N38293

Unknown
None

PIPER PA-28-181 S/N: 28-7790537

Accident Details

Date
Friday, September 22, 1995
NTSB Number
ANC95IA173
Location
GUSTAVUS, AK
Event ID
20001207X04398
Coordinates
58.419410, -135.779754
Aircraft Damage
Unknown
Highest Injury
None
Fatalities
0
Serious Injuries
0
Minor Injuries
0
Uninjured
1
Total Aboard
1

Probable Cause and Findings

fatigue failure of the propeller blade due to previous foreign object damage.

Aircraft Information

Registration
Make
PIPER
Serial Number
28-7790537
Engine Type
Reciprocating
Model / ICAO
PA-28-181 P28A
Aircraft Type
Fixed Wing Single Engine
No. of Engines
1
Seats
4
FAA Model
PA-28-181

Registered Owner (Current)

Name
L & A BENNETT SECOND FAMILY L P
Address
1204 N 42ND PL
City
RENTON
State / Zip Code
WA 98056-2170
Country
United States

Analysis

On September 21, 1995, at 1735 Alaska daylight time, a wheel equipped Piper PA-28-181 airplane, N38293, registered to and operated by L.A.B. Flying Service of Juneau, Alaska, experienced an in-flight separation of 4.5 to 5 inches of a propeller blade tip during climbout from Gustavus, Alaska. The mail flight, operating under 14 CFR Part 135, was departing Gustavus on a company visual flight rules flight plan and the destination was Juneau, Alaska. The commercial certificated pilot, the sole occupant, was not injured and there was no damage to the airplane.

According to the pilot, he was on climbout after taking off from Gustavus when the engine and airplane began to shake. He reduced the power to 1300 RPM and returned to Gustavus without further incident.

Ground examination of the airplane's propeller showed that approximately 4.5 to 5 inches of one propeller blade had separated. The separated portion of the blade was not recovered. The propeller was submitted to the NTSB Materials Laboratory Division for metallurgical examination. The examination showed that about 60 percent of the blade cross section contained fracture features indicative of fatigue cracking. The fatigue cracking emanated from an origin area located on the leading edge of the blade. The origin area contained a nick. The entire length of the nick could not be determined because the separated piece was not recovered. However, measurements showed that the portion of the nick on the propeller blade was approximately 0.35 inch long. A sectioned piece of the propeller blade was tested for hardness and material composition, and was found to meet the design specifications.

Data Source

Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# ANC95IA173