The C-20A/B, military versions of the Gulfstream III, was chosen in June 1983 as the replacement aircraft for the C-140B Jetstar. Three A models were delivered to the 89th Airlift Wing under a cost-saving accelerated purchase plan. Upon delivery of the C-20B's, Andrews transferred the three C-20A's to Ramstein Air Base and all C-140B's at both locations were phased out of the U.S. Air Force inventory. In 1992, Gulfstream delivered their latest model, the C-20H (Gulfstream IV) to Andrews AFB. In 2002, the C-20A was selected for decommissioning and two C-20Hs at Andrews were transferred to Ramstein.

General Characteristics
Primary Function: C-20B/H, special air and operational support airlift missions
Builder: Gulfstream Aerospace Corp.
Power Plant: C-20B, two Rolls-Royce Spey Mark 511-8 turbofan engines;C-20H, two Rolls-Royce Tay Mark 611-8 turbofan engines
Thrust: C-20B, 11,400 pounds each engine; C-20H, 13,850 pounds each engine
Length: C-20B, 83 feet, 2 inches (25.4 meters); C-20H, 88 feet, 4 inches (26.9 meters)
Height: 24 feet, 6 inches (7.5 meters)
Wingspan: 77 feet, 10 inches (23.7 meters)
Speed: 576 mph (501 nautical miles per hour) maximum
Maximum Takeoff Weight: C-20B, 69,700 pounds (31,610 kilograms); C-20H, 74,600 pounds (33,832 kilograms)
Range: C-20B, 4,250 miles (3,698 nautical miles) long-range; C-20H, 4,850 miles (4,220 nautical miles) long range
Ceiling: 45,000 feet (13,716 meters)
Load: 12 passengers
Unit Cost: All models, $29.4 (fiscal 1998 constant dollars)
Crew: Five (pilot, copilot, flight engineer, communication system operator, flight attendant)
Date Deployed: C-20B, 1988; C-20H, 1992
Inventory: C-20B, Active force, 5; ANG, 0; Reserve, 0
C-20H, Active force, 2; ANG, 0; Reserve, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=87

C-21

Delivery of the C-21 fleet began in April 1984 and was completed October 1985. DynCorp Technical Services provides full contractor logistics support at seven worldwide locations. C-21s stationed outside the continental United States are assigned to the theater commanders. Air Mobility Command is the lead command for the aircraft.

General Characteristics
Primary Function: Passenger and cargo airlift
Contractor: Learjet, Inc.
Power Plant: Two Garrett TFE-731-2-2B turbofan engines
Thrust: 3,500 pounds each engine
Maximum Takeoff Weight: 18,300 pounds (8,235 kilograms)
Length: 48 feet, 7 inches (14.71 meters)
Height: 12 feet, 3 inches (3.71 meters)
Wingspan: 39 feet, 6 inches (11.97 meters)
Fuel Capability: 931 gallons (3,537.8 liters) [1,120 gallons (4,256 liters) with ferry tanks]
Speed: 530 mph (Mach 0.81, 461 knots at 41,000 feet (12,496.8 meters)
Range: 2,306 miles (3,689.6 kilometers)
Ceiling: 45,000 feet (13,716 meters)
Maximum Load: : Eight passengers and 3,153 pounds (1,433 kilograms) of cargo, one litter patient or five ambulatory patients.
Crew: Two (pilot and co-pilot); aeromedical evacuation adds medical crew of three (one flight nurse and two medical technicians). Minimal medical crew may be one flight nurse and one medical technician as required
Unit Cost: $3.1 million (fiscal 1996 constant dollars)
Initial operating capability: April 1984
Inventory: Active forces, 34; ANG, 21; Reserve, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=88

C-22B

The aircraft 83-4615 began its career in 1965 as N-4615, "Jean," a Boeing 727-35 purchased by National Airlines and entered into service in February 1965. In the early 1980's, National Airlines was bought by Pan American Airways, who then renamed N-4615 "Ring Leader." She served there until she was sold to Boeing Military Aircraft in 1983 under a contract to the National Guard for airlift service for the National Guard Bureau.

General Characteristics

Primary Function: Passenger Transportation
Builder: Boeing Co.
Base model: C-22
Version:B
Power Plant: Three JT8D-7 turbofan engines
Thrust: 14,000 pounds each engine
Length: 133 feet, 2 inches (40.3 meters)
Height: 34 feet, (10.3 meters)
Empty Weight:80,602 lb, 36,554 kg
Gross Weight:170,000 lb, 77,097 kg
Wingspan: 108 feet (32.7 meters)
Maximum Take-off Weight: 170,000 pounds (76,500 kilograms)
Wingarea: 1,650.0 sq ft, 153.2 sq m
Maximum Payload: 20,000 pounds (9,000 kilograms)
Maximum Speed: 619 mph (Mach 0.82)
Range: 2,000 miles (1,739 nautical miles)
Endurance: 5.5 hours
Crew: Pilot, co-pilot, flight engineer, flight mechanic, and three or four in-flight passenger specialists
Unit Cost: No longer available.
Designation Period: 1962-Present
Date Deployed: 1963.
Inventory: Active force, 0; ANG, 3; Reserve, 0.

For more info go to http://www.boeing-c22b.org/aboutaircraft.php

C-32

he C-32 is a military version of the Boeing 757-200 extended range aircraft, selected along with the C-37A to replace the aging fleet of C-137 aircraft. Active-duty aircrews from the 1st Airlift Squadron, 89th Airlift Wing at Andrews Air Force Base, Md., fly the aircraft.

General Characteristics
Primary Function: High-priority personnel transport
Builder: Boeing Company
Power Plant: Two Pratt and Whitney 2040 engines
Thrust: 41,700 pounds static thrust each engine
Length: 155 feet, 3 inches (47.32 meters)
Height: 44 feet, 6 inches (11.02 meters)
Wingspan: 124 feet, 8 inches (37.99 meters)
Maximum Takeoff Weight: 255,000 pounds (115,668 kilograms)
Range: 5,500 nautical miles unrefueled range
Ceiling: 42,000 feet (12,727 meters)
Speed: 530 miles per hour (Mach 0.8)
Load: 45 passengers
Unit Cost: Unavailable
Crew: 16 (varies with mission)
Date Deployed: June 19, 1998
Inventory: Active force, 4; ANG: 0; Reserve: 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=90

C-37A

The 89th Airlift Wing's 99th Airlift Squadron, Andrews Air Force Base, Md., operates four C-37A's. The 6th Air Mobility Wing's 310th Airlift Squadron, MacDill AFB, Fla., operates three C-37A's. Both the 15th Airlift Wing, 65th Airlift Squadron at Hickam AFB, Hawaii, and the 86th Airlift Wing, 309th Airlift Squadron, at Chievres Air Base, Belgium, have one C-37A.

General Characteristics
Primary Function: Special air missions
Builder: Gulfstream Aerospace Corp.
Power Plant: Two BMW/Rolls Royce BR710A1-10 high bypass ratio turbofan engines
Thrust: 14,750 pounds each engine
Length: 96 feet, 5 inches (29.38 meters)
Height: 25 feet, 11 inches (7.9 meters)
Wingspan: 93 feet, 6 inches (28.5 meters)
Speed: 600 mph (.885 Mach) maximum
Maximum Altitude: 51,000 feet (15,545 meters)
Maximum Takeoff Weight: 90,500 pounds (41,050 kilograms)
Range: 6,300 miles (5,500 nautical miles) normal cruise
Load: 12 passengers
Unit Cost: $36 million (1998 constant dollars)
Crew: Five
Date Deployed: 1998
Inventory: Active force, 9; Air National Guard, 0; Reserve, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=91

C-40B/C

The Air Force selected the C-40B, a military version of the Boeing 737-700 Business Jet, to replace the aging fleet of C-137 aircraft for U.S. combatant commanders. The Air Force awarded the medium lift contract in August 2000.

General Characteristics
Primary Function: High-priority personnel transport
Prime Contractor: Boeing (airframe) and CFM International (engines)
Power Plant: Two GE CFM 56-7B27 turbofan engines
Thrust: 27,000 pounds static thrust each engine
Length: 110 feet, 4 inches (33.6 meters)
Height: 41 feet, 2 inches (12.5 meters)
Maximum Takeoff Weight: 171,000 pounds
Wingspan: 117 feet, 5 inches (35.8 meters)
Speed: 530 mph (Mach 0.8)
Ceiling: 41,000 feet (12,727 meters)
Fuel Capability: 60,000 lbs
Maximum Range: 4,500 to 5,000 nautical miles (based on payload) unrefueled range
Maximum Load: C-40B: 26 to 32 passengers; C-40C: 42 to 111 passengers
Crew:10 (varies with model and mission)
Date Deployed: Feb. 28, 2003
Unit Cost: $70 million
Inventory: Active force, 2 (4 planned); ANG, 2 (3 planned); Air Force Reserve, 3

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=189

C-5 Galaxy

Lockheed-Georgia Co. delivered the first operational Galaxy to the 437th Airlift Wing, Charleston Air Force Base, S.C., in June l970. C-5s are operated by active-duty, Reserve, and Air National Guard crews. They are currently stationed at Dover AFB, Del.; Travis AFB, Calif.; Lackland AFB, Texas; Stewart Air National Guard Base, N.Y.; Martinsburg ANGB, W.V.; Memphis ANGB, Tenn.; Wright-Patterson AFB, Ohio and Westover Air Reserve Base, Mass.

General Characteristics
Primary Function: Outsize cargo transport
Prime Contractor: Lockheed-Georgia Co.
Power Plant: Four General Electric TF-39 engines
Thrust: 43,000 pounds, each engine
Wingspan: 222.9 feet (67.89 meters)
Length: 247.1 feet (75.3 meters)
Height: 65.1 feet (19.84 meters)
Cargo Compartment: height , 13.5 feet (4.11 meters); width, 19 feet (5.79 meters); length, 143 feet, 9 in (43.8 meters)
Pallet Positions: 36
Maximum Cargo: 270,000 pounds (122,472 kilograms)
Maximum Takeoff Weight: 769,000 pounds (348,818 kilograms) (peacetime), 840,000 pounds (381,024 kilograms) (wartime)
Speed: 518 mph (.77 Mach)
Range: 6,320 nautical miles without air refueling; unlimited with in-flight refueling
Crew: 7 (pilot, co-pilot, two flight engineers and three loadmasters)
Unit Cost: C-5A - $152.8 million (fiscal 1998 constant dollars); C-5B - $179 million (fiscal 1998 constant dollars); Modification unit cost, $90 million (fiscal 2009 constant dollars)
Deployed: C-5A - 1969, C-5B - 1980, C-5M - 2009
Inventory: Total force, 111; C-5A, 59, C-5B, 47, C-5C, 2, C-5M, 3

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=84

E-3 Sentry (AWACS)

As proven in operations Desert Storm, Allied Force, Enduring Freedom and Iraqi Freedom, the E-3 Sentry is the premier C2BM aircraft in the world. AWACS aircraft and crews were instrumental to the successful completion of operations Northern and Southern Watch, and are still engaged in operations Noble Eagle and Enduring Freedom. They provide radar surveillance and control in addition to providing senior leadership with time-critical information on the actions of enemy forces. The E-3 has also deployed to support humanitarian relief operations in the U.S. following Hurricanes Rita and Katrina, coordinating rescue efforts between military and civilian authorities.

General Characteristics
Primary Function: Airborne battle management, command and control
Contractor: Boeing Aerospace Co.
Power Plant: Four Pratt and Whitney TF33-PW-100A turbofan engines
Thrust: 21,000 pounds each engine
Rotodome: 30 feet in diameter (9.1 meters), 6 feet thick (1.8 meters), mounted 11 feet (3.33 meters) above fuselage
Wingspan: 145 feet, 9 inches (44.4 meters)
Length: 152 feet, 11 inches (46.6 meters)
Height: 41 feet, 9 inches (13 meters)
Weight: 335,000 pounds (151,955 kilograms)
Maximum Takeoff Weight: 347,000 pounds (156,150 kilograms)
Fuel Capacity: 23,000 gallons (104,560 liters)
Speed: optimum cruise 360 mph (Mach 0.48)
Range: more than 5,000 nautical miles (9,250 kilometers)
Ceiling: Above 29,000 feet (8,788 meters)
Crew: Flight crew of four plus mission crew of 13-19 specialists (mission crew size varies according to mission)
Unit Cost: $270 million (fiscal 98 constant dollars)
Initial operating capability: April 1978
Inventory: Active force, 33 (1 test); Reserve, 0; Guard, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=98

F-15C Eagle

F-15C, D and E models were deployed to the Persian Gulf in 1991 in support of Operation Desert Storm where they proved their superior combat capability. F-15C fighters accounted for 34 of the 37 Air Force air-to-air victories. F-15E's were operated mainly at night, hunting SCUD missile launchers and artillery sites using the LANTIRN system.

General Characteristics
Primary function: Tactical fighter
Contractor: McDonnell Douglas Corp.
Power plant: Two Pratt & Whitney F100-PW-100, 220 or 229 turbofan engines with afterburners
Thrust: (C/D models) 23,450 pounds each engine
Wingspan: 42.8 feet (13 meters)
Length: 63.8 feet (19.44 meters)
Height: 18.5 feet (5.6 meters)
Weight: 31,700 pounds
Maximum takeoff weight: (C/D models) 68,000 pounds (30,844 kilograms)
Fuel Capacity: 36,200 pounds (three external plus conformal fuel tanks)
Payload: depends on mission
Speed: 1,875 mph (Mach 2 class)
Ceiling: 65,000 feet (19,812 meters)
Range: 3,450 miles (3,000 nautical miles) ferry range with conformal fuel tanks and three external fuel tanks
Crew: F-15A/C: one. F-15B/D/E: two
Armament: One internally mounted M-61A1 20mm 20-mm, six-barrel cannon with 940 rounds of ammunition; four AIM-9 Sidewinder and four AIM-120 AMRAAMs or eight AIM-120 AMRAAMs, carried externally.
Unit Cost: A/B models - $27.9 million (fiscal 98 constant dollars);C/D models - $29.9 million (fiscal 98 constant dollars)
Initial operating capability: September 1975
Inventory: Total force, 522

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=101

F-15E Strike Eagle

The F-15's superior maneuverability and acceleration are achieved through its high engine thrust-to-weight ratio and low-wing loading. It was the first U.S. operational aircraft whose engines' thrust exceeded the plane's loaded weight, permitting it to accelerate even while in vertical climb. Low-wing loading (the ratio of aircraft weight to its wing area) is a vital factor in maneuverability and, combined with the high thrust-to-weight ratio, enables the aircraft to turn tightly without losing airspeed.

General Characteristics
Primary function: Air-to-ground attack aircraft
Contractor: McDonnell Douglas Corp.
Power plant: Two Pratt & Whitney F100-PW-220 or 229 turbofan engines with afterburners
Thrust: 25,000 - 29,000 pounds each engine
Wingspan: 42.8 feet (13 meters)
Length: 63.8 feet (19.44 meters)
Height: 18.5 feet (5.6 meters)
Weight: 37,500 pounds ( 17,010 kilograms)
Maximum takeoff weight: 81,000 pounds (36,450 kilograms)
Fuel capacity: 35,550 pounds (three external tanks plus conformal fuel tanks)
Payload: depends upon mission
Speed: 1,875 mph (Mach 2.5 plus)
Range: 2,400 miles (3,840 kilometers) ferry range with conformal fuel tanks and three external fuel tanks
Ceiling: 60,000 feet (18,288 meters)
Armament: One 20mm multibarrel gun mounted internally with 500 rounds of ammunition. Four AIM-9 Sidewinder missiles and four AIM-120 AMRAAM, or eight AIM-120 AMRAAM missiles. Any air-to-surface weapon in the Air Force inventory (nuclear and conventional)
Crew: Pilot and weapon systems officer
Unit cost: $31.1 million (fiscal 98 constant dollars)
Initial operating capability: September 1989
Inventory: Total force, 223

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=102

F-16 Fighting Falcon

The F-16B, a two-seat model, has tandem cockpits that are about the same size as the one in the A model. Its bubble canopy extends to cover the second cockpit. To make room for the second cockpit, the forward fuselage fuel tank and avionics growth space were reduced. During training, the forward cockpit is used by a student pilot with an instructor pilot in the rear cockpit.

General Characteristics
Primary Function: Multirole fighter
Contractor: Lockheed Martin Corp.
Power Plant: F-16C/D: one Pratt and Whitney F100-PW-200/220/229 or General Electric F110-GE-100/129
Thrust: F-16C/D, 27,000 pounds
Wingspan: 32 feet, 8 inches (9.8 meters)
Length: 49 feet, 5 inches (14.8 meters)
Height: 16 feet (4.8 meters)
Weight: 19,700 pounds without fuel (8,936 kilograms)
Maximum Takeoff Weight: 37,500 pounds (16,875 kilograms)
Fuel Capacity: 7,000 pounds internal (3,175 kilograms); typical capacity, 12,000 pounds with two external tanks (5443 kilograms)
Payload: Two 2,000-pound bombs, two AIM-9 and 1,040-gallon external tanks
Speed: 1,500 mph (Mach 2 at altitude)
Range: More than 2,002 miles ferry range (1,740 nautical miles)
Ceiling: Above 50,000 feet (15 kilometers)
Armament: One M-61A1 20mm multibarrel cannon with 500 rounds; external stations can carry up to six air-to-air missiles, conventional air-to-air and air-to-surface munitions and electronic countermeasure pods
Crew: F-16C, one; F-16D, one or two
Unit cost: F-16A/B , $14.6 million (fiscal 98 constant dollars); F-16C/D,$18.8 million (fiscal 98 constant dollars)
Initial operating capability: F-16A, January 1979; F-16C/D Block 25-32, 1981;
F-16C/D Block 40-42, 1989; and F-16C/D Block 50-52, 1994
Inventory: Total force, F-16C/D, 1,280

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=103

F-22 Raptor

The Advanced Tactical Fighter entered the Demonstration and Validation phase in 1986. The prototype aircraft (YF-22 and YF-23) both completed their first flights in late 1990. Ultimately the YF-22 was selected as best of the two and the engineering and manufacturing development effort began in 1991 with development contracts to Lockheed/Boeing (airframe) and Pratt & Whitney (engines). EMD included extensive subsystem and system testing as well as flight testing with nine aircraft at Edwards Air Force Base, Calif. The first EMD flight was in 1997 and at the completion of its flight test life this aircraft was used for live-fire testing.

General Characteristics
Primary Function: Air dominance, multi-role fighter
Contractor: Lockheed-Martin, Boeing
Power Plant: Two Pratt & Whitney F119-PW-100 turbofan engines with afterburners and two-dimensional thrust vectoring nozzles.
Thrust: 35,000-pound class (each engine)
Wingspan: 44 feet, 6 inches (13.6 meters)
Length: 62 feet, 1 inch (18.9 meters)
Height: 16 feet, 8 inches (5.1 meters)
Weight: 43,340 pounds (19,700 kilograms)
Maximum Takeoff Weight: 83,500 pounds (38,000 kilograms)
Fuel Capacity: Internal: 18,000 pounds (8,200 kilograms); with 2 external wing fuel tanks: 26,000 pounds (11,900 kilograms)
Payload: Same as armament air-to-air or air-to-ground loadouts; with or without 2 external wing fuel tanks.
Speed: Mach 2 class with supercruise capability
Range: More than 1,850 miles ferry range with 2 external wing fuel tanks (1,600 nautical miles)
Ceiling: Above 50,000 feet (15 kilometers)
Armament: One M61A2 20-millimeter cannon with 480 rounds, internal side weapon bays carriage of two AIM-9 infrared (heat seeking) air-to-air missiles and internal main weapon bays carriage of six AIM-120 radar-guided air-to-air missiles (air-to-air loadout) or two 1,000-pound GBU-32 JDAMs and two AIM-120 radar-guided air-to-air missiles (air-to-ground loadout)
Crew: One
Unit Cost: $143 million
Initial operating capability: December 2005
Inventory: Total force, 137

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=199

HH-60G Pave Hawk

The Pave Hawk is a twin-engine medium-lift helicopter operated by Air Combat Command, Pacific Air Forces, Air Education and Training Command, U.S. Air Forces in Europe, Air National Guard and Air Force Reserve Command.

General Characteristics
Primary Function: Personnel recovery in hostile conditions and military operations other than war in day, night or marginal weather
Contractor: United Technologies/Sikorsky Aircraft Company
Power Plant: Two General Electric T700-GE-700 or T700-GE-701C engines
Thrust: 1,560-1,940 shaft horsepower, each engine
Rotor Diameter: 53 feet, 7 inches (14.1 meters)
Length: 64 feet, 8 inches (17.1 meters)
Height: 16 feet, 8 inches (4.4 meters)
Weight: 22,000 pounds (9,900 kilograms)
Maximum Takeoff Weight: 22,000 pounds (9,900 kilograms)
Fuel Capacity: 4,500 pounds (2,041 kilograms)
Payload: depends upon mission
Speed: 184 mph (159 knots)
Range: 504 nautical miles
Ceiling: 14,000 feet (4,267 meters)
Armament: Two 7.62mm or .50 caliber machineguns
Crew: Two pilots, one flight engineer and one gunner
Unit Cost: $26 million
Initial operating capability: 1982
Inventory: Active force, 70; ANG, 18; Reserve, 13

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=107

KC-10 Extender

A modified Boeing Company DC-10, the KC-10A entered service in 1981. Although it retains 88 percent systems commonality with the DC-10, it has additional systems and equipment necessary for its Air Force mission. These additions include military avionics; aerial refueling boom and aerial refueling hose and drogue; seated aerial refueling operator station; and aerial refueling receptacle and satellite communications.

General Characteristics
Primary Function: Aerial tanker and transport
Contractor: The Boeing Company
Power Plant: Three General Electric CF6-50C2 turbofans
Thrust: 52,500 pounds, each engine
Length: 181 feet, 7 inches (54.4 meters)
Height: 58 feet, 1 inch (17.4 meters)
Wingspan: 165 feet, 4.5 inches (50 meters)
Speed: 619 mph (Mach 0.825)
Ceiling: 42,000 feet (12,727 meters)
Maximum Takeoff Weight: 590,000 pounds (265,500 kilograms)
Range: 4,400 miles (3,800 nautical miles) with cargo; 11,500 miles (10,000 nautical miles) without cargo
Maximum Cargo Payload: 170,000 pounds (76,560 kilograms)
Pallet Positions: 27
Maximum Fuel Load: 356,000 pounds (160,200 kilograms)
Crew: Four (pilot, co-pilot, flight engineer and boom operator) Certain missions may require additional crew members. In aeromedical evacuation missions, a basic crew of five (two flight nurses and three medical technicians) is added. Medical crew may be altered as required.
Unit Cost: $88.4 million (fiscal 1998 constant dollars)
Date Deployed: March 1981
Inventory: Active force, 59; ANG, 0; Reserve, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=109

KC-135 Stratotanker

Air Mobility Command manages an inventory of more than 415 Stratotankers, of which the Air Force Reserve and Air National Guard fly 235 in support of AMC's mission.

General Characteristics
Primary Function: Aerial refueling and airlift
Prime Contractor: The Boeing Company
Power Plant: CFM International CFM-56 turbofan engines
Thrust: 21,634 pounds each engine
Wingspan: 130 feet, 10 inches (39.88 meters)
Length: 136 feet, 3 inches (41.53 meters)
Height: 41 feet, 8 inches (12.7 meters)
Speed: 530 miles per hour at 30,000 feet (9,144 meters)
Ceiling: 50,000 feet (15,240 meters)
Range: 1,500 miles (2,419 kilometers) with 150,000 pounds (68,039 kilograms) of transfer fuel; ferry mission, up to 11,015 miles (17,766 kilometers)
Maximum Takeoff Weight: 322,500 pounds (146,285 kilograms)
Maximum Transfer Fuel Load: 200,000 pounds (90,719 kilograms)
Maximum Cargo Capability: 83,000 pounds (37,648 kilograms), 37 passengers
Pallet Positions: 6
Crew: Three: pilot, co-pilot and boom operator. Some KC-135 missions require the addition of a navigator. The Air Force has a limited number of navigator suites that can be installed for unique missions.
Aeromedical Evacuation Crew: A basic crew of five (two flight nurses and three medical technicians) is added for aeromedical evacuation missions. Medical crew may be altered as required by the needs of patients.
Unit Cost: $39.6 million (fiscal 98 constant dollars)
Date Deployed: August 1956
Inventory: Active duty, 180; Air National Guard, 171; Air Force Reserve, 64

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=110

MH-53J/M Pave Low

The MH-53J's mission is to perform low-level, long-range, undetected penetration into denied areas, day or night, in adverse weather, for infiltration, exfiltration and resupply of special operations forces.

For more info go to http://www.fas.org/programs/ssp/man/uswpns/air/rotary/h53.html

T-1A Jayhawk

The first T-1A was delivered to Reese Air Force Base, Texas, in January 1992, and student training began in 1993.

General Characteristics
Primary Function: Advanced trainer for airlift and tanker pilots
Builder: Raytheon Corp. (Beech)
Power Plant: Two Pratt and Whitney JT15D-5B turbofan engines
Thrust: 2,900 pounds each engine
Length: 48 feet, 5 inches (14.75 meters)
Height: 13 feet, 11 inches (4.24 meters)
Wingspan: 43 feet, 6 inches (13.25 meters)
Maximum Speed: 538 miles per hour (Mach .70)
Ceiling: 41,000 feet (12,500 meters)
Maximum Takeoff Weight: 16,100 pounds (7,303 kilograms)
Range: 2,222 nautical miles (2,900 nm flying long-range cruise)
Armament: None
Crew: Three (pilot, co-pilot, instructor pilot)
Date Deployed: February 1992
Unit Cost: $4.1 million
Inventory: Active force, 178; ANG, 0; Reserve, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=123

T-37 Tweet

The T-37 Tweet is a twin-engine jet used for training undergraduate pilots, undergraduate navigator and tactical navigator students in fundamentals of aircraft handling, and instrument, formation and night flying.

Primary Function	Primary trainer in undergraduate pilot training, undergraduate navigator and tactical navigator training
Builder	Cessna Aircraft Co.
Power Plant	Two Continental J69-T-25 turbojet engines
Thrust	1,025 pounds (461.25 kilograms), each engine
Length	29 feet, 3 inches (8.9 meters)
Height	9 feet, 2 inches (2.8 meters)
Maximum Takeoff Weight	6,625 pounds (2,981 kilograms)
Wingspan	33 feet, 8 inches (10.2 meters)
Speed	315 mph (Mach 0.4 at sea level)
Ceiling	35,000 feet (10.6 kilometers)
Range	460 miles (400 nautical miles)
Armament	T-37B, none; T-37C has provisions for external armament
Unit Cost	$164,854
Crew	Two, student pilot and instructor pilot
Date Deployed	December 1956
Inventory	Active force, 507; ANG, 0; Reserve 0

For more info go to http://www.fas.org/programs/ssp/man/uswpns/air/trainer/t37.html

T-38 Talon

The Talon first flew in 1959. More than 1,100 were delivered to the Air Force between 1961 and 1972 when production ended. As the T-38 fleet has aged, specific airframe, engine and system components have been modified or replaced. Pacer Classic is the name given to a sustainment program that integrates essential modifications, and includes major structural replacements into one process.

General Characteristics
Primary Function: Advanced jet pilot trainer
Builder: Northrop Corp.
Power Plant: Two General Electric J85-GE-5 turbojet engines with afterburners
Thrust: 2,050 pounds dry thrust; 2,900 with afterburners
Thrust (with PMP): 2,200 pounds dry thrust; 3,300 with afterburners
Length: 46 feet, 4 inches (14 meters)
Height: 12 feet, 10 inches (3.8 meters)
Wingspan: 25 feet, 3 inches (7.6 meters)
Speed: 812 mph (Mach 1.08 at sea level)
Ceiling: Above 55,000 feet (16,764 meters)
Maximum Takeoff Weight: 12,093 pounds (5,485 kilograms)
Range: 1,093 miles
Armament: T-38A/C: none; AT-38B: provisions for practice bomb dispenser
Unit Cost: $756,000 (1961 constant dollars)
Crew: Two, student and instructor
Date Deployed: March 1961
Inventory: Active force, 546; ANG, 0; Reserve 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=126

T-43A

The majority of the T-43A trainers are used for navigator training at Randolph Air Force Base, Texas, where the Air Force also trains Air National Guard, Air Force Reserve, U.S. Navy, U.S. Marine and international students. The remaining planes are assigned to the Air National Guard at Buckley Air National Guard Base, Colo., where they are used for the U.S. Air Force Academy's airmanship program and to provide travel service for academy sports teams. In addition, U.S. Southern Command has a CT-43 used for commander transport.

General Characteristics

Primary Function: Navigator trainer

Builder: Boeing Co.

Power Plant: Two Pratt & Whitney JT8D-9A engines

Thrust: 14,500 pounds (6,525 kilograms) each engine

Length: 100 feet (30.3 meters)

Height: 37 feet (11.2 meters)

Maximum Takeoff Weight: 115,000 pounds (67,500 kilograms)

Wingspan: 93 feet (28.2 meters)

Speed: 535 mph (Mach 0.72) at 35,000 feet

Ceiling: 37,000 feet (11,212 meters)

Range: 2,995 miles (2,604 nautical miles)

Armament: None

Crew: 12 navigator students, six instructor navigators, pilot and co-pilot

Date Deployed: September 1973

Unit Cost: $5,390,000

Inventory: Active force, 13; ANG, 2; Reserve, 0

For more info go to http://usmilitary.about.com/library/milinfo/affacts/blt-43a.htm

C-17 Globemaster III

The C-17 made its maiden flight on Sept. 15, 1991, and the first production model was delivered to Charleston Air Force Base, S.C., June 14, 1993. The first squadron of C-17s, the 17th Airlift Squadron, was declared operationally ready Jan. 17, 1995. The Air Force originally programmed to buy a total of 120 C-17s, with the last one being delivered in November 2004. Current budget plans involve purchasing 205 aircraft.

General Characteristics
Primary Function: Cargo and troop transport
Prime Contractor: Boeing Company
Power Plant: Four Pratt & Whitney F117-PW-100 turbofan engines
Thrust: 40,440 pounds, each engine
Wingspan: 169 feet 10 inches (to winglet tips) (51.75 meters)
Length: 174 feet (53 meters)
Height: 55 feet 1 inch (16.79 meters)
Cargo Compartment: length, 88 feet (26.82 meters); width, 18 feet (5.48 meters); height, 12 feet 4 inches (3.76 meters)
Speed: 450 knots at 28,000 feet (8,534 meters) (Mach .76)
Service Ceiling: 45,000 feet at cruising speed (13,716 meters)
Range: Global with in-flight refueling
Crew: Three (two pilots and one loadmaster)
Aeromedical Evacuation Crew: A basic crew of five (two flight nurses and three medical technicians) is added for aeromedical evacuation missions. Medical crew may be altered as required by the needs of patients
Maximum Peacetime Takeoff Weight: 585,000 pounds (265,352 kilograms)
Load: 102 troops/paratroops; 36 litter and 54 ambulatory patients and attendants; 170,900 pounds (77,519 kilograms) of cargo (18 pallet positions)
Unit Cost: Unit Cost: $202.3 million (fiscal 1998 constant dollars)
Date Deployed: June 1993
Inventory: Active duty, 158; Air National Guard, 8; Air Force Reserve, 8

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=86

T-6A

Before being formally named in 1997, the T-6A was identified in a 1989 Department of Defense Trainer Aircraft Master Plan as the aircraft portion of the Joint Primary Aircraft Training System, or JPATS. The system includes a suite of simulators, training devices and a training integration management system

General Characteristics
Primary Function: Entry-level trainer in joint primary pilot training
Builder: Raytheon Aircraft Co.
Powerplant: 1,100 horsepower Pratt & Whitney Canada PT6A-68 turbo-prop engine
Wingspan: 33.5 feet (10.19 meters)
Length: 33.4 feet (10.16 meters)
Height: 10.7 feet (3.23 meters)
Speed: 320 miles per hour
Standard Basic Empty Weight: 6,500 pounds (2,955 kilograms)
Ceiling: 31,000 feet (9448.8 meters)
Range: 900 nautical miles (1,667 kilometers)
Crew: Two, student pilot and instructor pilot
Armament: None
Date Deployed: May 2000
Unit Cost: $4.272 million
Inventory: Active force, 446

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=124

A-10 Thunderbolt II

The first production A-10A was delivered to Davis-Monthan Air Force Base, Ariz., in October 1975. It was designed specially for the close air support mission and had the ability to combine large military loads, long loiter and wide combat radius, which proved to be vital assets to the United States and its allies during Operation Desert Storm and Operation Noble Anvil.

General Characteristics
Primary Function: A-10 -- close air support, A-10C - airborne forward air control
Contractor: Fairchild Republic Co.
Power Plant: Two General Electric TF34-GE-100 turbofans
Thrust: 9,065 pounds each engine
Wingspan: 57 feet, 6 inches (17.42 meters)
Length: 53 feet, 4 inches (16.16 meters)
Height: 14 feet, 8 inches (4.42 meters)
Weight: 29,000 pounds (13,154 kilograms)
Maximum Takeoff Weight: 51,000 pounds (22,950 kilograms)
Fuel Capacity: 11,000 pounds (7,257 kilograms)
Payload: 16,000 pounds (7,257 kilograms)
Speed: 420 miles per hour (Mach 0.56)
Range: 800 miles (695 nautical miles)
Ceiling: 45,000 feet (13,636 meters)
Armament: One 30 mm GAU-8/A seven-barrel Gatling gun; up to 16,000 pounds (7,200 kilograms) of mixed ordnance on eight under-wing and three under-fuselage pylon stations, including 500 pound (225 kilograms) Mk-82 and 2,000 pounds (900 kilograms) Mk-84 series low/high drag bombs, incendiary cluster bombs, combined effects munitions, mine dispensing munitions, AGM-65 Maverick missiles and laser-guided/electro-optically guided bombs; infrared countermeasure flares; electronic countermeasure chaff; jammer pods; 2.75-inch (6.99 centimeters) rockets; illumination flares and AIM-9 Sidewinder missiles.
Crew: One
Unit Cost: Not available
Initial operating capability: A-10A, 1977; A-10C, 2007
Inventory: Active force, A-10, 143 and A-10C, 70; Reserve, A-10, 46 and OA-10, 6; ANG, A-10, 84 and OA-10, 18

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=70

B-1B Lancer

The B-1A was initially developed in the 1970s as a replacement for the B-52. Four prototypes of this long-range, high speed (Mach 2.2) strategic bomber were developed and tested in the mid-1970s, but the program was canceled in 1977 before going into production. Flight testing continued through 1981.

General Characteristics
Primary Function: Long-range, multi-role, heavy bomber
Contractor: Boeing, North America (formerly Rockwell International, North American Aircraft); Offensive avionics, Boeing Military Airplane; defensive avionics, EDO Corporation
Power plant: Four General Electric F101-GE-102 turbofan engine with afterburner
Thrust: 30,000-plus pounds with afterburner, per engine
Wingspan: 137 feet (41.8 meters) extended forward, 79 feet (24.1 meters) swept aft
Length: 146 feet (44.5 meters)
Height: 34 feet (10.4 meters)
Weight: approximately 190,000 pounds (86,183 kilograms)
Maximum Takeoff Weight: 477,000 pounds (216,634 kilograms)
Fuel Capacity: 265,274 pounds (120,326 kilograms)
Payload: 75,000 pounds ( 34,019 kilograms)
Speed: 900-plus mph (Mach 1.2 at sea level)
Range: Intercontinental
Ceiling: More than 30,000 feet (9,144 meters)
Armament: 84 500-pound Mk-82 or 24 2,000-pound Mk-84 general purpose bombs; up to 84 500-pound Mk-62 or 8 2,000-pound Mk-65 Quick Strike naval mines; 30 cluster munitions (CBU-87, -89, -97) or 30 Wind-Corrected Munitions Dispensers (CBU-103, -104, -105); up to 24 2,000-pound GBU-31 or 15 500-pound GBU-38 Joint Direct Attack Munitions; up to 24 AGM-158A Joint Air-to-Surface Standoff Missiles
Crew: Four (aircraft commander, copilot, and two weapon systems officers)
Unit Cost: $283.1 million (fiscal 98 constant dollars)
Initial operating capability: October 1986
Inventory: Active force, 66 (test, 2); ANG, 0; Reserve, 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=81

B-2 Spirit

The first B-2 was publicly displayed on Nov. 22, 1988, when it was rolled out of its hangar at Air Force Plant 42, Palmdale, Calif. Its first flight was July 17, 1989. The B-2 Combined Test Force, Air Force Flight Test Center, Edwards Air Force Base, Calif., is responsible for flight testing the engineering, manufacturing and development aircraft on the B-2.

General Characteristics
Primary function: Multi-role heavy bomber
Contractor: Northrop Grumman Corp. and Contractor Team: Boeing Military Airplanes Co., Hughes Radar Systems Group, General Electric Aircraft Engine Group and Vought Aircraft Industries, Inc.
Power Plant: Four General Electric F118-GE-100 engines
Thrust: 17,300 pounds each engine
Wingspan: 172 feet (52.12 meters)
Length: 69 feet (20.9 meters)
Height: 17 feet (5.1 meters
Weight: 160,000 pounds (72,575 kilograms)
Maximum Takeoff Weight: 336,500 pounds (152,634 kilograms)
Fuel Capacity: 167,000 pounds (75750 kilograms)
Payload: 40,000 pounds (18,144 kilograms)
Speed: High subsonic
Range: Intercontinental
Ceiling: 50,000 feet (15,240 meters)
Armament: Conventional or nuclear weapons
Crew: Two pilots
Unit cost: Approximately $1.157 billion (fiscal 98 constant dollars)
Initial operating capability: April 1997
Inventory: Active force: 20 (1 test); ANG: 0; Reserve: 0

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?id=82

B-52 Stratofortress

For more than 40 years B-52 Stratofortresses have been the backbone of the manned strategic bomber force for the United States. The B-52 is capable of dropping or launching the widest array of weapons in the U.S. inventory. This includes gravity bombs, cluster bombs, precision guided missiles and joint direct attack munitions. Updated with modern technology the B-52 will be capable of delivering the full complement of joint developed weapons and will continue into the 21st century as an important element of our nation's defenses. Current engineering analyses show the B-52's life span to extend beyond the year 2040.

General Characteristics
Primary Function: Heavy bomber
Contractor: Boeing Military Airplane Co.
Power plant: Eight Pratt & Whitney engines TF33-P-3/103 turbofan
Thrust: Each engine up to 17,000 pounds
Wingspan: 185 feet (56.4 meters)
Length: 159 feet, 4 inches (48.5 meters)
Height: 40 feet, 8 inches (12.4 meters)
Weight: Approximately 185,000 pounds (83,250 kilograms)
Maximum Takeoff Weight: 488,000 pounds (219,600 kilograms)
Fuel Capacity: 312,197 pounds (141,610 kilograms)
Payload: 70,000 pounds (31,500 kilograms)
Speed: 650 miles per hour (Mach 0.86)
Range: 8,800 miles (7,652 nautical miles)
Ceiling: 50,000 feet (15,151.5 meters)
Armament: Approximately 70,000 pounds (31,500 kilograms) mixed ordnance -- bombs, mines and missiles. (Modified to carry air-launched cruise missiles)
Crew: Five (aircraft commander, pilot, radar navigator, navigator and electronic warfare officer
Unit Cost: $53.4 million (fiscal 98 constant dollars)
Initial operating capability: April 1952
Inventory: Active force, 85; ANG, 0; Reserve, 9

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=83

C-130 Hercules

Four decades have elapsed since the Air Force issued its original design specification, yet the remarkable C-130 remains in production. The initial production model was the C-130A, with four Allison T56-A-11 or -9 turboprops. A total of 219 were ordered and deliveries began in December 1956. The C-130B introduced Allison T56-A-7 turboprops and the first of 134 entered Air Force service in May 1959.

General Characteristics
Primary Function: Global airlift
Contractor: Lockheed Martin Aeronautics Company
Power Plant:
C-130E: Four Allison T56-A-7 turboprops; 4,200 prop shaft horsepower
C-130H: Four Allison T56-A-15 turboprops; 4,591prop shaft horsepower
C-130J: Four Rolls-Royce AE 2100D3 turboprops; 4,700 horsepower
Length: C-130E/H/J: 97 feet, 9 inches (29.3 meters)
C-130J-30: 112 feet, 9 inches (34.69 meters)
Height: 38 feet, 10 inches (11. 9 meters)
Wingspan: 132 feet, 7 inches (39.7 meters)
Cargo Compartment:
C-130E/H/J: length, 40 feet (12.31 meters); width, 119 inches (3.12 meters); height, 9 feet (2.74 meters). Rear ramp: length, 123 inches (3.12 meters); width, 119 inches (3.02 meters)
C-130J-30: length, 55 feet (16.9 meters); width, 119 inches (3.12 meters); height, 9 feet (2.74 meters). Rear ramp: length, 123 inches (3.12 meters); width, 119 inches (3.02 meters)
Speed:
C-130E: 345 mph/300 ktas (Mach 0.49) at 20,000 feet (6,060 meters)
C-130H: 366 mph/318 ktas (Mach 0.52) at 20,000 feet (6,060 meters)
C-130J: 417 mph/362 ktas (Mach 0.59) at 22,000 feet (6,706 meters)
C-130J-30: 410 mph/356 ktas (Mach 0.58) at 22,000 feet (6,706 meters)
Ceiling:
C-130J: 28,000 feet (8,615 meters) with 42,000 pounds (19,090 kilograms) payload
C-130J-30: 26,000 feet (8,000 meters) with 44,500 pounds (20,227 kilograms) payload.
C-130H: 23,000 feet (7,077 meters) with 42,000 pounds (19,090 kilograms) payload.
C-130E: 19,000 feet (5,846 meters) with 42,000 pounds (19,090 kilograms) payload
Maximum Takeoff Weight:
C-130E/H/J: 155,000 pounds (69,750 kilograms)
C-130J-30: 164,000 pounds (74,393 kilograms)
Maximum Allowable Payload:
C-130E, 42,000 pounds (19,090 kilograms)
C-130H, 42,000 pounds (19,090 kilograms)
C-130J, 42,000 pounds (19,090 kilograms)
C-130J-30, 44,000 (19,958 kilograms)
Maximum Normal Payload:
C-130E, 36,500 pounds (16,590 kilograms)
C-130H, 36,500 pounds (16,590 kilograms)
C-130J, 34,000 pounds (15,422 kilograms)
C-130J-30, 36,000 pounds (16,329 kilograms)
Range at Maximum Normal Payload:
C-130E, 1,150 miles (1,000 nautical miles)
C-130H, 1,208 miles (1,050 nautical miles)
C-130J, 2,071 miles (1,800 nautical miles)
C-130J-30, 1,956 miles (1,700 nautical miles)
Range with 35,000 pounds of Payload:
C-130E, 1,438 miles (1,250 nautical miles)
C-130H, 1,496 miles (1,300 nautical miles)
C-130J, 1,841 miles (1,600 nautical miles)
C-130J-30, 2,417 miles (2,100 nautical miles)
Maximum Load:
C-130E/H/J: 6 pallets or 74 litters or 16 CDS bundles or 92 combat troops or 64 paratroopers, or a combination of any of these up to the cargo compartment capacity or maximum allowable weight.
C-130J-30: 8 pallets or 97 litters or 24 CDS bundles or 128 combat troops or 92 paratroopers, or a combination of any of these up to the cargo compartment capacity or maximum allowable weight.
Crew: C-130E/H: Five (two pilots, navigator, flight engineer and loadmaster)
C-130J/J-30: Three (two pilots and loadmaster)
Aeromedical Evacuation Role: A basic crew of five (two flight nurses and three medical technicians) is added for aeromedical evacuation missions. Medical crew may be decreased or increased as required by the needs of patients.
Unit Cost: C-130E, $11.9, C-130H, $30.1, C-130J, $48.5 (FY 1998 constant dollars in millions)
Date Deployed: C-130A, Dec 1956; C-130B, May 1959; C-130E, Aug 1962; C-130H, Jun 1974; C-130J, Feb 1999
Inventory: Active force, 145; Air National Guard, 181; Air Force Reserve, 102

For more info go to http://www.af.mil/information/factsheets/factsheet.asp?fsID=92

C-141 Starlifter

President John F. Kennedy's first official act after his inauguration was to order the development of an all-jet transport to extend the reach of the nation's military forces. Lockheed's C-141 StarLifter was the result.

The C-141 Starlifter is the workhorse of the Air Mobility Command. The Starlifter fulfills the vast spectrum of airlift requirements through its ability to airlift combat forces over long distances, inject those forces and their equipment either by airland or airdrop, re-supply employed forces, and extract the sick and wounded from the hostile area to advanced medical facilities.

Primary Function	Long-range troop and cargo airlift.
Contractor	Lockheed-Georgia Co.
Power Plant	Four Pratt & Whitney TF33-P-7 turbofan engines.
Thrust	20,250 pounds (9,112.5 kilograms), each engine.
Length	168 feet, 4 inches (51 meters).
Height	39 feet, 3 inches (11.9 meters).
Wingspan	160 feet (48.5 meters).
Speed	500 mph (Mach 0.66).
Ceiling	41,000 feet (12,424 meters).
Maximum Takeoff Weight	323,100 pounds (145,395 kilograms).
Range	2,500 miles (2,174 nautical miles).
Unit Cost	$8.1 million (1992 dollars).
Crew	Six (pilot, co-pilot, two loadmasters, and two flight engineers).
Date Deployed	C-141A: May 1964; C-141B: December 1979.
Inventory	Active force, 241; ANG, 16; Reserve, 12.

For more info go to http://www.fas.org/programs/ssp/man/uswpns/air/cargo/c141b.html