Incident Overview

Date: Sunday 8 January 1995
Aircraft Type: Cessna 208 Caravan I
Owner/operator: A. McVinish
Registration Number: VH-MMV
Location: Toogoolawah Airport, QLD – ÿ Australia
Phase of Flight: Approach
Status: Substantial, repaired
Casualties: Fatalities: 0 / Occupants: 1
Component Affected: Aircraft EngineAircraft Engine
Investigating Agency: BASIBASI
Category: Accident
An aircraft engine lost power during final approach, resulting in a short landing due to a steep spiralling descent. The pilot exceeded bank limits during this descent, likely due to low fuel levels. A fuel flow interruption, originating from the wing cells to the collector tank, caused the engine flameout.An aircraft engine lost power during final approach, resulting in a short landing due to a steep spiralling descent. The pilot exceeded bank limits during this descent, likely due to low fuel levels. A fuel flow interruption, originating from the wing cells to the collector tank, caused the engine flameout.

Description

The pilot reported that the aircraft engine lost power when he made a power adjustment whilst on final approach. The propeller feathered and the aircraft landed short of the runway on unprepared ground, incurring substantial damage. The aircraft was being used for parachute drops from 14,000ft. When the last parachutist left the aircraft, the pilot would place the aircraft in a steep spiralling descent. During this type of descent, the pilot was known to exceed the 60 degree angle of bank limits for the aircraft. Low fuel states were reported as being used for the paradrops. It is probable that the fuel flow from the wing cells to the collector tank (18 litre capacity) was interrupted during the descent and air entered the system. The fuel pump was not designed to operate in other than a full collector tank. As a result it is likely that the fuel flow to the engine was interrupted, resulting in engine flame out.

Primary Cause

Fuel flow interruption from the wing cells to the collector tank during the descent and subsequent engine flameout.Fuel flow interruption from the wing cells to the collector tank during the descent and subsequent engine flameout.

Share on:

Leave a Reply

Your email address will not be published. Required fields are marked *