# TCDS A-814: Vickers-Armstrongs (Aircraft Limited)

- Type: Type certificate data sheet
- Status: Current
- Holder: Vickers-Armstrongs (Aircraft Limited)
- Revision: 22
- Revised: February 12, 1981
- Product: Aircraft, Large Airplane
- Certification basis: Part 25, CAR 10
- Data sheet PDF: https://openairdocs.org/files/sha256/e3/f0/e3f061b8f1f8d26eaa9c4e48335eb3aff1f9089b03b998c7ff12995019873b46
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D4E7C15DB71849B28525672A0062888B.0001
- Page: https://openairdocs.org/tcds/A-814

## Models (3)

As the data sheet lists them.

- Viscount 810
- Viscount 744
- Viscount 745D

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12
Rev. No. 22 22 22 22 22 22 22 22 22 22 22 22
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
A-814
Revision 22
VICKERS
Viscount
744
745 (See NOTE 5)
745D
810
February 12, 1981
AIRCRAFT SPECIFICATION NO.A-814
Type Certificate Holder Vickers-Armstrongs (Aircraft Limited)
Weybridge Works,
Weybridge Surrey, England
I - Model Vickers Viscount Type 744, Approved June 13, 1955; Type 745D Approved February 23, 1956
Engines 4 Rolls-Royce Dart 506 Turbo-propellers for Type 744
4 Rolls-Royce Dart 510 Turbo-propellers for Type 745D
Fuel Aviation Kerosene to Specification D.Eng.R.D.2482; and/or
American Specification MIL-F-5616 (JP-1); and/or
Canadian Specification 3-GP-23(a)
            OR
D.Eng.R.D.2486; and/or American Specification MIL-F-5624B or C
(JP-4)*; and/or Canadian Specification 3-GP-22B
Water-Methanol mixture; 62/38 parts by weight of water-methanol to Rolls-Royce
Specification GM-1-W/M (Issue 2).  Specific Gravity approximately 0.94 at 60°F/60°F
*  When fuel of these types are used the engine controls may require adjustment.
Engine limits
Static Sea Level Ratings  (Dart 506)
Ratings
Shaft
Horsepower
(S.H.P.)
Jet
Thrust
(lbs.)
Engine
Speed
(r.p.m.)
Maximum takeoff 1400 365 14,500
Maximum continuous  (unrestricted) 1120 295 13,800
Ground idling 40 7 5500 - 7500
(max.) (max.)
Static Sea Level Ratings  (Dart 510)
Ratings
Shaft
Horsepower
(S.H.P.)
Jet
Thrust
(lbs.)
Engine
Speed
(r.p.m.)
Maximum takeoff 1600 370 14,500
Maximum continuous  (unrestricted) 1365 325 14,000
Ground idling 40 7 5500 - 7500
(max.) (max.)

A-814 2
Airspeed limits Vmo (Maximum operating) 237 kts. at 10,000 ft.
at No Fuel Weight of 46,000 lbs. (1)
  (Calibrated air speed) Vne (Never exceed) 269 kts. at 10,000 ft.   (2)
Va  (Maneuvering) 174 kts. at 10,000 ft.   (2)
Vfe (Flaps down 0° to 20°) 208 kts.
Vfe (Flaps down 20° to Fully Down) 144 kts.
Vlo (Landing Gear Operation) 162 kts.
Vle (Landing Gear Extension) 190 kts.
Vll (Landing Light Extension) 162 kts.
(1) For values of Vmo at other altitudes and No Fuel Weights, see Approved Airplane
Flight Manual.
(2) For values of Vne at other altitudes, see Approved Flight Manual.
C.G. range
With Standard Fuel Arrangement
Forward Aft
Weight (lbs.) % SMC Sta. % SMC Sta.
Takeoff and landing Up to 42,000 .05 (369.1) .26 (394.9)
Takeoff and landing 42,000 - 60,000 .05 (369.1 .26 (394.9)
to to
.135 379.5)
Takeoff and landing 60,000 - 62,000 .135 (379.5 .26 (394.9)
to to
.141 380.3)
Takeoff and landing 62,000 - 63,000 .141 (380.3 .26 (394.9)
to to
.144 380.7)
Takeoff and landing 63,000 - 64,500 .144 (380.7 .26 (394.9)
to to
.148 381.2)
Enroute Up to 42,000 .04 (367.8) .26 (394.9)
Enroute 42,000 - 51,000 .04 (367.8 .26 (394.9)
to to
.09 374.0)
Enroute 51,000 - 64,500 .09 (374.0) .26 (394.9)
When Fuselage Center Fuel Tank is in Use
Forward Aft
Weight (lbs.) % SMC Sta. % SMC Sta.
Takeoff and landing Up to 42,000 .05 (369.1) .26 (394.9)
Takeoff and landing 42,000 - 51,000 .05 (369.1 .26 (394.9)
to to
.10 375.25)
Takeoff 51,000 - 64,500 .10 (375.25 .26 (394.9)
Landing 51,000 - 57,500 .10 (375.25) .26 (394.9)
to to
.126 378.4)
Enroute Up to 42,000 .04 (367.8) .26 (394.9)
Enroute 42,000 - 51,000 .04 (367.8 .26 (394.9)
to to
.09 374.0)
Enroute 51,000 - 64,500 .09 (374.0) .26 (394.9)
Maximum weights Landing: Normal Landing Type 744: 55,000 lbs.;
Type 745D: 57,500 lbs.
Takeoff: Type 744: 60,700 lbs.;
Type 745D: 60,285 lbs.

3 A-814
NOTE: When the fuel jettisoning system, Vickers Armstrongs Modification No.
D.1720 is installed and operable, the maximum takeoff weight is 63,000 lbs.
This modification applies only to aircraft Type 745D.  When in addition to
Modification D.1720, the Modification Nos. D2257, D.2273, either D.1237
or D.2481, and Landing Gear Equipments 201(a) with 201(b) and either
202(c) or 202(f), OR 201(e) with 201(f) and 202(d) are incorporated, the
maximum takeoff weight is 64,500 lbs.  These modifications apply only to
aircraft Type 745D.
Zero fuel gross weight: Type 744 - 49,168 lbs.; Type 745D - 50,168 lbs.
Type 745D - 51,680 lbs. with BAC Mod. D.3194 incorp.
3-engine ferrying (See NOTE 4)
Minimum crew 2 Pilot and co-pilot (91)
No. of seats 48 (Passengers).  This number may be increased provided the arrangement is approved
by either the Air Registration Board or the Federal Aviation Agency.
2 (Stewards)
1 (Supernumerary flight crew)
Maximum baggage Type 744
Forward upper compartment   600 lbs. (142)
Forward lower compartment 2060 lbs. (206)
Aft upper compartment 2300 lbs. (740)
Aft lower compartment 1740 lbs. (294)
Aft lower compartment 1740 lbs. (294)
Type 745D
Forward upper compartment   880 lbs. (156)
Forward lower compartment (with Radio Mod. No. D.1236) 1800 lbs. (203)
Forward lower compartment (without Radio Mod. D.1236) 1900 lbs. (204)
Aft upper compartment (with Freon & lugg. guard)   930 lbs. (750)
Aft upper compartment (with Freon & lugg. guard       0 lbs. (750)
at ZFW above 50,168 lbs.)
Aft upper compartment (without Freon refrig. system) 2300 lbs. (740)
Aft upper compartment (without Freon at ZFW 1050 lbs. (740)
above 50,168 lbs.)
Aft lower compartment (with Radio Mod. No. D.1236) 1680 lbs. (296)
Aft lower compartment (without Radio Mod. No. D.1236) 1700 lbs. (295)
Fuel capacity Fuel contained in four wing tanks:
Types 744.  745D Serial No. 242 only
2 inner wing tanks of 603.5 U.S. gals. each (usable) 8048 lbs. (396)
2 outer wing tanks of 564 U.S. gals. each (usable) 7520 lbs. (417)
Total wing fuel capacity of 2335 U.S. gals.
plus 20.4 U.S. gals. of unusable fuel.
Type 745D
2 inner wing tanks of 578 U.S. gals. each (usable) 7712 lbs. (397)
2 outer wing tanks of 564 U.S. gals. each (usable) 7520 lbs. (417)
Total wing fuel capacity of 2284 U.S. gals.
plus 25.2 U.S. gals. of unusable fuel.
When Vickers-Armstrongs Modifications D.1312 and D.1974
have been incorporated the following fuel capacity is available
in one fuselage tank.
1 fwd. fuselage (center) tank cell of 351 U.S. gals. 2336 lbs.
1 aft. fuselage (center) tank cell of 201 U.S. gals. 1336 lbs.
Total fuselage fuel capacity of 552 U.S. gals. 3672 lbs. (268)
with no unusable fuel.

A-814 4
When Vickers Armstrongs Modifications D.639, D.1692, D.1819
have been incorporated the following fuel capacity is available in
two wing slipper tanks:  2 wing slipper tanks of 171.5
U.S. gals. each (usable) plus 2.5 U.S. gals.
(unusable) in each tank. (390)
When Vickers Armstrongs Modifications D.2760 and
D.2924 have been incorporated, the following fuel
capacity is available in two wing slipper tanks of
305.4 U.S. gals. each (usable) plus 0.6 U.S. gals.
(unusable) in each tank. 2036 lbs. (382)
Water/Methanol Types 744, 745D Serial No. 242 only; 90 U.S. gals.
(2 wing tanks 45 gals. each)   750 lbs. (388)
Type 745D:  132 U.S. gals.
(2 wing tanks 66 gals. each) 1034 lbs. (388)
Oil capacity 4.8 U.S. gals. per engine contained in the engine     38.5 lbs. (263)
Control surface movements Elevator Up 20° Down 10°
Elevator trim tab (Right) Up 12° Down 12°
*Elevator Anti-Balance Tab (Left) Up 15° Down   7° 30'
Elevator Spring Tab Up 10° Down 20°
Rudder Right 15° Left 15°
Rudder Trim & Spring Tab Right 10° Left 10°
Aileron Up 20° Down 20°
Aileron Trim Tab (Right) Up 20° Down 20°
Aileron Balance Tab (Left) Up 20° Down 20°
Flaps Down 47°
*When V.A. Modification D.2021 is incorporated the Anti-Balance Tab is offset 3°
Down at elevator neutral and the tab movement is measured from this position.
Serial Nos. eligible Type 744 - 40, 41, 42, 50 to 60 inclusive.
Type 745D - 82, 103 to 139 inclusive, 183, 184, 185, 191, 198 to 217 inclusive, 225 to
234 inclusive, 242, 284 to 288 inclusive, 334, 391 and 392.  The United Kingdom
certificate of airworthiness endorsed as noted under "Certification basis" must be
submitted for each individual aircraft for which application for certification is made.
Certification basis Type Certificate No. 814 issued under CAR 10.  Each aircraft and any replacement
parts manufactured in the United Kingdom must be designated as "import" and clearly
labeled as such in accordance with CAR 10.30.  Airworthiness certificate may be issued
on basis of a United Kingdom certificate of airworthiness signed by a representative of
the Ministry of Transport and Civil Aviation containing the following notation:  "The
aeroplane covered by this certificate has been examined and found to comply with
British Civil Airworthiness Requirements published January 1951 and with the Special
Requirements notified to the Government of the United Kingdom by the Government of
the U.S.A."  (This certification equivalent to CAR 4b (Transport Category) as amended
to May 18, 1954)
Required equipment In addition to the relevant basic equipment required by B.C.A.R. dated January 1951,
and U.S. Special Requirements, the following items of equipment must be installed:
Type 744 - 1(e), 2(a), 3(a), 4(a), 102(a), 104(g), 105, 106(a), 109(c), 201(a), (b);
202(e), 203(d), 204(c), 301(a), 302(a), 303(e), 401(a), 402(a), 404, 405(b), 406,
501(a), (b); 502, 503, 504, 505.
Type 745D - 1(c), 2(a), 3(b), 4(a), 102(a), 104(a), 105, 106(a), 109(a), 201(a), (b);
202(a), 203(a), 204(a), 301(a), 302(a), 303(a), 401(c), 402(a), (b); 404, 405(a), 406,
501(a), (b); 502, 503, 504, 505.

5 A-814
II - Model Vickers Viscount Type 810, Approved April 22, 1958
Type 810 is similar to Type 745D but with:  Fuselage lengthened 46 inches, rear pressure bulkhead moved aft 65 inches,
rectangular doors and additional door, starboard side aft, introduction of structural changes to cater for increased A.U.W.
Engines 4 Rolls-Royce Dart 525 or 525F Turbo propellers
Fuel Aviation Kerosene to Specification D.Eng.R.D.2482; and/or
American Specification MIL-F-5616 (JP-1); and/or
Canadian Specification 3-GP-23(a);
            OR
D.Eng.R.D.2486; and/or American Specification MIL-F-5624 B or C
(JP-4) and/or Canadian Specification 3-GP-22B;
            OR
D.Eng.RF.D. 2494.
Water-Methanol mixture parts by weight Water  62 + 2%, Meth. 38 + 2% to Rolls-
Royce Specification AEP-1-W/M Issue 4.  Specific Gravity mixture .938 - .945 at
60°F/60°F.
Engine limits
Static Sea Level Ratings
Ratings
Shaft
Horsepower
(S.H.P.)
Jet
Thrust
(lbs.)
Engine
Speed
(r.p.m.)
Maximum takeoff 1750 480 15,000
Maximum continuous  (unrestricted) 1585 420 14,500
Ground idling (unrestricted) - - - - 6500 - 7500
Airspeed limits Vmo (Maximum operating) 267 kts. at 10,000 ft.   (1)
(Calibrated air speed) Vne (Never exceed) 296 kts. at 10,000 ft.   (2)
Va  (Maneuvering) 185 kts. at 69,000 ft.   (3)
Vfe (Flaps down 0° to 20°) 200 kts.
Vfe (Flaps down 20° to Fully Down) 152 kts.
Vlo (Landing Gear Operation) 170 kts.
Vle (Landing Gear Extension) 190 kts.
Vll (Landing Light Extension) 165 kts.
(1) For values of Vmo at other altitudes, see Approved Airplane Flight Manual.
(2) For values of Vne at other altitudes, see Approved Airplane Flight Manual.
(3) For values of Va at other weights, see Approved Airplane Flight Manual.
C.G. range
Forward Aft
Weight (lbs.) % SMC Sta. % SMC Sta.
Takeoff and landing Up to 50,000 .01 (410.2) .26 (440.9)
Takeoff and landing 50,000 - 69,000 .01 (410.2 .26 (440.9)
to to
.082 419.0)
Takeoff and landing 69,000 - 72,500 .082 (419.0 .26 (440.9)
to to
.091 420.2)
Enroute Up to 57,000 .00 (408.9) .27 (442.2)
Enroute 57,000 - 69,000 .00 (408.9 .27 (442.2)
to to
.05 415.1)
Enroute 69,000 - 72,500 .05 (415.1 .27 (442.2)
to to
.061 416.5)

A-814 6
Maximum weights Landing:  Normal Landing 62,000 lbs.
Takeoff:                  69,000 lbs.
Zero Fuel Gross Weight 55,500 lbs.
NOTE: When Vickers Modification G.1226 "Introduction of stiffeners to skin panels
in way of windows between Stns. 330-700 (approx.)" is incorporated the
permissible Zero Fuel Gross Weight is 57,500 lbs.  When in addition to
Modification G.1226, Landing Gear Equipment 201(j) or 201(l) is
incorporated, the maximum takeoff weight is 72,500 lbs.
3-engine ferrying:  See NOTE 4
Minimum crew 2 Pilot and co-pilot (91)
No. of seats 56 (Passengers).  This number may be increased provided the arrangement is approved
by either the Air Registration Board or the Federal Aviation Agency.
2 (Stewards)
1 (Supernumerary flight crew)
Maximum baggage Forward upper compartment (if fitted)     550 lbs. (154)
Forward lower compartment   1900 lbs. (231)
Aft lower compartment   1700 lbs. (324)
Aft upper compartment (if fitted)   1600 lbs. (847)
Forward lower compartment (Serial No. 320 only)   1600 lbs. (218.5)
Aft lower compartment (Serial No. 320 only)   2100 lbs. (319.1)
Forward lower compartment (Serial No. 341 only)   1720 lbs. (212.8)
Aft lower compartment (Serial No. 341 only)   2340 lbs. (315.2)
Aft upper compartment (Serial 341 only)   1000 lbs. (850.0)
Aft lower compartment (Serial No. 435 only)   2240 lbs. (318)
Fuel capacity Fuel contained in four wing tanks:
2 inner wing tanks of 792 U.S. gals. each (usable) 10560 lbs. (452)
2 outer wing tanks of 348 U.S. gals. each (usable)   4640 lbs. (457)
Total wing fuel capacity of 2280 U.S. gals.
plus 8.4 U.S. gals. of unusable fuel.
When Vickers-Armstrongs Modifications G.1782 has
been incorporated the following fuel capacity is
available in two wing slipper tanks:  2 wing
slipper tanks of 305.4
U.S. gals. each (usable) plus 0.6 U.S. gals.
unusable in each tank   2036 lbs. (428)
Water/Methanol 132 U.S. gals. (2 wing tanks, 66 gals, each)   1034 lbs. (434)
Oil capacity 4.8 U.S. gals. per engine contained in the engine    38.5 lbs. (309)
Control surface movements Elevator Up 20° Down 13°
Elevator trim tab (Right) Up 12° Down 12°
Elevator Anti-Balance Tab (Left) Up 20° Down 13°
Elevator Spring Tab Up 10° Down 20°
Rudder Right 15° Left 15°
Rudder Trim & Spring Tab Right 10° Left 10°
Aileron Up 20° Down 20°
Aileron Trim Tab (Right) Up 16° Down 16°
Aileron Balance Tab (Left) Up 20° Down 20°
Flaps                            Down 47°

7 A-814
Serial Nos. eligible 320, 341, 353, 354, 355, 356, 357, 358, 359, 360, 361, 362, 363, 364, 365, 366, 389,
435.  The United Kingdom certificate of airworthiness endorsed as noted under
"Certification basis" must be submitted for each individual aircraft for which
application for certification is made.
Certification basis Type Certificate No. 814 issued under CAR 10.  Each aircraft and any replacement
parts manufactured in the United Kingdom must be designated as "import" and clearly
labeled as such in accordance with CAR 10.30.  Airworthiness certificate may be issued
on basis of a United Kingdom certificate of airworthiness signed by a representative of
the Ministry of Transport and Civil Aviation containing the following notation:  "The
aeroplane covered by this certificate has been examined and found to comply with
British Civil Airworthiness Requirements published January 1951 and with the CAR 4b
Amendment 4b-4 April 1, 1957 and 4b-7 October 17, 1957, and with the Special
Requirements notified to the Government of the United Kingdom by the Government of
the U.S.A."  (See NOTE 7)
Required equipment In addition to the relevant basic equipment required by B.C.A.R. dated January 1951,
and U.S. Special Requirements, the following items of equipment must be installed:
1(d), 2(b), 3(c), 4(b), 102(e), 104(d), 105, 106(b), 109(b), 201(g), (h); 202(g), 203(b),
204(d), 301(b), 302(a), 303(c), 401(d), 402(c), (d); 404, 405(a), 406, 501(a), (b); 502,
503, 505.
Specifications Pertinent to All Models
Datum Station 0 is located at the exterior surface of the nose skin plating on the center line of
the aircraft.  Horizontal arms shown are plus (+) to the rear of the datum.  With
radome nose installed to Vickers Dwg. No. 81028 Sht. 3 or Vickers Dwg. No. 81028
Sht. 5. Station 0 is located on the center line of the aircraft 8 ins. aft of the exterior
surface of the nose.
Standard mean chord 123 in. leading edge of S.M.C. is at +363 in. for 744, 745D
  (S.M.C.) +409 in. for 810
Max. approved operating 25,000 ft.
  altitude
Equipment:
Propellers and Propeller Accessories
1. Propellers (including hubs, blades synchronising equipment, Rotol SN A/4)
(a) Deleted
(b) Deleted
(c) Type 745D: 4 Rotol (c) R130/4-20-4/12E with RA 25842 blades 1232 lbs. (243)
Diameter:  10 ft.
Pitch settings at .7 radius:
Ground Fine +4° NOTE: When Vickers Modification
D.1708 has been installed the
ground fine Pitch setting is 0°
Flight Fine +24°
Feathered +84° 24'
(d) Type 810: 4 Rotol (c) R179/4-20-4/33 with RA 25910 blades 1483 lbs. (289)
Diameter:  10 ft.
Pitch settings at .7 radius
Ground Fine      0°
Flight Fine Low + 25°
High + 36°
Feathered + 86°

A-814 8
1. (e) Type 744: 4 Rotol (c) R148/4-20-4/21E with RA 25840 blades 1176 lbs. (242)
Diameter:  10 ft.
Pitch settings at .7 radius
Ground Fine    0°
Flight Fine + 22° 30'
Feathered + 86°
2. (a) 4 propeller spinners and extensions 4CM/54 - (744, 745D)     94 lbs. (249)
(b) 4 propeller spinners and extensions 4CM/65 - (810)     96 lbs. (288)
3. (a) 4 propeller controller units, (c) CU/48E/1 (Type 744)     75 lbs. (281)
(b) 4 propeller controller units, (c) CU/50E (Type 745D)     70 lbs. (281)
(c) 4 propeller controller units, (c) Rotol CU/84 (810)     88 lbs. (306)
4. (a) 4 propeller feathering pumps and motors C RFP/18E - (744, 745D)     50 lbs. (262)
(b) 4 propeller feathering pumps and motors C RFP/26 - (810)     73 lbs. (308)
Engines and Engine Accessories
101. Deleted
102. (a) 2 gearboxes and front drives (inbd.) Rotol PTG5/11A and PTG5/11B:
Rotol ADE/157 (Types 744, 745D)   148 lbs. (331)
2 gearboxes and front drives (outbd.) Rotol PTG5/10A and PTG5/10B:
Rotol ADE/157 (Types 744, 745D)   138 lbs. (346)
or (b) 2 gearboxes and front drives (inbd.) Rotol PTG5/11A and PTG5/11B:
Rotol ADE/251 (Type 745D)   148 lbs. (331)
2 gearboxes and front drives (outbd.) Rotol PTG5/36A and PTG5/36B:
Rotol ADE/251 (Type 745D)   146 lbs. (347)
or (c) 2 gearboxes and front drives (inbd.) Rotol PTG5/29A and PTG5/11B:
Rotol ADE/216 (Types 745D)   149 lbs. (332)
2 gearboxes and front drives (outbd.) Rotol PTG5/28A and PTG5/10B:
Rotol ADE/216 (Types 745D)   142 lbs. (347)
or (d) 2 gearboxes and front drives (inbd.) Rotol PTG5/29A and PTG5/11B:
Rotol ADE/252 (Type 745D)   148 lbs. (332)
2 gearboxes and front drives (outbd.) Rotol PTG5/37 and PTG5/36B:
Rotol ADE/252 (Type 745D)   152 lbs. (347)
or (e) 2 gearboxes and front drives (inbd.) Rotol PTG14/4 and PTG14/2B:
Rotol ADE/281 (Type 810)   189 lbs. (380)
2 gearboxes and front drives (outbd.) Rotol PTG14/5 and PTG14/1:
Rotol ADE/281 (Type 810)   189 lbs. (395)
When Vickers Modification D.1582 or D.1899 is applied to the above
gearboxes the Pressurization System blower pressure may be raised
from 8.5 p.s.i. to 11.0 p.s.i. (Types 744, 745D)
103. Deleted (included in Item 102)
104. System Fuel:
(a) 2284 U.S. gals. capacity in four wing tanks:  15 U.S. gals.   100 lbs. (412)
undrainable (excluding 1.2 U.S. gals. undrainable in engine)
(10.2 U.S. gals. unusable but drainable (Type 745D)     68 lbs. (412)
(b) When fuselage (center fuel tank is installed
System fuel:  2851 U.S. gals. capacity in four wing tanks and center tank.
15 U.S. gals. undrainable and unusable   100 lbs. (412)
(Excluding 1.2 U.S. gals. undrainable in engine)
10.2 U.S. gals. unusable but drainable (Type 745D)     68 lbs. (412)
(c) When slipper tanks (174 U.S. gals.) are installed.
System fuel:  2632 U.S. gals. capacity in four wing tanks and slipper tanks
15.0 U.S. gals. undrainable and unusable   100 lbs. (412)
(excluding 1.2 U.S. gals. undrainable in engine)
15.0 U.S. gals. unusable but drainable (Type 745D)   100 lbs. (412)
                      OR
System fuel:  3175 U.S. gals. capacity in four wing tanks,
fuselage center tank and slipper tanks
15.0 U.S. gals. undrainable and unusable   100 lbs. (412)
(excluding 1.2 U.S. gals. undrainable in engine)
15.0 U.S. gals. unusable but drainable   100 lbs. (412)

9 A-814
104. (d) System fuel:  2280 U.S. gals. capacity in four wing tanks,     56 lbs. (454)
8.4 U.S. gals. undrainable (excluding 1.2 U.S. gals.
undrainable in Engine) (Type 810)       8 lbs. (327)
(e) When slipper tanks (306 U.S. gals.) are installed.
System fuel:  2892 U.S. gals. capacity in four wing tanks and slipper tanks     56 lbs. (454)
8.4 U.S. gals. undrainable and unusable in wing tanks       8 lbs. (327)
(excluding 1.2 U.S. gals. undrainable in engine)
1.2 U.S. gals. undrainable and unusable in slipper tanks (Type 810)       8 lbs. (428)
(f) When slipper tanks (306 U.S. gals.) are installed.
System fuel:  2896 U.S. gals. capacity in four wing tanks and slipper tanks
16.2 U.S. gals. undrainable and unusable   108 lbs. (410)
(excluding 1.2 U.S. gals. undrainable in engine)
10.2 U.S. gals. unusable but drainable (Type 745D)     68 lbs. (412)
(g) 2335 U.S. gals. capacity in four wing tanks:  15 U.S. gals. undrainable
(Excluding 1.2 U.S. gals. undrainable in engine)   100 lbs. (412)
5.4 U.S. gals. unusable but drainable (Types 744, 745D, Serial No. 242 only)     36 lbs. (412)
105. System oil:  4.2 U.S. gals. residual (744, 745D)     34 lbs. (281)
(810)     34 lbs. (327)
(19.2 U.S. gals. in engine not included in weight empty)
106. 4 starters (a) Rotax C.5104 (744, 745D)   116 lbs. (281)
(b) Rotax C.5104 (810)   116 lbs. (327)
107. Fuselage - Center Tank Fuel (745D only)   600 lbs. (271)
Vickers-Armstrongs Modifications D.1312 (fuel tanks) and D1974 (fuel system)
108. Slipper tank
Vickers-Armstrongs Modification D.639
D.1692 Pacitron System, D.1819 Lightning Strike (745D)   322 lbs. (390)
Vickers-Armstrongs Modification G.1782 (810)   360 lbs. (428)
Vickers-Armstrongs Modification D.2760, D.2924 (745D)   360 lbs. (382)
109. Fuel pumps: (a) Thompson TF. 27300-13 (745D)     57 lbs. (429)
(b) Thompson TB. 60200-6  (810)     57 lbs. (475)
(c) Thompson TF. 27300-8  (744)     57 lbs. (428)
Landing Gear
201. 4 Main wheel-brake assemblies
(a) Main wheels, Dunlop AH 50420 (744, 745D)   264 lbs. (419)
(b) Main wheel brakes, Dunlop AH50091/2 (744, 745D)   310 lbs. (419)
(c) Main wheel brakes, Dunlop AH50448/9 (745D)   276 lbs. (419)
(d) Maxaret brake units Dunlop AC10944 & AC10946 (745D)     21 lbs. (419)
(e) Main wheels, Dunlop AH 50450 (745D)   240 lbs. (419)
(f) Main wheel brakes, Dunlop AH50961/2 (745D)   305 lbs. (419)
(g) Main wheels, Goodyear 9531741 (810)   211 lbs. (465)
(h) Main wheel brakes, Goodyear 9560359 (L&R) (810)   352 lbs. (465)
(i) Anti-skid brake unit generator, Goodyear 9541144 (810)       1 lb.  (465)
(j) Main wheel brakes, Goodyear 9560359, Mod 1 (L&R) (810)   380 lbs. (465)
(k) Main wheels, Dunlop AH50780 (810)   265 lbs. (465)
(l) Main wheel brakes, Dunlop AH51310/11 (810)   335 lbs. (465)
(m) Maxaret brake units, Dunlop AC13614/6 (810)   181 lbs. (465)
(n) Maxaret brake units, Dunlop AC10942 and AC10948 (Type 744)     21 lbs. (419)
202. 4 main wheel tires and tubes (the following tires and tubes or any others that are equivalent
may be installed).
NOTE: When tires type DR.2622 and DR.2624 are fitted on aircraft  operating
at weights above 60,285 lbs. the life of these tires is limited to
two re-moulds only, and the inflation pressure must be 112 p.s.i.
(a) Dunlop DR.2622 (14 ply) tires with Dunlop DT.2607 tube (745D)   298 lbs. (419)
(b) Dunlop DR.2624 (14 ply) tires with Dunlop DT.2607 tube (745D)   303 lbs. (419)
(c) Dunlop DR.2623 (16 ply) tires with Dunlop DT.2607 tube (745D)   319 lbs. (419)
(d) Dunlop DR.2626 T (16 ply) tubeless tires (745D)   328 lbs. (419)
(e) Dunlop DR.2625 (14 ply) tires with Dunlop DT.2607 tube (744, 745D)   294 lbs. (419)
(f) Dunlop DR.2626 (16 ply) tires with Dunlop DT.2607 tube (745D)   312 lbs. (419)
(g) Goodyear GA.2211 tubeless tires (810)   298 lbs. (465)

A-814 10
202. (h) Dunlop DR.11021T (16 ply) tubeless tires (810)   310 lbs. (465)
(i) Goodyear 36 x 10.75-16-1/2 (16 ply) tires with Goodyear G23017 tube (744)   320 lbs. (419)
203. 2 Nose wheels
(a) Dunlop AH50026     (744, 745D)     35 lbs. (118)
(b) Goodyear E.30760   (810)     51 lbs. (117)
(c) Dunlop AH51142     (810)     42 lbs. (117)
(d) Dunlop AH51140     (744, 745D)     38 lbs. (118)
204. 2 Nose wheel tires and tubes (the following tires and tubes or any others that are
equivalent may be installed).
(a) Dunlop DR.7165 (10 ply) tires and Dunlop FB.2 tubes (745D)     55 lbs. (118)
(b) Dunlop DX.7167 ( 8 ply) tires and Dunlop FB.2 tubes (745D)     51 lbs. (118)
(c) Dunlop DX.7168 ( 8 ply) tires and Dunlop FB.2 tubes (744, 745D)     53 lbs. (118)
(d) Goodyear GA.2204 (10 ply) Tubeless tires (810)     52 lbs. (117)
(e) Goodyear GA.2212 ( 8 ply) Tubeless tires (810)     45 lbs. (117)
(f) Dunlop DX.7169T  (10 ply) Tubeless tires (810)     50 lbs. (117)
(g) Firestone 24 x 7.25-12 (10 ply) tires and tubes     55 lbs. (118)
Electrical Equipment
301. 4 Generators
(a) Rotax B2112 (744, 745D)   168 lbs. (329)
(b) Bendix 30E/0219 (810)   264 lbs. (379)
(c) Rotax B2804     (810)   272 lbs. (379)
302. 4 Alternators
(a) Rotax N.0505 (744, 745D)   104 lbs. (349)
             (810)   104 lbs. (399)
303. Batteries
(a) 3 Varley A/24/19/25 or (745D)   113 lbs. (389)
(b) 4 Varley A/24/19/25    (745D)   150 lbs. (389)
(c) 3 Dagenite 12-ECM13-VA (810)   126 lbs. (435)
(d) 4 Varley A/24/19/25 C  (810)   150 lbs. (435)
(e) 2 Sonotone CA20        (744, 745D)   100 lbs. (389)
Interior Equipment
401. A.R.B. Approved Airplane Flight Manual for:
(a) Viscount Type 744 (DOC. Ref. No. VS.1.6)
(b) Deleted
(c) Viscount Type 745D (DOC. Ref. No. VS.1.6)
(d) Viscount Type 810  (DOC. Ref. No. VS.1.11) (See also NOTE 7)
402. Windshield Wipers, Motors and Pumps
(a) Wipers, 2 Dunlop ACM 17096 (Left and Right) and
1 Dunlop ACM 17638 (Center) (744, 745D)
(b) Motors, 2 Dunlop AC  13208 (744, 745D)
(c) Wipers, 1 Dunlop ACM 19890 (Left) (810)     1.5 lbs. (62)
1 Dunlop ACM 19892 (Right) (810)     1.5 lbs. (62)
(d) Pump, 1 Dunlop AC  14372 (Double) (810)   20 lbs. (43)
403. Deleted
404. Hydraulic Fluid in System and Reservoir, Mineral Oil
DTD 585 or equivalent (744, 745D)   86 lbs. (240)
(810)   31 lbs. (178)
405. Automatic Pilot
(a) Bendix PB.10A (3 servos + elevator trim servo)
(1) [a] Servo stall forces measured at pilots controls:  (745D)
Elevator:  Nominal - 15 lbs.
Aileron:   Nominal - 15 lbs.
Rudder:    Nominal - 29 lbs.
[b] Corresponding servo stall torques measured at servo:  (745D)
Elevator: Nominal - 30 lbs. -ft.
Aileron:  Nominal - 25 lbs. -ft.
Rudder:   Nominal - 16 lbs. -ft.

11 A-814
405. (a) (1) [c] Servo stall forces measured at pilots controls:  (810)
Elevator:  Max. -  53 lbs. Min. - 39 lbs.
Aileron:   Max. -  23 lbs. Min. - 16 lbs.
Rudder:    Max. - 112 lbs. Min. - 82 lbs.
[d] Corresponding servo stall torques measured at servo:  (810)
Elevator: Max. - 44 lbs. -ft. Min. - 32 lbs.-ft.
Aileron:  Max. - 34 lbs. -ft. Min. - 23 lbs.-ft.
Rudder:   Max. - 44 lbs. -ft. Min. - 32 lbs.-ft.
(2) Maximum speed for auto-pilot operation is Vmo C.A.S.
(See A.R.B. Approved Airplane Flight Manual for altitude loss during auto pilot malfunctions)
(b) Collins AP-101 (3 servos + elevator trim servo)
(1) [a] Servo/torque measured at servo
Elevator: 12 lbs. -ft.
Aileron: 12 lbs. -ft.
Rudder: 12 lbs. -ft.
Elevator trim:   3.3 lbs. -ft.
(2) Maximum speed for auto-pilot operation is Vmo C.A.S.
(See A.R.B. Approved Airplane Flight Manual for altitude loss during auto-pilot malfunctions)
406. Pre-stall warning system
(a) Stickshaker, Safe Flight 20102
(b) Detector, Safe Flight 180A BT
De-Icing Equipment
501. (a) Wings - Inner, V.A. Dwgs. 72482 Sht. 3, 4 (744, 745D)
Inner, V.A. Dwgs. Left 81082 Sht. 9 or 81382 Sht 2 (810)
Right 80282 Sht. 137 or 81282 Sht 1 (810)
(b) Inboard Nacelle V.A. Dwgs. 70082 Shts. 23, 24 (744, 745D)
Inboard Nacelle V.A. Dwgs. 81082 Shts. 5, 6, 7, 8 (810)
502. Fuselage: V.A. Dwgs. 72482 Sht. 7 (744, 745D)
V.A. Dwgs. 80382 Sht. 3 (810)
503. Windscreen:  V.A. Dwg. 70182 Sht. 25 (744, 745D)
Nesa Glass (810)
504. Windscreen Spray Pump Dunlop AC12302 (744, 745D)     3 lbs. (110)
505. Propeller and Engine Intake de-icing Electrical Equipment (744, 745D) 181 lbs. (363)
less equipment on propellers (810) 190 lbs. (409)
602. Janitrol Combustion Heater 21C38 V.A. Dwg. 72455 Sht. 45 (744, 745D)
603. Deleted November 14, 1956
604. Fuel jettisoning system Vickers-Armstrongs Modification D.1720 (745D only)   87 lbs. (403)
605. Air Steps (Applicable to 745D only)
(a) Vickers-Armstrongs Modification D.1273 "To make provisions     3 lbs. (206)
for Air Step Installation"
(b) Vickers-Armstrongs Modification D.1675 "Introduction of Air Steps” 285 lbs. (392)
(c) Vickers-Armstrongs Modification D.1846 "To Introduce Propeller Brake”   15 lbs. (392)
606. Freon Refrigeration System Vickers-Armstrongs Modification D.2149 (745D only) 590 lbs. (457)
NOTE 1. Current weight and balance report, including list of equipment included in certificated weight empty, and loading
instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter
(except in the case of air carrier operators having an approved weight control system).
NOTE 2. Deleted May 16, 1958.
NOTE 3. Information essential to the proper maintenance of the aircraft, including retirement times of the critical parts, is
included in the Vickers-Armstrongs (Aircraft) Ltd., Viscount 744, 745D and 810 Instruction Manual, provided
with each aircraft.
NOTE 4. Ferry permits may be issued to Models 745D and 810 aircraft on which one engine is inoperative, with its
propeller removed or feathered under the following conditions:
(1) Operation of aircraft shall be in accordance with pertinent limitations contained in the applicable portion of
the Approved Airplane Flight Manual, pertinent appendices, and existing instructions.
(2) (a) Maximum takeoff weight 55,000 lbs. (745D) *

A-814 12
(b) Maximum takeoff weight 65,000 lbs. (810)  *
745D 810
(3) C.G. range for Forward C.G. 0.116 S.M.C. (377.25) (423.25)
landing and takeoff Aft C.G. 0.19  S.M.C. (386.3) (423.3)
*(Except when limited by runway length specified in approved Airplane Flight Manual).
NOTE 5. Specification for Model 745, approved November 7, 1955, has been deleted since aircraft of this model are no
longer on U.S. register.
NOTE 6. Model 744 Approved June 13, 1955.  Deleted from Specification Rev. 8 May 16, 1958.  Reinstated April 22,
1964.
NOTE 7. The Special Requirements include that for a fuel jettison system in accordance with CAR -4b. 437.  Compliance
with FAR 25.1001(b) and (c) is an acceptable alternative and is identified in the Doc. No. VS.1.11 Flig ht Manual
by Amendment P/23.  Amendment P/23 is required for operation of airplanes which have the alternative
configuration.
.....END.....
```

## ADs (128, first 50, in force first)

- [AD 98-23-13](https://openairdocs.org/ad/98-23-13): Nacelle Support Structures · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Dec 17, 1998
- [AD 98-12-17](https://openairdocs.org/ad/98-12-17): Struts · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jul 1, 1998
- [AD 95-22-08](https://openairdocs.org/ad/95-22-08): Fuselage Component Limits · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Nov 27, 1995
- [AD 95-19-11](https://openairdocs.org/ad/95-19-11): Horizontal Stabilizer · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Oct 20, 1995
- [AD 95-15-02](https://openairdocs.org/ad/95-15-02): Inspect "W" Frame Socket Fittings · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 23, 1995
- [AD 95-15-08](https://openairdocs.org/ad/95-15-08): Inspect for Corrosion of Tailplane Assembly · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 23, 1995
- [AD 95-14-08](https://openairdocs.org/ad/95-14-08): Nose Landing Gear · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 18, 1995
- [AD 95-03-04](https://openairdocs.org/ad/95-03-04): Nose Wheel Steering · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Mar 20, 1995
- [AD 94-26-16](https://openairdocs.org/ad/94-26-16): Taper Plugs & Split Bushings · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Mar 1, 1995
- [AD 94-26-14](https://openairdocs.org/ad/94-26-14): Inspect For Cracks In Chassis · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Feb 3, 1995
- [AD 92-22-03](https://openairdocs.org/ad/92-22-03): Rear Pressure Bulkhead · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Dec 3, 1992
- [AD 92-14-06](https://openairdocs.org/ad/92-14-06): Elevator Lower Skins · Vickers-Armstrongs Viscount 810. Effective Aug 20, 1992
- [AD 92-11-05](https://openairdocs.org/ad/92-11-05): Upper Boom of Wing Rib · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jul 9, 1992
- [AD 92-09-04](https://openairdocs.org/ad/92-09-04): Shuttle Valve Elbow Connection · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jun 2, 1992
- [AD 91-26-01](https://openairdocs.org/ad/91-26-01): Elevator Balance Weights · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Mar 23, 1992
- [AD 91-18-06](https://openairdocs.org/ad/91-18-06): Inspect Wing Flap Guide Rails · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Sep 23, 1991
- [AD 91-14-16](https://openairdocs.org/ad/91-14-16): Wing Break-Joint · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 9, 1991
- [AD 91-14-18](https://openairdocs.org/ad/91-14-18): Wing Spar Upper Boom · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 6, 1991
- [AD 91-11-12](https://openairdocs.org/ad/91-11-12): Doors · Vickers-Armstrongs Viscount 810. Effective Jul 1, 1991
- [AD 88-14-04](https://openairdocs.org/ad/88-14-04): Wing Surface · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Sep 6, 1988
- [AD 87-23-03](https://openairdocs.org/ad/87-23-03): Wing Surface · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Dec 9, 1987
- [AD 87-22-04](https://openairdocs.org/ad/87-22-04): Landing Gear · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Nov 13, 1987
- [AD 86-16-09](https://openairdocs.org/ad/86-16-09): Hydraulic Cut Out Valve · Vickers-Armstrongs Viscount 810. Effective Sep 8, 1986
- [AD 84-07-03 R1](https://openairdocs.org/ad/84-07-03-R1): Nose Landing Gear · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Mar 24, 1986
- [AD 86-02-05](https://openairdocs.org/ad/86-02-05): Hydraulic System Cut Out Valve · Vickers-Armstrongs Viscount 744 and Viscount 745D. Effective Feb 3, 1986
- [AD 85-14-08](https://openairdocs.org/ad/85-14-08): Alternators · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 16, 1985
- [AD 85-12-06](https://openairdocs.org/ad/85-12-06): Wheel Brake Unit · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jul 15, 1985
- [AD 84-19-07](https://openairdocs.org/ad/84-19-07): Hydraulic System · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Oct 22, 1984
- [AD 80-21-51](https://openairdocs.org/ad/80-21-51): Elevator Control System · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 27, 1981
- [AD 78-23-13](https://openairdocs.org/ad/78-23-13): MLG Shock Absorber Struts · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Dec 18, 1978
- [AD 77-15-07](https://openairdocs.org/ad/77-15-07): Aileron Control Rods · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 22, 1977
- [AD 76-19-01](https://openairdocs.org/ad/76-19-01): Elevator Control Mechanism · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Oct 15, 1976
- [AD 75-27-02](https://openairdocs.org/ad/75-27-02): Propeller Feathering · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jan 19, 1976
- [AD 75-26-12](https://openairdocs.org/ad/75-26-12): Torque Shaft Assemblies · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jan 14, 1976
- [AD 75-17-01](https://openairdocs.org/ad/75-17-01): Aileron Control In-Flight · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Sep 1, 1975
- [AD 65-18-03](https://openairdocs.org/ad/65-18-03): Engine Mount Assembly · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 27, 1975
- [AD 75-17-02](https://openairdocs.org/ad/75-17-02): Cable Assemblies · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Aug 15, 1975
- [AD 75-13-06](https://openairdocs.org/ad/75-13-06): Horizontal Stabilizer · Vickers-Armstrongs Viscount 744 and Viscount 745D. Effective Jun 6, 1975
- [AD 73-12-12](https://openairdocs.org/ad/73-12-12): Power Plant Fire Extinguisher · Vickers-Armstrongs Viscount 810. Effective Jul 6, 1973
- [AD 73-12-07](https://openairdocs.org/ad/73-12-07): Nacelle Tubes And End Fittings · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jul 5, 1973
- [AD 73-12-04](https://openairdocs.org/ad/73-12-04): Airsteps Hinged Fairing Link · Vickers-Armstrongs Viscount 810. Effective Jul 1, 1973
- [AD 72-18-09](https://openairdocs.org/ad/72-18-09): Control Rods And Electrical Systems · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Sep 6, 1972
- [AD 71-20-08](https://openairdocs.org/ad/71-20-08): Placard On Cabin Pressurization · Vickers-Armstrongs Viscount 810. Effective Aug 13, 1971
- [AD 71-19-04](https://openairdocs.org/ad/71-19-04): Placard On Cabin Pressurization · Vickers-Armstrongs Viscount 744 and Viscount 745D. Effective Aug 6, 1971
- [AD 71-08-04](https://openairdocs.org/ad/71-08-04): Undervoltage Sensing Unit · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective May 8, 1971
- [AD 71-01-02](https://openairdocs.org/ad/71-01-02): Flap Drive Motor Assembly · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Jan 21, 1971
- [AD 67-02-04](https://openairdocs.org/ad/67-02-04): Accessory Gear Boxes · British Aerospace Argosy AW.650 Series 101, Accessory Gear boxes, G-159 and 1 more. Effective Jun 23, 1970
- [AD 70-08-04](https://openairdocs.org/ad/70-08-04): Cabin Blower Drive Quill · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective May 14, 1970
- [AD 70-05-02](https://openairdocs.org/ad/70-05-02): Engine Breather Pipes · Vickers-Armstrongs Viscount 744, Viscount 745D and Viscount 810. Effective Mar 23, 1970
- [AD 70-04-05](https://openairdocs.org/ad/70-04-05): Automatic Feathering System · Vickers-Armstrongs Viscount 744 and Viscount 745D. Effective Mar 21, 1970

All 128: https://openairdocs.org/tcds/A-814/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Vickers VISCOUNT 744](https://openairdocs.org/model/vickers-viscount-744): 0 aircraft (registry code 9470204)
- [Vickers VISCOUNT 745-D](https://openairdocs.org/model/vickers-viscount-745-d): 0 aircraft (registry code 9470401)
- [Vickers VISCOUNT 810](https://openairdocs.org/model/vickers-viscount-810): 0 aircraft (registry code 9470602)

## STCs approved under this data sheet (23)

- [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc
- [STC SA392SW](https://openairdocs.org/stc/SA392SW): Installation of Collins 137Y-1A Doppler Antenna and installation of McMillan C-1681 radome. Associated Air Center, Inc. - c/o CT Corporation System
- [STC SA2016NM](https://openairdocs.org/stc/SA2016NM): Installation of a de-icing system on the Rolls Royce P/N RK29954A engine inlet cowl. ROBERT W. MURRAY
- [STC SA302WE](https://openairdocs.org/stc/SA302WE): Incorporate a de-icing system (as manufactured by applicant) externally on Rotol propeller spinner as an alternate to Dowty Rotol internal elements. If applied to original spinner, Montgomery Systems Tech., Inc. P/N 72196-2 will apply. If applied to a new aluminum nose spinner P/N 72196-1 will apply. Dowty Rotol Service Bulletin Section 61-170 pages 1 and 2 outlines a revised spinner de-icing system. This is a Napier external system. Approval of the A.R.B. is indicated. (Continued on page 3). ROBERT W. MURRAY
- [STC SA1-571](https://openairdocs.org/stc/SA1-571): Installation of flight data recorder.. United Airlines Inc
- [STC SA192CE](https://openairdocs.org/stc/SA192CE): Installation of Hoskins Supplemental Model A High Intensity Wing Tip Lights, Model C Tail Light with or without Models 2 High Intensity Fuselage Lights.. BF Goodrich Aerospace
- [STC SA399SW](https://openairdocs.org/stc/SA399SW): Installation of APU. Signature Flight Support Corporation
- [STC SA400SW](https://openairdocs.org/stc/SA400SW): Installation of interior arrangement.. Signature Flight Support Corporation
- [STC SA661WE](https://openairdocs.org/stc/SA661WE): Fuselage fuel tank, 755 gallon.. Rogerson ATS
- [STC SA376SW](https://openairdocs.org/stc/SA376SW): Interior modification.. Ward Intl Aircraft Service
- [STC SA416SW](https://openairdocs.org/stc/SA416SW): Interior modification.. Ward Intl Aircraft Service
- [STC SA407SW](https://openairdocs.org/stc/SA407SW): Installation of the Hamilton aural overspeed warning system type HF-100VM.. Hamilton Instruments Inc
- [STC SA379SW](https://openairdocs.org/stc/SA379SW): Installation of the Hamilton Co Type HF-V overspeed warning system.. Hamilton Instruments Inc
- [STC SA1394](https://openairdocs.org/stc/SA1394): Doppler navigation antenna.. AiResearch Aivation Service Co
- [STC SA15-06](https://openairdocs.org/stc/SA15-06): Flight Recorder 109C.. Lockheed Aircraft Service Co
- [STC SA261EA](https://openairdocs.org/stc/SA261EA): New cabin-to-cockpit door.. United Air Lines Inc
- [STC SA4-1395](https://openairdocs.org/stc/SA4-1395): Modification of interior.. AiResearch Aivation Service Co
- [STC SA4-357](https://openairdocs.org/stc/SA4-357): Two Aircraft Radio Corp. ADF loops and sense antenna masta and lead-in insulators.. Bayaire Avionics Inc
- [STC SA592WE](https://openairdocs.org/stc/SA592WE): Mach warning system.. Continental Airlines Inc
- [STC SA657WE](https://openairdocs.org/stc/SA657WE): AiResearch GTP30-54 auxiliary turbine power unit for ground operation only.. Qualitron Aero Inc
- [STC SA83EA](https://openairdocs.org/stc/SA83EA): Distance measuring equipment. (Applicable to aircraft which have incorporated Vickers-Armstrong Modification D.1236.). United Air Lines Inc
- [STC SA905WE](https://openairdocs.org/stc/SA905WE): Flexible hose assembly.. Resistoflex Corporation
- [STC SA1-411](https://openairdocs.org/stc/SA1-411): Goodyear SK306-1204 revision E propeller blade iceguard on Rotol propeller R130/4-20-4/12E with blades RA25842.. United Air Lines Inc

---
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