Incident Overview
During a practice forced landing descent, the airplane experienced a total loss of engine power. The pilot, who owned and operated the aircraft, reported that no suitable landing area was within gliding distance. Consequently, the pilot executed a landing in the rough terrain of a dry wash, which resulted in both main landing gear being sheared off.
Post-Accident Examination
After the aircraft was recovered, an examination was conducted. Investigators found that a clamp, which had been welded onto a bracket secured to the engine case, had broken. This clamp and bracket assembly supported the throttle cable. The break occurred at the weld, and when it failed, movement of the cockpit throttle control had no effect on the engine's revolutions per minute (rpm).
Component Details
The pilot described the weld as having been "bad." The component was not a Piper-manufactured part, indicating it was a non-original or aftermarket component. The failure of the weld directly prevented the throttle from controlling engine power, leading to the loss of engine power.
Conclusion
The investigation determined that the engine power loss was caused by a broken weld on the throttle cable support assembly. No other contributing factors were identified in the source.