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K-8 Karakorum  
Initial Operational Capability (IOC): 1996
Maiden Flight: 21 November 1990
Total Production: 350
Also Known As: JL-8, K-8E and K-8J
Origin: China 75% and Pakistan 25%
Corporations: AviChina lndustry & Technology Company Limited, Hongdu Aircraft Industry Group* and Pakistan Aeronautical Complex (PAC)   (*) lead contractor
Parent System: K-8 Karakorum
Initial Operational Capability (IOC): 1996
Maiden Flight: 21 November 1990
Total Production: 350
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Description: The K-8 Karakorum is a low life cycle cost, tandem two-seat basic and advanced trainer developed by China in cooperation with Pakistan. The program was launched in 1987 as a Chinese indigenous trainer named L-8 and re-named K-8 Karakorum when Pakistan joined the project. The first prototype took to the air in November 1990. The first K-8 aircraft was delivered to Pakistan in late 1996. It can be powered by either American TFE731-2A or Ukrainian AI-25TLK engines and can be fitted with western avionics. The flight instruments and cockpit view have been designed to replicate the arrangement of a combat aircraft.

The K-8 trainer has been ordered by the air forces of China, Pakistan, Egypt, Burma, Namibia and Zambia with at least 144 aircraft produced to date. Pakistani Air Force has a requirement for up to 100 K-8 trainers. The Egyptian Air Force K-8E procurement contract with China was signed on December 27, 1999, with the co-production of 80 trainers and an additional 40 options to be assembled in Egypt. PLAAF (China) K-8s may be powered by an indigenous engine.

K-8 Karakorum Specifications

Crew: 2
Number of Engines: 1
Service Life Flight Hours: 8,000
Area
Wing Area: 17.0 square meter (183 square foot)
Dimensions
Height: 4.21 meter (13.8 foot)
Length: 11.6 meter (38.1 foot)
Wingspan: 9.63 meter (31.6 foot)
G-load
Max Maneuvering Load Factor: 7.33 g
Min Maneuvering Load Factor: -3 g
Performance
Ceiling: 13,600 meter (44,619 foot)
Ferry Range: 2,140 kilometer (1,156 nautical mile)
Landing Run Distance: 530 meter (1,739 foot)
Max Range: 1,560 meter (0.84 nautical mile)
Take Off Run Distance: 440 meter (1,444 foot)
Speed
Climb Rate: 30 mps (5,882 fpm)
Top Speed at Sea Level: 800 kph (0.67 mach)
Time
Flight Endurance: 3.20 hour
Weight
Empty Weight: 2,757 kilogram (6,078 pound)
Fuel Load: 780 kilogram (1,720 pound)
Max Takeoff Thrust: 3,600 pound (1,633 kilogram)
Max Takeoff Weight: 4,332 kilogram (9,550 pound)
Operational Weight: 3,700 kilogram (8,157 pound)
Useful Load: 943 kilogram (2,079 pound)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Operators & Related Equipment


OperatorsItems
China200
YearHoldings
2014200
Egypt120
Venezuela24
Venezuela intended to purchase up to 24 K-8s in September 2008 with deliveries expected to start in 2009
YearHoldings
Mar 20106

Grand Total 3507
Propulsion Systems
AI-25TLK or WS-11x1
TFE731-2Ax1
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