From Aero Digest, April, 1935:
Lambert Aircraft Corporation, St. Louis, Missouri
• President: Wooster Lambert. Vice-president and General Manager: John C. N ulsen. Sales Manager: Clare W. Bunch. Chief Engineer: Tom Towle.
Two-place high-wing monoplane. Lambert R-266 engine, 90 horsepower. Span 32 feet. Length overall 20 feet 6 inches. Height overall, 6 feet 11 inches. Wing area 132.3 square feet. Power loading 17.6 pounds per horsepower. Wing loading 11.9 pounds per square foot.
Weight empty 935 pounds. Useful load 650 pounds. Payload 293 pounds. Gross weight 1585 pounds. Fuel capacity 28 gallons. Oil capacity 2.5 gallons.
Maximum speed 135 miles per hour. Cruising speed 112 miles per hour. Landing speed (with flaps) 40 miles per hour. Service ceiling 15,000 feet. Rate of climb 900 feet per minute. Cruising range 625 miles.
Fuselage: welded steel tubing, fabric covered. No internal wire bracing. Side-by-side seating arrangement. Wing: wood, fabric covered; two spruce spars; ribs are built up of bass-wood webs with spruce capstrips; single wire drag bracing and solid compression ribs; sheet aluminum covering on leading edge; Clark “Y” wing section fabric-covered flaps of wood construction between ailerons and fuselage, controlled by independent push-pull type control. Tail group: welded steel tubing, fabric covering. Fixed, divided-type landing gear, consisting of two side Vees, hinged inside the fuselage to the bottom longerons, with horizontal arms extending inwardly from the top of the front members; 6.5 X 10 tires.
Standard equipment includes Hamilton Standard metal propeller, Exide battery, navigation lights, radio bonding, tunnel cowling, fire extinguisher.
Instruments: tachometer, oil pressure gauge, oil temperature gauge, altimeter, clock, air speed indicator. Also see data in July, 1934, AERO DIGEST.