$4.1 million twin-engine trainer aircraft of the United States Air Force
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Manufactured by Raytheon Technologies and Hawker Beechcraft Corporation, the Raytheon T-1 Jayhawk is a trainer aircraft of the United States Air Force. The aircraft is a military version of the Hawker 400A that is utilized for advanced navigator training that can be operated in high and low altitude training missions.
The twin-jet aircraft has been used in the progressive stage of Air Force Joint Specialized Undergraduate Pilot Training for chosen students to fly a strategic or tactical airlift or a tanker plane. It is also in service with the United States Air Force Combat System Officers, and as a substitute of the T-39 Sabreliner in the intermediate stage of United States Navy or United States Marine Corps student training for naval flight officer.
On July 5 1991, the T-1 Jayhawk took its maiden flight.
In January 1992, the first aircraft was acquired by the US Air Force and dispatched to Reese Air Force base in Texas. In 1993, student training has started.
There are two variants of the T-1 Jayhawk namely, the T-1A and the T-400. The T-1A is powered by two JT15D-5B turbofan engines intended for the United States military while the T-400 commonly known as TX is intended for the Japanese military which is powered by two JT15D-5F turbofan engines. There were 180 and 13 units built respectively.
On December 15 2005, one of the military variant T-1A finished one million flight hours with the government of United States.
The T-1 Jayhawk was produced from 1992 to 1997.
T-1 Jayhawk Design
Initially designed to meet the demands of the United States Air Force and the Japan Air Self Defense Force, the T-1 Jayhawk is intended for training pilots in flying an airlift or a tanker plane. The aircraft is capable of resisting Low Level Turbulence (LLT) and dangerous bird strikes even when it is flying in a low level environment. It is capable of providing air support for a bare minimum of eighteen thousand flight hours.
The T-1 Jayhawk has an exterior length of 14.75 meters, height of 4.24 meters and fuselage diameter of 1.72 meters. Its swept wing has a wingspan of 13.25 meters and a wing area of 22.43 square meters. It has a wheelbase of 6 meters.
The aircraft has a cockpit seating for three crew; pilot, co-pilot or instructor and observer. It can also be configured with four optional seats for an additional crew member. Cockpit seats were outfitted with a five-point harness. The T-1 Jayhawk is equipped with a life raft, life vests, anti-exposure suits, crash axe, fire extinguishers and first aid kits for emergency purposes.
T-1 Jayhawk Avionics
The avionics system of the aircraft is supplied by Collins Aerospace inclusive of an Electronic Flight Instrument System (EFIS), Cathode Ray Tube (CRT) displays, an Automatic Direction Finder (ADF), a Very High Frequency (VHF) Omni-Directional Range (VOR) radio navigation system, a Horizontal Situation Indicator (HSI) that provides freedom from the uncertainty of reverse sensing on a localizer instrument approach procedure and an Aircraft Data Interface (ADI).
The aircraft is also equipped with a Distance Measuring Equipment (DME) that provides a constant slant range distance from station output by calculating time lapse of a signal being communicated by the aircraft to the station. It is also fitted with a Ground Proximity Warning System (GPWS) for warning the pilot during sudden danger, a Tactical Air Navigation System (TACAN), a Traffic Collision Avoidance System (TCAS) to minimize mid-air collision incidents between aircraft, a Radar Altimeter (RA) for measuring altitude, Weather Radar Systems and a Global Positioning System (GPS).
T-1 Jayhawk Engine and Performance
Two JT15D-5B turbofan engines from Pratt and Whitney powers the T-1 Jayhawk. Each engine has a maximum thrust of 2,900 lbf. The engine is unique among present-day turbofans because of a centrifugal compressor that acts as its main high-pressure system.
The T-1 Jayhawk has a maximum speed of 468 knots, cruising speed of 392 knots, travel range of 2,900 nautical miles, climb rate of 3,770 feet per minute and a service ceiling of 41,000 feet. It has a take off and landing distance of 1,190 meters.
The aircraft has a maximum take off and landing weight of 7,303 kg and 7,121 kg respectively. It can carry a maximum payload of 2,653 kg and a fuel tank capacity of 530 kg.