CESSNA TU206G

Full Narrative

On March 19, 2011, about 1115 Pacific daylight time, a Cessna TU 206G, N6169Z, sustained substantial damage to the forward portion of the fuselage and empennage during a forced landing following a loss of engine power while in the airport traffic pattern at the Pierce County Airport - Thun Field (PLU), Puyallup, Washington. The certified flight instructor and commercial pilot receiving instruction sustained minor injuries. The airplane was registered to the Civil Air Patrol and operated as a local instructional flight under the provisions of 14 Code of Federal Regulations Part 91. Visual meteorological conditions prevailed and a company visual flight rules flight plan had been activated for the local flight that departed from Puyallup.

A representative from the operator reported that the pilots performed the pre-landing checklist, and switched the fuel selector to the right tank position and activated the auxiliary fuel boost pump while on the left midfield downwind for landing on runway 34. Shortly thereafter, while turning from base leg to final, at 900 feet mean sea level (msl), the airplane began to sink and full engine throttle was applied. The engine subsequently did not power up, and the airplane collided with up-sloping terrain approximately 400 feet short of the approach end of the runway. The nose landing gear collapsed, and the airplane subsequently nosed over.

The airplane was equipped with a Continental TSIO-520-CCM engine. The engine is turbocharged, fuel injected and equipped with a constant speed propeller. The airplane’s fuel system incorporates a 2-stage electric auxiliary fuel boost pump. The fuel pump is placarded “emergency” and “start” and is utilized for engine starts and engine related emergencies.

The manufacturer’s approved checklist for the airplane denotes, in part, the following:

DESCENT
1. Power – AS DESIRED
2. Auxiliary Fuel Pump Switch - OFF

BEFORE LANDING
1. Fuel Selector valve – FULLER TANK
2. Auxiliary Fuel Pump Switch - OFF

A representative from the engine manufacturer reported that operating the auxiliary fuel boost pump at a low engine power setting would “flood” the engine and result in a loss of engine power.

Postaccident examination of the airframe and engine revealed no preaccident mechanical malfunctions or failures that would have precluded engine operations. An engine examination report is contained in the public docket for this case file.