MIA94LA029
1993-11-26 · MOORE HAVEN, Florida, United States · Minor · 1 aircraft · Status: Completed
Current FAA registration · N130HA
- Make / Model
- HILLER UH-12E
- Engine
- LYCOMING VO-540 SERIES (310 hp)
- Seats / Engines
- 4 seats · 1 engine
- Last airworthiness date
- 20120216
- ADS-B equipped
- Yes — Mode-S A07BE1
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
FAILURE OF THE PILOT-IN-COMMAND TO MAINTAIN AIRCRAFT CONTROL FOLLOWING LOSS OF ENGINE POWER FOR UNDETERMINED REASONS.
Factual narrative
On November 26, 1993, about 0945 eastern standard time, a Hiller UH-12E, N130HA, registered to Taylor Helicopter, Inc., crashed near Moore Haven, Florida, while on a 14 CFR Part 137, aerial application flight. Visual meteorological conditions prevailed at the time and no flight plan was filed. The aircraft received substantial damage and the commercial-rated pilot received minor injuries. The flight originated from a road near Moore Haven, Florida, on November 26, 1993, at 0940. The pilot stated he was flying east at 5 feet agl and at 50 knots, spraying a field. The engine sputtered and quit and the aircraft pitched up and then fell to the ground. He stated the aircraft contained 10 gallons of fuel at the time of engine failure. Postaccident examination of the aircraft by an FAA inspector indicated there was continuity of all engine and flight control systems. The aircraft's fuel tank contained 5 gallons of uncontaminated fuel. All fuel screens and lines were free of contamination and obstructions. The engine was motored using the starter and the engine assembly had continuity. Each ignition lead sparked normally during engine motoring. THE PILOT STATED THAT WHILE FLYING AT AN ALTITUDE OF 5 FEET AGL, SPRAYING CROPS, THE ENGINE SPUTTERED AND QUIT. THE AIRCRAFT PITCHED UP AND THEN DESCENDED INTO THE GROUND. POSTACCIDENT EXAMINATION OF THE ENGINE INDICATED THE ENGINE ROTATED NORMALLY AND EACH MAGNETO PRODUCED NORMAL SPARK. ALL FUEL LINES AND SCREENS WERE FREE OF DEBRIS. FIVE GALLONS OF UNCONTAMINATED FUEL WAS DRAINED FROM THE AIRCRAFT AND ENGINE FUEL SYSTEM. CONTINUITY OF ALL FLIGHT CONTROL AND ENGINE CONTROLS WERE CONFIRMED. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_1993_MIA94LA029.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…