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K-8 Karakorum

K-8 Karakorum

Training Jets
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Basic Information
Name
K-8 Karakorum
Designation
K-8 Karakorum
Alternate Designation
JL-8, K-8E (Egyptian version), K-8J
Equipment Type
Training Jets
Manufacturer
Hongdu Aircraft Industry Group, AviChina lndustry & Technology Company Limited, Kamra Aeronautical Complex
Date of Introduction
1996
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.

Air & Air Defense Specifications
Crew 2
Max Speed 800.0 km/h
Range 1.6 km
Service Ceiling 13600 m
Wingspan 9.60 m
Overview (Deagel)
Group Training Jets
Status Active
Also Known As JL-8, K-8E (Egyptian version), K-8J
Origin China, Pakistan
Contractors Hongdu Aircraft Industry Group*, AviChina lndustry & Technology Company Limited, Kamra Aeronautical Complex
Initial Operational Capability (IOC) 1996
First Flight November 21, 1990
Total Production 350
Specifications (Deagel)
Crew 2
Number of Engines 1
Service Life Flight Hours 8000
Area — Wing Area 17.0 square meter
Dimensions — Height 4.2 meter
Dimensions — Length 11.6 meter
Dimensions — Wingspan 9.6 meter
G-load — Max Maneuvering Load Factor 7.3 g
G-load — Min Maneuvering Load Factor -3.00 g
Mass — Empty Weight 2,757 kilogram
Mass — Fuel Load 780 kilogram
Mass — Max Takeoff Thrust 3,600 pound
Mass — Max Takeoff Weight 4,332 kilogram
Mass — Operational Weight 3,700 kilogram
Mass — Useful Load 943 kilogram
Performance — Ceiling 13,600 meter
Performance — Ferry Range 2,140 kilometer
Performance — Landing Run Distance 530 meter
Performance — Max Range 1,560 meter
Performance — Take Off Run Distance 440 meter
Speed — Climb Rate 30 mps
Speed — Top Speed at Sea Level 800 kph
Time — Flight Endurance 3.2 hour
Gear (Deagel)
Item 1 Turbofan Engines: AI-25TLK or WS-11 (1)
Item 2 Turbofan Engines: TFE731-2A (1)
Details
Country of Origin China
Classification
Domain
Air & Air Defense
Equipment Status
Active
Dimensions
Length
11.6 m
Width
9.6 m
Height
4.2 m
Weight
4332 kg
Operators (7)
China
Pakistan
Egypt
Myanmar
Namibia
Venezuela
Zambia
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