The Viscount 700 Series Specification
SECOND EDITION SEPTEMBER 1952
Version AL6 issued June 1954
2. PERFORMANCE, WEIGHTS AND DIMENSIONS
2.1 PERFORMANCE
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
tolerances.
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.
AERIALS
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
NOTE 1
The following approx gradients corresponding to the climb requirements are given for information only.
NOTE 2
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.
NOTE 3
The take-off and landing techniques employed will be in accordance of BCAR s Section D (1951).
NOTE 4
(ISA + 30 degrees C) is 'Tropical Maximum' temperature as defined in BCAR leaflet Z-8 Issue 1.
2.2 WEIGHTS
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.
Weight
Maximum take off weight* 58,500lb.
Speeds
Manoeuvring speed VA = 169 kts EAS.
Factors
Manoeuvring load factor 2.5
Estimated WEIGHT - ALTITUDE - TEMPERATURE limitations
* NOTE
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.
** NOTE
Design Cruising speed VC varies with all-up weight and actual weight without fuel.
2.4 LOAD DISTRIBUTION AND WEIGHT RECORDS
Loading instructions
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.
Ballast
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:-
Weight record
Each production aircraft will be weighed in the Weight Empty condition. A weighing report and weight schedule will be
provided for each aircraft.
2.5 DIMENSIONS
Length overall 81ft 2in.
Mainplanes
Gross Area 963 sq ft.
Flaps
Type - Double slotted.
Ailerons
Type - Westland Irving Internally balanced.
Tailplane and Elevator
Gross Area 238 sq ft.
Fin and Rudder
Gross Area 124 sq ft.
Fuselage
Fuselage length 81ft 2in.
