Cessna 320A N600JR

Summary

On 15 May 1996 at about 14:24 local time, a Cessna 320A registered N600JR was involved in an accident near Provo, Utah, United States. 2 people were on board and 2 died. The aircraft was destroyed. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

15 May 1996 at 14:24

Classification

Accident

Location

Provo, Utah, United States

Coordinates

Not recorded

Aircraft

Cessna 320A

Registration

N600JR

Category

Airplane

Engines

2

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Instructional

Phase of flight

Not recorded

Route

Salt Lake City → Provo

Aircraft damage

Destroyed

Weather

VMC

Light

Day

NTSB number

SEA96FA094

2 people died.

A fuel leak most probably ignited by hot exhaust gases from the leaking right engine manifold exhaust system, the decision by the pilots to operate the aircraft with knowledge of the fuel leak, and the pilot-in-command's failure to maintain adequate clearance with the lake surface.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

The owner and flight instructor were advised by a ramp service agent of a fuel leak coming from the underside of the right engine after starting the left engine. The left engine was shut down and one of the pilots examined the leak and then re-entered the aircraft. The aircraft's left engine was then restarted followed by the right engine, and then the aircraft was taxied out for takeoff. The first takeoff was aborted for undetermined reasons. The aircraft then departed. Approximately 40 minutes later a radio transmission from the aircraft indicated an engine fire. The aircraft was witnessed diving toward the surface of Utah Lake and then skipping over the water before disappearing in a plume of spray. The aircraft crashed approximately two miles northwest of the Provo Municipal airport in 12 feet of water. Postcrash examination revealed an extensive fire in the right engine accessory area and aft into the wing locker area. Metallurgical examination of the right engine exhaust manifold components revealed erosion, oxidization, pitting, cracking and holes in areas of the exhaust tubing.

Quoted verbatim from the NTSB record.