New Jersey

On January 16, 1989, Machen nacelle mounted induction air intercoolers were installed on N6894Y. On December 14, 1989, an annual inspection was performed, and a Machen superstar i-680 kit was installed. On December 21, 1989, N6894Y was at 6,000 feet when the pilot reported a problem with the right engine. The pilot reported a fire in the right engine. A couple of minutes later, he radioed he could not shut down the right engine. At 1034:37 the pilot advised his 'right engine just tore off' and that he was 'in a spin heading down.' The exhaust tailpipe of the left turbocharger on the right engine was found to have separated. Metallurgical examination revealed the tailpipe failed due to fatigue cracking. Records showed that part I of piper service bulletin 920 (engine tailpipe inspection) had been completed, while part II (addition of fire detection system) had not been accomplished due to the lack of available kits. The pilot, sole on board, was killed.

The aircraft was on final approach to runway 30 at Somerset airport, Somerville, New Jersey when there was a loss of power of the right engine. The pilot raised the landing gear and flaps, and the aircraft rolled to the right, descended toward the ground and crashed. The fuel selector valve to the right wing tank was in the closed position. The right engine magnetos were defective. All four occupants were injured, two seriously.

The crew was positioning the aircraft in preparation for a revenue flight and executing a non-directional beacon (NDB) approach to runway 05. The captain reported that the copilot was flying the aircraft. However, the captain stated that he took control of the aircraft during the approach and made some control corrections before returning control of the aircraft to the copilot. Radar data indicated that aircraft control was erratic throughout the approach and that the airspeed and descent rates were high (3,000 fpm sink rate) shortly before the accident. The aircraft struck a fence short of the runway and impacted the ground. The captain said he realized the aircraft was drifting left of course but did not correct it. He said he told the copilot to add power twice during the approach. The copilot's training history indicated difficulty in control, scan of instruments, and with instrument procedures. Company management described the captain as passive and the copilot as aggressive. Supervision of training and operations by management and surveillance of the company by the FAA was considered inadequate by NTSB.

Witnesses reported a normal takeoff. Radar indicated the aircraft turned right as cleared and began cruise at 1900 feet, heading northwest at 235 knots. 65 seconds after calling clear of the control zone the aircraft's radar track ended. The aircraft was fragmented by the impact with all flight control surfaces and aircraft extremities found at the impact site. Pitch trim was found in the normal cruise setting with gear, flaps, and spoilers in the retracted position. Examination of the engines indicated operation at impact. Aircraft struck the terrain in approx 80° nose down, wings level attitude and heading opposite to the previous direction of flight. In flight simulator tests, with the aircraft initially in level flight at 1,900 feet and then rolled inverted and the pitch control moved aft, the aircraft attitude was similar to the attitude at impact. There were two unauthorized passengers on board, one was the copilot's wife. The impact point was in a very small region of uncontrolled airspace very near the copilot's and relative's homes. The copilot was new to jet operations. The aircraft departed with several discrepancies uncleared. All four occupants were killed.

The aircraft disappeared from radar at approximately 1 mile final on a night ILS runway 13 approach. Radar data indicated that the aircraft completed almost 180° of turn prior to disappearing. The aircraft crashed in a heavily wooded area. No evidence of a preexisting failure on the engines or airframe was found. When the flying history of the pilot was examined, the hours presented on his resume exceeded his log book and his log book hours could not be totally verified. The copilot did not have an instrument rating. The pilot that preceded the accident aircraft on the approach said he experienced moderate turbulence, windshear and that the approach lights were very distracting. The pilot had received a weather briefing which included wind shear and moderate turbulence. All three occupants were killed.

During the takeoff roll witnesses observed the aircraft swerve from left to right with the engine(s) 'missing' or intermittent. The aircraft lifted off and climbed to approximately 50 feet agl and continued across a waterway in a left turn with the landing gear extended. The aircraft pitched up and rolled left wing down into the water. Examination of the engines revealed a cracked coil in the left magneto of the right engine. No other mechanical malfunction/failure could be determined. The pilot, sole on board, was killed.

During takeoff ground run, at a speed of 95 knots, the pilot pulled the control wheel back to lift off. The control wheel, according to the pilot, would not go back more than about 2 inches; which is less than half the normal full aft travel. The aircraft reached a speed of about 105 knots and had traveled more than half of the runway length when the pilot aborted the takeoff. The pilot was unable to stop the aircraft on the runway. The aircraft went off the runway and subsequently collided with an occupied car that was on a nearby street. The investigation revealed the left side VOR indicator had loosened from its mounting clamp on the instrument panel and it was laying against the control wheel tube, behind the instrument panel, limiting the control wheel to 2.5 inches of rearward travel. The pilot stated that he removed the control lock before engine start and performed a flight control check before takeoff. All four occupants were injured while on person in the car hit by the aircraft was killed.

A Dassault Falcon 50 jet (N784B) and an Air Pegasus Piper PA-28-181 Archer (N1977H) collided about 1500 feet over the towns of Fairview and Cliffside Park, New Jersey, USA. The Falcon 50 was cleared for a standard instrument approach procedure in visual meteorological conditions and was in a left turn to position itself on the downwind leg to runway 19 at the Teterboro Airport, and the PA-28 was transiting the airport traffic area from west to east when they collided. The accident occurred 4 1/2 miles east-southeast at the edge of the airport traffic area in visual meteorological conditions. Both airplanes had been in radio contact with the Teterboro control tower. The flightcrew, the only occupants aboard the Falcon 50, and the pilot and two passengers onboard the PA-28 were killed. The Falcon 50 crashed into an apartment building killing one resident and seriously injuring two bystanders.

The copilot begun takeoff with 2,700 rpm and 52 to 53.5' of manifold pressure (mp). Water injection was not used although 12 gallons was available. At 150 to 250 feet agl, the left engine lost power and the left propeller auto feathered. The captain took control and took action to verify left engine feathering. Neither pilot moved any of the other engine controls. A turn was initiated to return to the airport, but the aircraft began losing speed and altitude. Subsequently, it crash landed in a partly wooded area short of an open field and burned until firefighting personnel arrived. The impeller was demolished by fire, but evidence of debris from the impeller was found in the left engine intake and on top of its #3 and # 11 piston. The company's stated policy was to use water (wet takeoff), except when precluded by mechanical malfunction or lack of additional fluid; however, 4 dissimilar power charts were found in the aircraft. Takeoff weight was 38,670 lbs. Performance manual showed aircraft capable of 420 fpm climb with 12° of flaps, one prop feathered, landing gear up, dry power (no water). Max power setting was 2,700 rpm and 56' mp for dry takeoff; 2,800 rpm and 59.5' mp for wet takeoff. Both pilots were seriously injured.

The two atp rated pilots were en route back to their home base airport flying on an IFR flight plan in actual instrument weather conditions. Communications with ATC controllers was normal. During a night localizer approach into Millville municipal airport, an ATC specialist observed the aircraft passing through the localizer track and issued a vector for re-interception. The aircraft was subsequently observed tracking inbound on course. The pilot reported crossing the om. This was the last transmission heard from the pilot and was routine. The aircraft crashed into a wooded area just beyond the om and was destroyed in a post impact fire. Post accident examination of the wreckage revealed evidence to indicate the left engine was producing less power than the right engine at impact. Both occupants were killed.