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NAMC K-8 KARAKORUM 8 |
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TYPE: Tandem-seat jet basic trainer and light ground attack aircraft. PROGRAMME: Launched publicly (as L-8) by NAMC at 1987 Paris Air Show as proposed export aircraft to be developed jointly with international partner. Subsequently proposed to be co-developed with Pakistan as partner (25 per cent share); aircraft then redesignated K-8 and named after mountain range forming part of China/Pakistan border. Pakistan decided 1994 against own assembly line. Manufacture of four prototypes started January 1989; three flying prototypes: 001 (first flight 21 November 1990), 003 (first flight 18 October 1991) and 004; 002 is static and fatigue test aircraft. First preproduction aircraft (1001/L8 320101) used as demonstrator. Preproduction batch of six for Pakistan Air Force evaluation (ordered 9 April 1994) handed over in China on 21 September 1994 and delivered to PAF on 10 November; PAF evaluation (approximately 1,200 hours) completed in August 1995. China importing Progress AI-25 turbofans for use in domestic version (see under Power Plant). CUSTOMERS: Total of 12 (six each to PLA Air Force and Pakistan Air Force) delivered by end of 1996. Original joint venture agreement reportedly involved up to 75 for Pakistan Air Force, but Pakistan Secretary for Defence Production quoted in early 1996 as saying up to 100 to replace Cessna T-37. Chinese PLAAF has requirement for several hundred. Interest also reported from Bangladesh, Eritrea, Laos, Myanmar, Sri Lanka and Zambia. COSTS: $3 million to $3.5 million flyaway (1996) with TFE731 and Western avionics. DESIGN FEATURES: Tapered, non-swept low wings, with NACA 64A-114 root and NACA 64A-412 tip sections; 2° incidence at root, 3° dihedral from roots; sweptback vertical/non-swept horizontal tail surfaces; intended for full basic flying training plus parts of primary and advanced syllabi, but capable also of light ground attack missions. FLYING CONTROLS: Mechanically actuated primary control surfaces; variable incidence tailplane; electrically operated trim tab in rudder and port elevator; two-position Fowler flaps, and split airbrake under each side of rear fuselage, hydraulically actuated; ailerons have hydraulic boost. STRUCTURE: All-metal damage-tolerant main structure; ailerons of honeycomb, fin and rudder of composites. PAC share (initially only tailplane and elevators) increasing to 25 per cent with fin, rudder, rear fuselage and engine cowling/access panels. LANDING GEAR: Hydraulically retractable tricycle type, with single wheel and oleo-pneumatic shock-absorber on each unit. Main units retract inward into underside of fuselage; nosewheel, which has hydraulic steering, retracts forward. Mainwheel tyres size 561 x 169 mm, pressure 6.90 bars (100 lb/sq in). Chinese hydraulic disc brakes. Anti-skid units. Minimum ground turning radius 6.69 m (21 ft 11{1/2} in). POWER PLANT: One 16.01 kN (3,600 lb st) AlliedSignal TFE731-2A-2A turbofan in prototypes and preproduction aircraft, with Lucas Aerospace FADEC, mounted in rear fuselage. Production aircraft for China to be powered by 16.87 kN (3,792 lb st) Progress ZMKB AI-25 TL turbofans, ordered in 1997 (initial batch of 30 engines). Fuel in two flexible tanks in fuselage and one integral tank in wing centre-section, combined capacity 1,000 litres (264 US gallons; 220 Imp gallons); single refuelling point in fuselage. Provision for carrying one 250 litre (66 US gallon; 55 Imp gallon) drop tank on outboard pylon under each wing. Oil capacity 4 kg (8.8 lb). ACCOMMODATION: Instructor and pupil in tandem, on Martin-Baker Mk 10L zero/zero ejection seats; rear seat elevated 28 cm (11 in). One-piece wraparound windscreen; canopy opens sideways to starboard. Cockpits pressurised and air conditioned. SYSTEMS: AiResearch ECS 51833 air conditioning and pressurisation system, with maximum differential of 0.27 bar (3.9 lb/sq in). Hydraulic system, pressure 207 bars (3,000 lb/sq in), for operation of landing gear extension/retraction, wing flaps, airbrakes, aileron boost, nosewheel steering and wheel brakes. Flow rate 15 litres (3.96 US gallons; 3.30 Imp gallons)/min, with air pressurised reservoir, plus emergency back-up hydraulic system. Abex AP09V-8-01 pump. Electrical systems 28.5 V DC (primary) and 24 V DC (auxiliary), with 115/26 V single-phase AC and 36 V three-phase AC available from Ni/Cd battery and static inverter, both at 400 Hz. Liquid oxygen system for occupants. Demisting of cockpit transparencies. AVIONICS: Comms: Bendix/King VHF and Collins EFIS-86 system selected for first 100 aircraft, incorporating CRT primary flight and navigation displays for each crew member plus dual display processing units and selector panels for tandem operation. Magnavox AN/ARC-164 UHF radios.
Flight: Bendix/King KNR 634A VOR/ILS with marker beacon receiver, ADF, Type 265 radio altimeter, AHRS and air data computer and KTU-709 Tacan; WL-7 radio compass. Instrumentation: Collins EFIS-86T. Blind-flying instrumentation standard. Standby flight instruments include ASI, rate of climb indicator, barometric altimeter, emergency horizon and standby compass. ARMAMENT (optional): One 23 mm gun pod under centre-fuselage; self-computing optical gunsight in cockpit, plus gun camera. Two external stores points under each wing. Twin ejector racks on inboard stations can carry total of four 6, 11.5 or 50 kg practice bombs; single-store outboard stations can each carry a PL-7 air-to-air missile, a 12-round pod of 57 mm rockets, a 200 kg, 250 kg or BL755 bomb, or a drop fuel tank.
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