TYPE: Light utility turboprop.
PROGRAMME: Designed within Khrunichev bureau in Moscow by Evgeny P Grunin. Considerably modified Piper PA-31P Pressurised Navajo (PA-31T version also suitable for conversion).
Intracom had previously proposed a collaborative project with Piper, to be known as PA-31TXL, but this was rejected by the US company.
First flight (GM-17-000, registered RA-01559; the former N38RG) 6 December 2000; 10 sorties and 6 hours flown by February 2001, when laid-up for static testing. Further two prototypes were to have followed in 2001, using Navajos G-OIEA and SE-IGB as basis; programme delayed by change of partner company to Technoavia (chief designer Vyatcheslav Kondratiev) in November 2001 and renaiming of aircraft from Feniks (Phoenix) to Viper. Khrunichev prototype transferred to SmAZ at Smolensk for disassembly and rebuild; changes included replacement of winglets by tip tanks and revised nose contours; reflown January 2003 as GM-17-000-1; flew 60 hours before relegation to static testing in April 2003. Three PA-31P airframes (GM-17-001, 002 and 003) delivered to Technoavia in November 2001 and entered modification at SmAZ; GM-17-001/RA-44471 flown March 2003 and accumulated 60 hours in first three months, Russian demonstrator and exhibition at Moscow in August 2003; GM-17-002 scheduled for August 2003 first flight and initial customer delivery in October; GM-17-003 flown 2003 as European demonstrator, fitted with enlarged wingtip pods containing radar (starboard) and landing light. GM-17-004, final pre-series, for December 2003 first flight and February 2004 delivery.
Intended conversion of further 28 aircraft between 2004 and 2006, when new version of GM-17 will be available. All 32 initial aircraft to have Experimental category certification. Intended production of 32 aircraft by 2005; manufacture at Smolensk and flight testing in Switzerland.
COSTS: US$860,000 (2003).
DESIGN FEATURES: Single-engined turboprop for passenger and light freight transport; suitable for executive ferry, medical evacuation, patrol, geological survey and training.
All retained airframe and landing gear components overhauled before reassembly. Revised structure includes fireproof steel bulkhead (Frame 3) behind engines; new engine cowlings forward of Frame 4; replacement wing panels in former engine positions; tailplane root fillets; new window frames; ventral fin; revised tailplane incidence (+2°, replacing -2°); composites fintip; replaced fuel tanks and lines, oil system, electrical system (retaining some PA-31 parts), fire warning system and hydraulic system, de-icing system and oxygen system (reduced capacity).
Low-mounted, tapered wing with wingtip tanks or winglets; mid-positioned, tapered tailplane and sweptback fin.
Wing section NACA 632415 at root; 631212 at tip; leading-edge sweepback 5°; thickness chord ratio 14 per cent at root, 12 per cent at tip; dihedral 5°; incidence 1° 30'; twist -2° 30'. Tailplane incidence 2°; wingroot nib sweepback 28°.
FLYING CONTROLS: Conventional and manual. Trim tab in starboard aileron, rudder and both elevators. Flap settings 20° for take-off; 40° for landing. Aileron deflections +24°/-14°; rudder ±35°; elevators +16°/-20°.
LANDING GEAR: Tricycle type; hydraulically actuated; mainwheels retract inward; nosewheel rearward; single wheel on each unit. Nosewheel steerable ±28°; free castoring angle ±80°. Goodyear mainwheels and 6.50-10 (8-ply) tyres; Cleveland nosewheel with 6.00-6 (8-ply) tyres. Hydraulic brakes.
POWER PLANT: One 560 kW (757 shp) Walter M 601E turboprop, driving a five-blade V510 constant-speed, fully reversing propeller. (GM-17-000 and 001 have M 601D engine and V508E/99 three-blade propellers). Total fuel capacity 520 litres (137 US gallons; 114 Imp gallons) in wing tanks. Optional wingtip tanks of Piper design 125 litres (33.0 US gallons; 27.5 Imp gallons) each. Max fuel 960 litres (253 US gallons; 211 Imp gallons).
ACCOMMODATION: Two pilots and six passengers; forward four passengers in club arrangement; leather seats; lavatory and baggage area at rear. Externally accessed baggage compartment in nose. Single door, port, rear. Emergency exit, starboard. Cabin protected by up to 25 mm (1 in) of soundproofing material. Accommodation pressurised and air-conditioned. Emergency oxygen masks.
SYSTEMS: Hydraulic system, pressure 150 bar (2,175 lb/sq in); 27 V electrical system; emergency oxygen. De-icing system on all leading-edges; pneumatic on initial aircraft, but alcohol or electrical system for future installation.
AVIONICS: Comms: Garmin GNS 430 and GNS 530 VHF/NAV. Garmin GTX 327 transponder. C406-1 ELT.
Radar: Optional Bendix/King RDR 2000 weather radar in pod on starboard wing.
Flight: Bendix/King KR 87 radio compass, KI228 ADF KRA 10, HSI 525, Sandel SN-3 colour map and S-Tec 55 autopilot.
EQUIPMENT: Four landing lights as standard; further optional light in wingtip tanks, if fitted.
