Massachusetts

The airplane had undergone routine maintenance for slow acceleration on the right engine. Maintenance records revealed the fuel controls were changed from the right engine to the left engine. The airplane was released back to the pilot for service, and he departed for his home station. Several witnesses saw the airplane after takeoff at a low altitude, and at a slow speed. The airplane turned left, and the left wing struck the ground. Two witnesses saw the airplane pass by them at a low altitude, and wrote, '...at this point we could see the left (port) engine propeller was turning very slowly. You could actually see the individual blades of the propeller turning.' A complete disassembly of both engines, revealed no discrepancies other than impact, and post impact fire damage. Disassembly of the left propeller indicated that the propeller blades were at or near feather at impact. The pilot had a total of 106 flight hours in Beech A100 aircraft, all in the 90 days prior to the accident, and 56 hours in the 30 days prior to the accident.

The flight crew was advised prior to initiating the approach that visibility at the airport had decreased to 1/8 mile with light rain, fog and obscuration. Published landing visibility minimums for the approach was 1 mile. The 150 feet wide runway had been plowed 100 feet wide, and there were snowbanks up to 3 feet high on both sides. The airplane touched down on the unplowed portion of the runway onto a snowbank, collapsing the landing gear. The flightcrew stated that the approach lights and runway were in sight during the entire approach, and that the second pilot told the pic that he was too far left and needed to correct to the right as the airplane was about to touchdown. The tower controller stated that he lost sight of the airplane as it landed due to fog.

The pilot noted an over torque condition in the left engine as the aircraft was on an ILS approach. He made a go-around and initiated another approach with the engine shut down. He was unable to maintain altitude and the aircraft began a decent that was not arrested. Subsequently, it crashed into 2 homes, approximately 6 miles from the airport. An exam of the left engine revealed the drive shaft from the fuel pump to the fuel control was sheared at the plastic coupling. Further exam revealed the twin bearings that supported the driveshaft had failed. Also, there was evidence the drive shaft had shifted and subsequently an overtorque condition resulted. All three occupants were killed.

The pilot had just climbed to 2,500 feet when the right engine started to sputter. When he placed the fuel selector in crossfeed, both engines quit. The pilot elected to land in a field leading to substantial damage to the nose, wings, and tail section of the aircraft. A post crash inspection of fuel system revealed no fuel in the tanks or the fuel metering units for either engine. The pilot stated after the accident that the last time he refueled the aircraft was several weeks before and that it had been flown several times since its last refueling.

Before reaching his descent, the pilot advised approach control that his right engine was 'blowing some smoke' and losing oil pressure. Vectors were provided for a visual approach, but there were low clouds in the area and visibility was restricted due to haze. After reaching the vicinity of the airport, the pilot said it was in sight and he was entering a downwind for runway 30. Witnesses saw the aircraft on a left downwind, but said the aircraft overshot the 1st turn to final approach. Subsequently, while maneuvering to land, the aircraft crashed approximately 2,500 feet northeast of the runway in a wooded area. Witnesses agreed the aircraft was slow and in a steep right turn with the gear extended before it crashed in a steep descent and burned. An examination revealed evidence the starter on the right engine had backed off; 3 starter bolts had fractured thru the threaded area with signs of fatigue cracking; wear marks on the starter gear and engine gear ring indicated the starter motor had shifted aprx 3/4' rearward. Also, there was evidence the torsional damper was loose on its shaft before the accident and that both props were operating at low pitch during initial impact.

Shortly after the initial power reduction during takeoff, the pilot noted a partial loss of power in the right engine. He said he 'went to full power on both engines' and noted an 'extremely high' fuel flow indication to the right engine. He said, 'thinking that the engine was flooding, I placed the boost pump switch from high to off to possibly eliminate the problem with no result. I then placed the pump back to high and tried to decrease the fuel flow by leaning the mixture. This also did not seem to eliminate the problem.' While troubleshooting the problem, he turned to a downwind and stayed in the traffic pattern, but could not maint altitude. Subsequently, a wheels-up landing was made in an area of small trees approximately 1/2 mile before reaching runway 24. An examination of the right engine revealed the spark plugs were wet with fuel and black with soot. Also, its #5 fuel nozzle had been cross-threaded and was knocked out of its hole during impact. During an initial test, the right fuel pressure sensing switch did not sense operating pressure (over 6 psi); this would have resulted in a high boost/fuel flow condition. Later, the switch was tested ok. All nine occupants escaped uninjured.

The crew of the PA-31T Cheyenne had made one missed approach and the copilot was calling out the altitudes to the pilot. The pilot's reply to the copilot that he was just going to descend to 400 feet. The approach minimums were published for an MDA of 660 feet plus 80 feet when the control zone is not in effect. The aircraft flew into rising terrain. The copilot suffered minor injuries, the aircraft was destroyed due to impact and fire.

During arrival for a LOC runway 26 approach, the pilot was advised the abyss fan marker was notamed out-of-service. With abyss inoperative, the minimum descent altitude (MDA) was 2200 feet. After N65TD was cleared for the approach, radar service was terminated and the flight was cleared to advisory frequency. The crew contacted unicom and obtained airport and weather advisory. The Unicom operator advised winds light and variable, estimated 800 feet overcast, visibility 5 miles, slush and ice reported on runway 1/2 hr earlier. After the crew reported 'procedure turn inbound,' no further transmissions were received from the aircraft. Subsequently, it hit trees on rising terrain at an elevation of approx 2200 feet, approx 7 miles before reaching the final approach fix (FAF, DALTON NDB). Minimum altitude for the approach in that area was 3000 feet. No preimpact part problems were found during the investigation. Airport elevation was 1194 feet. Radio transcripts indicated the crew were getting a weak signal from the DALTON NDB. Although not a required navaid, CHESTER VORTAC was depicted on the approach chart as an additional source to id the FAF, but was notamed as out-of-svc. The pilot did not obtain notams before flight.

The pilot experienced inadequate left engine manifold pressure during a takeoff attempt at Newport. The takeoff was aborted and afterwards the pilot decided to ferry the aircraft to New Bedford for inspection. The engine were restarted and operation was good. The flight to New Bedford was without incident until the aircraft was on a two miles final to runway 05 at this time the left engine stopped while the pilot attempted to feather the engine, both the engine and part of the left wing caught on fire. The pilot continued to the airport with the flaps and gear down and a speed at 125 mph. The pilot stated he was in a good position to land when he heard a loud bang which he described sounded like a cable. The aircraft entered a 25° left bank. He leveled the wings by reducing right engine power. Collision with trees to the left of the runway occurred afterwards. Examination of the aircraft disclosed that the left engine exhaust manifold header assembly, which is connected to the turbocharger, was cracked along a weld seam. Also revealed was that the aileron cables that are routed behind the left engine were burned to separation. Both occupants were injured.

During IFR flight at 12,000 feet both aircraft vacuum pumps failed. Aircraft descended in right turn off radar. Witnesses observed aircraft at low altitude above trees, circle, make steep left turn, climb and descend to ground. The pilot, sole on board, was killed.