N1249D

Substantial
Minor

CESSNA 170AS/N: 20121

Accident Details

Date
Wednesday, September 11, 2024
NTSB Number
CEN24LA354
Location
Marshall, IN
Event ID
20240912195111
Coordinates
41.479367, -86.054200
Aircraft Damage
Substantial
Highest Injury
Minor
Fatalities
0
Serious Injuries
0
Minor Injuries
1
Uninjured
0
Total Aboard
1

Probable Cause and Findings

The fatigue fracture of the No. 6 piston connecting rod, which resulted in a loss of engine power.

Aircraft Information

Registration
N1249D
Make
CESSNA
Serial Number
20121
Engine Type
Reciprocating
Year Built
1951
Model / ICAO
170AC170
Aircraft Type
Fixed Wing Single Engine
No. of Engines
1

Registered Owner (Historical)

Name
STOKES DAVID
Address
905 ACORN DR
Status
Deregistered
City
SLEEPY HOLLOW
State / Zip Code
IL 60118-2687
Country
United States

Analysis

On September 11, 2024, at 1212 eastern daylight time, a Cessna 170A, N1249D, was substantially damaged when it was involved in an accident near Marshall, Indiana. The airline transport pilot received minor injuries. The airplane was operated under Title 14 Code of Federal Regulations Part 91 as a personal flight.

The pilot stated that during cruise flight at 3,500 ft above mean sea level and 120 mph, there was a loud repeating banging sound and a loss of engine power. Engine oil temperature increased to 220o F, engine oil pressure decreased below 35 psi, and engine oil sprayed onto the airplane’s windshield. As the airplane descended, the pilot looked for an area to perform a forced landing. The pilot planned to land the airplane on a short open area but overshot the open area because he could not dissipate enough of the airplane’s energy. He then landed the airplane on a corn field where it contacted the corn, nosed over, and impacted the ground. The airplane sustained substantial damage that included damage to the wings, vertical stabilizer, and rudder.

Postaccident examination of the engine revealed a hole in the crankcase above the No. 6 cylinder assembly. The No. 6 connecting rod was fractured near its base.

Metallurgical examination of the No. 6 connecting rod revealed fracture features that were consistent with fatigue cracking. The cracks initiated at multiple locations on the outer surface opposite the inner bearing surfaces that mated the crankshaft. These cracks propagated through most of the rod yoke arm cross section until the remainder subsequently fractured from tensile overstress. All other fracture surfaces were consistent with overstress fracture.

Maintenance records showed the engine received a major overhaul on September 27, 2010. The last annual inspection on the engine was dated March 1, 2024, and the engine had 572.7 hours since the major overhaul. Continental manual M-O Ch. 6-3, Table 6-1 states, C125, C145 series and O-300-A,B,C,D engines have a time between overhauls of 1,800.0 hours or 12 years, whichever comes first.

Data Source

Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# CEN24LA354