# Incident 19970627036149I: Sego Tool HAWK 1X, Tooele, UT, June 27, 1997

- Type: FAA incident report (Accident/Incident Data System), as reported
- Date: June 27, 1997, 09:30 local time
- Place: Tooele, UT
- Airport: Tooele Municipal Airport
- Damage: Minor damage
- Phase of flight: To Vertical (Helicopter Only)
- Operating rules: General operating rules (Part 91)
- Location: 40.5394° N, 112.3078° W: Placed by OpenAirDocs: center of Tooele, UT, within about 6 miles (OpenAirDocs)
- Nearby events: https://openairdocs.org/map.md?lat=40.5394&lon=-112.3078&mi=10
- Aircraft: N4379X, a cancelled registration (https://openairdocs.org/deregistered/N4379X-2018-03-23) (OpenAirDocs)
- Registry model: Sego Tool HAWK 1X (registry code 13017NF, https://openairdocs.org/model/sego-tool-hawk-1x) (OpenAirDocs)
- Registry engine: Lycoming T0-360 series (registry code 41528, https://openairdocs.org/engine/lycoming-t0-360-series) (OpenAirDocs)
- People aboard: 1
- Fatal injuries: 0
- Pilot flight hours: 14,400 total, 1 in this make and model, 60 in the last 90 days
- FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/)
- Page: https://openairdocs.org/incident/19970627036149I

## Narrative

As the FAA filed it, in capitals; the FAA replaces private details with ^PRIVACY DATA OMITTED^.

NARRATIVE: ON 06-27-97 THE TEST PROTOCOL REQUIRED EVALUATION OF THE NOSEWHEEL ANTI-SHIMMY DEVICE AND PERFORMANCE OF THE ROTOR SYSTEM. AT APPROXIMATELY 0930 A NORMAL TAKEOFF ROLL WAS STARTED. JUST PRIOR TO LIFTOFF THE RETREATING ROTORBLADE STRUCK THE GROUND A GLANCING BLOW. THE PILOT MISTOOK THE BLADE STRIKE AS A NOSE WHEEL SHIMMY AND PURSUED A NORMAL TAKEOFF AND "IN GROUND EFFECT ACCELERATION." APPROXIMATELY 30 SECONDS AFTER LIFTOFF, THE TEST PLAN CALLED FOR A BEST RATE CLIMB. THE PILOT OBSERVED DEGRADED CLIMB PERFORMANCE AND ELECTED TO MAKE A PRECAUTIONARY LANDING, ON LEVEL TERRAIN WITHIN THE AIRPORT BOUNDARY. A NORMAL LANDING WAS EXECUTED. NORMAL ENGINE/ROTOR SHUTDOWN WAS ACCOMPLISHED. POST FLIGHT DISASSEMBLY OF THE ROTOR SYSTEM REVEALED NO DAMAGE TO THE ROTORHEAD. INSPECTION OF THE ROTOR BLADES SHOWED ABRASION, APPROXIMATELY 2 CM OF LOWER BLADE SKINS AT THE ROTOR TIPS AND WRINKLING OF THE UPPER BLADE SKINS AFT OF THE SPAR. THIS IS A FINAL REPORT.

From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. For accidents, the NTSB's own investigation is the fuller record.

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