Avro Low Volume Production

In the summer of 1910 A. V. Roe and Company declared its willingness to build aeroplanes to other people's designs and the first such aircraft was a single seat Farman-Type pusher biplane for a Bolton business man. It was fitted with one of the few examples of the 20 h.p. two cylinder, horizontally opposed, aircooled Avro engines.

Single seat Curtiss Type biplane, it was a two-bay single-seat pusher biplane with wings of unequal span. The outer half of each upper wing carried a pair of ailerons; the larger inner one had a semicircular trailing edge extending well behind the wing trailing edge. Bamboo outriggers fore and aft of the wings supported leading elevators and tail surfaces plus rudder. Both elevator and rudder were operated by bamboo pushrods. Power was provided by a 50 h.p. Gnome Omega seven-cylinder rotary engine driving an 8 ft 6in propelle. Originally built as a landplane but converted to a seaplane, becoming the Lakes Water Bird.

Curtiss Type Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
41 ft	36 ft 5 in		365 sq ft	780 lb	1130 lb		45 mph/ 39 kn		800 ft
12.5 m	11.1 m		33.91 m2	354 kg	513 kg		72 km/h		244 m

Single-engined two-seat tractor monoplane, fitted with differentially operated surfaces above and below the central fuselage, developed by Lieut. R.F. Burga of the Peruvian Navy, who suggested that it might be better to effect lateral control with two rudder-like surfaces, mounted near the centre of gravity and at right angles to the wings.. Built at the same time as the prototype Avro Type E biplane, it used the same tail unit and undercarriage. Control surfaces apart, it differed primarily from the Type E in being a monoplane, but also in having a more slender fuselage, though still a two-seater. The wings were braced from below to strong points on the undercarriage and from above to a pylon just ahead of the front cockpit. A vertical shaft attached to this pylon appears also to have carried the leading edges of the lateral control surfaces; the one below the fuselage was almost rectangular but the upper one was shaped to avoid the passenger's head. One 50 h.p. Gnome powerplant.

Burga Monoplane Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW
	29 ft
	8.84 m

Two seat twin boom pusher reconnaissance biplane for the RFC, of convention wooden construction with fabric covering, with the exception of the steel tail booms. A capacious square-section nacelle, built up from four ash longerons and spruce cross struts, accommodated two crew in tandem. The observer/gunner sat in the nose for maximum field of vision with the pilot behind. Fuel and oil tanks were located behind the pilot's seat. Tail booms were of steel tubing braced by streamline section spruce struts, the rear extremities of which were built into the tailplane structure, mounted on the upper pair of booms, with the balanced rudder extending from above the upper to below the lower boom. There was no fixed fin. For ease of dismantling, the booms were jointed just ahead of the tailplane leading edge. The equal span mainplanes were structurally similar to those of the Avro 504 prototype, with a wide centre section carrying the first pair of interplane struts at its extremities, the dihedral commencing at this point as on the Avro 503. Ailerons were used for lateral control and the machine was noteworthy as the first Avro type to have aileron cables located inside the wing leading edge and running over buried pulleys.One 80 h.p. Gnome powerplant, carried on steel tubular bearers and driving a two-blade pusher propeller.

Type 508 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
44 ft	26 ft 9 in	10 ft	468 sq ft	1000 lb	1680 lb		65 mph/ 56 kn	4 hr
13.41 m	8.15 m	3.05 m	43.48 m2	454 kg	762 kg		105 km/h

Three seat, twin float pusher biplane of three bay configuration. Designed to meet a RNAS requirement for a heavy gun carrying aircraft and to be equipped with radio. Two 100 h.p. Gnome or 120 h.p. Austro-Daimler powerplants.

Type 509 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
80 ft	44 ft 3 in		931 sq ft	2800 lb	4510 lb		70 mph/ 61 kn
24.38 m	13.49 m		86.49 m2	1270 kg	2046 kg		113 km/h

Two seat two bay biplane fighter. Its unusually deep fuselage was of wire braced, box-girder construction with the fabric covering stretched over formers to give a more streamlined shape. The engine mounting consisted of strutted duralumin girders. The pilot occupied the front cockpit but the fuselage was so deep at this point that it almost filled the mainplane gap, leaving only enough room for a single Vickers gun in a plywood fairing on top of the fuselage. The top wing was thus on a level with the pilot's eyes, ensuring adequate view in all upward and forward directions while a rear gunner armed with a single Lewis gun on a Scarff mounting commanded the downward and rearward view. The wooden mainplanes were fabric covered and engine cooling was by means of a large frontal radiator. In the original form of the machine the lines of the short, blunt nose were improved by fitting a hollow, open-fronted metal spinner. The undercarriage was a low-drag unit comprising two narrow Vees faired with metal sheeting and braced by an internal Vee strut. Landing speed was reduced by trailing edge flaps, actuated by a handwheel in the pilot's cockpit, and fitted to both upper and lower mainplanes between the inboard ends of the ailerons and the fuselage. One 200 h.p. Hispano-Suiza.
Due to supply problems with the Hispano-Suiza, was afterwards re-engined with a 200 h.p. Sunbeam Arab and modified in various ways: an unfaired, wide angle Vee undercarriage was fitted, there was no spinner, and the tail fin was extended. New mainplanes were fitted, without flaps but with long-span ailerons and metal cuffs to fair the ends of the interplane struts into the wing. In view of its deep and capacious fuselage, the Avro 530 was offered in 1920 as a high speed touring aeroplane with comfortable tandem cockpits above a large baggage compartment. There is no evidence that this modification took place and the machine did not receive a civil registration.

Type 530 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
36 ft	28 ft 6 in	9 ft 7 in	325.5 sq ft	1695 lb	2680 lb	95 mph/ 83 kn	114 mph/ 99 kn	4 hr	18000 ft
10.97 m	8.69 m	2.92 m	30.24 m2	769 kg	1216 kg	153 km/h	183 km/h		5486 m

Two seat single bay light biplane, built for the 1924 Air Ministry Two Seat Light Aeroplane Trials at Lympne. An equal-span, equal-chord biplane with a single I-strut on each side, splayed at the ends to attach to both spars, the wing was built up with two I-section spars and Warren girder ribs, both of spruce, with drag bracing of solid piano wire. The top centre-section has tubular spars and struts but ordinary wood ribs. The spars were supported on two vees, one on each side, while the front spar was laterally braced by tubes converging on the centre-line of the fuselage, ahead of the front cockpit. Full span ailerons were fitted to all wings, with large diameter Duralumin leading edge forming a torque tube operated by cranks at the inner end. The ailerons also acted as flaps. The wings are arranged for folding. The fuselage comprised square-section longerons with Warren girder strut bracing, fabric covered, except for the deck fairing, which had a three-ply covering underneath the fabric. The tail consisted of a cantilever tail plane to which was hinged the divided elevator, and of a fairly large balanced rudder, hinged to the sternpost of the fuselage. There was no fixed vertical fin. An oleo undercarriage with very long travel was used, the front chassis struts acting as radius rods for the axle.
The aircraft was made available for the Lympne trials with either the 33 h.p. Bristol Cherub II (trials number 10) or 35 h.p. Blackburne Thrush (trials number 11) powerplants, although in the end the Thrush was never used. The geared Cherub II was replaced by the direct drive Cherub I in early 1926, and by the 38 h.p. Blackburne Thrush for the 1926 Light Aeroplane Trials.

Type 562 Avis (Cherub II) Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
30 ft 1 in	24 ft	9 ft	255 sq ft	565 lb	950 lb		75 mph/ 65 kn
9.17 m	7.32 m	2.74 m	23.69 m2	256 kg	431 kg		121 km/h

Single seat fleet fighter of all metal stressed skin construction, with interchageable wheel and float undercarriage, to meet Specification 17/25. A single bay sesquiplane with N-type interplane struts and full span Frise-type ailerons on the upper wing only, it had large diagonal bracing struts rather than bracing wires. Dihedral on the upper wing only. The wings did not fold, but could be quickly dismantled for stowage. The fuselage was a constant diameter light alloy tube of rivited duralumin tubes, tapered only at the tail, and positioned at mid gap by a number of steel struts. The first prototype featured a large triangular fin and balanced rudder, while the second prototype had a truncated fin and large horn-balanced rudder. Armament comprised two Vickers machine guns synchronised to fire through the propeller disc. One 180 h.p. Armstrong Siddeley Lynx IV powerplant.

Type 584 Avocet Specification (landplane)
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
29 ft	24 ft 6 in	11 ft 8 in	308 sq ft	1621 lb	2495 lb		133 mph/ 116 kn		23000 ft
8.84 m	7.47 m	3.56 m	28.61 m2	735 kg	1132 kg		214 km/h		7010 m

Night bomber to meet Specification B.19/27. Two 450 h.p. Armstrong Siddeley Jaguar IV powerplants. No detail design completed and the aircraft was not built.

Monoplane transport, a scaled down version of Type 652 with fixed, trousered undercarriage. Two 140 h.p. Armstrong Siddeley Genet Major IA powerplants. Mockup completed but cancelled.

Type 660 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
43 ft	32 ft	8 ft 5 in				140 mph/ 122 kn	165 mph/ 143 kn	420 mi
13.11 m	9.75 m	2.57 m				225 km/h	266 km/h	676 km