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N6749S accident description

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Crash location 35.716670°N, 83.600000°W
Nearest city Gatlinburg, TN
35.714259°N, 83.510164°W
5.0 miles away
Tail number N6749S
Accident date 11 Feb 1995
Aircraft type Beech 60(AF) Beech B60(NTSB)
Additional details: None

NTSB Factual Report


On February 11, 1995, at 1327 eastern standard time, a Beech B60, N6749S, collided with mountainous terrain at the 3500 foot level of Cove Mountain, seven miles west of Gatlinburg, Tennessee. The personal flight operated under the provisions of 14 CFR Part 91, with no flight plan filed. Instrument weather conditions prevailed at the time and location of the accident site. The aircraft was destroyed by impact forces and a post-impact fire; the commercial-rated pilot was fatally injured in the accident. The flight departed Knoxville, Tennessee, at 1314 hours.

At 1303, the pilot of N6749S radioed Knoxville clearance delivery, and requested a Visual Flight Rules,(VFR), clearance to Gatlinburg at 3500 feet. The pilot was issued a clearance as requested. After takeoff, radar coverage was provided until the flight was four miles southwest of Gatlinburg.

AT 1324, the pilot of N6749S radioed Knoxville Approach Control and requested the ILS approach to Knoxville. Within two minutes of the initial radio call to approach control, the pilot requested immediate vectors. The controller radioed that the airplane was in radar contact, twenty miles southeast of Knoxville. The controller requested the flight's altitude, but there was no response from the pilot. The approach controller issued vector information, and instructed the pilot to maintain visual weather conditions. At 1326:30, radar and radio contact were lost with N6749S.

A hiker in the vicinity of the accident site recalled hearing an airplane overhead. He stated that the sound of the aircraft engines continued until the airplane impacted the trees.


Information on the pilot is included in this report at the data field labeled "First Pilot Information." The pilot's flight logs were not recovered for examination.


Information on the airplane is included in this report at data field labeled "Aircraft Information."


The accident site was located at the 3500 foot level of Cove Mountain and 7 miles west of the city of Gatlinburg. Examination of the accident site revealed that aircraft debris was scattered on a 210 degree magnetic heading, over an area 650 feet long and 75 feet wide (see attached wreckage diagram). A review of the profile view of the accident site revealed that the wreckage debris was scattered over rolling terrain and a small body of water. There was a narrow swath through the trees at the initial part of the wreckage path. The wreckage path examination discovered that the post-impact fire was wide spread but mostly concentrated in the vicinity of the main wreckage.

Debris from the right wing assembly was scattered on the ground and lodged in trees at the initial part of the wreckage path. Approximately 210 feet southwest of the initial collision with the trees, additional debris from the airframe, such as the baggage door, was located on the upslope of another ridge. About 30 feet upslope from the baggage door were pieces of the right propeller assembly. One of the three propeller blades was torn from the hub assembly and was located 37 feet northwest of the propeller hub assembly. Examination of the right propeller assembly revealed that the blades had sustained twisting and impact damage.

Debris from the nose section of the airplane was located 21 feet southwest of the propeller assembly. The left horizontal stabilizer was also located in the immediate vicinity of the debris from the nose section. A piece of the vertical fin was found an additional 20 feet southwest.

A section of the right engine cowling was found 121 feet southwest of the vertical fin debris, under a freshly felled tree. The right engine assembly was located 3 feet southwest of the right engine cowling. Both components had sustained extensive impact damage. Several engine accessories were separated from their normally installed positions.

The main wreckage was located approximately 25 feet southwest of the right engine assembly. The fire damaged fuselage section and empennage assembly rested over a felled tree. The wreckage examination disclosed that the airframe center section sustained extensive fire damage. Flight and navigational instruments were also destroyed in the post-impact fire. Portions of both fire damaged wing assemblies, with the main landing gear attached, were attached to the airframe.

The left engine assembly rested adjacent to a tree 15 feet southwest of the empennage section. The propeller assembly had separated from the engine assembly and was not located at the accident site.

Both engines were removed from the accident site for further examination. The follow-up examination consisted of a complete disassembly of both engines. Both teardowns failed to disclose a mechanical malfunction or any component failure. The external and internal examinations also determined that impact damage to both engines was similar. The right engine sustained crankcase damage which prevented the rotation of the crankshaft. The left engine rotated freely and internal rotational action was established.

The left propeller was never located. Examination of the propeller hub extension retention bolts revealed that they failed in overload. The failure mode of the propeller hub extension bolts for the right propeller was also in overload.


Visual weather conditions prevailed at the time of the accident at the reporting facility. According to witnesses in the immediate area of the accident site, clouds obscured the tops of the mountain. Weather information is contained in this report at the data field labeled "Weather Information."


The postmortem examination of the pilot was performed by Dr. C. Blake at the Office of The Forensic and Pathological Office In Morristown, Tennessee, on February 13, 1995. The reported cause of death was multiple trauma secondary to the aircraft accident. The toxicological examinations revealed a carboxyhemoglobin saturation level of 2 % in liver samples. The liver samples also contained 0.22 mg/kg of chlorpheniramine(see attached toxicological report).


The aircraft wreckage was released to:

Mr. Kurt Brewer (insurance adjustor) 259 Spencer RD St. Peters, MO 63376

NTSB Probable Cause


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