TYPE: Aerobatic two-seat turboprop sportplane.
PROGRAMME: HDH A10 Wamira programme begun in 1982 to meet Royal Australian Air Force requirement for turboprop pilot trainer; redefined as A10B in May 1985 but rejected in December 1985 in favour of Pilatus PC-9. Prototype then substantially complete and HDH continued development with aim of late 1986 first flight. However, venture was cancelled and A$80+ million costs written off. Rights acquired by Endeavour, which plans to produce sportplane and touring versions for export market, while retaining military potential. Following implementation of funding plan, estimated two-year programme to complete prototype/demonstrator under Experimental certification.
CURRENT VERSIONS: Tandem: Sportplane or intermediate military trainer conforming to current preference.
Side-by-side: Original Wamira configuration. Tourer or basic military trainer.
Both to be available with choice of engine power and would be suitable for pilot training up to first 100 hours of a military syllabus. Version commonality is 80 per cent.
DESIGN FEATURES: Low-wing, high-performance, aerobatic turboprop; mid-mounted tailplane. Tapered wing planform with root nibs and dihedral. Enlarged rudder on higherpowered version. Sweptback fin with small fillet; tapered tailplane.
FLYING CONTROLS: Conventional and manual. Mass-balanced ailerons with tab each side, port tab electrically actuated. Electric trim tabs in elevators (two) and rudder. Pushrod actuation throughout. Electrically actuated flaps.
STRUCTURE: Aluminium 2024 semi-monocoque with twospar wing; single-spar rudder; tailplane as wings; some composites fairings. Comprehensive corrosion-proofing.
LANDING GEAR: Tricycle type; retractable. Mainwheels, with 7.00-8 tyres, retract inwards electromechanically and have no doors; nosewheel, 5.00-5, retracts rearward. All tyre pressures 2.9 bar (42 lb/sq in). Manual emergency extension. Oleo-pneumatic shock-absorber on each leg.
POWER PLANT: One Pratt and Whitney Canada PT6A-25C turboprop, flat-rated to either 559 kW (750 shp) or 634 kW (850 shp), driving a Hartzell HC-B3TN-T10173-11R constant-speed, fully feathering, reversible-pitch, three-blade propeller. Single fuel tank in lower centre fuselage, capacity 580 litres (153 US gallons; 128 Imp gallons).
ACCOMMODATION: Two pilots in tandem (single-piece canopy) or side-by-side (two-piece canopy) with raised rear seat. Separate windscreen; canopies slide rearwards. Partial pressurisation. Baggage space behind seats, with external access.
SYSTEMS: Hydraulic system for brakes; no pneumatic system. 28 V DC electrical system incorporating 28 V, 200A starter/ generator, with two 125 VA static invertors for AC supply. Crew oxygen system. Environmental control system.
| DIMENSIONS, EXTERNAL : | |
| Wing span | 11.00 m (36 ft 1 in) |
| Wing chord: at root | 3.03 m (9 ft 11 1/4 in) |
| at tip | 1.21 m (3 ft 11 1/2 in) |
| Wing aspect ratio | 6.1 |
| Length overall | 10.20 m (33 ft 51/2 in) |
| Height overall | 3.51 m (11 ft 6 1/4 in) |
| Tailplane span | 4.50 m (14 ft 91/4 in) |
| Wheel track | 4.00 m (13 ft 1 1/2 in) |
| Wheelbase | 3.10 m (10 ft 2 in) |
| Propeller diameter | 2.29 m (7 ft 6 in) |
| AREAS: | |
| Wings, gross reference | 20.00 m2 (215.3 sq ft) |
| WEIGHTS AND LOADINGS | (A: 559 kW; 750 shp engine, B: 634 kW; 850 shp engine): |
| Weight empty: A | 1,636 kg (3,607 lb) |
| B | 1,698 kg (3,744 lb) |
| Max ramp weight: A | 2,213 kg (4,878 lb) |
| B | 2,303 kg (5,077 lb) |
| PERFORMANCE (estimated; A, B as above): | |
| Never-exceed speed ( VNE ) | M0.575 (320 kt; 593 mph; 368 mph) EAS |
| Max level speed: | |
| at FL150: | |
| A | 238 kt (441 km/h; 274 mph) |
| B | 248 kt (459 km/h, 285 mph) |
| at S/L: A | 230 kt (426 km/h; 265 mph) |
| B | 238 kt (441 km/h; 274 mph) |
| Max cruising speed: | |
| at FL150: | |
| A | 229 kt (424 km/h; 264 mph) |
| B | 244 kt (452 km/h; 281 mph) |
| at S/L: A | 225 kt (417 km/h; 259 mph) |
| B | 227 kt (420 km/h; 261 mph) |
| Stalling speed: | |
| flaps up: A | 69 kt (128 km/h; 80 mph) |
| B | 71 kt (132 km/h; 82 mph) |
| flaps down: A | 59 kt (110km/h; 68mph) |
| B | 60 kt (112km/h; 69mph) |
| Max rate of climb at S/L: A | 885 m (2,905 ft)/min |
| B | 1,012 m (3,320 ft)/min |
| Time to FL150: A | 6 min 40 s |
| B | 6 min 5 s |
| Max certified ceiling | 9,570 m (31.400 ft) |
| T-O to 15 m (50 ft): A | 363 m (1.190 ft) |
| B | 397 m (1.300 ft) |
| g limits | +7.0/-3.5 |
