PAC MFI-17 Mushshak

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"Mushak" redirects here. For the village in Iran, see Mushak, Iran. For Mushak Kariz in Afghanistan, see List of places in Afghanistan.
MFI-17 Mushshak
Pakistan MFI-17 Super Mushshak Ryabtsev.jpg
Role Basic training aircraft + Light Attack Aircraft
Manufacturer Pakistan Aeronautical Complex
First flight 1981
Status In service In production
Primary users Pakistan Air Force
Egypt Air Force
Islamic Republic of Iran Air Force
Royal Saudi Air Force
Produced 1981-present
Number built 200+
Developed from Saab Safari

MFI-17 Mushshak (Urdu: مشاق) (English: Proficient) is a licence-built fixed-gear basic trainer aircraft improved version of the Saab Safari, used by the Pakistan Army and Pakistan Air Force. It is manufactured in Kamra, Pakistan by Pakistan Aeronautical Complex (PAC). As of 2006, 80 aircraft have been manufactured. Built to MIL-Spec and fully aerobatic, it is used for training, towing and other ground support roles. An upgraded version, the PAC Super Mushshak, has also been produced by PAC.

Design[edit]

Used for training undergraduate student pilots the fundamentals of aircraft handling, formation, instrument and night flying, the MFI-17 Mushshak is fitted with blind flying instrumentation. It is propelled by a single Textron Lycoming 4-cylinder engine with one twin-blade propeller. It has a fixed landing gear. Also used for reconnaissance, observation and transportation purposes, there are attachment points (hardpoints) under the wings for weapons, allowing the aircraft to perform light ground attack sorties and helicopter hunter missions.

Operators[edit]

 Egypt

 Iran

 Iraq

 Oman

 Pakistan

 Sierra Leone

 Syria

 Saudi Arabia

Specifications (MFI-17 Mushshak)[edit]

Data from Jane's All The World's Aircraft 1993–94[1]

General characteristics

  • Crew: 2–3, student, instructor and optional passenger
  • Length: 7.00 m (22 ft 11 12 in)
  • Wingspan: 8.85 m (29 ft 12 in)
  • Height: 2.60 m (8 ft 6 12 in)
  • Wing area: 11.90 m² (128.1 sq ft)
  • Empty weight: 646 kg (1,424 lb)
  • Max. takeoff weight: 1,200 kg (2,645 lb)
  • Powerplant: 1 × Textron Lycoming IO-360-AIB6 horizontally opposed 4-cylinder, 149 kW (200 hp)
  • Propellers: Hartzell HC-C2YK-4F/FC7666A-2 two-blade constant-speed metal propeller, 1 per engine
  • Landing gear: fixed tricycle

Performance

Armament

  • Hardpoints: 6× under-wing, maximum external load 300 kg (660 lb) total
  • Possible loads:
    • 2× 7.62 mm machine gun pods
    • 2× 75 mm unguided rocket pod (7 rounds)
    • 4× 68 mm unguided rocket pod (7 rounds)
    • 6× wire-guided anti-tank missiles (ATGMs)

See also[edit]

Related development

References[edit]

  1. ^ Lambert 1993, pp. 225–226.
  • Lambert, Mark. Jane's All The World's Aircraft 1993–94. Coulsdon, UK:Jane's Data Division, 1993. ISBN 0-7106-1066-1.

External links[edit]