Ling-Temco-Vought (LTV) XC-142 Airplane Videos and Airplane Pictures

Ling-Temco-Vought (LTV) XC-142 Video - Newsreel - XC-142A

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Ling-Temco-Vought (LTV) XC-142 Video - Overview

Ling-Temco-Vought (LTV) XC-142 Aircraft Information

Airplane Picture - XC-142A at the National Museum of the U.S. Air Force

Picture - XC-142A at the National Museum of the U.S. Air Force

Role: Experimental VTOL transport
Manufacturer: Ling-Temco-Vought (LTV)
First flight: September 29, 1964,
Primary user: NASA
Number built: 5

The Ling-Temco-Vought (LTV) XC-142 is a tiltwing experimental aircraft designed to investigate the operational suitability of vertical/short takeoff and landing transports. An XC-142A first flew conventionally on September 29, 1964, and on January 11, 1965, it completed its first transitional flight by taking off vertically, changing to forward flight and finally landing vertically. Its participants pulled out of the program one-by-one and it eventually ended due to a lack of interest after demonstrating its capabilities successfully.


In 1959 the United States Army, Navy and Air Force began work on the development of a prototype V/STOL airplane that could augment helicopters in transport-type missions. Specifically they were interested in designs with longer range and higher speeds than existing helicopters, in order to support operations over longer distances, or in the case of the US Marine Corps, from further offshore. On 27 January 1961 a series of DOD actions resulted in an agreement where all of the military arms would work on such a project under the overall leadership of the Navy's Bureau of Naval Weapons (BuWeps), the Tri-Service Assault Transport Program.

The original outline had been drawn up as a replacement for the Sikorsky HR2S, with a payload on the order of 10,000 lb (5,000 kg). BuWeps released a revised specification that specified the same payload, but extended the operational radius to 250 miles (400 km) and increased the cruising airspeed to 250-300 knots (460-560 km/h) and the maximum airspeed to 300-400 knots (560-740 km/h). However, for the Marine Corps mission, the requirement stated that the fuel load could be reduced so that the maximum gross weight would not exceed 35,000 pounds (16,000 kg), as long as a 100-nautical-mile (190 km) radius was maintained.

Vought responded with a proposal combining engineering from their own design arm, as well as Ryan and Hiller, who had more extensive helicopter experience. Their proposal won the design contest, and a contract for five prototypes was signed in early 1962 with first flight specified for July 1964. The design was initially known as the Vought-Ryan-Hiller XC-142, but when Vought became part of the LTV conglomerate this naming was dropped.

During the prototype development the Navy decided to exit the program. They were concerned that the strong propeller downwash would make it difficult to operate. Their existing HR2S fleet had a ground pressure of about 7.5 psi (500 hPa), and proved to blow people about on the ground and stir up considerable amounts of debris. The C-142 was predicted to have an even higher loading of 10 psi (700 hPa), which they believed would limit it to operations to and from prepared landing pads and was therefore unsuitable for assault operations.

The first prototype made its first conventional flight on 29 September 1964, first hover on 29 December 1964, and first transition on 11 January 1965. The first XC-142A was delivered to the Air Force test team in July 1965. During the XC-142A program, a total of 420 hours were flown in 488 flights. The five XC-142A's were flown by 39 different military and civilian pilots. Tests included carrier operations, simulated rescues, paratroop drops, and low-level cargo extraction.

During testing the aircraft's cross-linked drive shaft proved to be its Achilles heel. The shaft resulted in excessive vibration and noise, resulting in a high pilot workload. Additionally, it proved susceptible to problem due to wing flexing. Shaft problems, along with operator errors, resulted in a number of hard landings causing damage. One crash occurred as a result of a failure of the drive shaft to the tail rotor, causing three fatalities. One of the limitations found in the plane was an instability between wing angles of 35 and 80 degrees, encountered at extremely low altitudes. There were also high side forces which resulted from yaw and weak propeller blade pitch angle controls. The new "2FF" propellers also proved to generate less thrust than predicted.

Nevertheless the aircraft did seem to be successful for a prototype. In 1966, while the tests were still being performed, the Air Force requested a proposal for a production version, the C-142B. Since the Navy had backed out by this time, a major improvement was proposed to eliminate the Navy carrier compatibility requirement, which could dramatically reduce the empty weight. Other changes proposed for this version included a streamlined cockpit, larger fuselage, upgraded engines and simplified engine maintenance.

After reviewing the C-142B proposal, the tri-services management team could not develop a requirement for a V/STOL transport. XC-142A testing ended and the remaining flying copy was turned over to the NASA for research testing from May 1966 to May 1970.

A civilianised version, the Downtowner, was also proposed. This was designed to carry 40-50 passengers at a cruise speed of 290 mph (470 km/h) using only two of its engines.


The basic design was fairly typical for a cargo aircraft, consisting of a large boxy fuselage with a tilted rear area featuring a loading ramp. It had a wingspan of 67 ft (20 m) and was 58 ft (18 m) long overall. The fuselage housed a 30 ft (9.1 m) long, 7.5 ft (2.3 m) wide 7 ft (2.1 m) high cargo area with a somewhat boxy cockpit on the front for the crew of two pilots and a load master. The wing was high-mounted and the tail surfaces were a "semi-T-tail" to keep the rear area clear during loading. Tricycle landing gear were used, with the main legs retracting into blisters on the fuselage sides. In normal parked configuration it would appear to be a conventional cargo plane.

For S/VTOL operations, the aircraft "converted" by tilting its wing to the vertical. Roll control during hover was provided by differential clutching of the propellers, while yaw used the ailerons, which were in the airflow. For pitch control the aircraft featured a separate tail rotor, oriented horizontally to lift the tail, as opposed to the more conventional anti-torque rotors on helicopters that are mounted vertically. When on the ground, the tail rotor folded against the tail to avoid being damaged during loading. The wing could be rotated to 100 degrees, past vertical, in order to hover in a tailwind.

The C-142 was powered by four General Electric T64 turboshaft engines driving four 15.5-foot (4.7 m) Hamilton Standard fiberglass propellers. The engines and propellers were cross-linked on a common drive-shaft in order to prevent asymmetric thrust problems during VTOL operations in case of an engine-out situation. The aircraft was overpowered compared to conventional designs; each engine generated 3,080 shp to power an airframe with a 45,000 lb (20,000 kg) maximum weight, as compared to the contemporary C-130 Hercules (the D model) which featured four 3,750 hp engines powering a 125,000 lb (57,000 kg) aircraft. This extra power was required for VTOL operations in an engine-out situation, but also gave the aircraft excellent performance all-around. This included a very high maximum speed of over 400 mph (640 km/h), making it the fastest VTOL aircraft of the era. It could lose an engine on take-off and still clear a 50 ft (20 m) barrier in 400 ft (120 m) carrying a 10,000 pounds (5,000 kg) payload. Climb at sea level was a very good 6,800 ft/min (2,100 m/min), and an otherwise excellent 3,500 ft/min (1,100 m/min) with an engine out.

In service it would carry 32 equipped troops or 8,000 pounds (4,000 kg) of cargo. It had maximum gross weight of 41,000 pounds (19,000 kg) for a vertical take-off, or 45,000 pounds (20,000 kg) for a short take-off.


Of the five aircraft built, only one still survives.

XC-142A (s/n 65-5924) is on display in the experimental aircraft hangar at the National Museum of the United States Air Force at Wright-Patterson Air Force Base near Dayton, Ohio. It was flown to the Museum in 1970.

Specifications (XC-142A)

General characteristics

Crew: 2-3
Length: 58 ft 2 in (17.7 m)
Wingspan: 67 ft 6 in (20.6 m)
Height: 25 ft 8 in (7.8 m)
Max takeoff weight: 41,500 lb (18,824 kg)
Powerplant: 4x General Electric T64 turboshaft, 3,080 hp (2,298 kW) each


Maximum speed: 400 mph (643 km/h)
Cruise speed: 235 mph (378 km/h)
Range: 820 mi (1,319 km)
Service ceiling: 25,000 ft (7,620 m)


Comparable aircraft

Hiller X-18
Canadair CL-84
V-22 Osprey

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Source: WikiPedia

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