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Brief Descriptions of the New Dowty Rotol 7 ft. Stroke Vibrator for the Institute of Aviation Medicine and the New Dowty Rotol 100,000 lb. Thrust Vibrator for Westland Aircraft Ltd. A NEW vibrator—believed to have the longest stroke in the world—was recently demonstrated by Dowty Rotol Limited. Designed and built specifically for use on human specimens at the Institute of Aviation Medicine, Farnborough, the 7‐ft. stroke vibrator is the outcome of 21 years development work. Acceptance trials were scheduled to take place last month prior to delivery to Farnborough.

THE introduction of the pure jet gas turbine propelled aeroplane appeared to herald the demise of the propeller as a means of propulsion for other than small or specialised machines.

This article is written from the viewpoint of a structures engineer who has to make the best use of the materials available, rather than that of the metallurgist who aids their production or development.

Ducted Propulsors have been designed and developed specifically for piston engine powered General Aviation aircraft. This class of aircraft is defined as having a gross weight of less than 12 500 lbs. The main purpose of the development is to reduce the noise level. General Aviation aircraft were excluded from the original plans to control aircraft noise, but about four years ago legislation was proposed and subsequently introduced to control noise of small aircraft.

Dr W. F. Hilton, D.Sc., Ph.D., F.R.Ae.S., F.B.I.S., A.F.A.I.A.A., A.R.C.S., C.Eng., has been appointed Assistant to the Director of Engineering at British Aircraft Corporation's Guided Weapons Division in Stevenage.

(in service or under development) Pegasus Vectored Thrust Turbofan Pegasus vectored‐thrust turbofan engines powering the Hawker Siddeley Harrier V/STOL aircraft in service with the RAF and US Marine Corps have been performing well in nearly 75 000 hours' operations. Ruggedness and reliability of the Pegasus have not been sacrificed to give it V/STOL capability, and time between overhaul of the Pegasus is similar to other engines at the same stage of their service life.

THE five‐hundredth production RB 211–22 has recently been delivered to power a Lockheed TriStar wide‐bodied airliner. The RB 211 entered service in April 1972 and now powers the TriStar fleets of ten airlines operating in North America, Europe, and the Middle and Far East. More than 110 TriStars are now in service, including TriStars recently delivered to Saudia, the Saudi Arabian Airline, and to Cathay Pacific Airways in Hong Kong. LTU, the West German airline, will shortly commence operation of TriStar charter flights across the North Atlantic.

A series of examples illustrates the application and results of the method previously given for improving the conditioning of the primary redundancies. The transformation matrix giving locally orthogonal redundancies for the parent station is used also to generate the primary self‐equilibrating stress systems for sections with different (but related) geometry and varying ring stiffness. A double‐cell cross‐section is also treated and a brief investigation shows that the general methods developed for establishing primary redundancies in the fuselage can be usefully and economically applied to certain kinds of wing structure. Preparatory to a detailed discussion of cut‐outs and modifications in the fuselage structure, the necessary general theory is collected and summarized.

The Minister of Aviation in agreement with the Minister of Defence for the Royal Air Force, has appointed Air Vice‐Marshal E. James, C.B.E., D.F.C., A.F.C., as a Deputy Controller in the Guided Weapons and Electronics Division of the Ministry of Aviation.

DOWTY ROTOL has recent experience in the design, manufacture and testing of two different electronically controlled wing trailing edge flap high lift actuation systems — one for the British Aerospace B.Ae.146 aircraft and the other for the Construcciones Aeronatuicas/Nurtania CN.235 aircraft. This paper discusses the application of electronics to control and monitor these systems. The resulting equipment is described and the two systems are compared for complexity, type of electronic architecture and reliability.