A Symbol of Excellence in Aviation


K8 aircraft
Karakoram-8 (K-8), Basic Cum Advance Jet Trainer, is co-developed by Aircraft Manufacturing Factory (AMF), Pakistan Aeronautical Complex, Kamra, and China Nanchang Aircraft Manufacturing Company (CNMC). The aircraft is being used for imparting basic and operational jet training to newly inducted pilots at PAF Academy Risalpur. Its key features are:
  • Wide speed range and high maneuverability
  • Satisfactory flying qualities in accordance with the requirements set forth in MIL-F-8785C IV for highly maneuverable aircraft.
  • Good field of view and cockpit arrangement very close to a combat aircraft
  • Advanced turbofan engine with low specific fuel consumption and minimum operation and maintenance cost
  • State of the art equipment (including instrumentation, communication, navigation, etc.) satisfying the requirements of training pilots for the future
  • Highly reliable escape system
  • Advanced strap on environmental control system capable of providing cockpit air- conditioning both on the ground and in the air
  • Hydraulically operated wheel braking and nose wheel steering
  • Multi role capability for training
  • 8000 flight hours service life for airframe structure
  • Long endurance and high service ceiling adequate for a wide range of missions
  • Low life cycle cost
  • Short turn-around time and low maintenance work load

Technical Data

Power Plant Egress System / Escape System
K-8 is fitted with Honeywell TFE 731-2A-2A modular turbofan
engine with DEEC & hydro mechanical fuel control system.
Highly reliable escape system incorporating two Martin
Baker MK-10L fully automatic rocket assisted zero-zero
ejection seats to ensure survival capability within the entire
flight envelope.
Cockpit Layout Environmental Control System (ECS)
Cockpit is designed to meet the latest Military Specification
of Aircrew Station Geometry and vision requirements. EFIS
made by Collins is fitted in front and rear cockpits. UHF/VHF
communication system, TACAN/RADIO COMPASS & ILS are
available as per the customers requirement.
Incorporation of most effective ECS provides a roomy cockpit
environment with air conditioning capability even on
ground under an ambient temperature of -40 °C to +52 °C.
Fuel System Weights
The aircraft fuel system consists of the fuel tanks and the
fuel supply / transfer, vent/pressurization, fuel quantity
measuring / indicating, refuelling and fuel drain subsystems.
The total fuel contained in two fuselage bladder-type
rubber tanks and a wing integral tank is 2576 lbs. The
capacity of drop tanks is 428 lbs each.
Normal take-off weight : 3700 kg
Useful load : 943 kg
Internal fuel capacity : 780 kg
Weight empty : 2757 kg
Maximum take-off weight : 4332 kg

Engine Main Data TFE 731-2A-2A Flight Performance
Rated power maximum static thrust at sea level : 3600 lbs
SFC : 0.502 lb/lb thrust hr (maximum static thrust)
Air flow : 115 lbs /sec (take-off and maximum continuous)
Engine net weight : 812 lb
Pressure ratio : 13.9
Bypass ratio : 2.67
An access through which the engine is installed/removed,
is provided on the belly of the fuselage. With this provision,
replacement of the engine in the field takes 50 minutes
Maximum level speed : 800 km/hr
Rate of climb at sea level : 30 m/s
Service ceiling : 13600 m
Built-in Range : 1560 km
Ferry range (with drop tanks) : 2140 km
Endurance : 3.2 hrs
Maximum endurance (with drop tanks) : 4.2 hrs
Un-stick speed : 185 km/hr
Touchdown speed : 160 km/hr
Take-off ground run : 440 m
Landing ground run : 530 m
Limit load factor : +7.33 g -3.0 g
Overall length : 11.6 m
Overall height : 4.21 m
Wing area : 17.02 m2
Wing span : 9.63 m
Wheel track : 2.54 m
Wheel base : 4.442 m
The customers of K-8 are:
China Namibia Sri Lanka Ghana Bolivia
Pakistan Egypt Sudan Venezuela Zimbabwe