|A Vulcan B.2 of the RAF|
|National origin||United Kingdom|
|Manufacturer||A V Roe & Co (Avro)
Hawker Siddeley Aviation
|First flight||30 August 1952|
|Introduction||20 July 1956|
|Status||Retired from service|
|Primary user||Royal Air Force|
|Number built||136 (including prototypes)|
The Avro Vulcan (officially Hawker Siddeley Vulcan from July 1963) is a jet-powered delta wing strategic bomber, which was operated by the Royal Air Force (RAF) from 1956 until 1984. Aircraft manufacturer A.V. Roe and Company (Avro) designed the Vulcan in response to Specification B.35/46. Of the three V bombers produced, the Vulcan was considered the most technically advanced and hence the riskiest option. Several scale aircraft, designated Avro 707, were produced to test and refine the delta wing design principles.
The Vulcan B.1 was first delivered to the RAF in 1956; deliveries of the improved Vulcan B.2 started in 1960. The B.2 featured more powerful engines, a larger wing, an improved electrical system and electronic countermeasures (ECM); many were modified to accept the Blue Steel missile. As a part of the V-force, the Vulcan was the backbone of the United Kingdom’s airborne nuclear deterrent during much of the Cold War. Although the Vulcan was typically armed with nuclear weapons, it was capable of conventional bombing missions, a capability which was used in Operation Black Buck during the Falklands War between the United Kingdom and Argentina in 1982.
The Vulcan had no defensive weaponry, initially relying upon high-speed high-altitude flight to evade interception. Electronic countermeasures were employed by the B.1 (designated B.1A) and B.2 from circa 1960. A change to low-level tactics was made in the mid-1960s. In the mid-1970s nine Vulcans were adapted for maritime radar reconnaissance operations, redesignated as B.2 (MRR). In the final years of service six Vulcans were converted to the K.2 tanker configuration for aerial refuelling.
Since retirement by the RAF one example, B.2 XH558, named "The Spirit of Great Britain" was restored for use in display flights and air shows, whilst two other B.2s, XL426 and XM655, are kept in taxiable condition for ground runs and demonstrations at London Southend Airport and Wellesbourne Mountford Airfield respectively. B.2 XH558 flew for the last time in October 2015, before also being kept in taxiable condition at Robin Hood Airport, Doncaster.
- 1 Development
- 2 Design
- 3 Operational history
- 4 Variants
- 5 Operators
- 6 Accidents and incidents
- 7 Surviving aircraft
- 8 Specifications
- 9 Popular culture
- 10 See also
- 11 References
- 12 Further reading
- 13 External links
The origin of the Vulcan and the other V bombers is linked with early British atomic weapon programme and nuclear deterrent policies. Britain's atom bomb programme began with Air Staff Operational Requirement OR.1001 issued in August 1946. This anticipated a government decision in January 1947 to authorise research and development work on atomic weapons, the U.S. Atomic Energy Act of 1946 (McMahon Act) having prohibited exporting atomic knowledge, even to countries that had collaborated on the Manhattan Project. OR.1001 envisaged a weapon not to exceed 24 ft 2 in (7.37 m) in length, 5 ft (1.5 m) in diameter and 10,000 lb (4,500 kg) in weight. The weapon had to be suitable for release from 20,000 ft (6,100 m) to 50,000 ft (15,000 m).
In January 1947, the Ministry of Supply distributed Specification B.35/46 to UK aviation companies to satisfy Air Staff Operational Requirement OR.229 for "a medium range bomber landplane capable of carrying one 10,000 lb (4,500 kg) bomb to a target 1,500 nautical miles (1,700 mi; 2,800 km) from a base which may be anywhere in the world." A cruising speed of 500 knots (580 mph; 930 km/h) at heights between 35,000 ft (11,000 m) and 50,000 ft (15,000 m) was specified. The maximum weight when fully loaded ought not to exceed 100,000 lb (45,000 kg). In addition to a "Special" (i.e., atomic) bomb, the aircraft was to be capable of alternatively carrying a conventional bomb load of 20,000 lb (9,100 kg). The similar OR.230 required a "long range bomber" with a 2,000 nautical miles (2,300 mi; 3,700 km) radius of action with a maximum weight of 200,000 lb (91,000 kg) when fully loaded; this requirement was considered too exacting. A total of six companies would submit technical brochures to this specification, including Avro.
Required to tender by the end of April 1947, work began on receipt of Specification B.35/46 at Avro, led by technical director Roy Chadwick and chief designer Stuart Davies; the type designation was Avro 698. It was obvious to the design team that conventional aircraft could not satisfy the Specification; knowing little about high-speed flight and unable to glean much from the Royal Aircraft Establishment or the US, they investigated German Second World War swept wing research. The team estimated that an otherwise conventional aircraft, with a swept wing of 45°, would have doubled the weight requirement. Realising that swept wings increase longitudinal stability, the team deleted the tail (empennage) and the supporting fuselage, it thus became a swept-back flying wing with only a rudimentary forward fuselage and a fin (vertical stabilizer) at each wingtip. The estimated weight was now only 50% over the requirement; a delta shape resulted from reducing the wingspan and maintaining the wing area by filling in the space between the wingtips, which enabled the specification to be met. Though Dr Alexander Lippisch is generally credited as the pioneer of the delta wing, Chadwick’s team had followed its own logical design process. The initial design submission had four large turbojets stacked in pairs buried in the wing either side of the centreline. Outboard of the engines were two bomb-bays.
In August 1947, Roy Chadwick was killed in the crash of the Avro Tudor 2 prototype and was succeeded by Sir William Farren. Reductions in wing thickness made it impossible to incorporate the split bomb bays and stacked engines, thus the engines were placed side-by-side in pairs either side of a single bomb-bay, the fuselage growing somewhat. The wingtip fins gave way to a single fin on the aircraft's centreline. Rival manufacturer Handley Page received a prototype contract for its crescent-winged HP.80 B.35/46 tender in November 1947. Though considered the best option, contract placement for Avro's design was delayed whilst its technical strength was established. Instructions to proceed with the construction of two Avro 698 prototypes was received in January 1948. As an insurance measure against both radical designs failing, Short Brothers received a contract for the prototype SA.4 to the less-stringent Specification B.14/46; the SA.4, later named Sperrin, was not required. In April 1948, Vickers also received authority to proceed with their Type 660 which, although falling short of the B.35/46 Specification, being of a more conventional design would be available sooner; this plane entered service as the Valiant.
Avro 707 and Avro 710
As Avro had no flight experience of the delta wing, the company planned two smaller experimental aircraft based on the 698, the one-third scale model 707 for low-speed handling and the one-half scale model 710 for high-speed handling. Two of each were ordered. However, the 710 was cancelled when it was considered too time-consuming to develop; a high-speed variant of the 707 was designed in its place, the 707A. The first 707, VX784, flew in September 1949 but crashed later that month killing Avro test pilot Flt Lt Eric Esler. The second low-speed 707, VX790, built with the still uncompleted 707A’s nose section (containing an ejection seat) and redesignated 707B, flew in September 1950 piloted by Avro test pilot Wg Cdr Roland "Roly" Falk. The high speed 707A, WD480, followed in July 1951.
Due to the delay of the 707 programme, the contribution of the 707B and 707A towards the basic design of the 698 was not considered significant, though it did highlight a need to increase the length of the nosewheel to give a ground incidence of 3.5 degrees, the optimum take-off attitude. The 707B and 707A proved the design's validity and gave confidence in the delta planform. A second 707A, WZ736 and a two-seat 707C, WZ744 were also constructed but they played no part in the 698's development.
Vulcan B.1 and B.2
Prototypes and type certification
More influential than the 707 in the 698's design was wind-tunnel testing performed by the Royal Aircraft Establishment at Farnborough, which indicated the need for a wing redesign to avoid the onset of compressibility drag which would have restricted the maximum speed. Painted gloss white, the 698 prototype VX770 flew for the first time on 30 August 1952 piloted by Roly Falk flying solo. The prototype 698, then fitted with only the first-pilot's ejection seat and a conventional control wheel, was powered by four Rolls-Royce RA.3 Avon engines of 6,500 lbf (29 kN) thrust; there were no wing fuel tanks, temporary tankage was carried in the bomb bay. VX770 made an appearance at the 1952 Society of British Aircraft Constructors' (SBAC) Farnborough Air Show the next month when Falk demonstrated an "almost vertical bank". After its Farnborough appearance, the future name of the Avro 698 was a subject of speculation; Avro had strongly recommended the name Ottawa,[N 1] in honour of the company's connection with Avro Canada. Weekly magazine Flight suggested Albion after rejecting Avenger, Apollo and Assegai. The Chief of the Air Staff preferred a V-class of bombers, the Air Council announced the following month that the 698 would be called Vulcan after the Roman god of fire and destruction. In January 1953, VX770 was grounded for the installation of wing fuel tanks, Armstrong Siddeley ASSa.6 Sapphire engines of 7,500 lbf (33 kN) thrust and other systems; it flew again in July 1953.
The second prototype, VX777, flew in September 1953. More representative of production aircraft, it was lengthened to accommodate a longer nose undercarriage leg, featured a visual bomb-aiming blister under the cabin and was fitted with Bristol Olympus 100 engines of 9,750 lbf (43.4 kN) thrust. At Falk’s suggestion, a fighter-style control stick replaced the control wheel. Both prototypes had almost pure delta wings with straight leading edges. During trials in July 1954, VX777 was substantially damaged in a heavy landing at Farnborough. It was repaired and fitted with Olympus 101 engines of 11,000 lbf (49 kN) thrust before resuming trials in October 1955. While exploring the high speed and high altitude flight envelope, mild buffeting and other undesirable flight characteristics were experienced while approaching the speed of sound, including an alarming tendency to enter an uncontrollable dive, unacceptable to the Aeroplane and Armament Experimental Establishment (A&AEE) at Boscombe Down. The solution included the "Phase 2" wing, featuring a kinked and drooped leading edge and vortex generators on the upper surface, first tested on 707A WD480. An auto-mach trimmer introduced a nose-up attitude when at high speeds, the control column had to be pushed rather than pulled to maintain level flight.
Meanwhile, the first production B.1,[N 2] XA889, had flown in February 1955 with the original wing. In September 1955, Falk, flying the second production B.1 XA890 amazed crowds at the Farnborough Air Show by executing a barrel roll on his second flypast in front of the SBAC president’s tent. After two days flying, he was called in front of service and civil aviation authorities and ordered to refrain from carrying out this "dangerous" manoeuvre. Now fitted with a Phase 2 wing, XA889 was delivered in March 1956 to the A&AEE for trials for the type’s initial Certificate of Airworthiness which it received the following month.
The first 15 B.1s were powered by the Olympus 101 of 11,000 lbf (49 kN) thrust. Many of these early examples in a metallic finish remained the property of the Ministry of Supply being retained for trials and development purposes. Those entering RAF service were delivered to No 230 Operational Conversion Unit (OCU), the first in July 1956. Later aircraft, painted in anti-flash white and powered by the Olympus 102 of 12,000 lbf (53 kN) thrust, began to enter squadron service in July 1957. The Olympus 102s were quickly modified to Olympus 104 standard, ultimately rated at 13,500 lbf (60 kN) thrust. As far back as 1952, Bristol Aero Engines had begun development of the BOl.6 (Olympus 6) rated at 16,000 lbf (71 kN) thrust but if fitted to the B.1, this would have re-introduced the buffet requiring further redesign of the wing.
The decision to proceed with the B.2 versions of the Vulcan was made in May 1956. It was anticipated that the first B.2 would be around the 45th aircraft of the 99 then on order. As well as being able to achieve greater heights over targets, it was believed that operational flexibility could be extended by the provision of in-flight refuelling equipment and tanker aircraft. The increasing sophistication of Soviet air defences required the fitting of electronic countermeasure (ECM) equipment and vulnerability could be reduced by the introduction of the Avro Blue Steel stand-off missile, then in development. In order to develop these proposals, the second Vulcan prototype VX777 was rebuilt with the larger and thinner Phase 2C wing, improved flying control surfaces and Olympus 102 engines, first flying in this configuration in August 1957. Plans were in hand to equip all Vulcans from the 16th aircraft onwards with in-flight refuelling receiving equipment. A B.1, XA903, was allocated for Blue Steel development work. Other B.1s were used for the development of the BOl.6 (later Olympus 200), XA891; a new AC electrical system, XA893; and ECM including jammers within a bulged tail-cone and a tail warning radar, XA895.
The 46th production aircraft and first B.2, XH533, first flew in September 1958 fitted with Olympus 200 engines of 16,000 lbf (71 kN) thrust, six months before the last B.1 XH532 was delivered in March 1959. Rebuilding B.1s as B.2s was considered but rejected over cost. Nevertheless, to extend the B.1's service life, 28 were upgraded by Armstrong Whitworth between 1959 and 1963 to the B.1A standard, including features of the B.2 such as ECM equipment, in-flight refuelling receiving equipment, and UHF radio. The second B.2, XH534, flew in January 1959. Powered by production Olympus 201 of 17,000 lbf (76 kN) thrust, it was more representative of a production aircraft, being fitted with an in-flight refuelling probe and a bulged ECM tail cone. Some subsequent B.2s were initially lacking probes and ECM tail cones, but these were fitted retrospectively. The first 10 B.2s outwardly showed their B.1 ancestry, retaining narrow engine air intakes. Anticipating even more powerful engines, the air intakes were deepened on the 11th (XH557) and subsequent aircraft. Many of the early aircraft were retained for trials and it was the 12th B.2, XH558, that was the first to be delivered to the RAF in July 1960. Coincidentally, XH558 would also be the last Vulcan in service with the RAF, before being retired in 1992.
The 26th B.2, XL317, the first of a production batch ordered in February 1956, was the first Vulcan, apart from development aircraft, capable of carrying the Blue Steel missile; 33 aircraft were delivered to the RAF with these modifications. When the Mk.2 version of Blue Steel was cancelled in favour of the Douglas GAM-87 Skybolt air-launched ballistic missile in December 1959, fittings were changed in anticipation of the new missile, one under each wing. Though Skybolt was cancelled in November 1962, many aircraft were delivered or retrofitted with "Skybolt" blisters. Later aircraft (XL391 and XM574 onwards) were delivered with Olympus 301 engines of 20,000 lbf (89 kN) thrust. Two earlier aircraft were re-engined (XH557 and XJ784) for trials and development work; another seven aircraft (XL384-XL390) were converted circa 1963.
The last B.2 XM657 was delivered in 1965 and the type served till 1984. Whilst in service the B.2 was continuously updated with modifications including rapid engine starting, bomb-bay fuel tanks, wing strengthening to give the fatigue life to enable the aircraft to fly at low level (a tactic introduced in the mid-60s), upgraded navigation equipment, Terrain Following Radar (TFR), standardisation on a common nuclear weapon (WE.117) and improved ECM equipment. The B.1As were not strengthened, thus all were withdrawn by 1968. Nine B.2s were modified for the Maritime Radar Reconnaissance (MRR) role and six for the airborne tanker role.
Proposed developments and cancelled projects
- Avro Type 718
The Avro 718 was a 1951 proposal for a delta-winged military transport based on the Type 698 to carry 80 troops or 110 passengers. It would have been powered by four Bristol Olympus BOl.3 engines.
- Avro Atlantic
The Avro Type 722 Atlantic was a 1952 proposal (announced in June 1953) for a 120-passenger delta-winged airliner based on the Type 698.
- Avro Type 732
The Avro 732 was a 1956 proposal for a supersonic development of the Vulcan and would have been powered by 8 de Havilland Gyron Junior engines. Unlike the proposed Avro 721 low-level bomber of 1952 or the Avro 730 supersonic stainless steel canard bomber dating from 1954 (cancelled in 1957 before completion of the prototype), the Type 732 showed its Vulcan heritage.
- Vulcan Phase 6 (Vulcan B.3)
In 1960, the Air Staff approached Avro with a request into a study for a Patrol Missile Carrier armed with up to six Skybolt missiles capable of a mission length of 12 hours. Avro's submission in May 1960 was the Phase 6 Vulcan, which if built would have been the Vulcan B.3. The aircraft was fitted with an enlarged wing of 121 ft (37 m) span with increased fuel capacity; additional fuel tanks in a dorsal spine; a new main undercarriage to carry an all-up-weight of 339,000 lb (154,000 kg); and reheated Olympus 301s of 30,000 lbf (130 kN) thrust. An amended proposal of October 1960 inserted a 10 ft 9 in (3.28 m) plug into the forward fuselage with capacity for six crew members including a relief pilot, all facing forwards on ejection seats, and aft-fan versions of the Olympus 301.
Other countries expressed interest in purchasing Vulcans but, as with the other V-bombers, no foreign sales materialised.
As early as 1954, Australia recognised that the English Electric Canberra was becoming outdated and evaluated aircraft such as the Avro Vulcan and Handley-Page Victor as potential replacements. Political pressure for a Canberra replacement only rose to a head in 1962; at which point more modern types such as the BAC TSR-2, General Dynamics F-111C, and North American A-5 Vigilante had become available. The RAF would have transferred several V-bombers, including Vulcans, for interim use by the RAAF if they had purchased the TSR-2, but the RAAF selected the F-111C.
In the early 1980s, Argentina approached the UK with a proposal to buy a number of Vulcans. An application, made in September 1981, requested the 'early availability' of a 'suitable aircraft'. With some reluctance, ministers approved the export of a single aircraft but emphasised that clearance had not been given for the sale of a larger number. A letter from the British Foreign and Commonwealth Office to the Ministry of Defence in January 1982 stated that little prospect was seen of this happening without ascertaining the Argentine interest and whether such interest was genuine: 'On the face of it, a strike aircraft would be entirely suitable for an attack on the Falklands.' Argentina invaded the Falkland Islands less than three months later.
Despite its radical and unusual shape, the airframe was built along traditional lines. Except for the most highly stressed parts, the whole structure was manufactured from standard grades of light alloy. The airframe was broken down into a number of major assemblies: the centre section, a rectangular box containing the bomb-bay and engine bays bounded by the front and rear spars and the wing transport joints; the intakes and centre fuselage; the front fuselage, incorporating the pressure cabin; the nose; the outer wings; the leading edges; the wing trailing edge and tail end of the fuselage; the wings were not sealed and used directly as fuel tankage, but carried bladders for fuel in the void spaces of the wings; and there was a single swept tail fin with a single rudder on the trailing edge.
A five-man crew, the first pilot, co-pilot, navigator radar, navigator plotter and air electronics officer (AEO) was accommodated within the pressure cabin on two levels; the pilots sitting on Martin-Baker 3K (3KS on the B.2) ejection seats whilst on the lower level, the other crew sat facing rearwards and would abandon the aircraft via the entrance door. The original B35/46 specification sought a jettisonable crew compartment, this requirement was removed in a subsequent amendment, the rear crew's escape system was often an issue of controversy, such as when a practical refit scheme was rejected. A rudimentary sixth seat forward of the navigator radar was provided for an additional crew member; the B.2 had an additional seventh seat opposite the sixth seat and forward of the AEO. These seats were no more than cushions, a full harness and an oxygen and intercom facility. The visual bomb-aimer’s compartment could be fitted with a T4 (Blue Devil) bombsight, in many B.2s this space housed a vertically mounted Vinten F95 Mk.10 camera for assessing simulated low-level bombing runs.
Fuel was carried in 14 bag tanks, four in the centre fuselage above and to the rear of the nosewheel bay and five in each outer wing. The tanks were split into four groups of almost equal capacity, each normally feeding its respective engine though cross-feeding was possible. The centre of gravity was automatically maintained by electric timers which sequenced the booster pumps on the tanks. B.2 aircraft could be fitted with one or two additional fuel tanks in the bomb-bay.
Despite being designed before a low radar cross-section (RCS) and other stealth factors were ever a consideration, a Royal Aircraft Establishment technical note of 1957 stated that of all the aircraft so far studied, the Vulcan appeared by far the simplest radar echoing object, due to its shape: only one or two components contributed significantly to the echo at any aspect, compared with three or more on most other types.[N 3]
The two prototype Vulcans were finished in gloss white. Early Vulcan B.1s left the factory in a natural metal finish; the front half of the nose radome was painted black, the rear half painted silver. Front-line Vulcan B.1s had a finish of anti-flash white and RAF "type D" roundels. Front-line Vulcan B.1As and B.2s were similar but with 'type D pale' roundels.
With the adoption of low-level attack profiles in the mid-1960s, B.1As and B.2s were given a glossy Sea Grey Medium and Dark Green disruptive pattern camouflage on the upper surfaces, white undersurfaces and "type D" roundels. (The last 13 Vulcan B.2s, XM645 onwards, were delivered thus from the factory). In the mid-1970s: Vulcan B.2s received a similar scheme with matte camouflage, Light Aircraft Grey undersides, and "low-visibility" roundels; B.2(MRR)s received a similar scheme in gloss; and the front half of the radomes were no longer painted black. Beginning in 1979, 10 Vulcans received a wrap-around camouflage of Dark Sea Grey and Dark Green because, during Red Flag exercises in the USA, defending SAM forces had found that the grey-painted undersides of the Vulcan became much more visible against the ground at high angles of bank.
The original Vulcan B.1 radio fit was: two 10-channel VHF transmitter/receivers (TR-1985/TR-1986) and a 24-channel HF transmitter/receiver (STR-18). The Vulcan B.1A also featured an UHF transmitter/receiver (ARC-52). The initial B.2 radio fit was similar to the B.1A though it was ultimately fitted with the ARC-52, a V/UHF transmitter/receiver (PTR-175), and a SSB HF transmitter/receiver (Collins 618T).
The Navigation and Bombing System (NBS) comprised an H2S Mk9 radar and a Navigation Bombing Computer (NBC) Mk1. Other navigation aids included a Marconi radio compass (ADF), GEE Mk3, Green Satin Doppler radar to determine the groundspeed and drift angle, radio and radar altimeters, and ILS. TACAN replaced GEE in the B.1A and B.2 in 1964 . Decca Doppler 72 replaced Green Satin in the B.2 around 1969  A continuous display of the aircraft's position was maintained by a Ground Position Indicator (GPI).
Vulcan B.2s were eventually fitted with the twin-gyro free-running gyroscopic Heading Reference System (HRS) Mk.2, based upon the inertial platform of the Blue Steel missile, which had been integrated into the system when the missile had been carried. With the HRS a Navigator's Heading Unit (NHU) was provided which enabled the Navigator Plotter to adjust the aircraft heading, through the autopilot, by as little as 0.1 degrees. The B.2 (MRR) was additionally fitted with the LORAN C navigation system.
The original ECM fit as fitted to the B.1A and B.2 was: one Green Palm voice communications' jammer; two Blue Diver metric jammers; three Red Shrimp S-band jammers; ; a Blue Saga Passive Warning Receiver with 4 aerials (PWR); a Red Steer tail warning radar; and window (chaff) dispensers. The bulk of the equipment was carried in a large extended tail cone, and a flat ECM aerial counterpoise plate mounted between the starboard tailpipes.[N 4] Later equipment on the B.2 included: an L band jammer (replacing a Red Shrimp); the ARI 18146 X-band jammer; replacing the Green Palm; the improved Red Steer Mk.2; infra-red decoys (flares); and the ARI 18228 PWR with its aerials that gave a squared top to the fin.
The aircraft was controlled by a fighter-type control stick and rudder bar which operated the powered flying controls (PFCs). Each PFC had a single electro-hydraulic powered flying control unit (PFCU) except the rudder which had two, one running as a back-up. Artificial feel and autostabilisation in the form of pitch and yaw dampers were provided, as well as an auto mach trimmer.
The flight instruments in the B.1 were traditional and included G4B compasses; Mk.4 artificial horizons; and zero reader flight display instruments. The B.1 had a Smiths Mk10 autopilot. In the B.2, these features were incorporated into the Smiths Military Flight System (MFS), the pilots' components being: two beam compasses; two director-horizons; and a Mk.10A or Mk.10B autopilot. From 1966, B.2s were fitted with the ARI 5959 Terrain-following radar (TFR), built by General Dynamics, its commands being fed into the director-horizons.
The B.1 had four elevators (inboard) and four ailerons (outboard). In the B.2, these were replaced by eight elevons. The Vulcan was also fitted with six electrically-operated three-position (in, medium drag, high drag) airbrakes, four in the upper centre section and two in the lower. There were originally four lower airbrakes but the outboard two were deleted before the aircraft entered service. A brake parachute was installed inside the tail cone.
Electrical and hydraulic systems
The main electrical system on the B.1/B.1A was 112V DC supplied by four 22.5kW engine-driven generators. Backup power was provided by four 24V 40Ah batteries connected in series providing 96V. Secondary electrical systems were 28V DC, single-phase 115V AC at 1600Hz, and three-phase 115V AC at 400 Hz, driven by transformers and inverters from the main system. The 28V DC system was backed up by a single 24V battery.
For greater efficiency and higher reliability, the main system on the B.2 was changed to three-phase 200V AC at 400 Hz supplied by four 40kVA engine-driven constant speed alternators. Standby supplies in the event of a main AC failure were provided by a Ram Air Turbine (RAT) driving a 17kVA alternator that could operate at high altitude down to 20,000 ft (6,100 m), and an Airborne Auxiliary Power Plant (AAPP), a Rover gas turbine driving a 40kVA alternator, which could be started once the aircraft was below an altitude of 30,000 ft (9,100 m). Secondary electrical supplies were similar to the B.1.
The change to an AC system was a significant improvement. The Vulcan's powered flying controls were hydraulically actuated but each Powered Flying Control Unit (PFCU) had a hydraulic pump which was driven by an electrical motor. Because there was no manual reversion, a total electrical failure would result in a loss of control. The standby batteries on the B.1 were designed to give enough power for 20 minutes of flying time but this proved to be optimistic and two aircraft, XA891 and XA908, crashed as a result.
The main hydraulic system provided pressure for: undercarriage raising and lowering and bogie trim; nosewheel centring and steering; wheelbrakes (fitted with Maxarets); bomb doors opening and closing; and (B.2 only) AAPP air scoop lowering. Hydraulic pressure was provided by three hydraulic pumps fitted to Nos. 1, 2 and 3 engines. An electrically operated hydraulic power pack (EHPP) could be used to operate the bomb doors and recharge the brake accumulators. A compressed air (later nitrogen) system was provided for emergency undercarriage lowering.
The Rolls-Royce Olympus, originally known as the "Bristol BE.10 Olympus",[N 5] is a two-spool axial-flow turbojet that powered the Vulcan. Each Vulcan had four engines buried in the wings, positioned in pairs close to the centre of the fuselage. The engine's design began in 1947, intended to power the Bristol Aeroplane Company's own rival design to the Vulcan. A serendipitous arrangement in air intakes could cause the Vulcan to emit a distinctive "howl" when the engines were at approximately 90% power, which can be heard as the aircraft performs a flypast, such as at public airshows.
As the prototype Vulcan VX770 was ready for flight prior to the Olympus being available, it first flew using Rolls-Royce Avon RA.3 engines of 6,500 lbf (29 kN) thrust. These were quickly replaced by Armstrong Siddeley Sapphire ASSa.6 engines of 7,500 lbf (33 kN) thrust. VX770 later became a flying test bed for the Rolls-Royce Conway. The second prototype VX777 first flew with Olympus 100s of 10,000 lbf (44 kN) thrust. It was subsequently re-engined with Olympus 101 engines of 11,000 lbf (49 kN) thrust. When VX777 flew with a Phase 2C (B.2) wing in 1957, it was fitted with Olympus 102 engines of 12,000 lbf (53 kN) thrust.
Early B.1s were engined with the Olympus 101. Later aircraft were delivered with Olympus 102s. All Olympus 102s became the Olympus 104 of 13,000 lbf (58 kN) thrust on overhaul and ultimately 13,500 lbf (60 kN) thrust on uprating. The first B.2 flew with the second-generation Olympus 200 of 16,000 lbf (71 kN) thrust, design of which began in 1952. Subsequent B.2s were engined with either the uprated Olympus 201 of 17,000 lbf (76 kN) thrust or the Olympus 301 of 20,000 lbf (89 kN) thrust. The Olympus 201 was designated 202 on being fitted with a rapid air starter. The engine would later be developed into a reheated (afterburning) powerplant for the cancelled supersonic BAC TSR-2 strike bomber and the supersonic passenger transport Concorde.
In September 1956, the RAF received its first Vulcan B.1, XA897, which immediately embarked upon a round-the-world tour. The tour was to be an important demonstration of the range and capabilities of the aircraft, it also had other benefits in the form of conducting goodwill visits in various countries; in later life Vulcans routinely visited various nations and distant parts of the former British Empire as a show of support and military protection. This first tour, however, was struck by misfortune; on 1 October 1956, while landing in bad weather at London Heathrow Airport at the completion of the world tour, XA897 was destroyed in a fatal accident.
The first two aircraft were delivered to 230 OCU in January 1957 and the training of crews started on 21 February 1957, in the following months more aircraft were delivered to the OCU. The first OCU course to qualify was No. 1 Course, on 21 May 1957, and they went on to form the first flight of No.83 Squadron. No. 83 Squadron was the first operational squadron to use the bomber, at first using borrowed Vulcans from the OCU and on 11 July 1956 it received the first aircraft of its own. By September 1957, several Vulcans had been handed over to No.83 Squadron The second OCU course also formed a Flight of 83 Squadron, but subsequent trained crews were also used to form the second bomber squadron, 101 Squadron. The last aircraft from the first batch of 25 aircraft had been delivered by the end of 1957 to 101 Squadron.
In order to increase the mission range and flight time for Vulcan operations, in-flight refuelling capabilities were added in 1959 onwards; several Valiant bombers were refurbished as tankers to refuel the Vulcans. Continuous airborne patrols proved untenable, however, and the refuelling mechanisms across the Vulcan fleet fell into disuse in the 1960s. Both Vulcans and the other V-force aircraft routinely visited the Far East, in particular Singapore, where a fully equipped nuclear weapons storage facility had been constructed in 1959. During the Indonesia–Malaysia confrontation Britain planned to deploy three squadrons of V-bomber aircraft and 48 Red Beard tactical nuclear weapons to the region, although this was ultimately decided against, Vulcans trained in the region for both conventional and nuclear missions. Britain regularly deployed Vulcans to the Far East as a part of their contribution to SEATO operations, often to test the defenses of friendly nations in joint exercises. In the early 1970s, the RAF decided to permanently deploy two squadrons of Vulcans overseas in the Near East Air Force Bomber Wing, based at RAF Akrotiri in Cyprus; the Vulcans were withdrawn as Cypriot intercommunal violence intensified in the mid-1970s.
Vulcans did some very long range missions. In June 1961, one of them took off from RAF Scampton to Sydney, with an 18,507 km long journey, flown in only a bit more than 20 hours and three air refuellings. Vulcans frequently visited the United States during the 1960s and 1970s to participate in air shows and static displays, as well as to participate in the Strategic Air Command's Annual Bombing and Navigation Competition at such locations as Barksdale AFB, Louisiana and the former McCoy AFB, Florida, with the RAF crews representing Bomber Command and later Strike Command. Vulcans also took part in the 1960, 1961, and 1962 Operation Skyshield exercises, in which NORAD defences were tested against possible Soviet air attack, the Vulcans simulating Soviet fighter/bomber attacks against New York, Chicago and Washington. The results of the tests were classified until 1997. The Vulcan proved quite successful during the 1974 'Giant Voice' exercise, in which it had managed to avoid USAF interceptors 
As part of Britain's independent nuclear deterrent, the Vulcan initially carried Britain's first nuclear weapon, the Blue Danube gravity bomb. Blue Danube was a low-kiloton yield fission bomb designed before the United States detonated the first hydrogen bomb. These were supplemented by U.S.-owned Mk 5 bombs (made available under the Project E programme) and later by the British Red Beard tactical nuclear weapon. The UK had previously embarked on its own hydrogen bomb programme, and to bridge the gap until these were ready the V-bombers were equipped with an Interim Megaton Weapon based on the Blue Danube casing containing Green Grass, a large pure-fission warhead of 400 kt (1.7 PJ) yield.[N 6] This bomb was known as Violet Club. Only five were deployed before the Green Grass warhead was incorporated into a developed weapon as Yellow Sun Mk.1.
The later Yellow Sun Mk 2, was fitted with Red Snow, a British-built variant of the U.S. W28 warhead. Yellow Sun Mk 2 was the first British thermonuclear weapon to be deployed, and was carried on both the Vulcan and Handley Page Victor. The Valiant retained U.S. nuclear weapons assigned to SACEUR under the dual-key arrangements. Red Beard was pre-positioned in Singapore for use by Vulcan and Victor bombers. From 1962, three squadrons of Vulcan B.2s and two squadrons of Victor B.2s were armed with the Blue Steel missile, a rocket-powered stand-off bomb, which was also armed with the 1.1 Mt (4.6 PJ) yield Red Snow warhead.
Operationally, RAF Bomber Command and the U.S. Strategic Air Command cooperated in the Single Integrated Operational Plan (SIOP) to ensure coverage of all major Soviet targets from 1958, 108 aircraft of the RAF's V-Bombers were assigned targets under SIOP by the end of 1959. From 1962 onwards, two jets in every major RAF base were armed with nuclear weapons and on standby permanently under the principle of Quick Reaction Alert (QRA). Vulcans on QRA standby were to be airborne within four minutes of receiving an alert, as this was identified as the amount of time between warning of a USSR nuclear strike being launched and it arriving in Britain. The closest the Vulcan came to take part in potential nuclear conflict was during the Cuban missile crisis in October 1962, where Bomber Command was moved to Alert Condition 3, an increased state of preparedness from normal operations, however stood down in early November.
The Vulcans were intended to be equipped with the American Skybolt Air Launched Ballistic Missile to replace the Blue Steel, with Vulcan B.2s carrying two Skybolts under the wings; the last 28 B.2s were modified on the production line to fit pylons to carry the Skybolt. A B.3 variant with increased wingspan to carry up to six Skybolts was proposed in 1960. When the Skybolt missile system was cancelled by U.S. President John F. Kennedy on the recommendation of his Secretary of Defense, Robert McNamara in 1962, Blue Steel was retained. To supplement it until the Royal Navy took on the deterrent role with Polaris ICBM-equipped submarines, the Vulcan bombers adopted a new mission profile of flying high during clear transit, dropping down low to avoid enemy defences on approach, and deploying a parachute-retarded bomb, the WE.177B. However, since the aircraft had been designed for high-altitude flight, at low altitudes it could not exceed 350 knots. RAF Air Vice Marshal Ron Dick, a former Vulcan pilot, said "it is [thus] questionable whether it could have been effective flying at low level in a war against ... the Soviet Union.”
After the British Polaris submarines became operational and Blue Steel was taken out of service in 1970, the Vulcan continued to carry WE.177B in a tactical nuclear strike role as part of the British contribution to Europe's standing NATO forces, although they no longer held aircraft at 15 minutes readiness in peacetime. Two squadrons were also stationed in Cyprus as part of the Near East Air Force and assigned to Central Treaty Organization in a strategic strike role. With the eventual demise of the WE.177B and the Vulcan bombers, the Blackburn Buccaneer, SEPECAT Jaguar, and Panavia Tornado, continued with the WE.177C until its retirement in 1998. While not a like-for-like replacement, the multi-role Tornado interdictor/strike bomber is the successor for the roles previously filled by the Vulcan.
Although in operational usage the Vulcan typically carried various nuclear armaments, the type also had a secondary conventional role. While performing conventional combat missions, the Vulcan can carry up to 21 1,000 lb (454 kg) bombs inside its bomb bay. Since the 1960s, the various Vulcan squadrons were routinely conducting conventional training missions; the aircrews were expected to be able to perform conventional bombing missions in addition to the critical nuclear strike mission the Vulcan normally performed.
The Vulcan's only combat missions took place towards the end of the type's service in 1982. During the Falklands War, the Vulcan was deployed against Argentinian forces which had occupied the Falkland Islands. This conflict was the only occasion in which any of the V-bombers would participate in conventional warfare. The missions performed by the Vulcan became known as the Black Buck raids, each aircraft had to fly 3,889 mi (6,259 km) from Ascension Island to reach Stanley on the Falklands. Victor tankers conducted the necessary air-to-air refuelling for the Vulcan to cover the distance involved; approximately 1,100,000 imp gal (5,000,000 l) of fuel was used in each mission.
Five Vulcans were selected to participate in the operation. In order to do so, each aircraft had to receive various last-minute adaptations; including modifications to the bomb bay, the reinstatement of the long out-of-use in-flight refuelling system, the installation of a new navigational system derived from the Vickers VC-10, and the updating of several onboard electronics. Underneath the wings, new pylons were fitted to carry an ECM pod and Shrike anti-radar missiles at wing hardpoint locations; these hardpoints had originally been installed for the purpose of carrying the cancelled Skybolt nuclear missile. Engineering work to retrofit these Vulcans had begun on 9 April.
On 1 May, the first mission was conducted by a single Vulcan that flew over Port Stanley and dropped its bombs on the airfield concentrating on the single runway, with one direct hit, making it unsuitable for fighter aircraft. The Vulcan's mission was quickly followed up by strikes against anti-air installations, flown by British Aerospace Sea Harriers from nearby Royal Navy carriers. Three Vulcan missions were flown against the airfield, a further two missions in which missiles were launched against radar installations; an additional two missions were cancelled. At the time, these missions held the record for the world's longest-distance raids. The ECM systems on board the Vulcans proved to be effective at jamming Argentine radars; while a Vulcan was within the theatre, other British aircraft in the vicinity had a greatly reduced chance of coming under effective fire.
On 3 June 1982, Vulcan B.2 XM597 of No. 50 Squadron took part in the "Black Buck 6" mission against Argentinian radar sites at Stanley airfield on the Falkland Islands. While attempting to refuel for its return journey to Ascension Island, the probe broke, leaving the Vulcan with insufficient fuel, forcing a diversion to Galeão Air Force Base, Rio de Janeiro in neutral Brazil. En route, secret papers were dumped along with the two remaining AGM-45 Shrike missiles, although one failed to launch. After a mayday call, the Vulcan, escorted by Brazilian Air Force Northrop F-5 fighters, was permitted an emergency landing at Rio with very little fuel left on board. The Vulcan and her crew were detained until the end of hostilities nine days later.
Maritime radar reconnaissance
In November 1973, No. 27 Squadron reformed at RAF Scampton in the maritime radar reconnaissance role. Though initially equipped with a number of B.2 aircraft, the Squadron eventually operated nine B.2 (MRR) aircraft. The main external visual difference was the presence of a gloss paint finish, with a light grey undersurface, to protect against sea spray. TFR was not fitted and the aircraft were equipped with LORAN C navigational equipment. Five aircraft were further modified for the Squadron's secondary role of air sampling. These aircraft were distinguishable by the additional hardpoints outside of the underwing Skybolt points upon which could be hung pylons and the air-sampling pods, which had been constructed from de Havilland Sea Vixen drop tanks.
Aerial refuelling role
After the end of the Falklands War in 1982, the Vulcan B.2 was due to be withdrawn from RAF service that year. However, the Falklands campaign had consumed much of the airframe fatigue life of the RAF's Victor tankers. While Vickers VC10 tanker conversions had been ordered in 1979 and Lockheed TriStar tankers would be ordered subsequent to the conflict, as a stopgap measure six Vulcans were converted into single point tankers. The Vulcan tanker conversion was accomplished by removing the jammers from the ECM bay in the tail of the aircraft, and replacing them with a single Hose Drum Unit (HDU). An additional cylindrical bomb-bay tank was fitted, making a total of three, giving a fuel capacity of almost 100,000 lb (45,000 kg).
The go-ahead for converting the six aircraft was given on 4 May 1982. Just 50 days after being ordered, the first Vulcan tanker, XH561, was delivered to RAF Waddington. The Vulcan K.2s were operated by No. 50 Squadron, along with three Vulcan B.2s, in support of UK air defence activities until it was disbanded in March 1984.
Vulcan Display Flight
After the disbandment of No. 50 Squadron, two Vulcans continued flying with the RAF in air displays as part of the Vulcan Display Flight, based at Waddington but administered through No. 55 Squadron, based at RAF Marham. Initially displaying using XL426, in 1986 that aircraft was sold, having been replaced by XH558, which began displays in 1985. The VDF continued with XH558 until 1992, finishing operations after the Ministry of Defence determined it was too costly to run in light of budget cuts. Both aircraft subsequently entered preservation and survived, although a third, XH560, kept in reserve in the first years, was later scrapped.
Engine test beds
- The first prototype VX770 had its Sapphire engines replaced with four 15,000 lbf (67 kN) Rolls-Royce Conway RCo.7 turbofans in 1957. It was transferred to Rolls-Royce as the Conway test bed. It flew with the Conways, the first turbofans in the world, until its fatal crash in September 1958.
- The first Vulcan B.1 XA889 was used for the flight clearances of the Olympus 102 and 104.
- Vulcan B.1 XA891 was fitted with four Olympus 200 engines in the spring of 1958 for intensive flying trials. The aircraft crashed in July 1958 during a routine test flight.
- Vulcan B.1 XA894 flew with five Olympus engines, the standard four Mk.101s, plus a reheated Olympus 320 destined for the BAC TSR-2 in an underslung nacelle. This aircraft was destroyed in a ground fire at Filton on 3 December 1962.
- Vulcan B.1 XA896 was withdrawn from RAF service in June 1964 and transferred to be converted to the test bed for the Bristol Siddeley BS100 vectored thrust turbofan for the Hawker Siddeley P.1154. The P.1154 was cancelled in February 1965 and XA896 was scrapped before being converted.
- Vulcan B.1 XA902 was withdrawn from RAF service after a landing accident in 1958. After rebuilding, it replaced VX770 as the Conway test bed, fitted with four RCo.11s. The two inner Conways were replaced with Rolls-Royce Speys, flying for the first time in this configuration on 12 October 1961.
- Vulcan B.1 XA903, surplus to Blue Steel trials, was converted to a similar layout to XA894 to flight test the Olympus 593 Concorde installation. The first flight was on 1 October 1966 and testing continued through to June 1971. In April 1973, XA903 flew with an underslung Rolls-Royce RB.199 turbofan destined for the Panavia Tornado. The RB.199 engine included both the reheat and thrust reverser functions. XA903 was the last B.1 to fly, being retired in February 1979.
- Vulcan B.2 XH557 was used by BSEL for developing the Olympus 301 and first flew with the larger engine in May 1961. It was returned to Woodford in 1964 to be refurbished for the RAF.
- The initial production aircraft. First few with straight leading edge, later retrofitted with Phase 2 (kinked) wing. Early examples finished in silver, later changed to "anti-flash" white. Many converted to B.1A standard 1959-1963. Last few unmodified B.1s in RAF service with No. 230 OCU retired by 1966. Last flight by any B.1, an engine testbed XA903, March 1979.
- The B.1 with an Electronic Countermeasures (ECM) system in a new larger tail cone (as in B.2). Unlike the B.2, the B.1As did not undergo extensive wing strengthening for low-level flying and were withdrawn from service 1966-67.
- Developed version of the B.1. Larger, thinner wing than the B.1 (Phase 2C wing) and fitted with Olympus 201-202 engines of 17,000 lbf (76 kN) each, or Olympus 301 engines of 20,000 lbf (89 kN) each. Uprated electrics with Auxiliary Airborne Power Plant (AAPP) (Auxiliary power unit) and Ram Air Turbine (RAT). ECM similar to B.1A. Terrain-Following Radar (TFR) in nose thimble radome fitted to most aircraft in mid-60s. New Radar warning receiver aerials on tail fin giving it a square top from the mid-1970s.[N 7]
- B.2 (MRR)
- Nine B.2s converted to Maritime Radar Reconnaissance (MRR). TFR deleted. Five aircraft further modified for Air Sampling Role. Distinctive gloss finish with light grey underside.
- Six B.2s converted for air-to-air refuelling with Mark 17 Hose Drum Unit (HDU) mounted semi-recessed in tail cone. TFR deleted. Fitted with three bomb-bay drum tanks, it was the only mark of Vulcan that could jettison fuel in an emergency.
- Proposed version intended as a long endurance missile carrier capable of carrying up to six Skybolt ALBMs on flights of up to 12 hours duration. Never built.
|Length||97 feet 1 inch (29.59 m)||105 feet 11 inches (32.28 m)||110 feet 0 inches (33.53 m)|
|Height||26 feet 6 inches (8.08 m)||27 feet 2 inches (8.28 m)|
|Wingspan||99 feet 0 inches (30.18 m)||111 feet 0 inches (33.83 m)||121 feet 0 inches (36.88 m)|
|Engines||4 x Bristol-Siddeley Olympus 101/102/104||4 x Bristol-Siddeley Olympus 201 or 301||4 x Bristol-Siddeley Olympus 301|
|Armament||1 x Blue Danube or Yellow Sun;
21 x 1000 lb free-fall bombs
|1 x Blue Steel;
21 x 1000 lb free-fall bombs
|Up to 6 x Skybolt|
|6 July 1948||2||Prototypes||Two prototypes delivered in August 1952 and September 1953|
|14 August 1952||25||Vulcan B.1||First flight of production aircraft 4 February 1955, delivered between June 1955 and December 1957.|
|30 September 1954||20||Vulcan B.1||Delivered between January 1958 and April 1959.|
|30 September 1954||17||Vulcan B.2||Delivered between September 1959 and December 1960|
|31 March 1955||8||Vulcan B.2||Delivered between January and May 1961|
|25 February 1956||24||Vulcan B.2||Delivered between July 1961 and November 1962|
|22 January 1958||40||Vulcan B.2||Delivered between February 1963 and January 1965, one aircraft not flown and used as a static test airframe|
- Aeroplane and Armament Experimental Establishment aircraft used for trials and evaluation
- Royal Air Force
- No. 9 Squadron RAF (Operated the B.2 from 1962 to 1982)
- No. 12 Squadron RAF (Operated the B.2 from 1962 to 1967)
- No. 27 Squadron RAF (Operated the B.2 from 1961 to 1972 and the B.2 (MRR) from 1973 to 1982)
- No. 35 Squadron RAF (Operated the B.2 from 1962 to 1982)
- No. 44 Squadron RAF (Operated the B.1/B.1A from 1960 to 1967 and the B.2 from 1966 to 1982)
- No. 50 Squadron RAF (Operated the B.1/B.1A from 1961 to 1966, the B.2 from 1966 to 1984 and the K.2 from 1982 to 1984)
- No. 83 Squadron RAF (the first Vulcan squadron operated the B.1/B.1A from 1957 to 1960 and the B.2 from 1960 to 1969)
- No. 101 Squadron RAF (Operated the B.1/B1A from 1957 to 1967 and the B.2 from 1967 to 1982)
- No. 617 Squadron RAF (Operated the B.1/B1A from 1958 to 1961 and the B.2 from 1961 to 1981)
- No. 230 Operational Conversion Unit RAF from 1956 to 1981. The first unit to operate the Vulcan, it provided conversion to type and operational training for Vulcan aircrew
- Bomber Command Development Unit
- Vulcan To The Sky Trust (flying G-VLCN (formerly XH558) currently based at Robin Hood Airport Doncaster Sheffield)
- Aircraft were also operated at various times under the direction of the Ministry of Supply/Aviation for trials and evaluation by Avro, Bristol Siddeley Engines, Rolls-Royce and the Blind Landing Experimental Unit (BLEU).
- RAF Akrotiri in Cyprus was the base for two operational B.2 squadrons from 1969 to 1975
- RAF Coningsby was the base for three operational squadrons from 1962 to 1964
- RAF Cottesmore was the base for three operational squadrons from 1964 to 1969
- RAF Finningley
- 101 Squadron 1957-1961, formed in 1957 to be the second operational B.1 squadron, moved to Waddington in 1961.
- 230 OCU 1961-1969, moved from Waddington in 1961, moved to Scampton in 1969.
- RAF Scampton was the base for three operational squadrons at different times between 1961 and 1981
- 27 Squadron 1961-1972, formed in 1961 to operate the B.2 until it disbanded in 1972. Reformed in 1973 to operate the B.2 (MRR) variant until 1982.
- 83 Squadron 1960-1969, a former B.1/B.1A squadron at Waddington, reformed in 1960 to operate the B.2 until disbanded in 1969.
- 617 Squadron 1958-1981, formed in 1958 to operate the B.1, reformed to operate the B.2 in 1961 until disbanded in 1981.
- 230 OCU 1969-1981, moved from Finningley in 1969 until disbanded in 1981.
- RAF Waddington was the base for a number of operational squadrons at different times between 1957 and 1984, it was the first and last operational Vulcan base
- 9 Squadron 1975-1982, moved in from Akrotiri in 1975 until it was disbanded 1982.
- 44 Squadron 1960-1982, formed in 1960 to operate the B.1/B.1A, it converted to the B.2 in 1966 and disbanded in 1982.
- 50 Squadron 1961-1984, formed in 1961 to operate the B.1/B.1A, it converted to the B.2 in 1966, from 1982 it also flew the tanker version until disbanding in 1984.
- 83 Squadron 1957-1960, formed in 1957 to be the first operational squadron to operate the B.1 until 1960, it reformed at Scampton later in the year as a B.2 unit.
- 101 Squadron 1961-1982, moved from Finningley in 1961 with the B.1/B.1A, converted to B.2 in 1967 and disbanded in 1982.
- 230 OCU 1956-1961, formed in 1956 to train Vulcan crews it moved to Finningley in 1961.
V-Bomber dispersal airfields
In the event of transition to war, the V Bomber squadrons were to deploy four aircraft at short notice to each of 26 pre-prepared dispersal airfields around the United Kingdom. In the early 1960s the RAF ordered 20 Beagle Basset communication aircraft to move the crews to dispersal airfields; the importance of these aircraft was only brief, diminishing when the primary nuclear deterrent switched to the Royal Navy's Polaris Missile.
Accidents and incidents
|Vulcan B.1 XA897 prior to the accident, stopping over at RAF Khormaksar|
- On 1 October 1956, Vulcan B.1 XA897, the first to be delivered, crashed at London Heathrow Airport during Operation Tasman Flight, a flag-waving trip to Australia and New Zealand. After a GCA approach in bad weather, it struck the ground 700 yd (640 m) short of the runway just as engine power was applied. The impact probably broke the drag links on the main undercarriage, allowing the undercarriage to be forced backwards and damaged the wing's trailing edge. After the initial impact, XA897 rose back in the air. The pilot, Squadron Leader D. R. Howard, and co-pilot Air Marshal Sir Harry Broadhurst, AOC-in-C Bomber Command, both ejected and survived, the other four occupants (including a spare pilot and an Avro representative) were killed when the aircraft hit the ground again and broke up.
- In 1957, a Vulcan B.1 XA892 attached to the Aeroplane and Armament Experimental Establishment (A&AEE) at Boscombe Down for acceptance testing was unintentionally flown to an Indicated Mach Number (IMN) above 1.04, alarming the crew that it had reached supersonic speed. XA892's commander, Flt Lt Milt Cottee (RAAF), and co-pilot, Flt Lt Ray Bray (RAF), were tasked to fly at 478 mph (769 km/h) and 0.98 IMN, taking the aircraft to a load factor of 3 g. It climbed to 35,000 ft (11,000 m) and then dived, intending to reach the target speed at 27,000 ft (8,200 m). Approaching the target altitude, the throttles were closed and full up-elevator applied, but XA892 continued to pitch nose-down. Cottee contemplated pushing forward to go inverted and then rolling upright; instead, he opened the speed brakes. Although the airspeed was above their maximum operating speed, the speed brakes were undamaged and did slow the aircraft, which came back past the vertical at about 18,000 ft (5,500 m) and leveled off at 8,000 ft (2,400 m). There were no reports of a sonic boom, it is unlikely a true Mach Number of 1.0 was reached.[N 8] Afterwards, a rear bulkhead was found to be deformed.
- On 20 September 1958, Vulcan VX770 was flown by a Rolls-Royce test pilot on an engine performance sortie with a fly past at RAF Syerston Battle of Britain At Home display. It flew along the main runway then started a roll to starboard and climbed slightly, during which the starboard wing disintegrated and the main spar collapsed. VX770 went into a dive with the starboard wing on fire and struck the ground, killing three occupants of a controllers' caravan and all four crew on board. Proposed causes of the structural failure have included pilot error, metal fatigue due to air intake vibration, and inadequate maintenance.[N 9]
- On 24 October 1958, Vulcan B.1 XA908 of No. 83 Squadron crashed east of Detroit, Michigan, USA. A complete electrical failure occurred at around 30,000 ft (9,100 m), the backup system should have provided 20 minutes of emergency power, allowing XA908 to reach one of several airports in the area, however backup power only lasted three minutes due to a short circuit in the service busbar, locking the controls. XA908 went into a steep dive before crashing, leaving a 40-ft (13 m) crater in the ground, which was later excavated while retrieving wreckage. Despite extensive property damage, there were no ground fatalities, only one person on the ground was hospitalized. All six crew members were killed, including the co-pilot, who had ejected. The co-pilot's ejector seat was found in Lake St Clair, but his body was not recovered until the following spring. They were buried at Oak Ridge Cemetery in Trenton, Michigan, alongside 11 RAF student pilots killed during the Second World War in accidents at nearby Naval Air Station Grosse Ile.
- On 24 July 1959, Vulcan B.1 XA891 crashed due to an electrical failure during an engine test. Shortly after take-off, the crew observed generator warning lights and loss of busbar voltage. The aircraft commander, Avro Chief Test Pilot Jimmy Harrison, climbed XA891 to 14,000 ft (4,300 m), steering away from the airfield and populated areas while the AEO attempted to solve the problem. When it became clear that control would not be regained, Harrison instructed the rear compartment crew to exit the aircraft and the co-pilot to eject, before ejecting himself. All the crew survived, making them the first complete Vulcan crew to successfully escape. The aircraft crashed near Kingston upon Hull.
- On 26 October 1959, Vulcan B.1 XH498 participated in an airshow marking the opening of Wellington International Airport, formerly Rongotai Airport. After a ' touch-and-go landing' on Runway 34, it came around for a full stop landing. Turbulence and wind shear caused XH498 to land short of the runway threshold, the port undercarriage leg clipped the embankment at the Moa Point or southern end, damaging wing attachments, engine fuel lines and the main landing gear drag link, which was ruptured and unable to support the aircraft. The port wing tip nearly scraped the runway surface before it was able to lift off again, spilling fuel over the crowd. Pilot actions prevented a possible disaster as spectators were present on the western apron. XH498 flew to RNZAF Ohakea for a safe emergency landing on just the nose and starboard landing gear with little further damage. A UK repair team returned it to airworthiness; on 4 January 1960, XH498 departed, remaining in service until 19 October 1967.
- On 16 September 1960, Vulcan B.2 XH557 damaged the "Runway Garage" at Filton. XH557 had been allocated to Bristol Siddeley Engines to test the Olympus 301 engine and was being delivered to Filton. Approaching in poor weather conditions, the aircraft touched down halfway along the runway. The braking parachute was streamed but realising the aircraft would not stop in time, the captain opened the throttles to go round. The Runway Garage took the full force of the jet blast and property damage was sustained: four petrol pumps were blown flat, a street light on the A38 was knocked down, railings were blown over, and multiple cars had their windscreens shattered. The aircraft diverted to St. Mawgan, flying into Filton days later.
- On 12 December 1963, Vulcan B.1A XH477 of No. 50 Squadron crashed during an exercise in Scotland. Flying no less than 1,000 ft (300 m) above ground, XH477 struck the ground while climbing slightly, the cause was likely poor visibility.
- On 11 May 1964, Vulcan B.2 XH535 crashed during a demonstration. The aircraft entered a spin while a very low speed and high rate of descent was being demonstrated. The landing parachute was deployed, stopping the spin briefly before it began to spin again. At around 2,500 ft (760 m) the aircraft commander instructed the crew to abandon the aircraft. The commander and co-pilot ejected successfully, but none of the rear compartment crew did so, presumably due to the g forces in the spin.
- On 16 July 1964, Vulcan B.1A XA909 crashed in Anglesey after a midair explosion caused both No. 3 and No. 4 engines to be shut down. The explosion was caused by failure of a bearing in No. 4 engine. The starboard wing was extensively damaged, the pilot had insufficient aileron power, and both airspeed indications were highly inaccurate. The whole crew successfully abandoned XA909 and were found within a few minutes and rescued.
- On 7 October 1964, Vulcan B.2 XM601 crashed during overshoot from an asymmetric power practice approach at Coningsby. The copilot had executed the asymmetric power approach with two engines producing thrust and two at idle. He was being checked by the Squadron Commander, who was unfamiliar with the aircraft. When he commenced the overshoot the copilot moved all the throttles to full power. The engines that had been producing power reached full power more quickly than the engines at idle and the resultant asymmetric thrust exceeded the available rudder authority, causing the aircraft to spin and crash. All the crew perished.
- On 25 May 1965, Vulcan B.2 XM576 crash-landed at Scampton, causing it be written off within a year of delivery.
- On 11 February 1966, Vulcan B.2 XH536 of the Cottesmore Wing crashed in the Brecon Beacons during a low level exercise. The aircraft struck the ground at 1,910 ft (580 m) near the summit of Fan Bwlch Chwyth 1,978 ft (603 m), 20 mi (32 km) northeast of Swansea. All crew members died. Hilltops at the time were snow-covered and cloud extended down to 1,400 ft (430 m).
- On 6 April 1967, Vulcan B.2 XL385 burnt out on the runway at RAF Scampton at the beginning of its take-off run. The aircraft was carrying a Blue Steel missile training round. All the crew, including an Air Training Corps cadet, escaped unhurt. The aircraft was engulfed in flames and totally destroyed. The accident was caused by failure of an Olympus 301 HP turbine disc as the engine reached full power.
- On 30 January 1968, Vulcan B.2 XM604 crashed following a loss of control during an overshoot at RAF Cottesmore. The rear crew members were killed though both pilots ejected. The captain ejected at a very late stage and only survived because his deploying parachute was snagged by some power cables. The accident was caused by failure of an Olympus 301 LP turbine disc after the aircraft had returned to the airfield following indications of a bomb-bay overheat.
- On 7 January 1971, Vulcan B.2 XM610 of No.44 Squadron crashed due to a blade fatigue failure in the No. 1 engine, damaging the fuel system and causing a fire. The crew abandoned the aircraft safely, after which it crashed harmlessly in Wingate.
- On 14 October 1975, Vulcan B.2 XM645 of No.9 Squadron lost its left undercarriage and damaged the airframe when it undershot the runway at RAF Luqa in Malta. The aircraft broke up over the village of Żabbar while turning inbound for an emergency landing. The pilot and co-pilot escaped using their ejection seats, the other five crew members were killed. Large aircraft pieces fell on the village; one woman, Vincenza Zammit, was killed by an electric cable, some 20 others were injured.
- On 17 January 1977, Vulcan B.2 XM600 of No. 101 Squadron crashed near Spilsby, Lincolnshire. During a practice emergency descent, the bomb bay fire warning light flashed on followed by No.2 engine fire warning light. The captain shut the engine down and the AEO reported flames coming from the area of No.2 engine, just behind the deployed Ram air turbine (RAT). As the fire intensified, the captain ordered the aircraft to be abandoned. The three rear crew members escaped at around 6,000 ft (1,800 m). After ordering the co-pilot to eject, the captain ejected at around 3,000 ft (910 m), as control was lost. The cause was due to arcing on the RAT's electrical terminals, burning a hole in an adjacent fuel pipe and setting the fuel on fire.
- On 12 August 1978, Vulcan B.2 XL390 of No. 617 Squadron crashed during an air display at Naval Air Station Glenview, Illinois in the United States. The crew had been authorised to carry out a display at Chicago Lakeside airport, the captain had elected to carry out an unauthorised display at Glenview beforehand. After a low-level run, probably below 100 ft (30 m), the aircraft pulled up for an improperly-executed wingover, resulting in a low-level stall and crash, killing all on board.
- On 28 May 2012, Vulcan B.2 XH558 suffered failure of the two port engines while starting a take-off roll from Robin Hood airport, Doncaster, UK. Bags of silica gel desiccant were inadvertently left in the air intake after maintenance. Less than a second after increasing power from 80% to 100% these were ingested by one of the port engines, immediately destroying it. The remaining port engine ingested debris from the first engine, destroying this one as well. The fire prevention systems proved effective, neither the airframe nor control systems suffered damage. The pilot had no difficulty bringing the aircraft to a safe stop, having remained on the ground throughout. The airport incident response was exemplary. On 3 July 2012, XH558 returned to flight.
Several Vulcans survive, housed in museums in both the United Kingdom and North America (USA & Canada). One Vulcan, XH558 (G-VLCN) Spirit of Great Britain, was used as a display aircraft by the RAF as part of the Vulcan Display Flight until 1993. After being grounded it was later restored to flight by the Vulcan To The Sky Trust and displayed as a civilian aircraft from 2008 until 2015, before being retired a second time for engineering reasons. In retirement, XH558 is to be retained at its base at Robin Hood Airport as a taxi-able aircraft, a role already performed by two other survivors, XL426 (G-VJET) based at Southend Airport, and XM655 (G-VULC), based at Wellesbourne Mountford Airfield.
|Avro Vulcan B.2 cutaway showing internal compartments and bays|
|Avro Vulcan Cutaway from Flightglobal.com|
- Crew: 5 (pilot, co-pilot, AEO, Navigator Radar, Navigator Plotter)[nb 1]
- Length: 97 ft 1 in (29.59 m)
- Wingspan: 99 ft 5 in (30.3 m)
- Height: 26 ft 6 in (8.0 m)
- Wing area: 3,554 ft² (330.2 m²)
- Empty weight: 83,573 lb (including crew) (37,144 kg)
- Max. takeoff weight: 170,000 lb (77,111 kg)
- Powerplant: 4 × Bristol Olympus 101, or 102 or 104 turbojet, 11,000 lbf (49 kN) each
- Maximum speed: Mach 0.96 (645 mph ( 1038.03km/h)) at altitude
- Cruise speed: Mach 0.86 (567 miles per hour (912 km/h)) at 45,000 ft
- Range: 2,607 mi (4,171 km)
- Service ceiling: 55,000 ft (17,000 m)
- Thrust/weight: 0.31
- 21 × 1,000 pounds (454 kg) of conventional bombs
- 1 x Blue Danube nuclear gravity bomb
- 1 x Violet Club 400 kt nuclear gravity bomb
- 1 x U.S. Mark 5 nuclear gravity bomb supplied under Project E
- 1 x Yellow Sun Mk.1 400 kt nuclear gravity bomb
- 1 x Yellow Sun Mk 2 1.1 Mt thermonuclear gravity bomb
- 1 x Red Beard nuclear gravity bomb
Comparison of variants
|Wingspan||99 ft 5 in (30.30 m)||111 ft 0 in (33.83 m)|
|Length||97 ft 1 in (29.59 m)||105 ft 6 in (32.16 m) [99 ft 11 in (30.45 m) without probe]|
|Height||26 ft 6 in (8.08 m)||27 ft 1 in (8.26 m)|
|Wing area||3,554 sq ft (330.2 m2)||3,964 sq ft (368.3 m2)|
|Maximum takeoff weight||167,000 lb (76,000 kg)
185,000 lb (84,000 kg) (operational necessity)
|204,000 lb (93,000 kg)|
|Cruising speed||Mach .86 indicated|
|Maximum speed||Mach .95 indicated||Mach .93 indicated
(Mach .92 with 301 engines)
|Service ceiling||55,000 ft (17,000 m)||45,000 ft (14,000 m) to 56,000 ft (17,000 m)[nb 2]|
|Electrical system||112V DC||200V AC 3-phase 400 Hz|
|Battery||Ram air turbine and Airborne Auxiliary Power Plant|
|Engines||4 × Bristol
Olympus 101, 102 or 104
|4 × Bristol
|4 × Bristol Siddeley
Olympus 200-series, 301
|4 × Bristol Siddeley
|Fuel capacity (main)||9,280 gal (74,240 lb avtur)[nb 3]||9,260 gal (74,080 lb avtur)|
|Fuel capacity (bomb bay)||None||0-1990 gal (15,920 lb avtur)||1990 gal[nb 4]
(15,920 lb avtur)
|2985 gal[nb 5]
(23,880 lb avtur)
|Powered flying controls||1 x rudder (duplex), 4 x elevators, 4 x ailerons||1 x rudder (duplex), 8 x elevons|
|Armament||1 × free-fall nuclear bomb or
21 × 1,000 lb (450 kg)
|1 × Blue Steel missile or
1 × free-fall nuclear bomb or
21 × 1,000 lb (450 kg)
- Two extra seats could be fitted for Crew Chiefs if required, for a total of seven crew.
- Depended upon oxygen equipment fitted. No airframe limitation on height.
- At specific gravity of .8 (8lb/gal).
- 2 x 995 gal cylindrical tanks.
- 3 x 995 gal cylindrical tanks.
- Aircraft of comparable role, configuration and era
- Related lists
- RAF bombers had been traditionally named after inland towns in the British Commonwealth, or towns associated with industry.
- A contract for 25 production models had been made in July 1952. The same number of the rival Handley Page design were also ordered.
- Writing for the American Institute of Aeronautics and Astronautics, J. Seddon and E. L. Goldsmith noted that "Due to its all-wing shape, small vertical fin, and buried engines, at some angles [The Avro Vulcan] was nearly invisible to radar". While writing about radar systems, authors Simon Kingsley and Shaun Quegan singled out the Vulcan's shape as reducing the RCS. While aviation author Doug Richardson has credited the Vulcan as having been difficult to acquire on radar, he went on to state that this was unlikely to have conferred a great military advantage. In contrast, electronic warfare author and ex-Vulcan AEO Dr Alfred Price maintains "the Vulcan [...] possessed a large radar signature."
- Some B.2 aircraft armed with Blue Steel had an additional aerial plate fitted between the port tailpipes as the Blue Steel fin, in the lowered position, blanked signals from the starboard side.
- Bristol Aero Engines merged with Armstrong Siddeley in 1959 to form Bristol Siddeley which in turn was taken over by Rolls-Royce in 1966.
- According to UK parlance of the time, "megaton range" was understood to correspond to 500 kt or greater. The Green Grass warhead had a predicted yield of 500 kt.
- Some sources have attested to the existence of a Vulcan B.2A. This designation supposedly referred either to Vulcan B.2s fitted with Olympus Mk 301 engines or those modified to carry the Blue Steel missile. However, irrespective of the role or engine fit, the B.2 was the only official designation except for the MRR and tanker variants.
- When flying at a speed of Mach 1.0, the Vulcan suffered a position error of about 0.07.
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<ref>tag; name "Jefford27" defined multiple times with different content (see the help page).
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|Wikimedia Commons has media related to Avro Vulcan.|
- Avro Vulcan Bomber Tribute Page
- Vulcan to the Sky
- Vulcans in Camera
- Vulcan history
- Vulcan Restoration Trust
- Video of Roland Falk rolling a Vulcan at Farnborough in 1955
- Vulcan Test Pilot Roly Falk history
- Building the Vulcan a 1957 Flight article
- the Vulcan Story Flight article of 1958
- The Virtues of the Avro Vulcan a 1954 AVRO advertisement for the Vulcan in Flight magazine
- A radar signature scale model of the Vulcan used for testing radar echo visibility