as authority for the door removal. The airplane was not on the FAA-approved eligible list for such removal. The airplane needed to be refueled before flight, but the quantity of fuel in the airport's underground storage tank was below the electric cutoff level. Fuel was pumped manually from the storage tank into plastic jugs, which were used to refuel the airplane. Before takeoff, samples of fuel were reported to have been drained from the airplane's fuel tanks (sumps). According to witnesses, they heard an engine misfiring during takeoff. They observed the airplane level off during the initial climb and start a shallow right turn. The bank angle gradually increased from shallow to steep as the nose dropped and the airplane descended. Other witnesses observed the airplane in a steep dive just before it crashed in the rear of a residence. One person in the residence was killed. A postaccident fire destroyed the accessory sections of both engines. Examination of the airplane disclosed evidence that the right engine had been shut down and the right propeller had been feathered; however, no preimpact mechanical failure was found. A sample of excess fuel was obtained from the tank that was used to refuel the airplane, but no observable quantity of water or contamination was found.

The aircraft was VFR inbound to the Hailey airport when the pilot contacted the tower at 1247 and reported 10 miles south. During the next 7 minutes the pilot and controller communicated back and forth and the pilot never visually acquired the airport. A number of witnesses located north of the airport observed the aircraft flying northbound along the highway into upsloping, mountainous terrain at an estimated altitude of 400 feet above ground, and with the landing gear extended and the engines developing power. The aircraft was described as low and slow and was observed to dip its wings during a left turn and then descend steeply to the ground. The aircraft impacted terrain in a steep nose down attitude. There was no evidence of flight control or powerplant malfunctions. High density altitude conditions existed at the accident site. Toxicological examination revealed a finding of 0.068 ug/ml and 0.183 ug/ml of Chlorpheniramine (an over-the-counter antihistamine) in kidney and heart tissue respectively.

The pilot was cleared to land, and while on short final the airplane was observed to roll right then left into a yaw and then descend nose down into a parking lot. Witnesses reported the airplane being very low on final approach. According to the pilot's wife, his last flight was about 83 days prior to the accident. No current logbook or other maintenance-type records were recovered except for an invoice. The invoice was dated 12/20/94, and was for an annual inspection and for the replacement of six fuel inlet float valves in compliance with an airworthiness directive. Postaccident examination of the engines, propellers, and airframe components were conducted, with no discrepancies found. Symmetrical power signatures were observed on both propellers. An autopsy revealed mild focal patchy inflammation and mild cardiomegaly, and enlargement of the heart with focal patchy replacement fibrosis. Toxicology revealed Diphenhydramine, Naproxin, acetaminophen, and Salicylate in the blood and the urine at therapeutic levels. Diphenhydramine, at therapeutic levels, causes drowsiness.