Hongdu JL-8
From Wikipedia, the free encyclopedia
| JL-8 K-8 Karakorum |
|
|---|---|
| Type | Jet trainer Light attack |
| Manufacturer | Hongdu Pakistan Aeronautical Complex |
| Maiden flight | 1990 |
| Status | Operational |
| Primary users | PLA Air Force Pakistani Air Force Egyptian Air Force |
| Number built | 202 |
The Hongdu JL-8 (or Nanchang JL-8) is a two-seat training aircraft built in joint-cooperation between Pakistan and the People's Republic of China (PRC). The contractor for this plane is the Hongdu Aviation Industry Corporation. Export versions are designated K-8 Karakorum.
Contents |
[edit] History
The trainer was built through joint cooperation between the governments of Pakistan and the PRC. Initially, the aircraft was to feature many American parts, but due to political developments at the end of the 1980s, this plan was scrapped. The first prototype was built in 1989, with the first flight taking place at the end of 1990.
The Pakistan Air Force (PAF) first received fourteen jets in 1994 after which it decided to order 75 more to replace its fleet of Cessna trainers. The People's Liberation Army Air Force (PLAAF) received its first six jets in 1998. Later Chinese upgrades included indigenous engines. The PLAAF is anticipated to continue adding the trainer to its fleet in order to replace older trainers that are now obsolete.
Other nations have shown interest in the trainer, and it now also serves in the air forces of Egypt, Sri Lanka, Tanzania and Zimbabwe. While the plane primarily serves as a trainer, it can also be used in the ground-attack role.
Karakorum-8 (K-8), Basic Common Advanced Jet Trainer, is co-developed by Aircraft Manufacturing Factory (AMF), Pakistan Aeronautical Complex, Kamra, and China National Aero-Technology Import & Export Corporation (CATIC).
[edit] Design
 |
This article may require cleanup to meet Wikipedia's quality standards. Please discuss this issue on the talk page or replace this tag with a more specific message. This article has been tagged since January 2007. |
- Power plant: The K-8 is fitted with the Honeywell TFE731-2A-2A modular turbofan engine with DEEC & hydro-mechanical fuel control system. Because of U.S. sanctions against China, most versions were made with the AL-25 and Chinese WS-11 engines.
- Cockpit layout: The 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.
- Egress system / escape system: A 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.
- Environmental control system (ECS): The incorporation of most effective Allied Signal 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: The aircraft's fuel system consists of the fuel tanks and the fuel supply / transfer, vent/pressurization, fuel quantity measuring / indicating, fuel refuelling and fuel drain subsystems. The total fuel is contained in two fuselage bladder-type rubber tanks and a wing integral tank is 1720 lb. The capacity of each drop tank is 250 L.
- Flight control system: The aircraft is equipped with conventional flight control surfaces controlled by a rigid push-rod transmission system and are electrically or hydraulically operated. The aileron control system, of irreversible servo-control type, is composed of a hydraulic booster, an artificial feel device, a feel trim actuator and a rigid push-rod transmission mechanism. The elevator and rudder control system is of reversible push-rod type.
[edit] Main features
|
This article may require cleanup to meet Wikipedia's quality standards. Please discuss this issue on the talk page or replace this tag with a more specific message. This article has been tagged since January 2007. |
- Wide speed range and high manoeuvrability: The aircraft has satisfactory flying qualities in accordance with the requirements set forth in MIL-F-8785C IV requirements for highly manoeuvrable aircraft.
- Vision: The aircraft has a good field of view and cockpit arrangement very close to a combat aircraft.
- Engine: The aircraft has an advanced turbofan engine with low specific fuel consumption and minimum operation and maintenance costs.
- Avionics: The aircraft has state-of-the-art equipment (including instrumentation, communication, navigation, etc.) satisfying the requirements of training pilots for the next millennium.
- Highly reliable escape system: The aircraft has an advanced strap-on environmental control system capable of providing cockpit air conditioning, both on the ground and in the air.
- Landing gear: The aircraft has hydraulically-operated wheel brakes and nose-wheel steering.
- Mission: The aircraft has a multirole capability for training. It may also be used for airfield defence with little modification.
- Service life: The aircraft has 8000 flight hours of service life for the airframe structure.
- Performance: The aircraft has a long endurance and high service ceiling adequate for a wide range of missions.
- Low life cost: The aircraft has a short turn-around time and a low maintenance workload.
[edit] Operators
China: People's Liberation Army Air Force - 30
Egypt: Egyptian Air Force - 80
Myanmar: Myanmar Armed Forces - 12
Namibia: Namibia Defense Force - 4
Pakistan: Pakistan Air Force - 30
Sri Lanka: Sri Lanka Air Force - 6 ( 3 lost in an LTTE attack )
Zambia: Zambian Defence Force - 8
Zimbabwe: Air Force of Zimbabwe - 12
[edit] Technical Data
[edit] Main data
- Rated power: 3600 lbf max static thrust at sea level
- SFC: 0.502 lb/lbf.h (Max static thrust)
- Air flow: 115 lb/s (take-off and max 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 approximately 50 minutes.
[edit] Dimensions
- 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
[edit] Weights
- Normal take-off weight: 3700 kg
- Useful load: 943 kg
- Internal fuel capacity: 780 kg
- Empty weight: 2757 kg
- Max take-off weight: 4332 kg
[edit] Flight performance
- Max level speed: 800 km/h
- Rate of climb at sea level: 30 m/s
- Service ceiling: 13,600 m
- Built-in range: 1560 km
- Ferry range (with drop tanks): 2140 km
- Endurance: 3.2 hrs
- Max endurance (with drop tanks): 4.2 h
- Unstick speed: 185 km/h
- Touchdown speed: 160 km/h
- Take-off ground run: 440 m
- Landing ground run: 530 m
- Limit load factor: +7.33/-3.0 g
[edit] Literature
- Donald, David and Lake, Jon, ed. The Encyclopedia of World Military Aircraft (2000) p.391-392. NY: Barnes & Noble. ISBN 0-7607-2208-0
[edit] External links
- K-8 Karakorum at FAS.org
- K-8 Karakorum at Aerospaceweb.org
- JL-8 at Chinese Defence Today
- Karakorum-8 at PakistaniDefence.com
- K-8 Karakorum at PakDef.info
Comparable aircraft
Designation sequence
JL-8 - JL-9 - L-15
Timeline of aviation
Aircraft · Aircraft manufacturers · Aircraft engines · Aircraft engine manufacturers · Airports · Airlines
Air forces · Aircraft weapons · Missiles · Unmanned aerial vehicles (UAVs) · Experimental aircraft
Notable military accidents and incidents · Notable airline accidents and incidents · Famous aviation-related deaths
Flight airspeed record · Flight distance record · Flight altitude record · Flight endurance record · Most produced aircraft
