A two seat, high wing, single engine tractor configuration, the wing structure features a classical twin aluminum spar; the spars, the molded wing ribs and flap/aileron components are made from sheets of Al 6082-T6 or 6061-T6. All aluminum parts are CNC machined and protected by Alodine; a further layer of wash primer is applied where the fabric is glued to the structure. LH and RH wings are mated to the fuselage through a center cabane and extruded aluminum lift struts.
All the wing, flaps and ailerons are covered by fabric, riveted to the ribs. The fuselage structure features a TIG welded chromium molybdenum steel truss with integral wing fittings, vertical stabilizer, plywood frames and fabric covering. All the steel tubes are internally protected by a MIL-SPEC anti-corrosion treatment that leaves a waxy protective layer over the surface.
The untwisted, cantilever main wing features a rectangular planform with rounded tips, 1 degree dihedral from fuselage centerline and classical NACA4416 wing section at full span. The empennage features flat horizontal and vertical tail surfaces.
Push-pull rods for ailerons and elevator, 3/32in steel cables for rudder control. The aircraft is trimmed by the electrically actuated stabilizer. The wing flaps are electrically actuated as well.
Tail-wheel tricycle type; fixed main gear on steel struts with rubber shock absorber, hydraulic disc brakes and 6.00×6 wheels. The swiveling tail-wheel is connected to the rudder; it can be disconnected on the ground by removing a quick disconnect pin.
Tandem configuration with individual open cockpits (pilot in the rear seat); central stick controls, rudder pedals and throttles for both seats. Two luggage compartments, both with 44 lbs (20 kg.) capacity, one in the front and one in the rear.
The 14 VDC electrical system is powered by one engine driven alternator/generator and provides power for the flaps, trim, fuel pump and radio rack. The fuel is kept in two internally fitted aluminum tanks (one in each wing root), total capacity 31,6 US gallons (120 liters).
The airframe can be equipped with different engines; firewall forward kits for the following engines were available: radial ROTEC R2800 (rated power 110 HP) and the MIKRON MIIIC (rated power 80 HP). Under development was the LOM M132A (rated power 120 HP). The engine drives a 2 blade wooden propeller.
The kit comes complete from firewall to tail, including the fuselage, tail, and landing gear steel structure completely finished and TIG welded; no additional welding necessary; the spar caps completely riveted ready for assembly; pre drilled aluminum wing ribs; 6.00 x 6 wheels and hydraulic brakes; covering material (Dacron) and finishing tapes; steel firewall; aluminum fuel tanks with fuel level indicator; pre-cut steel/aluminum tangs, brackets; machined parts ready for assembly; polycarbonate windscreen; ready to install hand made Italian leather finishing; fiberglass head rest; complete AN hardware; electric flap/trim actuator; 2 seats with 4 point harness.
The firewall forward kit (less engine) includes: engine mount, TIG welded, cowling; wooden propeller; complete fuel system, including gascolator and electric fuel pump; oil system; oil tank; complete hardware kit; and was available for the Rotec R2800 or Mikron IIIC engine.
Options include full epoxy coating to steel structures; wheel fairing; classic style engine instruments set (5 pcs); passenger seat instrument panel with electronic tachometer and passenger brake system.
All parts are CAD designed and produced by CNC/laser cutting equipment to exacting tolerances and perfect finish.
The LoCamp and HiCamp models are readly available as standard 49% kit.

Engine: ROTEC R2800, 110 hp
Wing span: 29 ft 10 in / 9.10 m
Wing gross area: 145.3 sq.ft / 13.5 sq.m
Wheel track: 5 ft 6 in / 1,68 m
Propeller dia: 72 in / 1,829 m
Empty weight: 771 lb / 350 kg
Useful load: 496 lb / 225 kg
Max T-O weight: 1267 lb / 575 kg
VNE: 132 mph / 115 kts / 213 km/h
T-O distance @ S/L: 820 ft / 250 m
Landing distance @ S/L: 656 ft /200 m
Max range (w/res): 455 sm / 395 nm
Max level speed @ S/L: 121 mph / 105 kts / 195 km/h
g limits: 4.0/-2.0
Maneuvering speed (VA): 90 mph / 78 kts / 145 km/h
Max cruising speed @ S/L (75%): 106 mph / 92 kts / 171 km/h
Stalling speed clean @ S/L (Vs1): 45 mph / 39 kts / 72 km/h
Stalling speed full flaps @ S/L (Vs0): 41 mph / 36 kts / 67 km/h
Max rate of climb @ S/L, MTOP: 800 ft/min / 4 m/s

A two seat, low wing, single engine in tractor configuration, the LoCamp and HiCamp models are available as standard 49% kits. Of tandem configuration with individual open cockpits (pilot in the rear seat); central stick controls, rudder pedals and throttles for both seats. Two luggage compartments, both with 44 lb (20 kg) capacity, one in the front and one in the rear.
The untwisted, cantilever main wing features a rectangular planform with rounded tips, 3 degree dihedral from fuselage centerline and classical NACA4416 wing section at full span. The empennage features flat horizontal and vertical tail surfaces.
The wing structure features a classical twin aluminum spar; the spars, the molded wing ribs and flap/aileron components are made from sheets of Al 6082-T6 or 6061-T6. All aluminum parts are CNC machined and protected by Alodine; a further layer of wash primer is applied where the fabric is glued to the structure. LH and RH wings are mated to the fuselage through a center spar; the mating is achieved through conical pins. All the wing, flaps and ailerons are covered by fabric, riveted to the ribs. The fuselage structure features a TIG welded chromium molybdenum steel truss with integral wing fittings, vertical stabilizer, plywood frames and fabric covering. All the steel tubes are internally protected by a MIL-SPEC anti-corrosion treatment that leaves a waxy protective layer over the surface.
Push-pull rods for ailerons and elevator, 3/32in steel cables for rudder control. The aircraft is trimmed by the electrically actuated stabilizer. The wing flaps are electrically actuated as well.
The fixed main gear is on steel struts with rubber shock absorber, hydraulic disc brakes and 6.00 x 6 wheels. The swiveling tail-wheel is connected to the rudder, or it can be disconnected on the ground by removing a quick disconnect pin.
The 14 VDC electrical system is powered by one engine driven alternator/generator and provides power for the flaps, trim, fuel pump and radio rack. The fuel is kept in two internally fitted aluminum tanks (one in each wing root), total capacity 31.6 US gallons (120 lt).
The airframe can be equipped with different engines; firewall forward kits for the following engines were available: radial ROTEC R2800 (rated power 110 HP) and the MIKRON MIIIC (rated power 80 HP). Under development was the LOM M132A (rated power 120 HP). The engine drives a 2 blade wooden propeller.
The kit comes complete from firewall to tail, including the fuselage, tail, and landing gear steel structure completely finished and TIG welded; no additional welding necessary; the spar caps completely riveted ready for assembly; pre drilled aluminum wing ribs; 6.00 x 6 wheels and hydraulic brakes; covering material (Dacron) and finishing tapes; steel firewall; aluminum fuel tanks with fuel level indicator; pre-cut steel/aluminum tangs, brackets; machined parts ready for assembly; polycarbonate windscreen; ready to install hand made Italian leather finishing; fiberglass head rest; complete AN hardware; electric flap/trim actuator; 2 seats with 4 point harness.
The firewall forward kit (less engine) includes: engine mount, TIG welded, cowling; wooden propeller; complete fuel system, including gascolator and electric fuel pump; oil system; oil tank; complete hardware kit; and was available for the Rotec R2800 or Mikron IIIC engine.
Options include full epoxy coating to steel structures; wheel fairing; classic style engine instruments set (5 pcs); passenger seat instrument panel with electronic tachometer and passenger brake sys.

Engine: ROTEC R2800, 110 hp
Wing span: 29 ft10 in, 9,10 m
Wing gross area: 145.3 sq.ft, 13,5 sq.m
Wheel track: 5 ft 6 in, 1,68 m
Propeller dia: 72 in, 1,829 m
Empty weight: 848 lb, 385 kg
Useful load: 472 lb, 214 kg
Max T-O weight: 1320 lb, 599 kg
VNE: 132 mph, 115 kt, 213 kph
Max level speed @ S/L: 121 mph, 105 kt, 195 kph
T-O distance @ S/L: 820 ft, 250 m
Landing distance @ S/L: 656 ft, 200 m
Max range (with 30 min res): 455 nm
g limits: +4.0/-2.0
Fuel cap: 30 USG
Seats: 2 tandem
Cockpit width: 25 in
Undercarriage: tailwheel
Maneuvering speed (VA): 90 mph, 78 kt, 145 kph
Max cruise @ S/L (75%): 106 mph, 92 kt, 171 kph
Stalling speed clean @ S/L (Vs1): 45 mph, 39 kt, 72 kph
Stalling speed full flaps @ S/L (Vs0): 41 mph, 36 kt, 67 kph
Max rate of climb @ S/L, MTOP: 800 ft/min, 4 m/s