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C-5 Galaxy
IOC: 1970
Total Production: 126
Total Program's Cost: USD$23 billion
C-5M Super Galaxy
IOC: 2009
Also Known As
C-5 RERP
Origin
United States of America
Contractor/s
Lockheed Martin
Family Members
C-5 Galaxy
Power plant:
CF6-80C2 (4)
F138-GE-100 (4)
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Description:
The Avionics Modernization Program (AMP) will provide C-5s with a modern glass cockpit featuring digital avionics and flight instrumentation. The C-5A/B Reliability Enhancement and Re-engining Program (RERP) includes new F103 engines (a derivative of proven CF6 commercial engines), pylons and auxiliary power units, with upgrades to aircraft skin and frame, landing gear and the pressurization system. Overall RERP includes more than 70 system and equipment improvements.
AMP and RERP programs will restore C-5's maintainability and reliability, maintain structural and system integrity, reduce overall ownership costs and increase operational capability well into the 21st century. Overall, the C-5 upgraded aircraft fleet mission capable rate would represent at least 75 percent. The US Air Force (USAF) long-term goal is to keep the C-5 strategic transport aircraft fleet viable for the next 40 years. In actual facts, AMP program is the first phase of such effort, while RERP program will act as the second phase leading to the fully upgraded C-5 aircraft.
The AMP package installation on US Air Force C-5s started in June 2004 and is expected to last several years. In October 2004, the first C-5 AMP was delivered to Lockheed-Martin to undergo RERP upgrade modifications. The RERP program will see the first C-5 aircraft taking to the air in October 2005 or later for testing powered by four fuel efficient F138-GE-100 engines (a CF6-80C2 derivative). The test program is expected to complete in 2007. The C-5 aircraft that had received both AMP and RERP modifications will be re-designated C-5M. As of early 2006, the USAF plans call for 112 C-5A/B aircraft to undergo C-5M modernization program through 2020.
Specifications
Accommodation: Crew 7
Dimensions: Height 19.8 m, Length 75 m, Wingspan 67.9 m
Weights: Max Weight 381 t, Payload 122,500 kg (270,062 lb)
Engine/s Performance: Thrust 290,000 lb (131,544 kg)
Performance: Max Range 3,980 km (2,149 nm), Top Speed 256 mps (Mach 0.77)
Other: Number of Engines 4
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Notes
(*) lead contractor
IOC: Initial Operating Capability
FOC: Full Operating Capability
CEP: Circular Error Probable
Comm: Commissioning Date
Meters (m) Kilometers (km) Nautic Miles (nm) Inch (in) Yard (yd) Foot (ft) Millimeter (mm)
Pound (lb) Kilogram (kg) kN (KiloNewton) Ton (t)
Meters per Second (mps) Kilometers per Hour (kph) Knot (kt) Miles per Hour (mph)
Liter (l) Galon (gl)
Year (yr) Minutes (min) Second (sec)
Shaft-Horse-Power (shp)
Last Updated: Saturday, October 25, 2008
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