The Viscount 700 Series Specification
SECOND EDITION SEPTEMBER 1952
Version AL6 issued June 1954
2. PERFORMANCE, WEIGHTS AND DIMENSIONS
The following performance figures are guaranteed with pressurising system in operation but with de-icing system
inoperative, the total auxiliary power take-off being not greater than **. They apply to the aircraft as shown in
Fig 8 issue 1, equipped with the external aerials as defined below, and the engine being within the manufacturers delivery
NOTE:- These guarantees will be affected by any subsequent alterations resulting in any changes in profile or any
reduction in available power brought about by operator’s requirements.
VHF Two blades approx 2.5" x 0.25" x 24" long tapered.
ADF Sense aerial, approx 5’ 6” long x 3/8” diameter.
HF Aerial wire running from stub mast on starboard side to fin. Stub mast, approx 17" high, 6" at base to 4" at
top. Nominal aerofoil thickness approx 0.8".
ILS Localiser. One aerial each side of fin, 24" long x 0.5" x 0.25".
** 100 BHP (Provisional)
(1) Take-off distance to 50ft at 58,500lb of 1,620 yds (ISA sea level), and 1,760 yds (ISA +30 degrees C at sea
level) with water methanol injection. Tolerance on distances + 5 % - 10 % (take off surface, level dry concrete).
(2) Take-off distance to 50ft or accelerate to stop at 58,500 lb with an engine failure at the critical point of
1,860 yds (ISA sea level) and 2,040 yds (ISA + 30 degrees C sea level) with water methanol injection. Take-off surface
level dry concrete. Tolerance on distances +5% - 10%.
(3) ** From a take off weight of 58,500lb the gradient of the Net Flight Path determined in accordance with Chapter
D2-4 paragraph 2. 1. 2. Issue 2 of BCAR Section D dated January 1st 1951, shall not be less than 1.9% at a pressure
altitude of 9,000ft in ISA conditions.
(4) ** From a Take-off weight of 56,000lb the gross gradient of climb in the Initial En-route climb configuration
determined in accordance with Chapter D2-4 paragraph 2. 1. 3. of Issue 2 of BCAR Section D dated January 1st 1951, shall
not be less than (0.5 + 11 D/W)% at a pressure altitude of 12,500ft in ISA conditions.
Estimated climb performance at 13,600 rpm and 160 kts EAS.
(5) At a weight of 52,000lb the gross gradient of climb in the Baulked Landing condition determined in accordance
with Chapter D2-4 paragraph 2.3.2. of Issue 2 of BCAR Section D dated January 1st 1951, shall not be less than (1.5 + 14
D/W)% at a pressure altitude of 7,000ft in ISA conditions.
(6) A landing distance from 1.3 VSO at 50ft of 1,050 yds (ICAN and 1,225yds (ISA + 30 degrees C) at a weight of
52,000lb. Tolerance on distances + 5% - 10%.
(7) A climb in ICAN conditions from sea level to 20,000ft from a 58,500lb take-off using not more than 1,480lb of
fuel and covering less than 85 nautical miles from the commencement of climb point at the most suitable climbing speed.
(8) A cruising true air speed of 275 kts +/- 5% at 20,000ft ICAN with a consumption of 2,480 lb/hr +/- 2.5% of fuel
at a weight of 56,500lb.
** These guarantees are at weights selected to suit the manufacturers Flight Test Schedule. The equivalent
compliance altitudes at 58,500lb would be about 7,500ft for (3) and 11,000ft for (4).
Cruising speeds and maximum continuous rates of climb
The following approx gradients corresponding to the climb requirements are given for information only.
(0.5 + 11 D/W)% = 1.25% gradient on 3 engines on maximum continuous power.
(1.5 + 14 D/W)% + 3.25% gradient on 4 engines on T.O power, flaps and chassis down.
The following stalling speeds have been extracted from the Flight Manual and are reproduced only for the convenience of the
operator. They do not form part of the guaranteed performance.
Maximum landing flap 52,000lb 84 knots EAS.
Baulked landing flap 52,000lb 87 knots EAS.
Take-off flap 58,500lb 99 knots EAS.
Flaps up 58,500lb 107 knots EAS.
The take-off and landing techniques employed will be in accordance of BCAR s Section D (1951).
(ISA + 30 degrees C) is 'Tropical Maximum' temperature as defined in BCAR leaflet Z-8 Issue 1.
A weight summary will be produced in conformance with the standard weight summary sheet in Section 16. The weights quoted
therein refer to a standard type and are given as instances only. It will be based on the guaranteed empty weight of
Section 16 and the structural weight limitations shown below.
2.3 STRUCTURE LIMITATIONS
The aircraft complies with BCAR Section D, Issue 2 dated January 1st 1951, at the following limiting conditions.
Maximum take off weight* 58,500lb.
Maximum landing weight 52,000lb.
Maximum permissible weight without fuel 48,000lb.
If alternative fuel system is fitted (refer Optional Equipment) the permissible weight without fuel becomes 49,000lb.
Manoeuvring speed VA = 169 kts EAS.
Design speed for maximum gust velocity VB = 165 kts EAS.
Design cruising speed* VC = 219 to 235 kts EAS at 10,000ft.
Design diving speed VD = 296 kts EAS.
Design speed flaps down VF = 138 kts EAS.
Manoeuvring load factor 2.5
Gust velocities as BCAR.
Gust limit load factors
(1) At 50,000lb and VC = 225 kts EAS 2.71 & -0.71
(2) At 58,500lb and VC = 235 kts EAS 2.542 & -0.542
Estimated WEIGHT - ALTITUDE - TEMPERATURE limitations
for compliance with BRITISH CIVIL AIR WORTHINESS REQUIREMENTS - 1951
The airworthiness requirements of paragraph 1.4 can be met at an increased take-off weight should this be required
during the development of the aircraft. A maximum take-off weight of 59,500lb will not be exceeded.
Design Cruising speed VC varies with all-up weight and actual weight without fuel.
2.4 LOAD DISTRIBUTION AND WEIGHT RECORDS
These will be prepared to cover operation of the aircraft with the layout selected. They will be of simple form,
suitable for use by non-technical personnel, and will state, for a given total of freight and baggage, the amount to be
stowed in each compartment and the limits on this distribution. Passengers will, so far as practicable, be given free
choice of seats. In preparing the loading instructions the following factors will be taken into account.
(a) Variation in the aircraft 'Weight Empty' CG position, based on the modification state of the first aircraft at the
time of delivery.
(b) Passenger weight is 156lb.
(c) Flight Crew Weight is 198lb including 33lb baggage.
(d) Steward weight is 187lb including 33lb of baggage.
No ballast is required for any normal operating load.
Loading if freight
Subject to AUW and zero fuel weight, it is possible to fill the cargo compartments to the following maximum amounts:-
Forward upper 1,700lbs.
Forward lower 2,060lbs.
Aft lower 1,740lbs.
Aft upper 2,500lbs.
Each production aircraft will be weighed in the Weight Empty condition. A weighing report and weight schedule will be
provided for each aircraft.
Length overall 81ft 2in.
Height overall 26ft 9in.
Track oleo centres 23ft 10in.
Outer wheel centres 25ft 4.8in.
Wheelbase 24ft 10.6in.
Gross Area 963 sq ft.
Nett Area 834 sq ft.
Span 93ft 8.5in
Thickness Chord ratio at root 15.5%.
Thickness Chord ratio at tip 13%.
Root Chord 178in.
Tip Chord 53in.
Root section - Modified NACA 63.
Tip Section - Modified NACA 63.
Type - Double slotted.
Area per side 76.75 sq ft.
Flap chord / wing chord 27%.
Main flap span / wing span 50.6%.
Flapped area / wing area 58.2%.
Span per side 285in.
Type - Westland Irving Internally balanced.
Area aft of hinge 47.4 sq ft.
Aileron Chord / Wing Chord 22%.
Aileron span / wing span 34.1%.
Tailplane and Elevator
Gross Area 238 sq ft.
Nett Area 203 sq ft.
Thickness chord ratio at root 14%.
Thickness chord ratio at tip 12%.
Type of balance - Set back hinge.
Elevator area 103.5 sq ft.
Elevator aft of hinge 72.3 sq ft.
Fin and Rudder
Gross Area 124 sq ft.
Thickness chord ratio at root 14%.
Type of balance - Set back hinge.
Rudder area 62 sq ft.
Rudder area aft of hinge 41.3 sq ft.
Fuselage length 81ft 2in.
Maximum width of fuselage 10ft 8.1in.
Maximum height of fuselage 10ft 8.1in.
Total wetted area 2,100 sq ft.
Wing setting to fuselage datum - 2 degrees 30'.
Height of door sills from ground (average) 7ft 6in.