2 fatalities

Engine Exhaust Failure and In-Flight Fire Precede Loss of Control and Crash (N5780M)

Altus, United States of AmericaTakeoff (climb)

On February 6, 1985, a Cessna 402 (registration N5780M) operated by Altus Airlines was involved in an aviation accident near Altus, United States of America during takeoff. 2 people were killed. Investigators recorded the probable cause as: Exhaust system manifold/pipe corroded, failed totally, and leaked; maintenance inspection inadequate; manufacturer procedure inadequate; FAA surveillance inadequate; fire during climb; loss of control during approach (reason undetermined; pilot attempted… This summary draws on records from the Bureau of Aircraft Accidents Archives (B3A).

Sourcesthe Bureau of Aircraft Accidents Archives (B3A)Primary reportUpdated 2026-06-11Data APIEditorial standards

During preflight engine start, the left engine backfired multiple times. After takeoff, the pilot reported an engine fire. The aircraft entered an uncontrolled descent and crashed, killing both occupants. Investigation found a corroded exhaust manifold and insufficient maintenance.

Accident Narrative

During an engine start prior to flight, the left engine backfired two or three times. One witness described the first backfire as "the loudest I have ever heard." When the aircraft took off, two persons living near the departure end of the runway noted that the aircraft—believed to be the same—sounded different and had a "cluttering sound." While climbing, the pilot declared an emergency and reported a fire in the left engine. He was vectored toward Altus AFB while descending in instrument meteorological conditions (IFR). He descended into visual flight rules (VFR) conditions and saw the airport about three miles away. A witness observed smoke and fire trailing from the vicinity of the left engine. The witness stated that the aircraft's nose came up, the plane rolled to the left, then it entered a steep, nose-down, inverted attitude just before it crashed and burned. Both occupants were killed.

Investigation Findings

Examination revealed that the engine exhaust manifold header assembly had failed, allowing hot exhaust gases to escape into the engine nacelle in the vicinity of fuel and oil lines. Corrosion had progressed through the header assembly. Airworthiness Directive (AD) 75-23-08 requested a general inspection but contained a note stating "do not remove clamps." No record of replacement of the header assembly existed in the last 6,100 hours of operation.

Probable Cause

The official probable cause findings are presented as multiple occurrences:

  • Occurrence #1: Airframe/component/system failure/malfunction (phase of operation unknown) — The exhaust system manifold/pipe was corroded; maintenance inspection was inadequate; procedure was inadequate (manufacturer); surveillance of operation was inadequate (FAA); the exhaust system manifold/pipe experienced total failure and a leak.
  • Occurrence #2: Fire (phase of operation: climb to cruise) — A fire occurred, attributed to the exhaust system failure.
  • Occurrence #3: Loss of control in flight (phase of operation: approach VFR pattern final approach) — The reason for the loss of control was undetermined; weather condition included clouds; the pilot in command initiated a precautionary landing attempt; aircraft handling was not maintained.
  • Occurrence #4: In-flight collision with terrain/water (phase of operation: descent uncontrolled) — The aircraft descended uncontrolled and collided with terrain.