# Accident 19980407006149A: Amtr EXEC162F, Canton, CA, April 7, 1998

- Type: FAA accident report (Accident/Incident Data System), as reported
- Date: April 7, 1998, 19:30 local time
- Place: Canton, CA
- Damage: Substantial damage
- Phase of flight: Forced/Precautionary Landing
- Operating rules: General operating rules (Part 91)
- Location: 34.2391° N, 84.4906° W: From the FAA, an estimate near the named town, within about 3 miles
- Nearby events: https://openairdocs.org/map.md?lat=34.2391&lon=-84.4906&mi=10
- Aircraft: N623LB (not matched to a registry record)
- Reported make and model: AMTR EXEC162F
- Reported engine: AMTRRW ROTWY162
- Fatal injuries: 0
- Pilot flight hours: 1,352 total, 52 in this make and model, 90 in the last 90 days
- NTSB investigation: [NTSB MIA98LA122](https://openairdocs.org/ntsb/MIA98LA122) (OpenAirDocs)
- FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/)
- Page: https://openairdocs.org/incident/19980407006149A

## Narrative

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

DEPARTED HELO PAD ROTOR SPEED DECAYED DUE COLLECTIVE USE. UNABLE PAD. AUTOROTATED INTO LAKE. ROTORS STRUCK CABIN. (.4)THE PILOT STATED HE EXPERIENCED A LOSS OF ROTOR RPM DURING INITIAL TAKEOFF CLIMB OVER A LAKE. HE SAID HE 'ADDED MAX POWER & DECREASED COLLECTIVE; NO INCREASE IN ROTOR RPM NOTED.'  THE HELICOPTER WAS TURNED TOWARD THE SHORE, AND THE PILOT LOWERED THE COLLECTIVE PITCH TO INCREASE ROTOR RPM, BUT WITH NEGATIVE RESULTS. SUBSEQUENTLY, THE HELICOPTER SETTLED INTO THE WATER AND SANK. EXAMINATION OF THE ENGINE CONTROL UNIT (ECU) (AT AN AUTHORIZED REPAIR FACILITY) REVEALED THE ENGINE RPM STEADILY DECREASED AS THE PERCENTAGE OF THROTTLE POSITION WAS INCREASED 'RIGHT UP UNTIL IMPACT, ELEVEN (11) SECONDS FROM LIFT OFF.'  AN FAA INSPECTOR, WHO PARTICIPATED IN THE INVESTIGATION, STATED 'THE PILOT APPARENTLY APPLIED TOO MUCH COLLECTIVE PITCH TOO SOON AND IT APPEARS HE BASICALLY GOT BEHIND THE POWER CURVE.'                    (-23)THE AIRCRAFT DEPARTED A PRIVATE HELOPAD WITH THE PILOT AND ONE PASSENGER UNDER FAR 91 RULES.  11 SECONDS AFTER TAKEOFF THE AIRCRAFT CRASHED INTO THE LAKE.  BOTH THE PASSENGER AND THE PILOT RECEIVED MINOR INJURIES.  THE R                                    OTOR RPM DROPPED BELOW THAT NECESSARY TO SUSTAIN FLIGHT.

## The NTSB's investigation of this event (1)

From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model.

- [NTSB MIA98LA122](https://openairdocs.org/ntsb/MIA98LA122), Apr 7, 1998: Brock 162F (N623LB), Canton, GA, substantial damage. Probable cause: the pilot's improper use of throttle and collective pitch during initial takeoff climb, which resulted in a decay of rotor rpm and settling of the helicopter into a lake.

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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