CH-53 Super Stallion

Description The CH-53E Super Stallion has proven to be extraordinarily relevant to the execution of our national security strategy, Navy and Marine Corps warfighting concepts and the associated need for capable heavy lift. From the Scott O’Grady rescue mission in the Balkans to delivering critically needed combat support in Afghanistan, Iraq and the Horn of Africa, the CH-53E has been in incredibly high demand. There are currently 152 CH-53E aircraft in operation. The Super Stallion incorporates GPS, doppler radar, FLIR, and ANVIS-HUD sensors, and carries 7.62mm and 50 caliber guns (as a mission kit). Communications include UHF/VHF/HF radios, secure comm. capability, and IFF. Currently out of production. Requirement exists to operate the CH-53E through 2025, necessitating a Service Life Extension Program (SLEP).

Specifications Fuselage Length: 73 feet, 4 inches Overall Length: 99 feet Height: 2 8 feet, 4 inches Max Gross Weight: 73,500 pounds (with external load) Speed: 172 miles/hour (150 knots) Ceiling: 10,000 feet (without supplemental oxygen) Range: 621 statute miles (540 nautical miles) Power Plant: 3 General Electric T64-GD-416 turboshaft (4,380 SHP each) Crew: 4 – pilot, copilot, crew chief, and mechanic/gunner Contractor: Sikorsky Aircraft

T-6A Texan II turboprop trainer

Description

The T-6A Texan II is one component of the Joint Primary Aircraft Training System (JPATS) along with simulators, computer-aided academics, and a Training Integration Management System (TIMS). The joint program, of which the Air Force acts as the executive service, will replace Navy T-34C and Air Force T-37B aircraft. The program uses commercial-off-the-shelf (COTS) subsystems to the maximum extent possible. The aircraft-built by Raytheon Aircraft Company is a derivative of the Swiss Pilatus PC-9 aircraft with a Pratt & Whitney PT-6A-68 engine, digital cockpit, Martin-Baker ejection seats, cockpit pressurization, and an onboard oxygen-generating system. The Navy's total T-6A requirement is 328 aircraft. The T-6A entered development flight test in July 1998. The FAA approved type and production certification for the T-6A aircraft and production line on 30 July 1999. A successful flight test program and a successful Milestone III full rate production decision followed in December 2001. Both the U.S. Air Force and U.S. Navy have since entered into a full rate production contract with Raytheon for aircraft. To date the U.S. Air Force has received approximately 100 aircraft and the U.S. Navy has received 4 aircraft.

Specifications

Primary Function: All-purpose jet trainer. Contractor: Raytheon Aircraft Company. Date Deployed: First flight, July 1998; Operational, Nov. 1, 2002. Propulsion: one Pratt & Whitney Canada PT-6A-68 turboprop engine; 1,100 horsepower.

T-44 Pegasus

Description

The T-44A "Pegasus" aircraft is manufactured by Beech Aircraft Corporation, Wichita, Kansas. The aircraft is used for advanced turboprop aircraft training and for intermediate E2/C2 (carrier based turboprop radar aircraft) training at the Naval Air Station, Corpus Christi, Texas. The T-44 is equipped with deicing and anti-icing systems augmented by instrumentation and navigation equipment which allows flight under instrument and icing conditions. The interior includes a seating arrangement for an instructor pilot (right seat), a student pilot (left seat), and a second student. Two additional passenger seats are included. A distinguishing feature of the aircraft is the avionics fault insertion capabilities afforded the instructor pilot from the right-seat armrest and the second student/observer audio control panel that allows the second student to monitor all radio communications. The T-44A is powered by two 550 shaft horsepower PT6A-34B turboprop engines manufactured by Pratt & Whitney of Canada.

Specifications Primary Function: Training platform for Navy/Marine Corps pilots. Contractor: Beechcraft Propulsion: two Pratt & Whitney Canada PT-6A-34B 550 hp engines Length: 35 feet 6 inches Height: 14 feet 3 inches Wingspan: 50 feet 3 inches Airspeed maximum: 245 knots Ceiling: 31,300 feet. Range: 1,300 nautical miles Armament: None

T-45 Goshawk

Description The T-45A aircraft, the Navy version of the British Aerospace Hawk aircraft, is used for intermediate and advanced portions of the Navy/Marine Corps pilot training program for jet carrier aviation and tactical strike missions. The T-45A has replaced the T-2 Buckeye trainer and the TA-4 trainer with an integrated training system that includes the T-45A Goshawk aircraft, operations and instrument fighter simulators, academics, and training integration system. There are two versions of T-45 aircraft currently in operational use at this time, the T-45A and T-45C derivatives. The T-45A, which became operational in 1991, contains an analog design cockpit while the new T-45C (began delivery in December 1997) is built around a new digital "glass cockpit" design.

Specifications

Primary Function: Training platform for Navy/Marine Corps pilots. Contractor: Boeing Company. Date Deployed: First flight, April 1988; Operational, 1991. Unit Cost: $17.2 million. Propulsion: Rolls Royce F405-RR-401 turbofan engine with 5,527 pounds thrust. Length: 39 feet 4 inches (11.98 meters). Height: 13 feet 6 inches (4.11 meters).

TH-57 Sea Ranger

Description

The JetRanger was initially designed to compete in a U.S. Army light observation helicopter competition. Bell lost that competition but the 206 was commercially successful. The TH-57 Sea Ranger provides advanced (IFR) training to several hundred aviation students a year at Naval Air Station Whiting Field in Milton, Florida.

Specifications

Contractor: Bell Helicopter Textron. Date Deployed: First flight: 1961; Operational: 1968. Propulsion: One Allison 250-C20BJ turbofan engine. Length: Fuselage - 31 feet (9.44 meters); Rotors turning - 39 feet (11.9 meters). Height: 10 feet (3.04 meters). Rotor Diameter: 35 feet 4 inches (10.78 meters). Weight: 1595 pounds (725kg) empty, 3200 pounds (1455 kg) maximum take off. Airspeed: 138 miles (222 km) per hour maximum; 117 miles (188 km) per hour cruising. Ceiling: 18,900 feet (5,761 meters). Range: 368 nautical miles (420 statute miles, 676 km). Crew: One pilot, four students.

E-2C Hawkeye

Description

The E-2C is a twin engine, five crewmember, high-wing turboprop aircraft with a 24-foot diameter radar rotodome attached to the upper fuselage. The Hawkeye provides all-weather airborne early warning, airborne battle management and command and control functions for the Carrier Strike Group and Joint Force Commander. Additional missions include surface surveillance coordination, air interdiction, offensive and defensive counter air control, close-air support coordination, time critical strike coordination, search and rescue airborne coordination and communications relay. An integral component of the Carrier Strike Group air wing, the E-2C uses computerized radar, Identification Friend or Foe and electronic surveillance sensors to provide early warning, threat analysis against potentially hostile air and surface targets.

Specifications Primary Function: Airborne Command & Control, Battle Space Management. Contractor: Northrop Grumman Aerospace Corp. Date Deployed: January 1964. Unit Cost: $80 million. Propulsion: Two Allison T-56-A427 turboprop engines; (5,100 shaft horsepower each). Length: 57 feet 6 inches (17.5 meters). Height: 18 feet 3 inches (5.6 meters). Wingspan: 80 feet 7 inches (28 meters). Weight: Max. gross, take-off: 53,000 lbs (23,850 kg) 40,200 lbs basic (18,090 kg). Airspeed: 300+ knots (345 miles, 552 km. per hour). Ceiling: 30,000 feet (9,100 meters). Crew: Five.

F/A-18 E-F Super Hornet

Description

Built on the nation’s first strike fighter, the F-18 Hornet, today’s F/A-18E/F Super Hornet is an attack aircraft as well as a fighter through selected use of external equipment and advanced networking capabilities to accomplish specific missions. This “force multiplier” capability gives the operational commander more flexibility in employing tactical aircraft in a rapidly changing battle scenario. In its fighter mode, it serves as escort and fleet air defense. In its attack mode, it provides force projection, interdiction, and close and deep air support.

Specifications

Overall Length: 60 ft 3 inches Wing Area: 44 ft 9 inches Weight (Empty): Maximum Take Off Gross Weight is 66,000 pounds (29,932 kg). Internal Fuel: 18,840 lbs Speed: Mach 1.7+ Ceiling: 50,000 ft+ Range: Combat: 1,275 nautical miles (2,346 kilometers), clean plus two AIM-9s; Ferry: 1,660 nautical miles (3,054 kilometers), two AIM-9s, three 480 gallon tanks retained Crew: E models One; F models Two Armament: One M61A1/A2 Vulcan 20mm cannon; AIM 9 Sidewinder, AIM-9X (projected), AIM 7 Sparrow, AIM-120 AMRAAM, Harpoon, Harm, SLAM, SLAM-ER (projected), Maverick missiles; Joint Stand-Off Weapon (JSOW); Joint Direct Attack Munition (JDAM); Data Link Pod; Paveway Laser Guided Bomb; various general purpose bombs, mines and rockets

MH-65C Dolphin

Overview:

The H-65 helicopter — the Coast Guard’s most ubiquitous aircraft — is certified for operation in all-weather and night-time operations, with the exception of icing conditions. The H-65 is the only Coast Guard aircraft used aboard certified cutters during deployments. FLIR, a heads-up display and other avionics upgrades are being installed aboard the H-65 for law-enforcement operations. H-65 crews have completed night-vision goggle implementation, greatly enhancing night-time search capabilities. There are 101 H-65s in the inventory. As part of the ongoing H-65 Conversion / Sustainment Project, all HH-65Bs have been upgraded to HH-65C configuration, equipped with Turbomecca Arriel 2C2 engines. Furthermore, the re-designation of AUF HH-65Cs to MH-65Cs reflects the installation of armament and a significantly upgraded communications package. Helicopter Interdiction Tactical Squadron (HITRON) Jacksonville was the first operational Coast Guard unit to employ the MH-65C and have a total of 10 assigned to replace the MH-68As.

Specifications Power Plant

MH-65C: Two 853 shp Turbomeca Arriel 2C2-CG has turbine engines Performance

Max Speed: 175 knots (MH-65C) Cruising Speed: 148 nautical miles (MH-65C) Service Ceiling ~10,000 ft Range: 290 nautical miles (MH-65C)

Weight Gross Weight:9,480 lbs (MH-65C)

Dimensions Rotor Diameter: 39ft 2in Length: 44ft 5in Height: 13ft 5in

Crew 2 pilots 1 flight mechanic 1 rescue swimmer

MH-60 Sea Hawk

Description

The Sikorsky SH-60/MH-60 Seahawk (or Sea Hawk) is a twin turboshaft engine, multi-mission United States Navy helicopter based on the United States Army UH-60 Black Hawk and a member of the Sikorsky S-70 family. The most significant airframe modification is a hinged tail to reduce its footprint aboard ships. Able to deploy aboard any air-capable frigate, destroyer, cruiser, fast combat support ship, amphibious assault ship, or aircraft carrier, the Seahawk can handle anti-submarine warfare (ASW), anti-surface warfare (ASUW), naval special warfare (NSW) insertion, search and rescue (SAR), combat search and rescue (CSAR), vertical replenishment (VERTREP), and medical evacuation (MEDEVAC). All Navy H-60s carry a rescue hoist for SAR/CSAR missions.

specifications Crew: 3–4 Capacity: 5 passengers in cabin, slung load of 6,000 lb (2,700 kg) or internal load of 4,100 lb (1,900 kg) for B, F and H models; and 11 passengers or slung load of 9,000 lb (4,100 kg) for S-model Length: 64 ft 8 in (19.75 m) Rotor diameter: 53 ft 8 in (16.35 m) Height: 17 ft 2 in (5.2 m) Disc area: 2,262 ft² (210 m²) Empty weight: 15,200 lb (6,895 kg) Loaded weight: 17,758 lb (8,055 kg) ; for ASW mission Useful load: 6,684 lb (3,031 kg) Max. takeoff weight: 21,884 lb (9,927 kg) Powerplant: 2 × General Electric T700-GE-401C turboshaft, 1,890 shp (1,410 kW) take-off power each

T-39 Saberliner

Description

North American began development of the Sabreliner as an in-house project, and in response to the UTX request for proposals, they offered a military version to the Air Force. UTX combined two different roles, personnel transport and combat readiness training, into the same aircraft. The civilian version prototype, which carried the model number NA-265, made its first flight on September 16, 1958. It was powered by a pair of General Electric YJ85 turbojet engines. The type received its FAA certification in April 1963. The UTX candidate, designated the T-39A, was identical in configuration to the NA-265, but when the contract was awarded and the T-39A entered production, it was powered with two Pratt & Whitney JT12A8 turbojet engines.

specifications Crew: 4–5 Capacity: 5–7 passengers Length: 44 ft (13.41 m) Wingspan: 44 ft 6 in (13.56 m) Height: 16 ft (4.88 m) Wing area: 342.1 ft² (31.79 m²) Empty weight: 9,257 lb (4,199 kg) Loaded weight: 16,340 lb (7,412 kg) Max. takeoff weight: 17,760 lb (8,056 kg) Powerplant: 2 × Pratt & Whitney J60-P-3 turbojet, 3,000 lbf (13.3 kN) each

A-4 Skyhawk

Description

The delta winged, single-engined Skyhawk was designed and produced by Douglas Aircraft Company, and later McDonnell Douglas. It was originally designated the A4D under the U.S. Navy's pre-1962 designation system. The A-4 is a compact, light-weight design with a maximum takeoff weight of 24,500 pounds (11,100 kg) and has a top speed of more than 600 miles per hour (970 km/h).[1] The aircraft's five hardpoints support a variety of missiles, bombs and other munitions and was capable of delivering nuclear weapons using a low altitude bombing system and a "loft" delivery technique. Prior to the A-4E, power was supplied by the Wright J65; with the A-4E, the installed engine became the 9,300-pound-force (41 kN) Pratt & Whitney J52.

Specifications Crew: 1 (2 in OA-4F, TA-4F, TA-4J) Length: 40 ft 3 in (12.22 m) Wingspan: 26 ft 6 in (8.38 m) Height: 15 ft (4.57 m) Wing area: 259 ft² (24.15 m²) Airfoil: NACA 0008-1.1-25 root, NACA 0005-0.825-50 tip Empty weight: 10,450 lb (4,750 kg) Loaded weight: 18,300 lb (8,318 kg) Max. takeoff weight: 24,500 lb (11,136 kg) Powerplant: 1 × Pratt & Whitney J52-P8A turbojet, 9,300 lbf (41 kN)

A-10 Thunderbolt

Description

The Fairchild Republic A-10 Thunderbolt II is an American single-seat, twin-engine, straight-wing jet aircraft developed by Fairchild-Republic in the early 1970s. The A-10 was designed for a United States Air Force requirement to provide close air support (CAS) for ground forces by attacking tanks, armored vehicles, and other ground targets with a limited air interdiction capability. It is the first U.S. Air Force aircraft designed solely for close air support. The A-10 was designed around the GAU-8 Avenger, a heavy rotary cannon which forms the aircraft's primary armament (and is, to date, the heaviest rotary cannon ever mounted on an aircraft). The aircraft's hull incorporates over 1,200 pounds (540 kg) of armor and was designed with survivability as a priority, with protective measures in place which enable the aircraft to continue flying even after taking significant damage.

Specifications Crew: 1 Length: 53 ft 4 in (16.26 m) Wingspan: 57 ft 6 in (17.53 m) Height: 14 ft 8 in (4.47 m) Wing area: 506 ft² (47.0 m²) Airfoil: NACA 6716 root, NACA 6713 tip Empty weight: 24,959 lb (11,321 kg) Loaded weight: 30,384 lb (13,782 kg) On CAS mission: 47,094 lb (21,361 kg) On anti-armor mission: 42,071 lb (19,083 kg) Max. takeoff weight: 50,000 lb (23,000 kg) Powerplant: 2 × General Electric TF34-GE-100A turbofans, 9,065 lbf (40.32 kN) each