CHI99FA047

The airplane collided with the tops of trees during an ILS approach near the middle marker. Witnesses heard the airplane strike the trees and a '...whop, whop, whop sound...' it made as it continued its flight. Other witnesses observed the airplane flying a curved, descending, flight path until the aircraft impacted the ground. Visibility was reported as 1/2 mile at the airport. The on-scene examination revealed no airframe or engine anomalies that would prevent flight. A section of the right propeller and other pieces of airframe were found along the approach path after initial impact with trees. The trees along the flight path were about 30 to 60 feet high. The tops of the taller trees were broken or had fresh cut marks on their limbs. The pilot's blood alcohol level was 216 (mg/dL, mg/hg).

History of flight

On December 4, 1998, at 2045 eastern standard time (est), a Piper PA-31-350, N59902, piloted by an airline transport pilot, was destroyed during a collision with trees, and a subsequent impact with the ground and a post-impact fire. The airplane was flying an instrument landing system (ILS) approach to runway 09R at the Pontiac/Oakland County International Airport, Pontiac, Michigan. The positioning flight was operating under the provisions of 14 CFR Part 91, and was operating on an instrument flight rules (IFR) flight plan. The pilot was fatally injured. The flight departed Lansing, Michigan, exact time unknown.

The pilot of N59902 contacted the Pontiac /Oakland county International Airport's air traffic control tower local controller (local control) at 2044:08 est. At that time the pilot said his airplane was "...established on the ILS." The local controller advised the pilot of the altimeter setting and advised the pilot that "...several aircraft have reported they can see the approach lights but it's real tough finding the runway lights." At 2044:34 the pilot said he would "...check it out for [the local controller]." The local controller gave N59902's pilot the runway wind conditions at 2044:36. The pilot's last transmission was, "Roger that nine oh two." This transmission was made at 2044:42. At 2048:13 the local controller asked N59902's pilot, "Navajo niner zero two you on the ground safely." There were no other transmissions from the pilot of N59902.

A witness near the accident site said he heard airplanes "...coming in for... landing, heading east." He said he heard one airplane coming closer and "...heard it hit something... the engine continued to run with a whop, whop, whop sound, as if the propeller struck something. This sound continued for about 3-5 seconds then the plane crashed with a bright orange glow lighting up the sky." A second witness confirmed this witness' statement. Other witnesses observed the airplane flying a curved flight path before impacting the ground.

Personnel information

N59902's pilot received his airline transport pilot certificate on November 19, 1997. He obtained a first class medical certificate on November 9, 1998. There were no limitations on his medical certificate. The pilot passed a 14 CFR Part 135.297 pilot-in-command instrument proficiency check on September 28, 1998, while piloting a Piper PA-34-200T.

According to records provided by the pilot's employer, the pilot information sheet showed the pilot had a total and pilot-in-command time of 1,700 and 1,000 hours respectively. Company pilot records showed the pilot did not fly on December 3, 1998. The company flight records are appended to this report.

Aircraft information

N59902's maintenance records showed it had an annual inspection on August 31, 1998, with a total airframe time of 7,758.9 hours. N59902's left and right engines' had 132.6 and 150.8 hours respectively since overhaul at the annual inspection. The two cockpit altimeters were pressure tested on October 1 and 6, 1997, as required by 14 CFR Part 91.411. The transponder was tested as required by 14 CFR Part 91.413 on September 30, 1997. Excerpts of the maintenance records showing these tests are appended to this report.

Wreckage and impact information

N59902's wreckage was about one nautical mile west, southwest of runway 09 Right's approach threshold. The impact area was an empty field behind single-family homes. Small trees located about 30 to 50 feet north and northeast of the ground scars north end had branches that were cut at angles between 10 and 20 degrees to the branches' bark surface. Examination of the branches cut surfaces revealed they were moist and flexible.

Impact scars and craters showed the airplane was on an approximate 290 degree heading. The middle crater was about 20 inches deep and had various-sized pieces of plexiglas and what were airframe components that were crushed and torn. The pilot cockpit entrance door was located about 15 feet south of the center crater. The wreckage was positioned about 40 feet southeast of the impact scars and craters. Its heading was 360 degrees. A site drawing is appended to this report.

The airframe was burnt from the empennage forward. The only recognizable airframe components were the empennage, the left and right wing's outboard sections, and the right aileron. The outboard section of the right wing was found about 20 feet east of the burnt airframe. Both wing sections were also fire damaged. The right aileron was found about 40 feet northeast of the burnt airframe. The leading edges of both outboard wing sections were crushed aft.

The left stabilizer and elevator's tips were bent down about 30 degrees. The bend began at the elevator's outboard hinge point. The tip of the vertical stabilizer was bent about 10 degrees to the right. The rotating beacon assembly that is located on the tip was missing.

The left and right engine's cylinders had thumb compression when the crankshafts were rotated. Cylinder number six on the right engine was the exception. Thumb compression was not obtained on this cylinder. The left engine vacuum pump's rotor and vanes were intact. The right engine's vacuum pump's rotor was cracked and its vanes were intact. The oil, oil screens, and oil filters were clean for both engines. The right and left wing root in line fuel filters were clean. The fuel servos were fire damaged. Both fuel servo fuel screens had small pieces of a white Teflon-like tape strands on them. Other than the strands of tape, the screens were clean.

The right engine's turbocharger system was heat damaged. The waste gate was about 3/4 open and would not move. The turbo charger impeller blade's ends were scored. There were many scratches in the compressor housing. The left engine's waste gate was in the full open position and free to move. The turbocharger's compressor impeller blade tips were bent opposite the direction of rotation. The blades had varying degrees of scoring on their surfaces. The impeller is free to rotate.

The left engine's spark plug electrodes varied in color. Their color varied from a medium gray to dark brown. The right engine's spark plug electrodes varied in color. Their color range went from a medium brown to dark brown. The ignition leads and hoses on both engines were fire damaged. The post-impact fire destroyed the magnetos. The fuel pumps for both engines were fire damaged and could not be rotated.

One of the left propeller's blades suffered heat damage. About 1/2 of this blade was missing. The blade was bent aft. The second blade suffered heat damage. About six inches of its tip was missing. The third blade had fore and aft bending along its span. All the blades and propeller hub were blackened. The spinner dome was crushed over the hub and blade counterweights.

One of the right propeller blades had about 10 inches of its tip separated from the blade. Two pieces of propeller blade found in a wooded area previously described matched the shape of the propeller's end. This blade was bent aft about 30 degrees at the midspan location and had span wise twisting. The second propeller blade was bent aft about 30 degrees at the midspan location. Sections of the leading edge were melted. The third blade was bent forward. Its tip was missing. Chordwise scoring was found on the camber side of the blade.

Medical and pathological information

The Office of the Medical Examiner, Oakland County, Pontiac, Michigan performed an autopsy on the pilot.

The Federal Aviation Administration (FAA), Oklahoma City, Oklahoma, prepared a Forensic Toxicology Fatal Accident Report.

The toxicology report indicated the following results:

* 216 (md/gL, mg/hg) Ethanol detected in Blood * 150 (md/gL, mg/hg) Ethanol detected in Muscle Fluid * 159 (md/gL, mg/hg) Ethanol