M-311
Maiden Flight: Wednesday, June 01, 2005
Also Known As
M311
Origin
Italy
Contractor/s
Alenia Aermacchi
Power plant:
JT15D-5C
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Description:
The Alenia Aermacchi M-311 light jet trainer is a derivative of S-211 aircraft fitted with a new avionics suite, revised aerodynamic configuration, strengthened structure and a more powerful engine. The strengthened structures and landing gear allows for a service life of 15,000 flight hours as well as allows for an increase of maximum maneuver load factors. The new aircraft replicates military turboprop-powered trainers in terms of acquisition and life-cycle costs but with the enhanced performance of jet propulsion.
The M-311 trainer is powered by a single Pratt & Whitney Canada JT15D-5C turbofan engine developing 3,190 pounds of thrust. The engine, belonging to the commercial range, features low fuel consumption as well as outstanding reliability and performance. The aircraft's glass cockpit includes three LCDs 5x7 inches in the front and rear. In addition, the M-311 has HOTAS controls, two mission computers, GPS, HUD in the front cockpit and a rear cockpit repeater.
The Alenia Aermacchi development team has revised the accessibility for systems and has introduced a built-in Health and Usage Monitoring System (HUMS) for airframe, engine and systems to ease maintenance. Pressure refueling and OBOGS (On-Board Oxygen Generating System) also helps to reduce the maintenance workload. All in, these improvements translate into more economic operating costs and higher flight hours availability. Optionally, the M-311 may be equipped with embedded simulation, stores management system and digital moving map.
Alenia Aermacchi is marketing the M-311 as a basic jet trainer for military pilots which is intended to complement the M-346 advanced/lead-in fighter trainer. The avionics demonstrator aircraft made its maiden flight on June 1, 2005. Afterwards, the M-311 prototype was displayed at the Paris Air Show June 2005. So far, the M-311 aircraft has been evaluated by the United Kingdom and the air forces of Singapore and Turkey.
Specifications
Accommodation: Crew 2
Dimensions: Height 3.7 m, Length 9.5 m, Wing Area 13 square meter, Wingspan 8.5 m
Weights: Fuel Load 696 kg (1,534 lb), Max Takeoff Weight 4,000 kg (8,818 lb), Min Weight 2,200 kg (4,850 lb), Payload 1,000 kg (2,205 lb)
Engine/s Performance: Thrust 3,190 lb (1,447 kg)
Performance: Ceiling 40,000 ft (12,192 m), Climb Rate 4,850 fpm (), Landing Run Distance 460 m (1,509 ft), Max Range 970 nautical mile () with two auxiliary tanks, Take Off Run Distance 450 m (1,476 ft), Top Speed 400 kt (740 kph)
G Loads: Max Maneuvering Load Factor 7 g, Min Maneuvering Load Factor -4 g, Sustained Load Factor 4 g
Other: Number of Engines 1, Service Life (Flight Hours) 15,000
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