Hughes 369HS N9116F

Summary

On 12 July 1993 at about 19:55 local time, a Hughes 369HS registered N9116F, operated by Allison, David C., was involved in an accident near Talladega, Alabama, United States. 2 people were on board and one died, one was seriously injured. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

12 July 1993 at 19:55

Classification

Accident

Location

Talladega, Alabama, United States

Coordinates

33.4300, -86.0909

Aircraft

Hughes 369HS

Registration

N9116F

Category

Helicopter

Engines

1

Operator

Allison, David C.

Operating rule

Part 91: General Aviation

Purpose of flight

Personal

Phase of flight

Not recorded

Route

Birmingham → Unknown

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

ATL93FA127

1 person died.

THE PILOT'S POOR IN-FLIGHT DECISION TO LAND DOWNWIND IN A CONFINED AREA THAT WAS SURROUNDED BY HIGH OBSTRUCTIONS, AND HIS FAILURE TO PROPERLY COMPENSATE FOR THE TAILWIND CONDITION. A FACTOR RELATED TO THE ACCIDENT WAS: THE PILOT'S LACK OF TOTAL EXPERIENCE IN THE TYPE OF AIRCRAFT.

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

Read the full NTSB narrative

THE HELICOPTER PILOT HAD ATTAINED 9 HOURS OF FLIGHT TIME IN THIS MAKE & MODEL OF AIRCRAFT. HE WAS ATTEMPTING A DOWNWIND LANDING IN A CONFINED AREA OF THE TALLADEGA SUPER SPEEDWAY, ALTHOUGH OPEN & UNCONFINED AREAS WERE LOCATED NEARBY. THE SITE WAS 168 FEET LONG & 105 FEET WIDE, AND WAS SURROUNDED ON ALL SIDES BY TALL FENCES & POWER LINES. WITNESSES STATED THAT JUST BEFORE TOUCHDOWN IN THE CONFINED AREA, THE HELICOPTER BEGAN TO OSCILLATE FROM SIDE TO SIDE. THE HELICOPTER THEN ASCENDED TO A HEIGHT OF ABOUT 25 FEET, THEN IT BEGAN TO SPIN IN A COUNTERCLOCKWISE DIRECTION. THE RIGHT FRONT SEAT PASSENGER RECALLED BRACING HIS HANDS ON THE CONSOLE & DOOR OF THE HELICOPTER DURING THE EVENT; HOWEVER, HE DID NOT RECALL THE POSITION OF HIS FEET DURING THE EVENT. EXAMINATION OF THE AIRCRAFT DID NOT REVEAL ANY PREIMPACT MALFUNCTION OF THE TAIL ROTOR SYSTEM. METALLURGICAL EXAM OF FRACTURES ON THE COLLECTIVE STICK, COLLECTIVE STICK HOUSING, COLLECTIVE PUSH-PULL ROD & ROD END FROM THE ROTOR HEAD REVEALED NO EVIDENCE OF PROGRESSIVE CRACKING (BEFORE IMPACT).

Quoted verbatim from the NTSB record.