In–Flight Disoriented Pilot Aircraft Goes Into A Spin And Breaks Up
On September 26, 2007, at 1033 eastern daylight time, a Piper PA-32R-301T, N8341G, sustained substantial damage when it impacted terrain about 7 miles west of Defiance, Ohio. The pilot, the sole occupant, received fatal injuries.
The 14 Code of
Federal Regulations Part 91 flight departed the Campbell Airport (C81),
Radar track data indicated that the airplane was in cruise flight about 7,000 feet mean sea level (msl). At 1032:27, Toledo Approach Control instructed the pilot to descend from 7,000 feet to 3,000 feet msl, and the pilot acknowledged the descent instructions at 1032:31.
The Toledo Approach Control's last radar contact with the airplane was at 1032:53, and the airplane was about 6,500 feet msl. Toledo Approach Control reported that the pilot made no distress call and he did not indicate that the airplane was experiencing any mechanical difficulty.
crew was installing a drainage culvert on
They could hear the airplane when it was in the clouds for about a minute with the sound of the engine getting louder and louder. Two of the witnesses observed the airplane when it descended out of the clouds. The airplane was traveling from the southeast to the northwest. The airplane was in about a 45-degree nose down attitude as it was descending, and the airplane was spinning rapidly.
The oscillating engine noise grew increasingly louder as it descended, and it appeared that the airplane was missing part of one of its wings. The witnesses reported that the airplane suddenly nosed straight down and impacted the ground in a steep, nose down attitude.
The pilot was a 57-year-old private pilot with single-engine and instrument airplane ratings. He held a third-class medical certificate that was issued in December 2006. He had a total of about 1,949 hours of flight time. He completed a biennial flight review on March 4, 2007. He had flown about 52 hours in the accident airplane in the last 90 days, and 17 hours in the accident airplane in the last 30 days.
The airplane was a single-engine Piper PA-32R-301T with a Lycoming 300-horsepower TIO-540-S1AD engine. The engine was overhauled on August 15, 2006, and had about 255 hours since the major overhaul at the time of the accident. The last annual maintenance inspection, conducted on August 17, 2007, indicated that the airplane had a total time of 3,720 hours. The estimated total time on the airplane at the time of the accident was about 3,747 hours.
Weather Service (NWS) Surface Analysis Chart for 1100 depicted a cold
front to the west of the accident site. The station models on the
Surface Analysis Chart closest to the accident site depicted a cyclonic
shift in the wind between
Defiance Memorial Airport (DFI) was located approximately 5 miles northeast of the accident site. The airport was equipped with an Automated Surface Observation System (ASOS) and reported the following weather conditions surrounding the time of the accident:
DFI weather observation at 0953, automated, wind variable at 3 knots, visibility 6 miles in mist, ceiling broken at 1,000 feet, overcast at 1,400 feet, temperature 21 degrees Celsius (C), dew point temperature 19 degrees C, altimeter setting 30.01 inches of Mercury (Hg). Remarks: automated observation system, ceiling 700 variable 1,300 feet, sea level pressure 1015.7-hectopascals (hPa), temperature 21.1 degrees C, dew point 19.4 degrees C.
DFI weather observation at 1011, automated, wind variable at 3 knots, visibility 6 miles in mist, few clouds at 800 feet, ceiling broken at 1,400 feet, overcast at 2,200 feet, temperature 22 degrees C, dew point temperature 19 degrees C, altimeter setting 30.01 inches of Hg. Remarks: automated observation system.
DFI weather observation at 1053, automated, wind from 320 degrees at 9 knots, visibility 10 miles, ceiling broken at 1,000 feet, overcast at 3,600 feet, temperature 21 degrees C, dew point temperature 18 degrees C, altimeter setting 30.02 inches of Hg. Remarks: automated observation system, ceiling 900 variable 1,300 feet, sea level pressure 1016.3-hPa, temperature 20.6 degrees C, dew point 18.3 degrees C, 3-hour pressure tendency risen 0.8-hPa.
The Geostationary Operations Environmental Satellite number 12 (GOES-12) data depicted an enhanced area of clouds over northeastern and southern Ohio associated with cumulonimbus type clouds to the west and southwest of the accident site, with a general northeast-to-southwest band of low- and mid-level clouds extending over the region with the accident site located near the leading edge of the band of mid-level clouds. The GOES-12 depicted that a band of cumulus clouds was over or in the immediate vicinity of the accident site at the time of the accident.
The closest NWS Weather Surveillance Radar-1988, Doppler (WSR-88D) was located approximately 55 miles west of the accident site. The WSR-88D base reflectivity images depicted a narrow line of echoes oriented in a northeast to southwest direction developing and moving eastward through the period.
The line moved across DFI at 1019. At 1031, reflectivities of 25 to 30 decibels (dBZ) (very light - light to moderate turbulence and with possible lightning) were over the flight track of N8341G, with the maximum echoes of 45 dBZ (very strong turbulence with possible lightning) located 5 miles southwest of the accident site.
The next scan at 1037, depicted the line of echoes immediately east of the accident site with an echo of 35 dBZ (light to moderate) located 1-mile east-southeast, and a cell of 50 dBZ ("intense" with severe turbulence, lightning) located approximately 3 miles south-southwest of the accident site. The images between 1031 and 1037 showed echoes of 25 to 35 dBZ or moderate intensity echoes along the flight path.
At 1031, the echo over the flight track depicted reflectivities of less than 5 dBZ (weak), with the maximum echo of 40 dBZ (strong) located approximately 4 miles southwest. The WSR-88D spectrum width product at 1032:18 depicted an area of shear between 12 to 24 knots along the last know position of the accident airplane and the accident site, and it indicated significant wind velocities along the flight track.
impacted the top edge of a drainage embankment that was between a
The crush of the leading edges of both wings and the crush of the fuselage indicated an impact angle that was consistent with 80-degrees nose down, inverted attitude. The leading edges and main spars of both wings were crushed and bent aft. The impact of the wings created a ground scar about 8 - 12 inches deep. The front of the engine and propeller were found about four feet beneath the surface.
The outboard section of the left wing was found about 0.6 nautical miles (nm) from the main wreckage on a 133-degree magnetic bearing. The coordinates of the left wing section were 41 degrees 15.330 minutes north latitude and 084 degrees 27.915 minutes west longitude. Small pieces of the airplane were also found near the left wing section.
The airplane wreckage was removed from the field and taken to a hangar for inspection. Fuel was found pooled in the soil when the engine was extracted from the clay soil. The inspection of the engine revealed that the case halves were separated at the crankshaft flange, and the crankshaft and number 1 connecting rod and journal were exposed.
The crankshaft was bent to the right about 45 degrees. The front end of the camshaft was broken off about 7.5 inches aft of the gear. The impact damage to the number 1 and 2 cylinders exposed both connecting rods. The engine could not be rotated. The dual magneto remained attached to the accessory but was loose at the base and could be rotated.
The left side magneto tower was separated. The aft side of the vacuum pump was separated and the fractured pump vanes were exposed. The remainder of the vacuum pump was removed from the engine and the shear shaft was intact. The fuel servo was fractured at its mount and the throttle and mixture settings could not be determined.
Visual inspection of the propeller revealed that blade "A" exhibited extensive leading edge gouges, blade twist to low pitch, and chordwise scratching. Blade "B" exhibited leading edge gouges near the blade tip and chordwise scratching. Blade "C" was bent forward at its mid-span and it exhibited spanwise scratching.
The fuselage was fragmented. The belly of the aircraft remained attached to the main spar box, which included the rear cabin floor, rear baggage floor and the forward cockpit floor. The instrument panel, including the tee bar, rudder pedal assemblies and the forward cabin door comprised a separate section of the wreckage. All radios and the majority of the instruments were destroyed. The control columns were separated, and all handles on the pilot and co-pilot's control yoke were broken off. The rudder pedal torque tube on the pilot's side was broken in half just outboard of the inboard pedal. The throttle quadrant was pushed forward into the instrument panel. The pilot's attitude gyro was found crushed and broken. The inspection of the gyro's rotor and rotor housing revealed rotational scoring.
The left wing separated from the main spar about 93 inches (at the upper spar cap) and 84 inches (at the lower spar cap) outboard of the wing root. The inboard section of the left wing was crushed aft starting at the wing root leading edge and continued outboard for 93 inches. This section of leading edge was crushed aft and exposed the main spar. The main spar was bent aft 30 degrees starting about 48 inches outboard of the wing root.
The upper spar cap, at the fracture, was bent upwards at about a 45-degree angle. The fracture surface was clean and granular. The lower spar cap, at the fracture, was bent upward at about a 10-degree angle. That fracture surface was also clean and granular. The outboard 108 inches of the left wing was located about 0.6 nm west of the main wreckage.
The outboard 108 inches of the wing broke upwards at the fracture surfaces. They were clean and granular in appearance. Aileron cable continuity was established from the aileron bell crank to the chain and sprocket assemblies in the cockpit.
The right wing remained attached to the fuselage and the main spar box. The leading edge between the wing root and the right main gear was crushed aft. Aileron cable continuity was established from the aileron bell crank to the chain and sprocket assemblies in the cockpit.
The empennage was separated from the fuselage just forward of the rear bulkhead. Elevator cable continuity was established from the balance weight forward to the tee bar assembly in the cockpit. The anti servo trim tab assembly and connecting rod remained attached to the tab and rear bulkhead. The jack screw measured 12 threads or 1 3/8 inches, which equated to a neutral to a slight nose up position. Rudder cable continuity was established between the rudder bell crank and the rudder bar assembly in the cockpit.
An autopsy of the
pilot was conducted at the Lucas County Coroner's Office,
The pilot's third-class medical certificate included a restriction that stated, "Not valid for any class after December 31, 2007." The pilot was required to submit to cardiovascular evaluations at 12-month intervals beginning on December 1, 2007, in order to maintain his medical certificate.
The accident flight was the first leg of an "Angel Flight." Angel Flight provides free air transportation for charitable and medical needs. The pilot was en route to FDY to pick up a patient to transport him/her to a medical facility. The pilot's flight logbook indicated that the pilot had flown about 23 volunteer Angel Flights in the last 3 years.
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