FLIGHT International, 13 January 1979 133 F107 cruise-missile turbofan. The DoD's decision to estab­lish a second source provides both emergency capacity and price competition. Teledyne's own F106 turbofan lost out to the Williams Research unit in 1975 when all four cruise-missile bidders opted for the F107. Teledyne has a substantial 30 per cent holding in Curtiss Wright, which is also working on small expendable engines in its SETE project for the US Navy. Teledyne CAE has built around 13,000 small turbojets for RPVs, missiles and aircraft. A high proportion of the engines are supplied to CAE's sister division, Teledyne Ryan.

JG9 (Models 352 and 356) Single-shaft turbojet. Probably the world's most numerous RPV engine, the J69 has been produced by the thousand to power USAF and USN Tele­dyne Ryan MQM-34s, AQM-34s, BQM-34s and BGM-34s. The main versions of the turbojet are the 1,7001b J69-T-29 and the 1,9201b J69-T-41A and J69-T-406. There is also the 1,0251b J69-T-25A for man-carrying aircraft, particularly the Cessna T-37B and -37C. Main production version at present is the J69-T-41A for the USAF. J69-T-406 specification Single-stage axial plus single-stage centrifugal compressor, annular reverse-flow combustor, single-stage turbine. Take-off 1,9201b, pressure ratio 5-45:1, mass flow 29-91b/sec, length 44-8in, width 22-3in, height 25-6in, weight 3501b.

J402 (Model 370) Single-shaft turbojet. This engine has two large-scale applications: the J402-CA-400 powers the US Navy/McDonnell Douglas AQM-84A and RQM-84A Harpoon anti-shipping missile, and the J402-CA-700 for the US Army/Beech MQM-107A Streaker Variable Speed Training Target (VSTT). Both are now in full production for US and foreign services. J402-CA-400 specification Single-stage axial plus single-stage centrifugal compressor, annular reverse-flow com­bustor, single-stage turbine. Take-off 6601b, pressure ratio 5-6:1, mass flow 9-61b/sec, length 29-44in, diameter 12-52in, weight 101 -51b.

Model 490 (Larzac) Two-shaft turbofan. The Model 490 is the licence-built version of the Turbomeca-Snecma Larzac, and is one of the engines being considered by US industry for the US Navy's VTX advanced trainer project.

TUMANSKI (USSR) The Tumanski bureau has specialised in medium-to-large

afterburning low-pressure-ratio and single-shaft turbojets for high-speed military aircraft. Its R-ll turbojet has a basic rating of 8,6001b, rising with reheat to 11,2401b on early versions, and to 13,6701b on later R'-l 1-300 versions. These engines power the MiG-21 and are licence-built in India (by HAL) and Czechoslovakia, and in China without a licence. Later MiG-21s have the uprated and lighter R-13 derivative rated at 11,2401b basic, rising to 14,5501b with reheat. Details of the R-ll and R-13 are likely to be avail­able to Western military intelligence as a result of Rolls-Royce assistance in the overhaul and repair of Egyptian MiG engines after a breakdown in Soviet and Egyptian relations. Much larger than the R-ll and R-13 is the R-266, rated at 20,1201b dry and 27,1201b with reheat. This engine powers the MiG-25 intercepter, and is now probably well known to the West as a result of the MiG-25 flight to Japan in September 1976 by a defecting Soviet pilot. Believed to be of 1950s vintage, the R-266 has led to the derivative RD-F of 31,0001b afterburning thrust, which powered the E-266M in its record-breaking time-to-height flights in 1975. This engine is likely to power more recent versions of the MiG-25.

TURBODYNE Turbodyne. Headquarters: France.

A joint venture—groupement d'interet economique—by ABG Semca and Turbomeca for development, production and marketing of auxiliary power units.

Turbodyne was formed in 1976-77 and brings together

ABG Semca's experience with alternator/generator systems and Turbomeca's small-turboshaft expertise in a new range of APUs. First of these units is the AST600 for medium-size transport aircraft. This comprises a 590 h.p. Turbomeca Astazou turboshaft driving an ABG Semca lOOkVA AC generator to form a complete APU system. Total weight of the AST600 is 3531b.

TURBOMECA (France) Turbomeca SA. Headquarters: Bordes, 64320 Bizanos. Tel: (59) 32 84 37.

Private company engaged in aero and non-aero gas-turbine manufacture. Corporate sales in 1977 were un­changed at Fr939 million (£110 million), of which aero­engine sales represented a very high proportion. Export sales accounted for 73 per cent of the total. Corporate employees about 4,600.

Turbomeca reported no growth in turnover during 1977. The order backlog, however, increased from Fr340 million (£40 million) in 1976 to Fr362 million (£42-3 million). Nine hundred engines were built during the year, repre­senting some 50 per cent of the workload. Second major activity was spare parts manufacture, equivalent to 35 per cent of turnover. Two factors are expected to assist the company's development: a forecast growth in the helicop­ter market (by far Turbomeca's largest outlet); and the development of new products, of which APUs would appear to be one sector. In 1977 the company produced 689 helicopter turboshafts, 201 turbofans/turbojets for air­craft, missiles and RPVs, six turboprops, and 12 industrial turbines.

1000PS/800KW Turboshaft. A collaborative development by a new joint company, MTU-Turbomeca SARL.

Adour Two-shaft augmented turbofan. This engine is being manufactured jointly with R-R. Control of the programme is vested in Rolls-Royce/Turbomeca.

Arbizon Single-shaft turbojet. Low-cost expendable turbo­jet for RPVs and missiles. Its main application, as the 8801b Arbizon III, is the Matra/Oto Melara Otomat ship-to-ship missile, which has been ordered in quantity by a number of navies. Production rate for this application is 14 engines a month. The lighter and more simple Arbizon IV, which first ran in July 1977, is under development at a rating of 8101b. Arbizon III specification Single-stage centrifugal com­pressor, annular reverse-flow combustor, single-stage turbine. Take-off 8801b, pressure ratio 5-5:1, length 57-5in, diameter 21-6in, weight 2531b.

Arriel Free-turbine two-shaft turboshaft. Close on 400 Arriels have now been ordered, and over 40 production engines have been delivered following manufacture of 18 prototype units. FAA certification was obtained in June 1977. As Turbomeca's entry in the 650-800 h.p. sector for the 1980s, it is firmly launched in the AS.350 Ecureuil and SA.365 Dauphin 2. Basic version of this fully modular turboshaft is the 641 s.h.p. Arriel 1. A more powerful 750-800 s.h.p. version, the Arriel III, is being studied. The new Franco-Brazilian helicopter company, Helibras, is planning to build 200 Ecureuils over the next ten years, so ensuring introduction of the Arriel into South American markets. Arriel 1 specification Single-stage axial plus single-stage centrifugal compressor, annular reverse-flow combustor, two-stage compressor turbine, single-stage power turbine. Rear-located gearbox. Take-off 690 s.h.p., pressure ratio 8:1, mass flow 5-31b/sec, length 47-2in, width 16-5in, height 24-7in, weight 2401b.

Artouste Single-shaft turboshaft. The Artouste continues in production in its 870 s.h.p. Series III version for the Aerospatiale SA.315B Lama and Alouette III. Artouste MB specification Single-stage axial plus single-