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The Short Scion

The Short Scion October, 1934 AIRCRAFT ENGINEERING 275 BRITISH CIVIL AEROPLANES A High-Wing Monoplane with Tw o Pobjoy Niagara Engines H E Short Scion is a twin-engined mono­ plane designed as a low-powered trans­ port aeroplane for small aircraft oper­ ators for special charter work or for use on feeder lines to main aircraft routes. I t is a high wing full cantilever monoplane with the engines mounted forward of the leading edge of the wing and, except for non-essential parts , is entirely of metal construction. Pobjoy Engines The engines are the 90 h.p. geared Pobjoy Fig. 3 shows the machine in part skeleton Wing Construction Niagara with the new low drag cowling and the erection and gives a good idea of the general The wing construction is well illustrated in nacelles are carefully faired into the low surface construction. Fig. 4, from which it will be seen that the of the wing. To the right may be seen the centre portion spar booms are of cruciform section with tubular The fuel is carried in light alloy tanks fitted of another fuselage with the spar attachments braces connected to the booms by fish plates. in the leading edge, the feed to the engines and centre section tubes clearly visible, while The ribs are the usual Short type of light being entirely by gravity. Each engine is on the bench in the foreground is an engine duralumin tubing and pressed duralumin sheet provided with its own petrol and oil systems. nacelle structure. rib clips with hollow steel rivets. Accessibility and ease of maintenance have ft will be seen that the leading edge is com­ received special attention both in the engine pletely sheeted in duralumin to preserve the installation and throughout the whole aeroplane. correct aerofoil section. Means are provided for starting the engines The fuel tank brackets and retaining straps from the ground. are on the front spar. The hose sheeting in this The pilot is situated in the forepart of the region is made easily detachable to facilitate fuselage in an enclosed cockpit with sliding th e removal of the tank. roof and opening side windows. The position is The exhaust is carried over the wing making slightly off centre in order to provide easy th e cabin quiet and free from fumes. access to his seat. The cabin is arranged to accommodate five Tail Unit passengers in addition to the pilot, with ample Fig. 5 illustrates the tail end, from which a seating space for each. good idea of the fuselage and tail unit con­ All control surfaces are balanced, being very struction may be gathered. The cylinder on the light in operation and well harmonized. lower longerons is for the brake gear com­ The aeroplane is of very sturdy construction, pressed air. Standard type of tail trimming the fuselage frame being of welded high tensile gear is provided, the range of adjustment being steel tube, fabric covered and suitably faired, easily adequate to cater for any variation of with the addition of a hinged nose piece of light loading. The screw gear and operating chain framework permitting easy access to the con­ and cable may be seen in the photograph. trols, dashboard, etc. PRINCIPAL CHARACTERISTICS The main spar is a built-up box girder in duralumin of a type which has proved ex­ Spa n .. .. .. .. .. 42 ft. (12·8 m.) Overall length .. .. .. .. .. 31 ft. 6 in. (9·6 m.) ceedingly satisfactory, the wings being tor- Overall height—thrust line horizontal. . . . 10 ft. 9 in. (3·28 m.) sionally very stiff with a complete absence of Fuselage width.. .. .. .. .. 3 ft. 6 m. (1·07 m.) Whee l track .. .. .. .. .. 9 ft. 8 in. (2·94 m.) vibration or tendency to "flutter." Mam plane area.. .. .. .. .. 255·5 sq ft. (23·75 sq. in.) The planes are detachable at the fuselage. Tar e weight (machine fully equipped less accumulator) 1,7101b. (775 kg.) The ribs, ailerons, tail unit, etc., follow the Fuel 31 gallons @ 7·7 lb./gal.. .. .. .. .. 239 lb. (108·5 kg.) lines of Short standard practice in duralumin. Oil, 3 gallons @ 9·7 lb./gal.. .. .. .. .. 29 lb. (13·2 kg.) Pa y load (including pilot) .. ... .. 1,022 lb. (463-3 kg.) dros s weight .. .. .. .. .. 3,000 lb. (1,360 kg.) Maximu m speed a t ground level.. .. 125 m.p.h . (201 k.p.h.j Land or Sea Plane Cruising speed (at 3,000 r.p.m.). . .. 102 m.p.h . (164 k.p.h.) Landin g speed.. .. .. .. .. 50 m.p.h . (80·3 k.p.h.) The undercarriage fittings are designed to Rat e of climb (ground level) .. .. 700 ft./m. (214 m.p.m.) tak e either a land chassis of low pressure wheels Service ceiling.. .. .. .. .. 13,000 ft. (3,970 ill.) Take-off time (no wind). , .. .. .. .. 12secs. with pneumatic brakes differentially controlled, Take-off run .. .. .. .. .. 120 yds . (109·5 in.) and friction damped spring shock absorbers; Landin g mil .. .. .. .. .. 100 yds. (91·4 in.) Petrol consumption .. .. .. .. .. 8 gallons per hour or a twin-float chassis of Short standard design Air miles pe r gallon cruising a t 3,000 r.p.m.. .. .. .. .. 12·75 and construction. Rang e emising a t 3,000 r.p.m. with 30 gallons of fuel 380 miles (612 kms.) For the land undercarriage a fully castoring tail wheel is fitted. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

The Short Scion

Aircraft Engineering and Aerospace Technology , Volume 6 (10): 1 – Oct 1, 1934
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029860
Publisher site
See Article on Publisher Site

Abstract

October, 1934 AIRCRAFT ENGINEERING 275 BRITISH CIVIL AEROPLANES A High-Wing Monoplane with Tw o Pobjoy Niagara Engines H E Short Scion is a twin-engined mono­ plane designed as a low-powered trans­ port aeroplane for small aircraft oper­ ators for special charter work or for use on feeder lines to main aircraft routes. I t is a high wing full cantilever monoplane with the engines mounted forward of the leading edge of the wing and, except for non-essential parts , is entirely of metal construction. Pobjoy Engines The engines are the 90 h.p. geared Pobjoy Fig. 3 shows the machine in part skeleton Wing Construction Niagara with the new low drag cowling and the erection and gives a good idea of the general The wing construction is well illustrated in nacelles are carefully faired into the low surface construction. Fig. 4, from which it will be seen that the of the wing. To the right may be seen the centre portion spar booms are of cruciform section with tubular The fuel is carried in light alloy tanks fitted of another fuselage with the spar attachments braces connected to the booms by fish plates. in the leading edge, the feed to the engines and centre section tubes clearly visible, while The ribs are the usual Short type of light being entirely by gravity. Each engine is on the bench in the foreground is an engine duralumin tubing and pressed duralumin sheet provided with its own petrol and oil systems. nacelle structure. rib clips with hollow steel rivets. Accessibility and ease of maintenance have ft will be seen that the leading edge is com­ received special attention both in the engine pletely sheeted in duralumin to preserve the installation and throughout the whole aeroplane. correct aerofoil section. Means are provided for starting the engines The fuel tank brackets and retaining straps from the ground. are on the front spar. The hose sheeting in this The pilot is situated in the forepart of the region is made easily detachable to facilitate fuselage in an enclosed cockpit with sliding th e removal of the tank. roof and opening side windows. The position is The exhaust is carried over the wing making slightly off centre in order to provide easy th e cabin quiet and free from fumes. access to his seat. The cabin is arranged to accommodate five Tail Unit passengers in addition to the pilot, with ample Fig. 5 illustrates the tail end, from which a seating space for each. good idea of the fuselage and tail unit con­ All control surfaces are balanced, being very struction may be gathered. The cylinder on the light in operation and well harmonized. lower longerons is for the brake gear com­ The aeroplane is of very sturdy construction, pressed air. Standard type of tail trimming the fuselage frame being of welded high tensile gear is provided, the range of adjustment being steel tube, fabric covered and suitably faired, easily adequate to cater for any variation of with the addition of a hinged nose piece of light loading. The screw gear and operating chain framework permitting easy access to the con­ and cable may be seen in the photograph. trols, dashboard, etc. PRINCIPAL CHARACTERISTICS The main spar is a built-up box girder in duralumin of a type which has proved ex­ Spa n .. .. .. .. .. 42 ft. (12·8 m.) Overall length .. .. .. .. .. 31 ft. 6 in. (9·6 m.) ceedingly satisfactory, the wings being tor- Overall height—thrust line horizontal. . . . 10 ft. 9 in. (3·28 m.) sionally very stiff with a complete absence of Fuselage width.. .. .. .. .. 3 ft. 6 m. (1·07 m.) Whee l track .. .. .. .. .. 9 ft. 8 in. (2·94 m.) vibration or tendency to "flutter." Mam plane area.. .. .. .. .. 255·5 sq ft. (23·75 sq. in.) The planes are detachable at the fuselage. Tar e weight (machine fully equipped less accumulator) 1,7101b. (775 kg.) The ribs, ailerons, tail unit, etc., follow the Fuel 31 gallons @ 7·7 lb./gal.. .. .. .. .. 239 lb. (108·5 kg.) lines of Short standard practice in duralumin. Oil, 3 gallons @ 9·7 lb./gal.. .. .. .. .. 29 lb. (13·2 kg.) Pa y load (including pilot) .. ... .. 1,022 lb. (463-3 kg.) dros s weight .. .. .. .. .. 3,000 lb. (1,360 kg.) Maximu m speed a t ground level.. .. 125 m.p.h . (201 k.p.h.j Land or Sea Plane Cruising speed (at 3,000 r.p.m.). . .. 102 m.p.h . (164 k.p.h.) Landin g speed.. .. .. .. .. 50 m.p.h . (80·3 k.p.h.) The undercarriage fittings are designed to Rat e of climb (ground level) .. .. 700 ft./m. (214 m.p.m.) tak e either a land chassis of low pressure wheels Service ceiling.. .. .. .. .. 13,000 ft. (3,970 ill.) Take-off time (no wind). , .. .. .. .. 12secs. with pneumatic brakes differentially controlled, Take-off run .. .. .. .. .. 120 yds . (109·5 in.) and friction damped spring shock absorbers; Landin g mil .. .. .. .. .. 100 yds. (91·4 in.) Petrol consumption .. .. .. .. .. 8 gallons per hour or a twin-float chassis of Short standard design Air miles pe r gallon cruising a t 3,000 r.p.m.. .. .. .. .. 12·75 and construction. Rang e emising a t 3,000 r.p.m. with 30 gallons of fuel 380 miles (612 kms.) For the land undercarriage a fully castoring tail wheel is fitted.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Oct 1, 1934

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