N43904
"Nine-oh-four" is a 1998 Spacewalker II

Spacewalker-II, N93409, was constructed by Mark T. Brown of Yadkinville, North Carolina, and was issued an Experimental Amateur Built Airworthiness Certificate on June 27, 1998. I purchased the aircraft in June 2015, with only 117 hours of flying time on the aircraft, and moved it to St. Louis Downtown Airport.

The SPACEWALKER II is an amateur built airplane licensed in the EXPERIMENTAL category.  It was designed by Jesse Anglin in 1990 to fill a need for a reasonably sized, two place, open cockpit, sport monoplane.  The nostalgic look of a 1930s-type aircraft has been recreated in a modern airplane that is affordable to build and fly.  It was built to fly just for fun and is not intended for aerobatics.  It is quite strong, responsive, and stable.  The light wing loading allows slow landing speeds and short field operations.  The fuselage, tail, landing gear, engine mounts, and struts are constructed from TIG-welded 4130 steel tubing.  Construction of the plane has been kept as simple as possible.  The SPACEWALKER is a small airplane, but by no means a little one.  It is large enough to do the job expected of it.  It is easy and fun to fly.  The plane handles well on the ground as well as in the air.  Figure 1-1 provides the three profile views of the SPACEWALKER II.

The aircraft fuselage is made of conventional Chrome Moly 4130 welded steel tubing, giving the steel cage excellent structural integrity and safety.  The wings are constructed with a conventional aircraft-grade spruce wood I-beam spar that has been boxed in for durability.  The ribs are made of wood with Chrome Moly 4130 steel truss attachments between the front and rear spar.  The aircraft is covered in Stits Poly Fiber fabric.  The wing leading edge is 2mm plywood for a clean straight line.  The trailing edge is aluminum, pre-bent into the correct shape.  The wing consists of three pieces, the two outer sections and the center section.  The ailerons are constructed similar to the wing with the exception that only one spar is used.  The wing tips and engine cowling are molded fiberglass.

The tail assembly is wire-braced for the strongest possible structure at the lowest possible weight.  The tail itself is made from 4130 steel tubing.  Flying cables transfer the flying load to the fuselage.

The flight controls are light, smooth, and positive.  All the control rods and tubes are located under the floorboards resulting in a clean cockpit layout.  The ailerons use push-rods and belcranks in the outer wing panels.  All the movements work with spherical ball rod ends.  The rudder and elevators are controlled by conventional steel control cables and pulleys.  A cable-activated elevator trim control is conveniently located on the rear cockpit throttle quadrant.

AIRCRAFT SPECIFICATIONS

Length                                            19’9”
Height                                             65”
Fuselage Width                              27”
Empty Weight                                821 lbs.
Maximum Gross Weight               1,400 lbs.
Wing Span                                      28’
Wing Area                                      126’
Wing Cord                                      4.5’
Aspect Ration                                 6.22
Rated H.P.                                      115 HP
Max Speed Sea Level                     120 mph
Normal Cruise                                100 mph
VNE                                                125 mph
Rate of Climb                                 1,200 fpm
Take off run                                    325’
Landing roll                                    350’ 
Prop ground clearance                   18”
Roll rate                                          45 degrees/second
Design Stress Limits                      +3.3 / -2.0 G’s
Ultimate Stress limits       +5.0 / -3.0 G’s (Failure Limits)