ATL98LA096
1998-07-10 · VERO BEACH, Florida, United States · None · 1 aircraft · Status: Completed
Airport VRB
Current FAA registration · N1493H
- Make / Model
- PIPER PA-14
- Seats / Engines
- 4 seats · 1 engine
- Last airworthiness date
- 19550805
- ADS-B equipped
- Yes — Mode-S A0C6E8
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
The pilot's improper flare which resulted in a hard landing.
Factual narrative
On July 10, 1998, about 0830 eastern daylight time, a Piper PA-28-201, N1493H, collided with the runway during takeoff at the Vero Beach Municipal Airport, Vero Beach, Florida. The airplane was operated by FlightSafety International, Inc., under the provisions of Title 14 CFR part 91, and visual flight rules. Visual meteorological conditions prevailed, and a flight plan was not filed for the local, instructional flight. The commercial flight instructor and the commercial pilot under instruction were not injured, however the airplane was substantially damaged. The flight was originating at the time of the accident. According to the operator, one pilot was receiving instruction to be a certified flight instructor (CFI), and was operating the flight controls. He requested an option takeoff from the tower, to accomplish a simulated engine failure on takeoff, with a landing straight ahead on the departure runway, runway 22. About 50 to 100 feet above the ground, he reduced the throttle to initiate the simulated engine malfunction. When the airplane was flared for the simulated emergency landing, a high sink rate was not arrested, and the airplane collided with the runway. The airplane came to rest in the intersection of runway 22 and 29. According to the operator, one pilot was receiving instruction to be a certified flight instructor (CFI), and was operating the flight controls. He requested an option takeoff from the tower, to accomplish a simulated engine failure on takeoff, with a landing straight ahead on the departure runway, runway 22. About 50 to 100 feet above the ground, he reduced the throttle to initiate the simulated engine malfunction. When the airplane was flared for the simulated emergency landing, a high sink rate was not arrested, and the airplane collided with the runway. The airplane came to rest in the intersection of runway 22 and 29. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_1998_ATL98LA096.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
data.ntsb.gov ↗.
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Related research
Matched on aircraft type or causal vocabulary (engine failure). All research papers
- arXiv 2022 · arXiv preprint Multi-level Adaptation for Automatic Landing with Engine Failure under Turbulent Weather
This paper addresses efficient feasibility evaluation of possible emergency landing sites, online navigation, and path following for automatic landing under engine-out failure subject to turbulent wea…
- NASA NTRS 2019 · Conference Paper Simulation of Liquid Rocket Engine Failure Propagation Using Self-Evolving Scenarios
Traditional probabilistic risk assessment approaches often require failure scenarios to be explicitly defined through event sequences that are then quantified as part of the integrated analysis.
- NASA NTRS 2019 · Conference Paper Rocket engine failure detection using system identification techiques
The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented.
- NASA NTRS 2019 · Conference Paper Rocket engine failure detection using system identification techniques
The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented.
- NASA NTRS 2019 · Technical Memorandum (TM) A simulator investigation of engine failure compensation for powered-lift STOL aircraft
A piloted simulator investigation of various engine failure compensation concepts for powered-lift STOL aircraft was carried out at the Ames Research Center.
- Semantic Scholar 2019 · Article (AIAA Scitech 2019 Forum) Impact of Engine Failure Constraints on the Initial Sizing of Hybrid-Electric GA Aircraft
Potential advantages of hybrid-electric aircraft are fuel savings, lower emissions, and reduced noise. Since these aircraft generally apply multiple power sources, they can also be designed to sustain…