Cessna 205 N8464K

Summary

On 2 April 1999 at about 22:25 local time, a Cessna 205 registered N8464K was involved in an accident near Edison, Washington, United States. One person was on board and one had minor injuries. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

2 April 1999 at 22:25

Classification

Accident

Location

Edison, Washington, United States

Coordinates

48.5595, -122.4396

Aircraft

Cessna 205

Registration

N8464K

Category

Airplane

Engines

1

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Personal

Phase of flight

Not recorded

Route

Bellingham → Unknown

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

SEA99LA046

1 person had minor injuries.

A total loss of engine power due to fatigue of the number six crankcheek resulting in crankshaft separation, and the lack of suitable terrain. Contributing factors were the sign and the ditch.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

Shortly after takeoff, and while cruising at 3,000 feet (mean sea level) over Samish Bay, the Cessna 205's Continental IO-470-S engine ceased developing power. With the propeller continuing to windmill, and only muddy fields available, the pilot initiated a forced landing to a north/south paved road at the south end of the bay. The pilot, observing power lines along the west side of the road, landed along the east side. During the landing roll the left wing impacted a sign. With the pilot being unable to maintain directional control of the aircraft following the sign impact, the aircraft departed the left side of the road into a deep ditch. Post-crash examination of the engine revealed that the crankshaft had separated at the number six cheek. Metallurgical examination of the crankshaft revealed that a large area in the central portion of number six cheek fracture surface displayed a smooth texture and contained multiple crack arrest features, characteristic of fatigue progression originating at the outboard flat surface of the crankcheek, approximately at the mid point between the horizontal centerlines for the main and rod journals. No further determination could be made regarding the initiating condition of the fatigue due to post-separation heat and mechanical damage to the fracture features.

Quoted verbatim from the NTSB record.