TYPE : Side-by-side ultralight/kitbuilt.

PROGRAMME : Design of original Jabiru LSA, started 1987; prototype (first of two, VH-JCX and VH-JQX) made first flight August 1989; first customer delivery April 1991; factory-built version certified to CAO 101 Pt 55 on 1 October 1991; 20 built with KFM engine before change to 44.7 kW (60 hp) Jabiru 1600 flat-four, many of these subsequently re-engined; kitplane construction certification achieved in Australia, New Zealand, South Korea, UK and USA by early 1997; marketed in US as amateur-built kit, achieving FAR Pt 21.191 (g) certification on 8 February 1996 (as well as Australian CAO 19 equivalent); marketing office opened at Aiken, South Carolina, in anticipation of substantial US sales of at least 100 per year but later closed in favour of network of dealerships. Total of 54 built with 1600 engine between April 1993 and March 1996. More powerful ST version introduced in 1994.
Joint venture announced in 1998 with CDE Aviation Company of Sri Lanka, subsidiary of Lionair, to establish Jabiru Asia for manufacture of Jabiru ST3 for Asian markets, especially India. Jabiru factory at Koggala, in southern Sri Lanka; intended to have production capacity for 40 aircraft per year, using engines and avionics imported from Australia, and airframes manufactured locally. Nothing further had been beard of this by 2003.

CURRENT VERSIONS: Jabiru LSA: Light Sport Aircraft; factory-built; registered under AUF (Australian Ultralight Federation) rules (Pt 101.55). 'Short span; short fuselage' version: span 8.03 m (26 ft 4 in), length 5.03 m (16 ft 6 in), wing area 7.90 m² (85.0 sq ft).
Jabiru ST: Certified version; in factory production from mid-1994; first was 50th production Jabiru in mid-1998, the 17th production ST was registered VH-JRU to Jabiru Aircraft as the first ST3 short span and fuselage.
Jabiru SK: Quick-build kit version of ST (components are manufactured alongside production aircraft); first was 66th production Jabiru; quoted home-build time is 600 hours.
Jabiru SP4: Kit, combining longer fuselage of UL 450 with Jabiru 2200 engine and short-span wings of SK; originally designated SP. MTOW 470 kg (1,036 lb); stalling speed 39 kt (73 km/h; 45 mph); optimised for Canadian, Chilean and South African markets, among others. Fuel capacity 70 litres (18.5 US gallons; 15.4 Imp gallons).
Jabiru SP6: Company designation of SP4 kit with 89.5 kW (120 hp) Jabiru 3300 engine. Also known as Jabiru SP 3300. MTOW 500kg (1,102 lb). Cruising speed 117 kt (217 km/h; 135 mph). Fuel capacity as SP4, or 85 litres (22.5 US gallons; 18.7 Imp gallons) optional.
Jabiru SP-T: Tailwheel version of SP. Enlarged rudder; mainwheel legs moved forward; steerable tailwheel and differential braking. Prototype built by Peter Kayne of Narrogin, Western Australia.
Jabiru SP480: Proposed version of SP for JAR-VLA certification, with maximum take-off weight of 480 kg (1,058 lb); under development in late 1999.
Jabiru Calypso: Initially factory-built; now available only as kit; previously known as UL 450; SLA (Small Light Aeroplane to UK's now-replaced BCAR Section S), first aircraft was built in Ireland in 1998. Launched in UK in 2000 and meeting 35 kt (65 km/h; 41 mph) stalling speed requirement. Differences from SK include wing span increased by 1.37 m (4 ft 6 in); fuselage by 0.61 m (2 ft 0 in); flaps by total of 1.83 m (6 ft 0 in); and reduced ventral fin. Also available with tailwheel as Calypso T. Meets FAA LSA. 150 plus sold by end 2001.
J200 and J400: Stretched version; described separately.

CUSTOMERS : Production of complete and kit aircraft totalled some 535 by December 2002. Sold to 22 countries.

COSTS: Calypso: US$20,900: SP US$19,900 (2003) both minus engine. Flyaway Calypso 2200 US$59,995 (April 2002).

DESIGN FEATURES : Designed to Australian AUFPt 101.55 and British BCAR Section S. with reference to FAR Pt 21 and JAR-VLA. Ultralight or certified aircraft, suitable for factory or amateur assembly. Unswept wing (braced) and tailplane, swept fin; dorsal and ventral fins; all flying surfaces square-tipped; wings detachable for storage and transportation.

Wing section NASA 4412; drooped wingtips; dihedral 1° 15'; incidence 2° 30'; no twist.

FLYING CONTROLS : Conventional and manual. In-flight adjustable pitch trim; wide-span slotted flaps. Original short rudder supplanted by full-height rudder (also available as retrofit) on all versions. From 2002, enlarged fin version (3/4 height rudder) adopted, entire vertical tail being moved further forward.

STRUCTURE : All-GFRP except metal wing struts, nosewheel assembly and engine mount.

LANDING GEAR : Non-retractable tricycle type, with 15° steerable nosewheel coupled to rudder. Cantilever selfsprung GFRP mainwheel legs; rubber block nosewheel shock-absorption; wheel fairings standard over 4.00-6 or 5.00-6 tyres; Bigfoot 6.00-6 tyres optional. Nosewheel 2.60-4, 4.00-4 or 5.00-6; tailwheel 250x50.

POWER PLANT : One 59.7 kW (80 hp) Jabiru 2200A/J flat-four engine, driving a two-blade, fixed-pitch, wood/composites propeller. Fuel capacity 65 litres (17.2 US gallons; 14.3 Imp gallons).

SYSTEMS : 12 V DC electrical system with 100 W capacity 20 Ah battery.

AVIONICS : Comms: VHF antenna (inside fin) and intercom standard.

Instrumentation: Basic VFR; vacuum instruments optional

Data below refer to Jabiru Calypso with Jabiru 2200 engine.

Wing span: normal 9 40 m (30 ft 10 in)
- with winglets 9.56 m (31 ft 41/2 in)
Length overall 5.64 m (18 ft 6 in)
Height overall 2.01 m (6 ft 7 in)
Cockpit max width at shoulder 1.07 m (3 ft 6 in)
Wings, gross 9.29 m2 (100.0 sq ft)
Weight empty, equipped 242 kg (534 lb)
Max T-O weight 450 kg (992 lb)
Never-exceed speed ( VNE ) 120 kt (222 km/h; 138 mph)
Max level speed 110 kt (204 km/h; 127 mph)
Cruising speed at 75% power 100 kt (185 km/h; 115 mph)
Stalling speed, flaps down 35 kt (65 km/h; 41 mph)
Max rate of climb at S/L 305 m (1,000 ft)/min
T-O run 100 m (330 ft)
Landing run 168 m (555 ft)
Range with max fuel 430 n miles (796 km; 494 miles)