Endeavour Phoenix

TYPE: Aerobatic two-seat turboprop sportplane.

COUNTRY OF ORIGIN: Australia

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
 

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