LoCamp BiCamp

 

 Rendering HiCamp

HiCamp - DATA SHEET

 

 

 

TYPE
Two seat, high wing, single engine in tractor configuration.

DESIGN FEATURES
The untwisted, cantilever main wing features a rectangular planform with rounded tips, 1° dihedral from fuselage centerline and classical NACA4416 wing section at full span. The empennage features flat horizontal and vertical tail surfaces.

FLIGHT CONTROLS
Push-pull rods for ailerons and elevator, 3/32" steel cables for rudder control. The aircraft is trimmed by the electrically actuated stabilizer. The wing flaps are electrically actuated as well.

STRUCTURE
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.

LANDING GEAR
Tail-wheel tricycle type; fixed main gear on steel struts with rubber shock absorber, hydraulic disc brakes and 6.00x6 wheels. The swiveling tail-wheel is connected to the rudder; it can be disconnected on the ground by removing a quick disconnect pin.

 

ACCOMODATION
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.

 

SYSTEMS
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).

POWERPLANT
The airframe can be equipped with different engines; at this time we provide firewall forward kits for the following engines: radial ROTEC R2800 (rated power 110 HP) and the MIKRON MIIIC (rated power 80 HP). We are evaluating the LOM M132A (rated power 120 HP).
The engine drives a 2 blade wooden propeller.

 

SPORT PILOT

 


The Sport Pilot version (LSA and E-LSA) is currently under development. Our aircraft have been designed according the prescription of the JAR-VLA Rule, a well established and known European aviation Standard We plan to reach certification by summer 2008.

Production positions are available for reservation; please send enquires to info@aerolab.it

 

 

 

KIT DESCRIPTION

 

 

THE KIT COMES COMPLETE FROM FIREWALL TO TAIL:

  • Fuselage, Tail, Landing Gear: steel structure completely finished and TIG welded; no additional welding necessary;

  • Spar caps completely riveted ready for assembly;

  • Pre drilled aluminum wing Ribs;

  • 6.00x6 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;

 

FIREWALL FWD. KIT (LESS ENGINE):

  • Engine Mount, TIG welded
  • Cowling;
  • Wooden Propeller;
  • Complete Fuel System, including Gascolator and electric Fuel Pump;
  • Oil System;
  • Oil Tank;
  • Complete Hardware kit;
    • Firewall Fwd. Kit for Rotec R2800 Engine
    • Firewall Fwd. Kit for Mikron IIIC Engine

 

OPTIONS:

  • Full epoxy coating to steel structures;
  • Wheel Fairing;
  • Classic style Engine Instruments Set (5 Pcs);
  • Passenger seat Instrument Panel with electronic Tachometer;
  • Passenger Brake sys.

 

 

DIMENSIONS - WEIGHTS - PERFORMANCE

 

EXTERNAL DIMENSIONS
Wing span 29’10’’ ft 9,10 m
Wing gross area 145,3 sq/ft 13,5 m²
Wheel track 5’6’’ ft 1,68 m
Propeller diameter 72’’ 1,829 m
  

WEIGHTS AND LOADINGS

Empty weight (Rotec R2800) 771 lbs 350 kg
Useful load 496 lbs 225 kg
Max T-O weight 1267 lbs 575 kg
  
PERFORMANCE
(ROTEC R2800 110 HP ENGINE)

Mph

Kts

Km/h

Never-exceed speed (VNE)

132

115

213

Max level speed @ S/L

121

105

195

Maneuvering speed (VA)

90

78

145

Max cruising speed @ S/L (75%)

106

92

171

Stalling speed clean @ S/L (Vs1)

45

39

72

Stalling speed full flaps @ S/L (Vs0)

41

36

67

Max rate of climb @ S/L, MTOP

800 ft/min

4 m/s

Maximum ceiling (without oxygen)

12,000 ft

3,658 m

T-O distance @ S/L

820 ft

250 m

Landing distance @ S/L

656 ft

200 m

Max range (with 30 min reserve)

455 sm

395 nm

g limits

+4.0/-2.0

+4.0/-2.0