# NTSB MIA98LA122: Brock 162F, N623LB, Canton, GA, April 7, 1998 - Type: NTSB accident investigation - Classification: Accident · Serious injuries · Limited investigation · Final report - Date: April 7, 1998, 19:30 local (23:30 UTC) - Place: Canton, GA - Coordinates: 34.239101, -84.490554 (estimated) - Nearby events: https://openairdocs.org/map.md?lat=34.2391&lon=-84.4906&mi=10 - Phase of flight: [Takeoff](https://openairdocs.org/ntsb-phases/300) (OpenAirDocs' grouping) - Highest injury: Serious injuries - Injuries: 1 serious, 1 minor - Status: Completed, report October 30, 1998 - Report: Approved by Office Director - NTSB case key (mKey): 38488 - NTSB case page: https://web.ntsb.gov/investigations/?ntsbnumber=MIA98LA122 - NTSB report (PDF, downloads): https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/38488/pdf - Page: https://openairdocs.org/ntsb/MIA98LA122 ## 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. ## Sequence of events In NTSB's coding before 2008 (https://www.ntsb.gov/GILS/Documents/codman.pdf). - In flight collision with terrain/water, takeoff - throttle/power control - improper use of, pilot in command (cause) - collective - improper use of, pilot in command (cause) - rotor rpm - not maintained, pilot in command (cause) - terrain condition - water ## Analysis 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.' ## Factual narrative On April 7, 1998, about 1930 eastern daylight time, a Brock 162F, experimental helicopter, N623LB, registered to a private owner, operating as a 14 CFR Part 91 personal flight, experienced a decay in rotor rpm on initial climbout from a private unregistered heliport. A forced landing (autorotation) was conducted into Lake Altoona, located in the vicinity of Canton, Georgia. Visual meteorological conditions prevailed and no flight plan was filed. The helicopter sustained substantial damage. The private pilot reported minor injuries, and the passenger reported serious injuries. The flight originated about 2 minutes before the accident. The pilot stated he was on initial takeoff climb over the lake at about 100 feet and 60 knots, when he noticed a decay in rotor rpm. The engine rpm was okay. He made a left turn towards the shoreline and lowered the collective pitch to increase rotor rpm with negative results. He determined he would be unable to make it back to shore and continued with an autorotation. A deceleration was initiated at 50 feet, initial pitch at 10 feet and cushioning pitch as the helicopter entered the water, and simultaneous left cyclic input. The main rotor blades collided with the water, windscreen, himself and the passenger. The helicopter sank. He released his restraints, assisted the passenger in releasing hers, and exited the helicopter deploying the water wings. They came up on the surface and was assisted to shore by a boater. The engine control unit (ECU) was removed and sent to the Arizona FSDO located in Scottsdale, Arizona, for further examination at the Syntronix Corporation in Tempe, Arizona. The flash memory chip was removed from the computer board which contains the engine operational data and installed in a newly manufactured P/C board, and stored data was downloaded. The test data is recorded in 1 second increments, and the following information was retrieved: "At mark seventeen (0:00:17) seconds the engine start became steady with a stabilized idle. At mark two (2) minutes and fifty seven (0:02:57) seconds the helicopter becomes light on the landing skids. Lift off occurs at (3) minutes and three (0:03:03) seconds. The engine rpm steadily decreases as the percentage of throttle position increases right up until impact, eleven (11) seconds from lift off." The FAA inspector stated, "The pilot apparently applied too much collective pitch too soon and it appears he basically got behind the power curve."( See FAA inspector statement dated May 7, 1998). The helicopter was released to Mr. Olen B. Brock Jr., on April 23, 1998. The ECU was released to Mr. Brock on June 2, 1998. ## Aircraft - Registration: N623LB (not matched to a registry record) - Reported make and model: Brock 162F - Category: Helicopter, amateur-built - Serial number: 6189 - Airframe hours: 52 - Engines: Rotorway 162F 150 horsepower reciprocating - Damage: Substantial damage - Flight: Personal, Part 91 - Registered owner: Olen B. Brock Jr. - Last inspection: Continuous airworthiness, April 7, 1998, 0 hours before - Departed: N/A ## Flight crew As NTSB recorded them. NTSB leaves out names. - Pilot; age 42; private; airplane ratings: multi-engine land, single-engine land; instrument ratings: airplane; medical: class 3, valid medical--no waivers/lim.; seat: left; flight hours: 1,352 total, 52 in this make and model, 1,102 as pilot in command, 90 in the last 90 days, 30 in the last 30 days, 2 in the last 24 hours ## Weather - Conditions: Visual (VMC), Day - Wind: 210° at 6 knots - Visibility: 15 statute miles - Lowest ceiling: none - Temperature: 73 °F, dew point 50 °F - Altimeter: 29.00 inHg - Observed at: MGE ## FAA reports on this event (1) The FAA's own accident and incident reports, matched to the aircraft by N-number and date (OpenAirDocs). - [Accident 19980407006149A](https://openairdocs.org/incident/19980407006149A), Apr 7, 1998: Amtr EXEC162F, Canton, CA, Substantial damage. 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… 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. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.