N185DG

Substantial
None

Cessna A185F S/N: 18503802

Accident Details

Date
Tuesday, June 16, 1998
NTSB Number
ANC98LA074
Location
TALKEETNA, AK
Event ID
20001211X10212
Coordinates
62.449302, -149.790878
Aircraft Damage
Substantial
Highest Injury
None
Fatalities
0
Serious Injuries
0
Minor Injuries
0
Uninjured
3
Total Aboard
3

Probable Cause and Findings

The failure of the right main landing gear leg due to fatigue cracking. A factor associated with this accident is the inadequate inspection procedure specified by the manufacturer.

Aircraft Information

Registration
Make
CESSNA
Serial Number
18503802
Engine Type
Reciprocating
Model / ICAO
A185F C185
Aircraft Type
Fixed Wing Single Engine
No. of Engines
1
Seats
6
FAA Model
A185F

Registered Owner (Current)

Name
TOBOL REED
Address
42620 LOSCHEIDER RD
City
RONAN
State / Zip Code
MT 59864-8859
Country
United States

Analysis

On June 16, 1998, at 1215 Alaska daylight time, a wheel/ski equipped Cessna A185F airplane, N185DG, sustained substantial damage during takeoff from the 6,900 feet msl level of the Kahiltna Glacier, 50 miles northwest of Talkeetna, Alaska. The commercial pilot and the two passengers were not injured. The flight was operated under 14 CFR Part 135 by Douglas Geeting Aviation, Inc., of Talkeetna, as an on demand charter transporting mountain climbers from the Kahiltna Glacier to Talkeetna. Visual meteorological conditions prevailed at the time of the accident, and a VFR flight plan was filed.

The pilot reported to the NTSB Investigator-In-Charge during a telephone interview that during his landing roll on the glacier he heard a "bang." He stated that he inspected the airplane and skis, and found no damage. During acceleration for takeoff from the glacier, after reaching 45 knots, the right ski separated from the airplane, the airplane swerved right, and both wings contacted the snow.

Inspection of the fractured landing gear leg at the NTSB metallurgical laboratory on July 13, 1998, revealed multiple site fatigue cracking at the location of both landing gear attachment bolt holes.

The airplane had accumulated 6,561 hours of operation at the time of the accident. There is no established life limit (hours or cycles) for Cessna 185 landing gear legs. There is no inspection requirement or procedure to detect fatigue cracks in the landing gear legs except for a visual inspection conducted during 100 hour and annual inspections. No nondestructive inspection technique requiring removal of wheels or skis, or removal of paint coatings to facilitate crack detection, had been specified by the manufacturer or FAA at the time of the accident.

Data Source

Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# ANC98LA074