PROGRAMME: Precursor was two-seat conversion of five Piper PA-25-235 Pawnees to -235/A8 or -235/A9 Fatman standard in 1986-90. Prototype GA200 (VH-BCE) registered 1991; this and second aircraft used airframes from damaged Pawnees, No 3 (VH-SKG) was first newbuild, in 1992. Designation derived from hopper capacity in US gallons. Full Australian CAA certification in both Normal and Agricultural categories (to CAO 101.16 and 101.22 and FAR Pt 23 Amendment 23.36) awarded 1 March 1991; FAR Pt 23 certification awarded 15 October 1997 in Restricted category. Certification also achieved in Brazil, Canada and elsewhere. Production at Traralgon, Victoria, since 1993.
CURRENT VERSIONS: GA200: Initial version; 194 kW (260hp) Textron Lycoming O-540-H2A5 engine. Hopper capacity 776 litres (205 US gallons: 170 Imp gallons). Replaced by GA200C.
GA200 Ag - trainer: Training version, with dual controls, dual rudder pedals and smaller hopper. Total of three built, plus unspecified number of conversions from GA200s.
GA200B: Unofficial designation of GA200 with extended wingtips. Most built up to 1998 were to this standard.
GA200C: As described. Uprated (224 kW; 300 hp IO-540-K1A5) engine beneath cowling of revised shape constant-speed propeller; 1,050 litre (277.4 US gallon; 231 Imp gallon) hopper capacity. In early 1998, 21st production (23rd overall) aircraft completed as prototype GA200C; all subsequent aircraft to this standard. Textron Lycoming AEIO-580 of246 kW (330 hp) installed in newbuilt 45th aircraft and first flown 11 February 2003, retaining GA200C designation.
CUSTOMERS: Delivery of 44th (including prototypes) effected in November 2001; 45th flown February 2003. Exports to Brazil (one), Canada (one), China (nine). New Zealand (eight, beginning 1994), South Africa (two) and USA (five).
DESIGN FEATURES: Purpose-designed agricultural aircraft. Braced low wing, with large integral hopper forward of cockpit; crash-resistant, corrosion-proofed structure; gapsealed ailerons; detachable wingtips. Although initially based on Piper Pawnee, GA200 in current form is substantially different. Wing dihedral 7° from roots. Flaps and ailerons non-handed. Horn-balanced elevators and rudder.
FLYING CONTROLS: Conventional and manual, cable actuated. Single-slotted trailing-edge wing flaps can be deployed to tighten turning radius during agricultural operations: T-O setting 15°, maximum 38°. Interconnect system applies bias to elevator trim spring when flaps extended, to avoid pitch trim changes. Fixed tab on rudder
STRUCTURE: Fuselage of welded SAE 4130 chromoly steel tube with removable metal side and top panels: wings (braced by overwing inverted V strut of aluminium each side) and wire-braced tail surfaces conventional all-metal, but wing spars constructed from sheet metal to expedite repairs; wingtips detachable. Rear fuselage and tail surfaces are fabric covered.
LANDING GEAR: Non-retractable, with 6 in diameter Cleveland P/N 40-84A mainwheels mounted on tubular steel side Vs: wire-cutter on leading tube of landing gear legs; rubber cord shock-absorption with hydraulic dampers and Cleveland heavy duty hydraulic disc brakes. Mainwheel tyres size 8.50x6 (6 ply). Scott 3200 steerable/castoring tailwheel, size 5.00-5 (4 ply) mounted on multileaf flat springs.
POWER PLANT: One 224 kW (300 hp) Textron Lycoming IO-540-K1A5 flat-six engine, driving a Hartzell HCC2YR- 1BF/F8475R constant-speed, two-blade metal propeller. AEIO-580 installation under test in 2003. offering additional 22 kW (30 hp). Fuel in integral tank in each wing, combined usable capacity 200 litres (52.8 US gallons; 44.0 Imp gallons), plus small 14 litre (3.7 US gallon; 3.1 Imp gallon) header tank in upper front fuselage. Oil capacity 11.4 litres (3.0 US gallons: 2 5 Imp gallons).
ACCOMMODATION: Two energy-absorbing seats, side by side (smaller, right-hand seat for loader/driver); dual controls and second set of rudder pedals for right-hand seat in Agtrainer. Four-point 25 g restraint hamess(es). Cockpit doors open upward, each with bulged window to improve shoulder room and outward view. Pressurisation system minimises dust and chemical ingress.
SYSTEMS: 14 V 95 A automotive alternator and automotive or R-35 aviation battery for electrical power: 50 A circuit breaker switch serves as master switch.
AVIONICS: Instrumentation: Basic VFR instruments and VHF torn only.
EQUIPMENT: One 1.050 litre (277 US gallon; 231 Imp gallon) capacily hopper in forward fuselage (approximately 76 litres: 20.0 US gallons; 16.7 Imp gallons less in Agtrainer) with minimum load dump time of five seconds. Multirole door/hopper outlet, eliminating need to change nulla when changing between solids and liquids, can also be used for fire bombing or laying of fire retardants. Spreader vanes can be added to increase swath width. Cable cutters on landing gear legs and windscreen. 100 W landing light in each wingtip; 28 V night working lights system (two retractable underwing 600 W lights, powered by separate 28 V 55 A alternator) also available.
|DIMENSIONS. EXTERNAL :|
|Wing span, standard version||11.985 m (39 ft 33/4 in)|
|Wing chord, constant||1.60 m (5 ft 3 in)|
|Wing aspect ratio||7.3|
|Laiglh overall (flying attitude)||7.48 m (24 ft 61/2 in)|
|Height (static) over cockpit canopy||2.33 m (7 ft 73/4 in)|
|Tailplanespan||2.90 m (9 ft 61/4 in)|
|Wheel track||2.335 m (7 ft 8 in)|
|Propeller diameter||2.13 m (7 ft 0 in)|
|Wings, gross||19.59 m2 (210.9 sq ft)|
|Ailerons (total)||0.79 m2 (8.49 sq ft)|
|Flaps (total)||0.71 m2 (7.63 sq ft)|
|Fin||0.48 m2 (5.155 sq ft)|
|Rudder, incl tab||0.63 m2 (6.76 sq ft)|
|Tailplane||1.295 m2 (13.92 sq ft)|
|Elevators (total)||1.37 m2 (14.725 sq ft)|
|WEIGHTS AND LOADINGS:|
|Weight empty||758 kg (1,671 lb)|
|Operating weight empty||868 kg (1,914 lb)|
|Max hopper capacity. Normal category||544 kg (1,199 lb)|
|Max T-0 weight: - Normal category||1.524 kg (3,359 lb)|
|- Agricultural category||1,995 kg (4,398 lb)|
|Max landing weight||1,448 kg (3.192 lb)|
|Max wing loading||101.8 kg/m2 (20.86 lb/sq ft)|
|Max power loading||8.91 kg/kW (14.63 lb/hp)|
|Never-exceed speed ( VNE )||144 kt (266 km/h; 165 mph)|
|Max cruising speed at 75% power||115 kt (213 km/h: 132 mph)|
|Econ cruising speed||100 kt (185 km/h; 115 mph)|
|Stalling speed: - flaps up||58 kt (108 km/h; 67 mph)|
|- flaps down||53 kt (99 km/h; 61 mph)|
|Max rate of climb at S/L||290 m (950 ft)/min|
|T-0 run. normal category||350 m (1,148 ft)|
|T-0 to 15 m (50 ft), normal category||475 m (1,558 ft)|
|Landing from 15 m (50 ft)||360 m (1.181 ft)|
|Max range||400 n miles (740 km; 460 miles)|