SEA94LA008
1993-10-05 · CORVALLIS, Oregon, United States · None · 1 aircraft · Status: Completed
Airport CVO
Current FAA registration · N16ED
- Make / Model
- CESSNA 172RG
- Year of manufacture
- 1985 · 8 years old at event
- Engine
- LYCOMING 0-360-A1D (180 hp)
- Seats / Engines
- 4 seats · 1 engine
- Last airworthiness date
- 19850701
- ADS-B equipped
- Yes — Mode-S A0EFBD
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
THE CFI'S INADEQUATE IN-FLIGHT PLANNING, AND HIS INADVERTENT GEAR-UP LANDING. FACTORS INCLUDE THE CFI'S DIVERTED ATTENTION.
Factual narrative
On Tuesday afternoon, October 5, 1993, at 1340 Pacific daylight time, a Cessna 172RG, N16ED, operated by Avia Flight Services, impacted the runway while landing at the Corvallis Municipal Airport, Corvallis, Oregon. There was no flight plan filed for the local training flight, which took off at 1225. The flight was conducted under 14 CFR 91 in visual meteorological conditions. The certified flight instructor and the commercial pilot were not injured in the accident. The aircraft was substantially damaged. There was no fire. Flight instructor Anderson reported that he pulled the landing gear circuit breaker to deactivate the warning horn while he was conducting training for commercial pilot Foster. He said that after finishing several training maneuvers, he reduced the throttle while over the airport to simulate an engine failure, and the commercial pilot initiated a forced landing to the runway. The landing gear handle was placed in the down position, but the gear did not fully extend. Just as the aircraft was touching down on the runway, the CFI noticed that the gear was not fully down, but there was not sufficient time for remedial action. The aircraft then impacted on the runway with the gear partially extended. WHILE EXECUTING COMMERCIAL FLIGHT TRAINING MANEUVERS, THE CFI PULLED THE CIRCUIT BREAKER FOR THE LANDING GEAR. AT THE COMPLETION OF THESE MANEUVERS, THE CFI PULLED THE ENGINE TO IDLE TO SIMULATE AN ENGINE FAILURE. THE STUDENT THEN EXECUTED A FORCED LANDING, DURING WHICH THE GEAR HANDLE WAS PLACED IN THE DOWN POSITION. NEITHER PILOT REMEMBERED THAT THE LANDING GEAR CIRCUIT BREAKER HAD BEEN PULLED, AND THEREFORE THE GEAR DID NOT FULLY EXTEND, AND THE GEAR WARNING HORN DID NOT SOUND. THE CFI NOTICED THE GEAR WAS NOT FULLY EXTENDED JUST AS THE AIRCRAFT WAS TOUCHING DOWN ON THE RUNWAY, BUT THERE WAS INSUFFICIENT TIME FOR REMEDIAL ACTION. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_1993_SEA94LA008.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…