Sonex Aircraft Onex

Sonex Aircraft Onex
Prototype of Sonex Aircraft Onex
Role	Homebuilt aircraft
Manufacturer	Sonex Aircraft
Designer	John Monnett
First flight	27 January 2011
Status	In production
Number built	17 incl 2 prototypes as of Apr 2014
Unit cost	USD$25,299 (estimated cost of purchasing and completing aircraft)
Developed from	Sonex Aircraft Sonex

The Onex (pronounced "One-X" ) is an American single-seat, low-wing aircraft first flown on 27 January 2011 and currently being produced by Sonex Aircraft as a kit for amateur construction.

The Onex was designed to be economical, have aerobatic capabilities and folding wings, allowing storage in a standard 7 ft (2.1 m) high by 8 ft (2.4 m) wide residential garage. The aircraft has been designed to standard light aircraft FAR-23 static load requirements with the wings supporting more than 10,000 pounds in sandbags during the tests. Intended for the US experimental home-built and light-sport aircraft categories, the company estimates the total price to purchase and build the aircraft to be around US$25,299, making it the least expensive of their kits. The FAA's National Kit Evaluation Team has approved construction checklists demonstrating compliance with the homebuilt requirement that the "major portion", or 51% of the aircraft, is completed by the builder, not the manufacturer. This also allows the owner to seek commercial help with construction.

The first prototype was flown with conventional landing gear with the first flight of the tricycle gear version taking place on October 5, 2011. The prototype was equipped with an AeroVee Volkswagen air-cooled engine.

In a February 2, 2011 webinar, Monett discussed many of technical aspects of the Onex, as well as providing a description of the early flight tests. The Onex is constructed from 6061 aluminum and features a single 15-gallon molded plastic fuel tank mounted in the fuselage, situated so the pilot can see the level of the fuel remaining. Monett claims that this type of tank is the safest and placing it in the fuselage, as opposed to in the wing, will reduce the chances of a fire in case of an accident. A further advantage of this configuration is that the fuel system will be gravity-fed and therefore not require a fuel pump, as it would if the tank were in the wings. Monett discussed the aim of simplicity and that a major goal is to reduce the parts count and thereby cost and weight. He also indicated that on the first test flight the aircraft climbed at 1200 ft per minute and was very responsive to the controls. Monett stated also that he had done some cursory testing of the flaps and found the 45° flap position to be very effective.