Anderson Greenwood AG-14 (AND-51-A)
United States — Single-engine Two-seat Light Cabin Monoplane

Archive Photos ¹

[Anderson Greenwood AND-51-A (N314AG, s/n 3, 1950) on display 8/19/2006 at the Camarillo Air Show, Camarillo, CA (John Shupek photos copyright © 2006 Skytamer Images)]

Overview ²

  • Anderson Greenwood AG-14
  • Role: Utility aircraft
  • Manufacturer: Anderson Greenwood
  • Designer: Ben Anderson, Marvin Greenwood & Lomis Slaughter Jr.
  • First flight: 1947
  • Introduction: 1950
  • Number built: 6
  • Variants: Cessna XMC, XAZ-1 Marvelette

The Anderson Greenwood AG-14 is a two-seat utility aircraft developed in the United States shortly after World War II. It is an all-metal, shoulder-wing monoplane of pod-and-boom configuration, equipped with a pusher propeller, side-by-side seating and fixed tricycle undercarriage.

Development ²

Anderson Greenwood's sole aircraft design was actually a collaborative effort of three engineers: Ben Anderson, Marvin Greenwood & Lomis Slaughter Jr. The name of the last member of the design team was not included in the product name as it was thought it would not boost sales.

The prototype first flew in October 1947, but plans to mass-produce the aircraft were interrupted by the Korean War. Eventually, only five more examples were built before Anderson Greenwood abandoned the project in favor of producing aircraft components for other manufacturers.

The aircraft's design placed the wing behind the cabin and allowed easy entry via automobile-like doors on each side of the cabin. The propeller is well protected and provides safety on the ground in comparison to tractor configuration aircraft. The airfoil employed is a NACA 4418 giving high lift and a stable stall characteristics. The flaps are two-position and mechanically operated by a flap handle on the cabin floor between the seats. The engine starter is foot-actuated and the nose-wheel steering is connected to the control wheel.

The AG-14 has very good visibility and one reviewer termed it “amazing”.

The aircraft was certified on 20 September 1950 in the normal category. The certification includes a prohibition on aerobatics and spins. One reviewer termed it as “positively spin resistant.”

Serial numbers 1, 2 and 3 were produced in 1950, while 4 and 5 were built in 1953.

In 1969 one AG-14 aircraft was acquired by Cessna Aircraft Company and taken to Wichita, Kansas for evaluation. Cessna designed and constructed a single prototype aircraft of similar configuration, the Cessna XMC, equipped with a Continental O-200 engine of 100 hp (75 kW), with the goal of a possible Cessna 150 replacement. The Cessna evaluation program ran though 1971 and 1972. While performance was similar to a C-150, the aircraft suffered from high cabin noise levels as well as cooling problems, while not providing any performance advantages over the Cessna 150.

An AG-14 was also used as the basis of the XAZ-1 Marvelette test bed aircraft built by the Mississippi State University in the 1960s.

Operational History ²

In May 2009 the five production aircraft were still on the US registry listed as Anderson Greenwood AND-51-A.

Specifications (AG-14) ³


  • Two-seat light cabin monoplane


  • Shoulder-wing cantilever monoplane.
  • All-metal structure of high aspect ratio and constant court and thickness.
  • Entire trailing-edge hinged, inner portions acting as flaps and other sections as ailerons.
  • Gross wing area hundred and 20 ft.² (11.15 m²)


  • Short central nacelle enclosing cabin and pusher engine installation.
  • All metal structure.

Tail Unit

  • Monoplane type carried by booms extending from the wing center-section.
  • Each boom terminates in fin and rudder.
  • All-metal structure.

Landing Gear

  • Fixed tricycle type.
  • Main wheels on internally-sprung cantilever struts.
  • Steerable nose wheel.

Power Plant

  • One 90 hp Continental C90 horizontally-opposed air-cooled engine driving a pusher propeller.
  • Fuel tanks in leading-edge of center-section.


  • Cabin seats to side-by-side with dual controls
  • Pilot on left has conventional controls.
  • No rudder pedals to starboard seat as all normal movements can be made with control wheel alone.
  • Door on each side of cabin.
  • Baggage space aft of seats.


  • Span: 34 ft 0 in (10.37 m)
  • Length: 22 ft 6 in (6.86 m)
  • Height: 7 ft 6 in (2.28 m)

Weights and Loadings

  • Weight empty: 850 lbs (386 kg)
  • Maximum payload: 250 lbs (113.5 kg)
  • Disposable load: 550 lbs (250 kg)
  • Weight loaded: 1,400 lbs (636 kg)
  • Wing loading: 11.7 lbs/ft² (57 kg/m²)
  • Power loading: 15.5 lbs/hp (6.9 kg/hp)


  • Maximum speed: over 120 mph (192 km/h)
  • Cruising speed: over 110 mph (176 km/h)
  • Initial rate of climb: over 700 ft/m (213.5 m/m)
  • Ceiling: over 19,000 feet (5,800 m)


  1. Shupek, John. “Anderson Greenwood AND-51-A (AG-14),” The Skytamer Archive, Copyright © 2006 Skytamer Images. All Rights Reserved
  2. Wikipedia, the free encyclopedia. Anderson-Greenwood AG-14
  3. Bridgman, Leonard. Jane's All the World's Aircraft 1950-51, Anderson Greenwood: The Anderson Greenwood AG-14. London: Sampson Low, Marston & Company, Ltd., 1951. pp. 197c-198c

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