Pilot Debrief

CESSNA 182A near Safford, AZ — 2016-11-24

Final reportWPR17LA038
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Date
2016-11-24
Location
Safford, AZ, USA
Airport
SAD
Aircraft
CESSNA 182A
Registration
N6077B
Category
Airplane
Highest injury
None
Fatalities
0
Phase of flight
Cruise

Probable cause

The total loss of engine power due to the failure of the No. 5 piston, piston pin, or connecting rod assembly for reasons that could not be determined due to the severity of the post fracture damage.

NTSB narrative

The commercial pilot reported that, during cruise flight, he noticed the oil pressure begin to fluctuate and he decided to return to the departure airport. As the airplane neared the airport, the engine experienced a total loss of power, and the pilot initiated an off-airport forced landing. During the landing roll, the airplane struck two dirt berms and the nose landing gear collapsed. Postaccident examination of the engine revealed that the connecting rods, pistons, piston pins, bearings, and bushings in cylinder Nos. 5 and 6 exhibited numerous fractures and severe deformation. Due to the widespread postfracture damage to many of the fracture surfaces, it was not possible to determine which component fractured first. The No. 5 cylinder connecting rod and cap were severely deformed and battered. The piston pin had fractured in multiple places, and the underside of the piston exhibited gouging consistent with impact from adjacent components. In addition, the skirt and pin boss of the piston had fractured in multiple locations. The features on these fracture surfaces were generally consistent with having fractured in and around the pin boss; therefore, the likely initial point of failure in cylinder No. 5 was either the piston pin boss, the piston pin, or the pin side of the connecting rod. Based on the degree of damage observed, the components in the No. 5 cylinder likely began to fracture first, followed by fractures in the No. 6 cylinder.

Analysis

Primary failure mode
Engine power loss
First missed decision gate
Pilot could have landed immediately after oil pressure fluctuations were noticed.

NTSB coding

Evidence available

  • 6 docket documents
View NTSB final reportView NTSB docket

Docket documents6

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