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T56 / Model 501
Type	Turboprop
National origin	United States
Manufacturer	Allison Engine Company Rolls-Royce plc
Major applications	C-130 Hercules E-2 Hawkeye P-3 Orion
Developed from	Allison T38

The Allison T56 is a single shaft, modular design military turboprop with a 14 stage axial flow compressor driven by a four stage turbine. It was originally developed by the Allison Engine Company entering production in 1954, and is now produced under Rolls-Royce which acquired Allison in 1995. The commercial version is designated 501-D. Over 18,000 engines have been produced since 1954, logging over 200 million flying hours.

Contents 1 Variants 1.1 Commercial 1.2 Military 2 Applications 2.1 Military 2.2 Civilian 3 Specifications (T56 Series IV) 4 References 5 External links

[edit] Variants

[edit] Commercial

• Series I
  • 501-D13,A, D, H
• Series II
  • 501-D22
  • 501-D36A (non-type certified)
• Series III
  • 501-D22A, C, G

[edit] Military

• Series I
  • T56-A-9D, E
• Series II
  • T56-A-7A, B
  • T56-A-10WA
• Series III
  • T56-A-14, LFE
  • T56-A-15, LFE, GFE
  • T56-A-16
  • T56-A-425
• Series IV
  • T56-A-427
  • T56-A-427A Is next for the Advanced Hawkeye

[edit] Applications

[edit] Military

Notable applications include:

• Lockheed Martin C-130A-H, R, and T Hercules
• Lockheed Martin P-3 Orion
• Northrop Grumman E-2 Hawkeye
• Northrop Grumman C-2 Greyhound

[edit] Civilian

Notable applications include:

• Convair 580 and Convair 5800
• Lockheed L100 Hercules
• Lockheed L-188 Electra
• Aero Spacelines Super Guppy

[edit] Specifications (T56 Series IV)

General characteristics

• Type: Turboprop
• Length: 146.1 in (3,711 mm)
• Diameter: 27 in (690 mm)
• Dry weight: 1,940 lb (880 kg)

Components

• Compressor: 14 stage axial flow
• Combustors: 6 cylindrical flow-through
• Turbine: 4 stage
• Fuel type: JP8 2412 pounds per hour
• Oil system: 2 systems (1 each for power section and reduction gearbox)

Performance

• Maximum Power output: 4,350 shp (3,915 kW) limited to 4,100
• Overall pressure ratio: 14.5:1
• Turbine inlet temperature: 860 c
• Power-to-weight ratio: 2.75:1 (shp/lb)

[edit] References

[edit] External links

• T56 page at Rolls-Royce website

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