AIRCRAFT MIG-21F-13 TECHNICAL DESCRIPTON VOLUME IV SPECIAL EQUIPMENT R

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78-03066R000200020001-6
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 418
• Document Creation Date: December 22, 2016
• Document Release Date: April 18, 2012
• Sequence Number: 1
• Publication Date: January 1, 2000
• Content Type: REPORT

Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
.':)C~...KC 1
NO FOREIGN DISSEM, / NO DISSEM ABROAD / CONTROLLED DISSEM5QX1-HUM
AIRCRAFT
MiG - 21 F -13
TECHNICAL DESCRIPTION
VOLUME IV
SPECIAL EQUIPMENT
SECRET I ".F??
NO FOREIGN DISSEM / NO DISSEM ABROAD / CONTROLLED DISSEM
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N. LUG _. 21F - 13
TEGITNICAL DFSCRTPTION
`01 UN:E; IV
SPECTAI: EQUIPMENT
NO FORETGtd DISSE,/d:) -ILL S'';, ABROAD/(,OFITROLL1;0 J) ;;cam
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Figure 1. The MiG-21F-13 Aircraft
(Front View)
?Kr. wo.1P'r t Si,
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4 NO FOREIGN DISSEM/NO DISSEM ABR6ADICONTEULLED S 1
The MIG-21F-13
Aircraft
Technical Description
Book IV
Special Equipment
Page 4
Introduction
The Mi. -21F-13 aircraft is equipped with modern inst:~.,,;Jcnts and radio
equipment, making it possible for the aircraft to carry out its mission in
all kinds of weather, day or night.
The compact positioning of the instruments in the cockpit provides
sufficient convenience for pilot operation. Control of the electrical
aggregates, of the instruments, and of the radio equipment, is, in the
main, by remote means.
All of the aircraft's special equipment has been divided into groups
as follows:
electrical equipment;
radio equipment;
instrumentation;
oxygen equipment;
photographic equipment.
Each of these groups carries out a definite, independent function; but
at the same time, each group is closely connected with the others.
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The aircraft's electrical equipment consists of the power source, the
equipment using the power, and the electrical network.
The electrical equipment serves to ensure operation and checking of
the operation of various of the aircraft's systems and aggregates.
The aircraft's radio equipment includes the radios used for communications,
the blind landing equipment, including the automatic radio compass, the
Pale .>
receiver marker installation and the radio altimeter, the responder in the
recognition radar system, and the range-only radar, which functions in
conjunction with the aerial gunnery sight.
The radio equipment provides the means for solving various .:f the
problems conce.:rit.d with radio communications, recognition, sig_. ..ng, piloting,
navigation, et.c.
The aircraft's instrumentation includes the piloting and naviga._..ng
instruments, the instruments for checking the power plant, and the instruments
for checking the operation of the individual aggregates and systems.
The installed instrumentation permits flying day or night, in all kinds
of weather at any altitude up to service ceiling; ensures ~.;entation in
space and along the course; and provides the means for chec:.cig the
operation of the power plant and other aircraft systems. The instrumentation
ensures correct use of the flight and tactical capabilities of the aircraft.
The aircraft's oxygen equipment consists of the KKO-3 outfit with oxygen
excess pressure in the hermetically sealed helmet and in the pneumatic system
for the pressure equalizing flight suit, regulated automatically according
to flight altitude.
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iY FOREIGN DiSu1:.ON0 DISSl AERCAD/CQ dTt:JLui.j1LK..'ry:
xcy cr equipment serves to provide the necess r y environ7ant for
wage 6
akin safeguards his capacity to function bot while at hi-h
co and when being ejected.
photographic equipment in the aircraft cons s s of the AFA-39 aerial
a1. the SSh-45-I-10O-0S gamera ? un.
aerial camera is designed for carr-ring )UL aerial reconnaissance.
h-45-I-100-0S aerial camera gun is designed ;,o check sightin.:-
vy. Materials on the SSh-45-I-100-OS are coma: .led in Book 11, "Armament,
s the technical description.
book on technical description consists of five chapters, in the
in, sequence:
Cnapter l - Electrical Equipment
apter 2 - R,,. ,u Rquipn,ent
gaiter 3 - Instrumentation
;apter 4 - Oxygen Equipment
;ter 5 - Photographic Equipment
took contains information needed to master and overate the aircraft,
ar as the special equipment is concerned, and i, also provides
c;i>>ns for the installation and the removal of t,e most imUortant of
.ent aggregates.
ornation on the aggregates manufactured by spec _alized enverprises is
ed in orief in order that the reader can become acquainted with them.
information on the design and the operation c" these aggregates ;ut
:.=.W-?d from the descriptions and instructions prc : ided for them by t!-:e
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The main feeder circuits, as well as circuits which are grouped in the
aircraft are added to the book in the form of an appendix (in a separate
portfolio) for convenience in handling.
Page
8
Chapter I
Electrical Equipment
1. General Information
The electrical equipment in the aircraft is an assembly of electrical
devices, connected in groups by type of function and interconnected by
electric cables. These groupings form the various electrical systems in
the aircraft.
The aircraft's electrical equipment consists of the power source, the
equipment using the power, and the electrical network. It includes the
protective devices, switching apparatus, electric wiring and electrical
connectors.
The chief source of electric power is the starter-generator, type GSR-ST-
12000VT, connected to the electrical network installed in the aircraft. The
GSR-ST-12000VT is driven by the aircraft power plant and is the source of
supply after the engine is started.
When the aircraft is on the ground the power supply is provided from the
airfield when it is time to start the engine. At this time the starter-
generator is a power consumer.
Page }
Two storage battcriea, type 15-STsS-45, serve as reserve power sources
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,.u .%7Y 1'sitstV J `O I'j;Lhi1 AH-R11',.i)/\, it Ttiil`'.'v J~ 1.,.h: .MSC M
: ,c ground in other than airsicid condit .rs.
zt hull is ,he common negative for aa.i1 e electri wal devices.
_? 1,0: fror the sources of supply i_s f,, :o the chnsumi. -.g
has a sp*C-_ai receptacle .o take tzve a . z` eld power sup )i1T
ypes t O-(5uA, PO-500A, and PT-500'Ts, st ay 115 vilts, ,C
volts direct current.
em the sources is fed to the equipmerr~: re( :.ring it.
e'trical energy in the aircraft are;
uio and radar installations:
gregates in the cannon and rocket ins-aailt ions;
A:`;E-5ND air gunnery sight, and the SIV-` 2 it ::'rated vie inder.
~c .erratic diagram of electric power distribud e,: n to
;.suming devices
tem aggrega,,es;
s for regulation cockpit air temperature;
s for the fire protection equipment..;
for clocks. pilot tube and storage oattr ?ies;
and lighting apparatus;
i
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T T
(Append page 9b here)
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piloting and navigation instruments;
instruments for checking engine operation;
pump station and electrical mechanism for trim effect;
aggregates in the hydraulic system, the air system, landing
gear, wheel brakes, and others.
The bus bar of the power supply unit, connected to the starter-generator,
to the storage batteries, and to the receptacle taking the airfield power
supply, is used to distribute electric power. Figure 3 shows the devices
using electricity.
The power. supply unit (Figure 4+) furnishes power directly for certain
uses and is connected to:
(TEXT CONTINUES IMMEDIATELY FOLLOWING LEGEND FOR FIGURE 3)
Figure 3. Legend
1. Starboard forward switchboard
2. Bus bar number 2
3. Bus bar number 1.
4. Starboard after switchboard
5. Bus bar number 3
6. RVU MRP 5A (22R)
7. Emergency transfer switch for converter 5A (7R)
8. AGD 5A (1 N )
9. KSI 1OA (ION)
10. RVU MRP 5A (34R)
11. Radio oil pressure 5A (3R)
12. SRO 10A (l9R)
13. Floodlights 25A (41S)
14. Sight. 10A (2P)
15. Sight, Sight heater 20A (1P)
16. SRD 5A (6R)
17. SIV-52 5A (l6P)
18. RS 1OA (11+B)
19. SS heaters 20A (28B)
20. Cannon 10A (25P)
21. FKP 5A (19P)
22. SS Silament 10A (29B)
23. SS launch lOA (30B)
24. AFR 10A (3F)
25. (blurred) 13A (l7M)
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26. (blurred) (9B)
27. (blurred) (68M)
28. (blurred) 5A (87M)
29. IR, SS, RS (blur) 5A (17P)
30. Signal suspension RS APU 5A (1B)
31. IRK 15A (5R)
32. (blurred) 5A (31E)
33. (blurred) 5A (2S)
34. (blurred) panel 5A (22S)
35. (blur) booster system 5A (83M)
36. UPR landing gear (blur) 5A (34M)
37. UFO (blurred) (35s)
38. (blurred) 5A (IT)
39. Cone interlock (blur) 10.A (33M)
40. IORM parachute 5A (46M)
41. Recorder (blur) (37K)
42. Heater elements for clocks (sym. DT), heater element DUAS (gym. 9T)
43. Heater TP156 10A (11T)
44. Clock heaters 20A (7T)
45. Heater element TP-156 (sym. lOT)
46. Relay =[e-53PD (sym. 18R)
47. Relay TKYe-56PD (sym. 32 R) for emergency transfer switch supplying IS,
ARK, PT, DIM, radio
48. AGD-1 blocks (sym. 3N and 24N), relay (sym. 19N)
49. KSI course system blocks (sym. 25N, 18N, 9N, and 7N), relay (sym. 16N)
50. Relay (sym. 27R). RVU, MRP, MRP-56P marker radio receiver installation
connections
51. Relay for connecting RSIU-5 (sym. 9R) communications radio set,
ABV block (sym. 10R), and amplifier UD-2M series 5 for RSIU set
52. Filter from SRO
53. MPRF-1A landing and taxying lights (sym. 43S and 449), relays (sym. 15S,
48s and 49s)
54. ASP-5ND block No 1 (sym. 12P), damping push button (sym. 8P), potentio-
meter (sym. 15P), ASP-5ND block No 7 (sym. 16P) (TN: Block No could be "2")
55. F-14A filter (sym. 4P), block No 1 (sym 12P), potentiometer (sym. 15P)
56. Relay for connecting SRD (sym. 8R), SRD supply block
57. Relay (sym. 48R) for triggering converter (sym. 15R) and delivery of
115 volts AC to SIV (sym. 44P) supply block
58. Indicator lights (sym. 12B, 13B), PUS-36 (sym. 16B, 17B), projectiles
59. K-13 missile heater elements
60. Electrical firing for cannon (sym. 27P), cannon readiness light
(sym. 37P), electropneumatic valve (sym. 40P), relay (sym. 38P)
61. VM-2 timing mechanism (sym. 43P ), SSh-45-i-100-(5 (sym. 42P)
camera gun
62. Filament circuits for K-13 and EPU-13 in APU-13 launching system
63. Launch circuits, K-13
64. Aerial photographic equipment (sym. 1F and 2F)
65. MU-100AP electric motor for moving seat
66. DE-57 (sym. 11B, 4OB) racks for K-13 missile, 5DE-56Ye rack
67. ARU-3V, series 2 automatic device (sym. 73M), control block
(sym. 52M)
68. ARU-3V, series 2 control block (sym. 52M)
69. Relay (sym. 26P, 28P, 37B, 41P, 4B)
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i. '..aVJ (syr 24B, 25B, 7B)
rot panel, ARK-10 automatic radio compass
plL T-?, T for external landing
r na'rigation lights (sym. 19S, 20S, 21S), lights
indication (sym. 12S, 13S, 145), PPS-2 (sym. I LS), lamp (sym. loS)
?lectro-hydraulic transfer switches (sym. 122M, 32 'A) for speed
:aak.e control
:,clays (sym. 84m, 85M), indicator lights (sym. 43K, 44K), relay
45K)
lectro-hydraulic valves (sym. 36M, 44m) for loweri,1g landing gear
u d a laps
'rater element for sealed helmet, lamps (sym. 37S, kOS), ARUFOSh-45
14T),
C ,ckpit air temperature regulator (sym. 3T), relay clock (sym.
_.,?ctricai air control (sym. 4T)
blurred) ettisonin
lectro-pneumatic valves (sym. 130M, 132M) for streaming and g
1-a:, chute
_2-717A (sym. 39K) barometric speed indicator (baro3pidograf), K2-717A
syn. 38K) filter
,L ctro-pneumatic valves 695000/A (sym. 52M, 6T), f -re extinguisher
23K) 250 {sy ,. I1K)
Trddicator transmitters (sym. 1K, 15K), 2EDM-
/;-5OD (sym. 12M) contactor, indicator light (syn. .>K)
2121-50D (syn. 17M) contactor, indicator light (sym. -K)
??'lectro-pneumatic valves (sym. 23M, 92M, 22M) for r-leasing the landing
;r whee.i. brakes, relay (sym. 93M, 134M) celcrator,
Terminal switches for KAF-13D (syn. 97M) hydraulic 'A
==..rburetor (sym. 5Ye), KVC-1 (sym. 151M), GA-164 (s;m. 153M)
Up-53 (sym. 6N), "generator off" indicator light T--6 display (sym. 47S),
y-lay (sym. 11F and 33E), KLSRK-45 (sym. is)
K?F-15A (Sym. 4M), AV7-44-5 (sym? 1M), winding "Sh" GSR-ST-12000VT and
other start aggregates
r44-50D contactor (sym. 6M)
Relays 3V, R10, R1.3, 3 of box (sym. 4M), valve (sym, 63M)
_re extinguishing equipment, deicer 5A (9K)
ED Hydraulic indicator (blur) 5A (13K)
Pump No 1 5A (14M)
'=limp No 3 5A (9M)
Automatic wheel braking 10A (20M)
Afterburner 10A (P91 ,I)
obliterated) 5A (34K)
Start aggregates 25A (1 Ye)
Pump No 2 5A (5M)
Start (blur) 10A (31Ye)
._,,s bar number I
Port switchboard
5TsS - 45
rower unit bus bar
Di' -400D
1i
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108. GSR-ST-12000VT
109. From ASS (sym. lYe)
107A. PO-500A (sym. 15R) converter
108A. Box for delivery of signals KVS-l (sym. 151M)
109A. Pump 495A (sym. 11M) 3rd group of fuel tanks
110. Pump 422A (sym. 16M) 1st group of fuel tank
ill. Pump 495A (sym. 8M) 2nd group of fuel tanks
112. PO-750A (sym. 1R) converter
113. PO-750A (sym. 2R) converter
114. Pump station NP-21T (sym. 79M)
115. Contactor (sym. 70M) for cutting in pump station NP-2T
116. Electrical mechanism MP-100M for loading mechanism for T-4 display
lamp (sym. 59M)
117. Electro-hydraulic valve (sym. 81M) for cutting out stabilizer booster
118. Electro-hydraulic valves (sym. blurred) for cutting in (blur) booster
(blur)
119. PT-500Ts converter (sym. 2N)
120. MPRF-1A (sym. 43S and 44S) landing and taxying lights
the pumps in the 1st, 2nd, and 3rd groups of fuel tanks;
converters PE-750A and PO-500A
pump station NP-27T;
the hydraulic and electrical valves for controlling the boosters;
the stabilizers and ailerons;
the box containing the automatic device for the afterburner, KAF-13D;
the MP-100M electrical mechanism for the trim effect loading mechanism;
the MPRF-lA floodlight;
the Pr-500Ts converter..
Page 12
.Figure 4. Power Supply Unit Schematic
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Key to Figure 4
1. Conductor connector plug from relay box
2. Relay box
3. Bracket
4+. KM-100D contactor
5. KM-50D contactors
6. Panel with inertial fuses
7. DMP-1100D
8.. KBM-31 condenser
9. TS-9M transforrrer
10. IP-15 inertial fuse
11. Socket for measuring (one word blurred) from generator
12. Inertial fuse
13. Inertial fuse
14. Ammeter shunt
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"he remainder of the electric power supplies the four distribution busses
un the switchboards for the port and starboard consow.es in the cockpit.
The starboard console has two switchboards, one ::onward, and one aft.
Two bus bars No 2 and No 4, are installed on the for:rard switchboard. One
jus, No 3, is installed on the after, or rear, switc.:board.
The port console has one switchboard. Bus bar N;, 1 is installed on this
T,vt tchboard .
us bar No 2 provides the supply for the MI, ;;1 , floodlights (sym. 43S,
t5), relay (sym. 32R), the emergency converter switc:. (sym. 1R,. 2171) and the
:?e+ay (sym. 18R) for energizing the RVU and NRP in t1t, blocks for the RSIU-5G,
SRO-1 and 1YRP-56P and the relay (sym. 9R, 27R) for cutting in the 115 volts,
+,)0 cycles AC for the RSIU-5G, RV-U and NRP-56P, and for the oil pressure
gna1.
Bus bar No. 4 provides the supply to the relay (sy'n. 48R, 3R) for cutting
.u e 115 volts, 400 cycles AC, to the SIV-52 infrared viewfinder and the
"aage-only radar, as well as to the ASP-51U) sight, th- cannon, the FKP, RS, and
K-13 homing missiles ("SS").
Tus bar No 3 provides the supply to the cone and ':he apparatus for inter-
_.cking the throttle, controlling the lamps in the T-(: display, the cockpit
ie-sting appliances, the ANO, the portable light, as well as the ARUFOSh
ghts, for heating the KKO, for the flap control aggregates, for the landing
,ear and the drag chute, for landing gear
Page 15
3osition indication, for the speed brake control aggregates, for the ARK-10
.nits, as well as the firing button (syn. 18P), the APJ control aggregate,
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the relay (sym. 81M, 85M) for disconnecting the boosters from the hydraulic
system, and the aggregates for checking pressure in the main and booster
hydraulic systems.
Bus bar No 1 provides the supply for the engine start aggregates, for
signalling when the generator is cut in, for the EUP-53, KLSRK, the after-
burner regime aggregate, the fire extinguishing equipment aggregate, the
aggregate for measuring the pressure in the hydraulic system, for signalling
levels in the fuel tank in use, as well as in the suspended tank, for the
pumps for the lst and 3rd groups of fuel tanks, for the clock heating element,
and'for the aggregates which automatically release the wheel brakes.
Electric power consumers are grouped according to the type of operation
they perform.
The aircraft equipment falls into the following functional groupings:
power;
engine operation and control;
cone control, flap control, air bypass, and throttle interlocking;
fuel;
aircraft control:
Page 16
means for taking of and landing;
lighting equipment;
heating;
air navigation;
armaments;
radio supply.
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au 1'U?J11GN DISSEM/NO DISSEM Ala. L DTS,cTV
IT. :lectrical Network
General Information
The electrical network installed in the aircraft is a single-wire system,
wVh the negative side grounded to the airframe, and the positive side led
? the aggregates through cables insulated from the airframe.
the appliances supplied from the F-14A and F-lJV'I' electrical filters are
nected to the internal network by a two-wire syster,?.
2. Type, guage, laying and plugging in of cables
The electrical network installed in the aircraft i.s, for the most part,
dAe up of type BPVL and BPT cables of various guages (0.5 - 70.P mm2),
pending upon the amount of current required by t:he .;,gregate.
The BFVL cables in the aircraft are color-coded a_ follows:
ED - armaments electrical systems;
jLUE - radio equipment electrical system;
14HITE - electrical equipment electrical syste.,.-..
VL cable is not heat resistant. It is used for installations in zones
d=_--ere temperatures are normal, that is, in the cockpit, above and below the
.waling section of the fuselage, upper (two words obl",terated) equipment,
1g, fin.
B T cable is heat resistant. It is used for instz-Llations in zones
ere temperatures are elevated: in the engine zone, t.:e afterburner zone
1 section). In high temperature zones TM-250 eondactor, having a guage
3.75-6mm2Is used.
Cables are grouped in individual runs and are laic behind the instrument
sLs, and along the sides of the cockpit behind the consoles. These are
cockpit and cockpit control r ns.
SECRET
10 FOREIGN DISSEM/NO DISSEM 11RFfl'r'rrnNT?OT,7.77
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLL SSa 50X1-HUM
In.the fuselage is the upper fuselage control run, the upper fuselage
run, the run in the nose section of the fuselage (frames 1-11), the run supplyin
.the radio, the run along the port side of the fuselage, the run along the
starboard side of the fuselage, the control run along the starboard side, the
lower fuselage run, the power runs, the runs to the pumps in the lst, 2nd,
and 3rd groups of tanks, and others.
In the tail section of the fuselage, and in the fin, are the main run in
the tail section, and the run for controlling the tail'section.
The wings contain: the runs in the removable section of the-port wing--
the armament run, those for the flaps, floodlights, and the main landing
gear; the runs in the removable section of the starboard wing-- the armament
run, and the run for the main landing gear, and others.
All runs are protected by tubing made of AKhKR wire mesh. Additional
protection, in areas where high temperatures prevail, around the engine, for
example, is provided by the use of duralium tubing, tubing made of 14V22 heat
resistant rubber, and AAS and ANZM wire mesh coverings. Hoses made of armored
rubber, and other materials, are used in areas where there are sharp edges.
Page 19
The cable runs are secured in place with normally used, rigid and pliable
fasteners.
Rigid fasteners (locks and clamps) are secured to the aircraft structure.
I Pliable fasteners (pliable metal clamps, straps made of chlorovinyl
plastic) are used to connect individual runs to each other.
3. Cable Markings
The cables in the aircraft's electrical network are marked for convenience
of assembly and disassembly, as well as to facilitate finding and eliminating
troubles. The cable marking system consists of letters and numbers and
19
SECRET
NO.FOREIG1 .DI.SSEM/Il0 DISSEM ARRna17(ONTROLLED DT_c~P`TV
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
0 FO'_;ETGN DISS EM/NO DISSEMJABE N t NSI
? estipposes that instructions will be placed on individual
vaole tars.
1. ;roupings for electrical equipment aggregates.
All special equipment in the aircraft included in this category
has been divided into 10 groups, according to purpose, as follows:
aup
_u~er Name of
equipment included in
group
Power system equipment (sources of supply)
Electrical devices
Ignition aggregates
{ Check instruments
3 Light signals and illumination
9 Pa e 20
J Air navigation equipment
I' Instrument heating
R Radio equipment
Armament
Tanks
The ordinal number of an aggregate container; in one of these groups.
The number of the cable run (this will depe.ad upon the number of
ales coming out of a given aggregate).
The number of terminals for the plug, or aggregate, to which the
The location to which the particular cable runs.
20
SECRET
10 FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEyf
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET eUX1-hUIVI
NO FOPETCN DISSEM/N0 DISSEM ABRUAD/UVYEAUJLZD Dz5M
An example is:
R 5581 - 36R
where:
4 is the number of plug terminals to which the cable must be
connected;
55 is the ordinal number for the aggregate contained in the particular
group;
R is the group letter (radio equipment)
1 is the number of the cable run coming from the equipment;
36R is the location to which the particular cable runs.
Page ?21
4. Connecting and distributing devices - plugs, electrical switchboards
A. Plugs
Honeycomb connector plugs, type ShR (Sh-connector, R-plug), and type ShRG
(Sh-connector, R-plug, Q'-airtight), have been installed in the aircraft to
facilitate installation and removal of individual aggregates and electrical
runs.
The type ShR plugs are used to connect individual sections of electrical
circuits which need,.not be hermetically sealed, such as relay boxes, the
electrical switchboards which are part of the port and starboard consoles in
the cockpit, the nose and tail sections of the fuselage, the wings, and the
fuselage.
The ShRG plugs provide a means for bringing the electrical cables through
the airtight wall of the cockpit.
Figure 5 shows the location of the electrical plugs in the aircraft.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSS
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
22
Si CRFT
-O FOREIGN DISSE,i{NO J)TSSE M ABROAD/CO\ LOL
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001 6 Mg ,*14
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 I
V/\1-1 1'. M
SECRET,
NO FOREIGN DISSEM/NO DISSEM ABROAD /CONTEOLLED
B. Electrical switchboards
The electrical equipment installed in the aircraft has automatic: circuit
breakers as well as manual switches. The breakers and switches have been
centralized on separate electrical switchboards.
Page 22
Schematic diagram of electrical plug locations throughout the aircraft.
Page 23
The switchboards are located in the cockpit on the starboard and port
consoles and include:
the forward electrical switchboard for the starboard console;
the after electrical switchboard for the starboard console;
the electrical switchboard for the port console.
In order to provide for easy.removal of the electrical switchboards, the
latter have cable runs which terminate in connector plugs.
The forward electrical switchboard for the starboard console (figure 6)
is installed on the vertical section of the starboard console, between frames
number 7 and 8 and consists of two blocks of circuit breakers and switches
installed on a single panel.
An AZS (sym. 22R) is installed above the forward switchboard - "In the
event of failure of P0-750:1W, RVU" - to protect the circuit and to furnish
the supply to the winding of the relay (sym. 18R) which, when energized, cuts
in the supply to the RVU, MP station.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DIsS7V
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
-Ia-. ? Iun
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
A NU FUREIGN D1S61;M/NO DISSEM A ,,..-.;
Upper Block
Switch 2V-1+5 (sym. 11+E) - "Aircraft storage batter=airfield" - for cutting
in and cutting out the aircraft storage batteries 15-STsS-1+5 and the source
of supply used while on.the ground.
Switch VTK (sym 9E) - "Generator" - for cutting in and cutting out the
GSR-ST-12000VT starter-generator.
Page 21+
Figure 6. Forward electrical switchboard for the s-6arboard console
and the electrical schematic
Page 25
Switch 87K (sym. 69M) - "Pump Station" - for supplying power from the air-
craft network to the contactor for cutting in the pump station NP-27T.
Switch 87K (sym. 55M) - "Trim Effect" - for delivery of current to the
switch controlling the MP-100M electric motor for the loading mechanism.
AZS-5A (sym. 1N) - "AGD" - for circuit protection and delivery of current
to the STsGV (sym..21+N) hydraulic transmitter for the AGD-1 unit and to the
relay (sym. 19N) for starting the PT-500Ts (sym. 2N) converter.
AZS-5A (sym. 10N) - "KSI" - for circuit protection and delivery of-current
to the KSI course system and to the relay (sym. 16N) for starting the PT-500Ts
(sym. 2 N) converter.
AZS-5A (sym. 31+ (letter obliterated) ),- "MRP-RVU" - for circuit protection
and delivery of current to the relay (sym. 27R) for energizing RVU-!4P and
to MRP-56Ts.
AZS-5A (sym 3R) - "Radio station - oil pressure" - for circuit protection
and delivery of current for the relay energizing the radio station (sym. 9R),
the "ABV" block (sym. 10R) and amplifier UK-2M of series Ye connected to
2S
SECRET
NO FOREIGN DISSEM/,NO D.ISSEM ABEOADJCONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 ---
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
.? ) 6,1TCr DISS DI/NO DISSEM P
';.ta ion RSIU-5 (letter obliterated). (Translate:-'s Note:
J`'r.cnslation made with reserve because of condition of Mext).
? -1C. (sym. 49R) - "SM" - for circuit protection and delivery of
h?re:., co the responder ORO-1 (possibly SRO-I)
Page 26
r.S-5A (sym. 7R) - "Emergency Converter Switch" - :-"or circuit protection
.d delivery of current to the relay winding (sym. 32.) for emergency
:-inverter switch.
'.ZS-5A (sym. 22R) - RVU, r1RP" - for circuit protec,ion and delivery of
rur:ent ~o the relay winding (sym. 18R) for energizir. ; IN2P-RVU in event of
y'ure of PO-750A and to the relay winding (sym. 57R,) for disconnecting
"J-'T50A.
Lower Block
(;ZS-25A (sym. 41S) - "Floodlights, external signal landing gear" - for
circuit protection and delivery of current to switch or controlling the
c-.avigational and landing flood lights (sym. 1+3S, 44S
,,f,S-l0A (sym. 2P) - "Sight" - for circuit protect:... j.z and supplying the
';-o-cage iron the aircraft network to the sight block ; SP-5r1D
AZS-20A (sym. 1P) - "Sight, sight heater" - for c;.rcuit protection and
c--!-ivery of current to filter F-14A (sym. 4P) of sig ht ASP-5ND.
A ZS-15A (sym. 6R) - "SR Range Only" - for circuit ;2,roteetion and delivery
-l current to the radio range and to the relay (sym. iR) for energizing the
range-only radar.
.'S-5A (sym. 46P) - "SNV" - for circuit protectiC.i and delivery of current
,o he winding of the relay (sym. 48R) for starting converter 2O-500A (syn.
SR) and providing block which supplies SIV-52 with 45 volts, 40L) cycles a.c.
26
0 FOPFT(N DISSEI+L/N0 DISSFM P ' ROAD /CON ., L DISS tit
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET -HUM
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS^!
Page 27
AZS-10A (sym. 145) - "RS" - for circuit protection and delivery of
current to the RS block.
AZS-10A (sym. 3F) - "AFA" - for circuit protection and delivery of current
to the block for the aerial camera AFA-39.
AZS-10A (sym. 25P) - "Cannon" - for circuit protection and delivery of
.current to the electric trigger-.and to the'valve for reloading. the cannon.
AZS-5A (sym. 19P) - "FKP" - for circuit protection and delivery of current
to the timing mechanism VM-2 and to the gun camera SSh-1+5-1-100-SS.
AZS-20A (sym. 28B) - "SS Heater" - for circuit protection and delivery of
current to K-13 missile system heater element.
AZS-10A (sym. 29B) - "SS Filament" - for circuit protection and delivery
of current for the tube filaments of the K-13 system.
AZS-10A (sym. 303) - "SS Launch" - for circuit protection and delivery of
current for launching missiles in the K-13 system.
After electrical switchboard for the starboard console (figure 7) is
installed on the vertical section of the starboard console in the cockpit
between frames 9 and 10 and consists of two blocks of circuit breakers and
switches., mounted on one panel.
2?
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS1%T
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
5UX1-NUM
SEC CET,
"O'C FOREIGN DISSEM/NO DISSEM ABROAD? j U ,y . LI.SBtiM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET 50X1-HUM
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NO FOREIGN DISSEM/NO,DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1-HUM
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SECRET
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '"
JX1-HUM
'SECRET;
Wn rrMv -V 1 TSSEM/NO DISSFM A RvrvA77((NT'RGLLED DIS EGA
Page 98
The engine start system consists of a circuit for supplying the units
required to start,the engine from two storage batteries., 15STsS-45, furnishing
24 or 43 volts.
The starter-generator MR-ST-12000VT.will not, when supplied with
24+ volts (the storage batteries connected in parallel) turn the engine turbine
over at revolutions for "low gas"'operation.
In order to ensure reliable engine start on a start cycle of 7.1 seconds,
the storage batteries are automatically switched.to series connection and the
starter-generator, as well as the other starting units (the block of ignition
coils for starting fuel, the starting fuel pump electric motor, the starting
fuel valve electromagnet, the make-up fuel valve electromagnet, and the electro-
magnet for the valve controlling by-pass air with the hydraulic valves), are
supplied with the increased voltage.
-NOTE: The increased voltage supply to the starter-generator increases
the torque on the starter-generator shaft and intensive engine crank-up,
occurs.
The units used in the starting procedure are switched to supply from the
series connected batteries because, on starting, the battery voltage drops
considerably (approximately three times).
Page 99
A reduced voltage supply;(from one battery) results in ignition coil
malfunction ("Jerky" operation ofl.the interrupter, formation of an electrical
arc and burning of the interrupter contacts), reduced flow from the starting
fuel pump (which slows the starting process or results in failure to start),
non-operation of the valve electromagnets of the valves for starting fuel,
make-up fuel, and for by-pass air'hydraulic valve control.
97
SECRET
NO FOREIGN DISSEI/NO DISSE;( ABROAD/CONTROLLED DISSIM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 tigX1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
10 FOPPTGN DISSEM/NO DISSEM ABROAD/CONTxu. LLV litb,~.+#M
As starter-generator revolutions increase its power demand drops and the
voltage of the series connected batteries is restored
In order/ to protect the starting units from over-voltage (more than
29.5 volts) a relay, RN, is installed in the starting relay box. This relay,
when the voltage increases to over 29.5 volts, switche the supply to the
units to one battery.
NOM: The RN relay operates at a voltage of e5 volts +0.5 and
t,I15, volt, but in order to cause the relay to fur ation at a voltage
of 29.5 volts a resistance Rn has been inserted in the relay winding
circuit.
The engine start system,'consisting of the circuit for supplying the units
required to start the engine with 24 or 4+8 volts, permits:
Page 100
starting the engine from battery on the ground;
starting the engine from the airfield supply source;
starting the engine in the air;
turning the engine over cold.
Operation of the Electrical System
(a) Starting the engines from on-board storage batteries is accomplished
directly from the starter-generator, which obtains its supply from the batteries
(sym. 1CE).
The starting procedure requires turning on of switch (sym. 11E) and
circuit breakers (sym. lYe, Me. ,'514., 34K-.9 13K). The throttle is set in the
"low gas" position. The oxygen make-up selector switch (sym. 1214) and the
conservation selector switch (sym. l4Ye) are set in the operate position.
When the switch (sym. 14E) is closed the contactor (sym. 19$, 26E)
function, connecting the storage batteries (in parallel] to the aircraft's
98
electrical system. SECRET
140 FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 S
NO FOREIGN DISSEM/N0 DISSEM ABR0AD/UUVTnv1wrv V. Dcu:9
When the AZS (sym? 5M) is cut in the contactor (sym. 5M) which connects
the electric motor for the pump on the fuei. tank in use (sym. 8M) through
filter (sym. 7M) to the circuit operates.
Page 101
When the AZS (sym. 29Ye) is cut in "positive" voltage is fed to the relay
winding (sym. 28M) through contacts 2-1(one number blurred) of the relay
(sym. 38M, 2914).
The relay (sym. 28M) functions, contacts 2-1 break the supply circuit to
the terminals for the hydro-electric valve (sym. 153M) from the power unit bus
through fuse symbol 154M and contacts 6-5 close the circuit supplying terminal
2 of the hydro-electric valve plug (sym. 163M) from the AZS (sym. 29Ye).
The engine nozzle valve is switched to the after burner position.
The supply, accordingly, is fed directly from the No. 1 (sym. 10E) storage
battery, through fuse symbol 12E, contacts 3-1 of contactor symbol and
terminals 14, 38, 18 and 35 of the plug for the start relay box (sym. 1M) to:
contact 9 of relay R6 through contacts 1-2. of relay R1+;
contact 3 of relay R8;
contact 5 of relays R3 and Rh.;
contact 3 of relays R14 and 8;
contact 2 of relay R10.
When AZS (sym. lA) is turned, on the aircraft network supply is fed to con-
.tact 3 of relay (number illegigie } in the start relay box (sym. 11M) through
terminal (illegible) of the box connector and to contacts h-5, 2-1 of relay
I~Ze 102
OSh, while power is supplied, through fuse symbol M, to:
5'9
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 )'/50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
..., i vnr,.L x1Y L100. M/1'RU DISSEM ABR AD C N =:_ Isla,
contact 3 of relays R6 and R7 and contact 6 of relay R5 respectively'
via tez als 37 and 29 of the plug for the start relay box (sym. 4M);
;t croswitches 1 and 2, contacts 2 and 5 of relay A3, contact 3 of relay
A4 via tei tnal 10 of the plug for the automatic timer (sym. 3x), as well as
the start 'i)~;ton.(sym, 2Ye) via contacts O-N3 of microswitch 2 and terminal 7
of the plug or the automatic timer (sym. IM).
The stvi button (sym. 2Ye) is pressed. The following must be connected
in the circui when the start button is pressed:
main fu ignition coil (sym. 4Ykr);
the pilc light indicating ignition on (sym. 188);
the elect i is motor for the pump providing starting fuel (sym. 2M);
the elect'.c motor for the automatic timer (sym. 3.M);
afterburner fuel ignition coil (sym. 83Ye).
The main ignition coil ,~ s.Ym. 4Ye) obtains its supply from a circuit
which includes t.it start button (sym. 2Ye), contacts 2-1 of relay G (sym. JiM),
contacts 1-2 of ~ )lay R31 (sym. 4M), switch contacts (sym. 18Ye), contacts 4-5
of relay 3V (sym ?K), contacts 4-5 of relay R5 (sym. 4M), the winding of relay
sym. 4M), Rely ., Z,
Page 10
f'"unctioning, closet its contacts ,3-2, 5-6 and supplies "plus" from the battery
to the ignition coil. (sym.- 4Ye) via a fuse .(sym. 42E), contacts 2-1 of the
contactor (sym. 44E) and then two more fuses (sym. 39Ye and 32Ye) and the con-
tacts of switch symbol 14Ye.
The pilot light (sM. 18S) indicating ignition on is connected through
a circuit consisting of a fuse (sym. 41Ye), contacts 2-1 of relay KR (sym 97M),
and contacts 13-14 of relay symbol 15Ye..
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEV
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 I XI-HUM
4
ONT9
s NO FOREIGN DISSEM/NO DISSEM ABROAD/C
The after burner fuel ignition coil (sym. 3Ye) is connected through a
cricuit consisting of a fuse (sym. 41Ye), contacts 2?1 of relay KR (sym 97M),
contacts 5-4 of relay R7 (sym. 4M), and contacts 3-2 of relay R9 (sym 4M).
Relay R9 is cut in through contacts of switch symbol 18Ye.
The spark plug for afterburner fuel ignition is prechecked
(prior to
feeding afterburner fuel).
The electric motor for the pump which uppl.ies starting fuel (sym. 2M)
is energized by a circuit which consists of the start button (gyp. 2Ye),
contacts 2-1 of relay G (sym. 41), contacts 1-2 of relay R11)sym. 4M), switch
contacts (sym. l3Ye), contacts 4-3 of relay 3V (sym. 4M), and the winding of
relay R14. Relay R14 (sym. 4M) functions, closing contacts 3-2 and 6-5 and
connecting the on-board network to the electric motor for the pump supplying
starting fuel. The motor begins to run.
Page 104
The automatic timer electric motor (sym. 1M) is energized by a circuit. which
consists of the push button (sym. 2Ye), contacts 2-i of relay G (sym. 4M),
contacts 1-2 of relay R11 (sym. 44, terminal 12 and the winding of relay Al
(sym. ]M). The relay operates and current is supplied via contacts 9~i8 to
the winding of relay Al (sym. 1M) and via contacts 4-5 of relay A2 (sym. 1M).
Relay A4 functions and via contacts 3-2 feeds "+" from the aircraft's network
through the AZS (sym. lYe) and, a fuse (sym. 3M). The electric motor begins to
rotate the automatic timer cam,,, closing the corresponding microswitch in the
start circuit. The development of the start cycle program begins.
Current is supplied simultaneously to microswitches 3, 4, 5, 6, and 7 so
0 that relay A3 functions and closes contacts 2-3, 5-6 (the supply for the
.
winding of relay A3 is through contacts 5-6 of relay Al). The circuit con-
6 and 7 is ready for operation.
sisting of microswitches 3
4
5
,
,
,
SECRET
NO FOREIGN DISSEMJNO DISSEM ABROADJCONTROLLED DIS5EJ
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 --0X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
I TO FfRTTGN DISSL /NO DISSEM AbHUAll/l,Viri.c+v+."...- -'w---a
When the start button (s;'n. 2Ye) is pressed rely RV (sym.M) is also
cut in via contacts 2-1 of relay G.
When relay RV functions contacts 3-2 cut in relay R16 which, in turn, through
contacts 1-2, opens the circuit supplying the windin4 of relay RN.
The development of the start cycle program for the automatic timer
1
(sym. 1M) takes place in the following sequence.
Pae10
After an interval of 1.4 seconds microswitch 1 closes and delivers, through
its contacts 0-NR, "+" to the winding of relay A4, to the winding of relay Al
via contacts 5-4, relay A2 and contacts 8-9 of relay Al and to the winding of
relay A3 through contacts 5-6 of relay Al. Relay Al picks up and the start
button (sym. 2Ye) can be released.
The automatic timer electric motor, as well as microswitches 3, 4, 5, 6 and
,T are now supplied when the start button is-released,
"+" is also supplied to
the winding of relay R2 through the circuit breaker, an overvoltage type
AZP-1MA (sym. 46R).
Relay R2 functions and when its contacts open-the circuit which connects
the generator-starter (sym. lE) to the aircraft's internal system is broken.
After an interval of 1.6 seconds microswitches b and 7 function.
Microswitch 6 supplies "+" to the winding of relay R through its contacts
0-NZ, through contacts 5-4 to relay R3 and through contacts 9-8 to relay R4.
Relay R8 functions and through contacts 3-2.supplies current to the electro-
magnet (sym. 35Ye) for the fue;Ld`ump valve.
Microswitch 7, through contacts 0=1M, supplies "+" to the winding of
relay R4. Relay R4 functions and, through contacts 5--6p cuts in the electromagne
(sym. 42Ye) for the valve which controls air by-pass through-.the hydraulic
valve system.
102
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10 FOREIGN DISSEMINO DISSEM ABROAD/CONTROLLED DISS M
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 vl-HUM
140 FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLEIfDIS 1M
battery number 2.(sym. 10E) to the series winding of the starter-generator '
Sh (sym. 4M), and through contacts 2-3 to relay Al (sym, 1M).
The contactor (sym, 38E) functions and supplies "+'' from storage
1
After an interval of 1.9 seconds microswitch 2 functions and through
contacts 0-NR supplies '"+" to the contactor winding (sym. 38E) and relay
(sym. 1E) through a resistance (sym. SE).
Page 106
The starter-generator is connected through the. resistance (sym. SE) so
that engine turbine turnover will be smooth.
Relay Sh (sym.14M) functions, contacts 1-2 disconnect the shunt
winding of the starter-generator (sym.lfl) from the RUG-32 (sym.3E), while
contacts 3-2 supply "+" from the 'internal network to the shunt winding
of the generator (sym. 113) through the AZS (sym. lYE) and contacts-4-6
and 2-1 of relay OSh (sym. 4M).
The starter-generator (sym, 113) receives mixed excitation:
after an interval of 4.1 seconds nicroswitch 3 functions and
contacts 0-NR deliver 1'+'a to the windings of the contactor (sym. 37E)
and the relay (sym, S1M), The contactor (sym. 3713) is cut in, blocking
the resistance,, (sym. 5E) and increasing the excitation current in the
series winding of the starter-generator. The relay (sym. 51M) functions',
contacts 7-8 cut out winding'.LR, the RUG-32 voltage regulator coil (sym,
3Ye), (so that when the storage,,batteries are switched to 48 volts RUG-32
does not burn out), while contacts 5-6 ready the circuit for switchover
(via KNA-4, sym, 3013) to 48 volts when starting the engine from the
airfield supply source.
SECRET
103
tMORET
NO FOREIGN DISSELO DISSEM ABROAD /CONTROLLER pISSy3
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6'1X1-HUM
brIkAMb1 I I
1"r1 7MOW-Fru TtTSSEM/NO DISS1!f Al OAT)/CONTROLI,P D DISSEM
Page 107
After an interval of 7.1 seconds microswitch 5 functions and
contacts 0-iVR supply "+" to the winding of relay R10 (sym. 4M) through
the switch contacts (sym. 18Ye) and contacts 5-6 of relay Sh, as well
as to contact 5 of relay RIO. Relay RIO functions, supplying current
through contacts 5-6 to the contactor windings (sym. 27E, 28E) and to
the winding of relay R7 through contacts 1-2 of relay R3 (sym. 4M).
Contacts 2-3 serve to cut in the electromagnet (sym. 6Ye) for starting,
fuel. Contactors, symbols 27E and 28E; operate and switch the storage
batteries (sym. 10E) to series connection, that is to 48 volts. When
relay R7 functions its contacts 3-2 supply current to the selector
switch ST and VDT of the BU-4B control block (sym. 1O+Ye), while contacts
5-4 break the circuit for prechecking the plug for igniting afterburning
fuel (sym. 33Y-e).
The VDT contacts furnish the "+" to the winding of relay R6 (sym.
4M). Relay R6 functions and its contacts 5-6 close a supplemental circuit
to supply the electromagnet (sym. 42Ye) for the valve which controls by-
pass air with the hydraulic valve system (in parallel with contacts 5-6
relay R4), while contacts 3-2 feed "+" to the winding of the contactor
(sym. 44E) through contacts 2-3 of relay R12, contacts 2-1 of relay RiS,
Page 108
contacts 11-12 of relay R14 in.the.start relay box (sim. 4M) and through,
contacts 2-1 of relay symbol 12Ye.
The contactor (sym. 44E).functions and contacts 3-1 connect the
ignition coil (sym, 4Ye) to 48 volts over a circuit consisting of contacts
aa4
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSMY
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 0X1-HUM
I NO FORrTGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
3-2 and 5-6 of relay Z (sym. 4M), fuses (sym. 38Ye, 39Ye) and contacts of
the selector switch (sym. 14Ye).
Selector switch ST operates when revolutions correspond to 32%.of
rotor revolutions at high pressure (3500-38-- rpm). Selector switch. VDT
operates when revolutions correspond to 48% of rotor revolutions at high
pressure (5300-5800 rpm).
If the engine-turns up to revolutions for "low gas" (3500-3800 rpm)
sooner than the automatic timing program (sym. 1M) evolves, selector
switch ST supplies "+" to the winding of relay R5 (sym. 4M). Relay R5
functions and contact's 2-1 break the negative circuit of relay Al
(sym. 1M). Relay Al is dead, its contacts 5-6 open, and the supply
circuit to the winding of relay A3 opens. Relay A3 goes dead in turn and
the opening of contacts 2-3 and 5-6 break the circuit supplying micro-
switches 3, 4, 5, 6, and 7. The automatic timer (sym. 1M) curtails program
development, despite the fact that its electric motor will run until such
Page 109
time as microswitch 1 contacts O-NZ are no longer closed and the circuit
supplying the winding of relay A4 is no longer broken.
Contacts 6-5 of relay R5 supply "+ to the winding of relay Z.
Relay Z functions and its contacts 3-2 and 5-6 connect the ignition coil
(sym.,4Ye),
When an rpm rate is reached,, .
which corresponds to 48% of rotor revolur:
tions at high pressure (5300-5800 rpm) the VDT selector switch functions
and the winding of relay R6 receives no current. The relay drops its
contacts 3-2 and 5-6 and the circuit which supplies the electromagnets
(sym, 42Ye, 32Ye) and the contactors (sym, 44E) is opened.
105
SECRET
NO FOREIGN DI:'lEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 FfX1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/NO DISSEM CONTEULLIW F-
After an interval of 12.6 seconds microswitch 4 functions and contactors
14Z-0 deliver "+.""to the winding of relay SSh and nil in the box (sym. 4M).
When relay SSh functions the supplementary resistance Rsh is unblocked
mnd is connected to the starter-generator (sym. 1E) shunt winding circuit.
The current in the shunt winding is decreased 3 to 4 times. The starter-
jenerator (sym 1E) revolutions increase.
Relay Rll blocks itself through its contacts 6-5, while contacts 2-1
interrupt the circuit which supplies the winding of relay R8 (sym.4M).
Within 0.5 second after its supply is cut off relay R8, through contacts
3-2, breaks the circuit supplying the winding of relay R10. (TN: Maybe
relay R16). Relay R16 opens contacts 1-2 and connects relay Rn to the
ignition coil (syrn. 4Ye).
Page 110
With the appearance of from 26.5 to 29.5 volts across the ignition coils,
relay Rn functions, contacts 2-3 close and is sup-?lied to the winding of,
relay R12 (sym. 4M). Relay R12, self-blocking by contacts 2-1, with con-
tacts 2-3 interrupts the supply circuit to the contactor winding (sym. 44E).
The contactor drops contacts 2-1 and the ignition coil circuit is connected
to the supply from a single storage battery, Number 1 tsym. 14E).
NOTE: I. If the voltage across the ignition coils is less than
26.5-29.5 volts, supply for,the coils will be furnished from the series-
connected storage batteries-'to: time 25.3 seconds; that is, when micro-
switch 4 functions;
2. If the ignition coils obtain a supply from one storage
battery, then at the time to start the engine low voltage is fed to the
166
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTBQLLED DISSE1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 ]X1-HUM
- NO FOREIGN DISSEM/NO DISSEM A~ROAD/CONTRULLED 311
quite low) which would result in the interrupter contacts sticking;
ignition coils (i.e., the storage battery voltage at start time i
microswitch 6 returns to its initial position in 16.6 seconds and opens
the supply circuit to the winding of relay R8. Relay R8 drops contacts 3-2,
breaking the electromagnet (sym. 35Ye) circuit for the fuel dump value;
microswitch 4 returns to its original position in 25.3 seconds and
contacts 0-NR supply." +" to the winding of relay R15. Relay R15 functions
and, through contacts 2-1,
Page 111
opens the circuit supplying the contactor (sym. 44E) winding. Contacts 1-2
`in the contactor (sym. 44E) open and switch the ignition coil (sym. 4Ye)
supply from storage battery Number 1 (sym. 10E); that is, storage battery
voltage has been restored;
microswitch 7 returns to the.original position in 25.6 seconds, opening
the supply circuit to the winding of relay R4 which, in turn, opens, through
contacts 1-2, the circuit supplying the electromagnet (sym 82Ye) of the
make-up fuel value, and opening the supply circuit, with contacts 5-6, to
the electromagnet (sym. 42Ye) of the control value for by-pass air by
hydraulic values.
NOTE: The electromagnet (sym. 42Ye) continues to receive a supply
from contacts 5-6 in relay ,R6 (sym. 4M) until such time as the relay
winding is deenergized by eoptacts in transfer switch VDT;
microswitch 3 returns to the original position in 42.0 seconds and
breaks the circuit supplying the contactor (sym. 87E) winding, once-again
cutting~in the supply to'the series winding of the starter-generator (sym.'_:iE)
107
SECRET
3O FOREIGN,DISSEMINO DISSEM ABROAD/,CONTROLLER DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6'1X1-HUM
NO FOR71TCN DISSEM/NQ DISSEM ABRO~D/UUhTKVJAj9W ..:..
and resistance (sym. 5E), as well as opening the circuit supplying the winding
of the relay (sym.,51M) which connects the starter-generator to RUG-82 (aym.3E);
ricroswitch 2 returns to the original position in 42.7 seconds and
Page 112
cuit to the start button (sym. 2Ye);
microswitch 5 returns to its original position in 43.4 seconds and
opens the circuit supplying the winding of relay R10 (3ym. 4M). Contacts
in relay R10 provide a supply circuit for the winding of relay R7 and
the contactors (sym. 27E, 28E). Storage batteries numbers 1 and 2 (sym. 10E)
are switched from series to parallel connection;
in 44 seconds microswitch 1, through contacts 0-NR, opens the circuit
supplying the winding of relay A. Relay All. drops contacts 3-2, breaking
';he circuit supplying the L-2R motor. Motor L-2R, in the automatic timer
AV7-44-5 (sym. 1M), stops. The start program sequence is terminated.
NOTE:: If, for some reason, the starting procedure is interrupted
and a new attempt is made to start the engine, tb~=T automatic timer
motor will continue the program to its termination and it will then be
possible to start the engine (in 42.7 seconds mie:?oswitch 2 functions
and supplies the start button).
(b) Starting the engine from the airfield Source of sup is
similar to that program used in 'starting the engine from the aircraft's
storage batteries.
Page 113
The difference is that when the airfield's power supply is plugged in
the starter-generator and the aircraft's electrical system obtain their
108
,SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTR{a.LPD DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6'1X1-HUM
NO P(rrTaN DISSEM/NO DISSEM ABROADJCONTROLLED DIM
supplies from the airfield's source. When this source is plugged in the
changeover to the``airfield's storage battery takes place with the functioning
of contactor //
KP-400D, installed in box KPA-4 (sym. 30E) of the ground supply.
'Supply is furnished to. the winding of contactor KP-400D after the con-
tactors (sym. 27E) 28E) have functioned through contacts 6-5 of the relay
(syn. 51M) and the plug for hooking up the airfield supply source ShRA-250
MLK (sym. 13E).
(c) Starting the engine when airborne is accomplished by cutting in the
AZS-10 ('sym. 3lYe).
When the AZS (sym. 3lYe) is cut in relay "3V" in the box (sym. 4m)
operates and, through contacts 6-5, supplies the winding of relay "3".
A positive voltage is simultaneously supplied to the oxygen make-up
value (sym. 634) through contacts 3-2 of relay 3V and to the winding of relay
R10 through contacts 9-8 of relay 3V. Relay R10 operates and, through its
contacts 3-2, supplies the start fuel valve (sym. 6Ye)..
Relay "3", operating, furnishes a positive supply through its contacts
3-2 and 5-6 to:
ignition coil KNA-114 (sym. 4Ye) and the pilot light for signalling
ignition on'(sym. 18S);
Page 114
the winding of relay R14, which functions and, through its contacts'3-2 and
5-6, supplies power to the startiump PNR-10-9M (sym. 2M) motor.
109
SECRET
NO FOREIGN DISSEM/NO DISSEM .ABROAD/CONTROLLED pISSyM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
FnvrTnu DISSEM/NO DISSEM ABROADJCO ROLLED ISSZE
Page 115
3. Engine afterburner systn
General information
The system in designed to cut in the afterburner regime in order to
increase engine thrust.
System operation is carried out with the electrical devices shown in
the table.
SECRET
NO FOREIGN DISSEMJNO DISSEM ABROAD/CONTdi JLLED DISS 2M
i
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO. FOREIGN DI,934M/NO DISSEM ABROAD/CONTROLLW S'I'N
r
F-W .O
? n
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O is ?i
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91-1
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N
P
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cd
111
43
N
NO FOREIGN DISSEM/NO Dl---.'-.
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03'066R000200020001-6
 tifX1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FnR1i;TCN DISSEM/NO DISSEM ABROAD/.CONT UbLLFU Ju10041x
m ?rl 3' .Q
4-1
A
w
l^ }1 S/~
44
W
V
y Ej Qi
4-~ m
w ro
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L r, n ~n ns .o
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fa w
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SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTEULLED AISS'Ek
4-1 P 4)
v 0 0 M
M ?L Q! C CL) S
w
t+7
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED ISSEM
t
Cutting n the afterburner is' done by setting the engine control lever'
Pa e 118
Afterburner operation
(RUD) to the "minimum afterburner" stop. However, afterburner cut-in will
take place only after operation of the units for interlocking the afterburner.
with respect- to engine turnover (the terminal switch for the.
hydraulic decelerator and transfer switch BFO), that is, after the engine is
operating at the number of revolutions selected as'the condition for stable
engine operation with the afterburner. The dogs of the transfer switches,
BFO-2 and BFO-lo in control block BU-4B are set corresponding to 60% and 65%
of high pressure rotor revolutions, while the terminal switch for-the
hydraulic decelerator of'regulator pump NR-21F.is set for 98% of low pressure
rotor revolutions.
When the RUD is moved forward 68? with respect to the limb on control.
panel PURT-lF the panel transfer switch PK operates and this prepares the
circuit for energizing relay "Z" in the KAF-13D afterburner automata box.'
nZ"
When an engine rpm is reached which matches that for closing the terminal'
switch and switch BFO-1 in block BU-4B, power is fed to the winding of relay
which, operating, blocks the terminal switch of the hydraulic decelerator.
Page 119
and switch BFO-1, as well as.t6:the relay winding (sym. 38M). Relay
symbol 38M operates and its contacts 5-6 ensure that the relay will pick.
SECRET
NO FOREIGN DISSEM/_NC DISSEM ABROAD/CONTROLLED DISSEM
itself up through the.closed contacts of transfer switch BF0-2.
Contacts 2-1 in the' relay (sym. 38M) function at-the same time. The relay
(sym.'28M) is disconnected, clos?s contacts 2-1, and opens contacts 6-5.
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '1X1; HUM
. 51aJwI
NO FOREIGN DISSEMINO I'_'S.1;N ABROAD
J.'he hydraulicelectric valve (sym. i;';M) will switch itself to the "meucimum
position.
When the engine control lever iE set to the "minimum afterburner" stop
(730 on the limb on panel PURT-1F) t:rrtnsfer switch EFS (flaps for blocking
the afterburner) in PURT-1F and relay F1 in KAF-13D function.
When relay N functions the eleci.comagnetic valves for the carburetor
and the KNA-114 ignition coil for afterburner fuel are cut in.' When operating
fuel at rated pressure is obtained in the NR-22F pump regulator the terminal
switch for pump NR-22F cuts out the supply to the winding of relay N and.,
at the same time, cuts out both electromagnetic valves for the carburetor
and for the afterburner fuel ignition coil.
Page 120
Relay F2, "operating, breaks the circuit to terminal 3 of the plug for
hydraulicelectric valve GA-164M and the supply circuit to terminal 2 of the
plug for GA-164M is closed. Relay Ye also cuts in and this relay, in turnj,
connects the hydraulicelectric valve GA-164M into the follow-up system
consisting of rheostat R-1, polarized relay RPS-5 and transmitters DOS-1A
and DR-3A.
The principle of operation of the follow-up system is as follows. The
shaft of transmitter DR-3A is rigidly coupled to the"shaft of the PURT-1F
aggregate and is rotated by the-.engine control lever and sets in motion the
sliding contact of the resistander.type-transmitter t-3A which, until this
time, has been at a stop suitably varying the relationship of the resistances
contained in the bridge arm.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEJM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO I'ORETGN DISSEM/N0 DISSEM
polarized relay RCS-5, furnishing a supply to the winding of relay a and b
in KyS-l.
The resultant unbalancing of the bridge activates the sensitive,
Relay a and b closes the supply circuit to the GA-164M valve. Value
GA-164M opens the intake for the. hydraulic fluid of one: or the other of the
cylinders. The piston, as well as the sliding contact of transmitter DOS-1A;
move until such time as the bridge is balanced. When the bridge is balanced
the current falls to a value which is less than the sensitivity current for
RPS-5 and the hydraulic-electric valve GA-164M is cut-out.
When the RUD is set at the "minimum afterburner" stop, thanks to a'
previously set
Page 121
mismatch of DOS-IA and DR-3A, a current flows in the winding of polarized
relay.RPS-5, contacts Ya and 'L close, cutting in relay b in KVS-l. When
relay b functions a voltage is fed to the number Z terminal of GA-164M. The;
initial movement of the DR-3A-,slide._
This is ensured by the follow-up system being out in prior to the
flaps move front the initial "maximum" position to the "minimum afterburner"
position.
The flaps remain in the, "minimum afterburner" position during the period
of movement of the RUD forward to the 7.8? position on the limb of the PURT-1F.
For each successive movement afthe RUD ahead to 108? on th
FURY
e
-1F
in' the winding of the polarized, relay (until balance is established), con
limb a mismatch will occur in the follow-up system and a current will flow
tacts Ya and L. will close, and relay b in KVS-1 cuts in. Relay b, functioning,
1,15
SECRET
NO FOREIGN DISSEM/NO DIS
SEM ABROAD/CONTROLLED DISSIrga.'
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
60 ,PI1
NO Ff11;!TrN DISSEM/'NO DISSI' I ABROAD /CO14 RO `l
:supplies a voltage to terminal 2 of the plug for the hydraulic-electric valve
3A-164M. The flaps smoothly increase their diameter to :"full afterburner.'
During the course of moving the RUD forward from 1080 to 1120 on the
Limb ("full afterburner"), the flaps retain "full' afterburner" diameter as
a result of the DR-3A slide-being in the.fixed resistance section.
Page 122
When the RUD is-moved in the opposite direction (inward) flap movement
takes place in a manner similar to that described abo?e, but in the section
from 1080 to 78? on the graduated dial of the PORT-1F a mismatch occurs in
the follow-up system, with the result that current flows in the winding.. of
polarized relay RPS-5, but in the opposite direction. Contacts Ya and P in
this relay close, cutting in relay a in the KVS-l. When relay a functions
. supply is provided for the relay winding (sym. 37M). The Relay (sym. 37M)
operates, contacts 2-3, close, and current is suppliee. to terminal 3 of the
hydraulic-electric valve, GA-164M plug. This permits the flow of the
hydraulic fluid into the other cylinder. The piston, along with the DOS-IA
transmitter slide, move in the opposite direction.te flaps smoothly
,educe the diameter to '!minimum afterburner."
Contacts 5-6 and 8-9 in the relay (sym. 37M) close at the same time.
Make-up for the electromagnet of the afterburner fuel pump is provided and
the process of disconnecting relay F2 is blocked (in the event the engine
control level is abruptly moved>to a position less than 73? on the limb of
the PURT-1F) despite the fact that no current flows in the Fl. relay winding
and the relay has dropped its contacts.
116
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD /CONTROLLED..DI$,$ N ,
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 : CIA-RDP78-03066R000200020001-6 JX1-HUM
310 FOREIGN DISSEM/NO..DISSEM ABROAD/CONTROLLED DISS Y
for engine nozzle'flaps can be used., The switch marked "emergency nozzle
In, the event of a`failure of the follow-up system the emergency . control.
ition when this procedure is used.
Page 123
Relay v in the KAF-13D operates. If the RUD is. in the "full afterburner"
position (1000 on-the PURT-1F limb) the flaps will be set for "maacimum" dia-
afterburner" position (from 100' to 112?.) the flaps will be set. for "full,
meter. Afterburner operation is.cut out. If the RUD is beyond the "full
Control of engine operating conditions with nozzles satisfactory for
-all conditions, anticipates a delay (in'time) of the opening of the jet nozzle
flaps and delivery of afterburner fuel. The delay in the change in the
.diameter of the flaps takes place between RUD positions for "minimum
.position and the stop (from 108?.to 112? on the scale).
"full afterburner" (from 730 to 1080 on the scale), and,
in the event emergency control is used, between the "full'afterburner"
The delay can be set for 0, 0.5, 1.0, 1.5 or 2 seconds. These delays are
The time delay in the opening of the flaps is needed in order to avoid
the possibility of a'drop in R4 pressure when the afterburner is cut in.
provided for by time-delay relays RV, RV2, RV3, RV4; relays "c it and "d"
and also by proper setting of lock switches.A, B,, V, G, D, and Ye iii the
KAF-13D box. T.N.-"lock switch";is an arbitrary translation of the Russian
word, shlits, normally meaning "spline". The part is not described but
Russian-word implies a .slotted mechanism, possibly L-shaped or U-shaped)
later text indicates its a two-position open-closeswitching device. The
117
SECRET
NO FOREIGN DISSI? /N0 DISSEM ABROAD/CONTROLLED DISS!1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Q 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 =,
NCPPOP TGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS131
The time delay, for flaps, as well as for fuel, is provided for only
when no current fl6ws in the'time relay windings. This is accomplished by
opening the normally closed contacts in relay Fl.
Electrical circuit operation
When the RUD is moved forward to the 680 mark on the limb on the a control
panel, PURT-iF (sym. 7Ye), transfer switch PK on the panel operates, readying
the circuit which cuts in'relay Z in KAF-13D (sym. 97M). When the engine
reaches rpm for closing terminal switch BFO-1 (transfer switch BFO-2 is
already closed) in block BU-4B (sym lOYe), current from the aircraft network
is supplied to the winding of relay Z through the "afterburner" AZS (circuit
breaker) (sym. 29Ye), to transfer switch BFO-l, to the contacts of terminal
switch for hydraulic decelerator (sym. 34Ye) and transfer switch PK. Relay
operates and, with its contacts 2-3, blocks the terminal switch for the
hydraulic decelerator and transfer switch BFO-1.
Current is provided to the relay winding (sym. 38M') through the BFO-1
contacts as well. The relay (sym. 38M) operates and contacts 1-2 break the
supply circuit to the winding of relay symbol 28M. Contacts 5-6 are inter-
socked through transfer switch BFO-2. The relay (sym 28M) goes dead and
contacts 5-6 break the supply circuit to-terminal 2 of the hydraulic-electric
valve GA-164M (sym. 153M), while contacts 1-2 supply current to terminal ,3,
this same valve through contacts 5-4 of relay F2 in the KAF-13D (97M).
The flaps will move from.the;"afterburner" position to the "maximum"
position.
When the RUD is set on "irfaximun afterburner" stop, transfer switch(blur)
i
on PURT-1F operates. Current is fed to the winding of relay F1 through AZS
118
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/,NO DISSEM ABROAD/CON C
and contacts 4-5 ot. relay (blur). Relay F1 operates and feeds current
ti
"'afterburner" contacts' 5-6 of relay. "Z", contacts 4-5 of transfer switch(blur
Page 12
to the electromagnet for the valve of pump NR-22F (gym. llYe) and the
pilot light which indicates that the afterburner is cut in (sym. 3OYe)
through the contacts of lock switch Ye and contacts 7-8 of relay KR in box
KAF-13D (sym. 97M), as well as to the winding of relay F2 through the_ contacts
of lock switch D in KAF-13D (sym. 97M) and to the winding of relay N through
contacts 1-2 of the terminal switch for pump NR-22F (sym. 9Ye), as well as
to the winding of the relay (sym. 29M) through the contacts of lock switch
Ye in KAF -1 D (s
3 ym. 97M) and normally closed contacts, 7-8 of relay KR. The
relay (sym. 29M) operates and, with contacts 2-1, once again breaks the
circuit supplying the relay winding (sym. 28M),
Relay N in KAF-13D functions and contacts 2-3 and 5-6-provide the supply
path from the aircraft network through the AZS "afterburner" (sym. 29Ye) to
coil KNA-114 (sym. 33Ye) through the transfer switch (sym. 14Ye) contacts.
the electromagnetic valves for the carburetors (sym. 5Ye) and the ignition;
When operating fuel at rated pressure is obtained in the pump regulator
NR-22F, the terminal switch(sym, 9Ye) opens the supply circuit to the
winding of relay N, both carburetor electromagnetic valves (sym. 5Ye) and
the ignition coil (sym. 33Ye) are, disconnected.
Relay F2, operating, breaks `t1je, circuit supplying terminal 3 of the
hydraulic-electric valve GA-164M (sym. 153M) through contacts 5-4, with
contacts 2-3 closing the circuit supplying the winding of relay "Yee? through
contacts*8-7 of relay v. Relay "Ye" functions and connects, through contacts
SECRET
40 FOREIGN DISSEM/NO IISSEM ABROAD /CONTROLLED
DISS Sf
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 ,nyl-I-ii IRA
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
110 T1n'6r' T(;N DISSEMINO DISSEM ABROAD/CON 'ROLLIW PiS .?iM
5)-6, the follow-up system to the circuit supplying terminal 2 of the plug
for the hydraulic=,electric valve GA-164M (sym. 153M).
Page 126
With the RUD against the "minimum afterburner" stop, and because of the,
i
previously assigned mismatch between transmitters. DOE-lA (sym. 152MM) and
D-R-3A (sym. 44Ye) a current flows in the winding of polarized relay RPS-5
in the signal distribution box (sym. 151M). Contacts Ya and L in this relay
close, energizing relay b in the KVS-1 (sym. 151M)-
Relay b operates, supplying current to terminal 2 of valve GA-164M
(sym? 153M)? ?
The flaps move from the initial position "maximum" to the "minimum
afterburner" position.
The flaps remain in the "minimum afterburner" positon when the BUD is
moved forward to the 780 mark. As the RUD is moved further forward, to the
y.08? mark a mismatch occurs in the follow-up system and a current flows in
she-winding of relay RPS-5 (until such time as the bridge in the follow-up-
system is balanced) and contacts Ya and L close, cutting in relay b in the
KVS-1 (sym. 151M). When relay b operates it closes its contacts 3-2 and a
voltage is supplied to.terminal 2 of the plug for the GA-164M (sync. 153M).
The flaps increase their diameter to "full afterburner".
As the RUD is moved from?1080 to 112? on the PURT-iF (sym. 7 Ye) scale
a;he flaps retain the "full afterburner" diameter because the BR-3A (aym. 44Ye)
slide moves onto the fixed resistance section.
SECRET
J90 FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DIS
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066ROO0200020001-6
f t
SECRET 50X1-HUM
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEA
Page 127
If the RUD is moved backward into the section between 1080 and 780 on
the PURT-1F (~ym 7Ye) scale, a mismatch occurs in the follow-up system such
.that a current flows in the winding of relay RPS-5 in the opposite direction.
Contacts L and P of this relay close,
their diameter to "minimum afterburner" and remain in this position until'the
73? mark on the scale of the PURT-1F.
GA-164M (sym. 153M) is broken by contacts 3-2 of relay b. The flaps reduce
of the relay (sym. 37M) via the."afterburner" AZS (sym. 29Ye).
When the relay (sym. 37M) operates a supply is provided to terminal 3
of the GA-164M (sym. 153M) plug. The supply circuit to terminal 2 of the
providing a supply to the winding
of relay a in the KVS-1 (sym. 151M). When relay a functions its contacts
3-2 close and complete the circuit from the aircraft network to the winding
With further movement of the RUD the flaps take the "maximum" position.'
At revolutions corresponding to 65% of high pressure rotor revolutions
transfer switch BFO-l opens its contacts, but the relay (sym. 38M) is ,.
.self-supplied through the contacts of the BFO-2 transfer swtich. At
flaps take the "full afterburner" position.
revolutions corresponding to 60%,of high pressure rotor revolutions the
,contacts of the BFO-2 transfer switch open and no current flows in the' relay
winding.(sym. 38M). The relay (sym. 28M) is energized by way
Page 128
of contacts in relay symbol and relay symbol 29M. Contacts 2-1-open
relay symbol 28M, but its contacts. 6-5 cut in the supply to terminals 3
and 2 respectively of the.hydraulic-electric valve (sym: 153M) plug. The
SECRET
NO FOREIGN DISSEM/NO IISSEM ABROADjCONTROLLED_DISSJW
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066ROO0200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
NO FOREIGN DISSEM'NO DISSEM ABROAD/CON' *-1
Switch symbol 14$M is used. to cut in the emergency system for controlling
the nozzles. In this event relay v in the KAF-13D functions. If the RU!)
is beyond the 'full afterburner" position (100? on the PURT-1F scale), a
current is supplied to terminal 2 of the GA-164M (sym. 153M) plug through
fuse IP-5 (sym. 154M), contacts 2-1 of relay symbol 28M and contacts45-4 of
relay F2. The flaps will have the diameter. used for "maximum."
If the RUD is set beyond the "full afterburner" positon (from 1000 to
112? on the PURT-1F scale) a supply is provided to the winding of relay F
in the KAF-13D (sym. 97M) by way. of the "afterburner" AZS (sym. 29Ye),
contacts 2-3 of relay Z, transfer switch 4 of the FORT-lF (sym. 7Ye), and'
contacts 6-5 of relay v. Relay Fl operates and closes its contacts 2-3,
supplying current from the aircraft network to the winding of relay F2
through the contacts of lock switch D of the KAF-13D box. Relay F2 operates3
and, through its own contacts 2-3 and the-closed contacts 8-9 of relay V.
furnishes supply to terminal 2 of the plug for the hydraulic-electric valve
GA-164M (sym. 153M). The supply circuit to terminal 3 of the GA-164M plug
is broken by contacts 5-4 in relay F2. The flaps will have the diameter
setting for "full afterburner'.'.
Page 129
There is a delay in the cl9ange in diamerter of the flaps between
positions of the RUD for "minimum afterburner" and "full afterburner,'"
in the event of emergency control, from the "full afterburner"
position to the stop .(1000 - 112 on the PURT-1F dcale).
When lock switch.A is set in the closed position (look switches B, V,
open),-and with the functioning of-relay Fl, the supply circuit to the.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSU
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
i oUX1-HUM
SECRET
NO I'OREICN. DISSEM/N0 DISSFr.4 ABRQ. n jcvMrrivx,.UaD Dri ,
winding of relay RVl 'is closed. In 0.5 second this'relay, with contacts
3-2, interrupts the supply circuit to the winding of relay RV2 and the
winding of relay s. Relay 'a .has no current and, through its normally?close'd
contacts 1-2 stpplies the winding of relay F2. Relay F2,operates and its
contacts 3-2 connect a supply to terminal 2 of the GA-164M (sym. 153Nt) valve,
after a delay of 0.5 second.
When lock switch B is set in the closed position (A, V) G open) the
only after the contacts of relays RV1 and RV2 drop out (eahh of which will
delay equal to 1 second, and this will close its normally closed contacts
signal for shifting, the flaps will be delivered from relay s with a time.
When V is set in the closed position (A) B, G open), the signal for
drop its contacts after 0.5 second).
delay equal to
only after. the,
contacts in'
When G is set in the closed position (A, B, V open) the signal for
0.5 second) have dropped out.
shifting the flaps will be supplied from relays with a time
1:5 seconds. This relay closes its normally'closed contacts
contacts of relays RV1, RV2 and RV3 (each of.which drops its
in.0.5 second) have dropped out.
contacts of relays RV1, RV2, RV3 and RV4 (each of wl4ch drops its contacts
to 2 seconds. Relay s closes its normally closed contacts only after the
shifting the flaps will be delivered from relay s with a time delay equal
Pa e 130
When D is set in the. closed positon, and when relay Fl operates,.the
circuit supplying the winding of, relay RV1 is broken and, in 0.5 second,
through contacts 3-2, interrupts the supply circuit to the winding of,
?123
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NO FOREIGN .DISt'.~M/NO DISSEM ABROAD /CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
N'O FOREIGN DISSEM/NO DISSEM ABROAD/GUBIA'J"" w m10QZ A
relay RV2. Relay RV2'now has no supply and in 0.5 second, through its
contacts 3-2, breaks the supply circuit to the winding, of relay d. Relay d
goes dead andthe.normally closed contacts 1-2 provide a supply path to
electromagnetic valve for pump NR-22F (sym. llYe) and the "afterburner"
pilot light (sym. 30Ye) with a delay of 1 second.
When lock switch Ye is set in-the closed position; the signal. for cutting
in the electromagnetic valve of the NR-22F ax3 the supply to the "afterburner"
pilot light will be delivered with a time delay equal to 2 seconds from
relay d which closes its normally closed. contacts onl~f after the contacts
of relays RV1, RV2, RV3 and RV4 (each of which drops its contacts in 0.5
second) have dropped out.
There are various combinations of settings for lock switches A, B, V
and G (flap time delay) and for D and Ye (fuel time delay) so that different.
time delay variations for both flaps and fuel can be obtained.
The engine control lever is moved away from the "minimum afterburner"
stop to cut out the afterburner regime. This results in cutting out relay
F1 and opening contacts 2-3 of this relay.
The pilot light which signals that the afterburfl r is cut in is
extinguished, the supply to relay F2 is cut off and the electromagnetic
valve for the NR-22F pump (sym. llYe) for the afterb};:ner is disconnected.
Page 131
4. Instruments' for controlling engine operation
Instruments included in the group controlling erl;ine operation include.
the remote electrical tachometer, ITE-2;
exhaust gas thermometer, TVG-llT?;
the remote electrical oil,guage, DIM-8T.
121#
SECRET
NO FOREIGN DISSEM(NO DISSEM ABROAD/CONTR.JLLED DISS't
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1 .HUM
110 FO1tEIGN DISSEM'YNO DISSEM ABROAD/COHTHULLNV DIM
electrically connected only to each other and are not connected to the air-
the indfGator (sym. 30K);
the low pressure rotor transmitter, DTE-1 (sym. 31K);
the high pressure rotor transmitter, DTE-1 (sym. 32K).
The indicator..(sym. 30K) and the transmitters (symbols.311C and 32K) are
craft's electrical network.
The ITE-2 ;consists of:
The TVG-11T consists of:
the temperature indicators (sym. 27K);
the receiver of exhaust gas temperatures (sym. 29K);
the thermocouple connecting block (sym. 28K).
The TVG-11T elements are connected electrically only with each other
and have no connection with the electrical system in the aircraft.
and contacts i1-13 of the relay Q's'.Ymbol 32R).
400'cycle's, from converter PO-750A (sym. 1R) through fuse SP-5 (sym. 22Ye)
the primary winding of the transformer,(23Ye) is supplied with 115 volts,
the indicator, UI1-$. (sym. 16Ye);
the oil guage transmitter, IDT-8 (sym. Me);
the 115 volt/36 volt transformer (sym. 23Ye).
The elements of the DIM-8T are electrically interconnected. In addition,
Information with respect to the purposes for which the instruments are
intended, as well as the scale graduations on the indicators, is given in
the chapter on "Instrumentation"-of this description.
125
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLEb DIS M!
Page 132
The DIM-8T consists of:
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1 -HUM
NO FOREIGN DISSEU/NO D' ;SEM AB
Pad,= 133
5. By-pass air loor control system
General information
Two symmetrically located doors, on the port and starboard aides of
the fuselage, between frames 2 and 2A, are installed in order to prevent
compressor stalling action in the inlet ducts.
The doors or flaps, open outward into the airstream. The doors are
controlled both automatically and manually.
The electrical' devices which do the work-of controlling the doors are
listed in the table.
126
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSESf
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 J /1_._.. A._._.__.._ J L_.- P9_1_--- ^^A^/l1 A ,A l1 /' 1A flfl Y- nr.n/'~/'~1'1111111I111nne. 111111 A r' )X1-HUM
NO FfPrT!'V DISSEM/Na DISSEM ABROAD/CONTRU1,i,J!ill 1 i M
.u b o i- u w ...r .~ .-0 4 a
0 $4 CL
? O q i7 V w .O N o
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r
tj 4j 0 ON
>% 41
*j 41 Vj to 41 41
tb a' .4 9-4 X Nr+ w y ..a 1 W 4 x p aa0
0
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROT4 D DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SE(: ET 1)JX1-HUM
fT1 fi 1 Tr' 1)TSSEM/NO'DIScP-r AR-Pnen CONTROLLED bTSS'M
The door mechanism is interlocked with the eng.ne control lever and
with the aircraft'control stick.
Electrical circuit operation
For automatic control of the by-pass air doors the transfer switch
(sym. 120M) is set in the "automatic" position".
When flight speed corresponds to about Mach 1.5 the supply from the
aircraft network is distributed from terminal B of the filter (sym. 50M) for
Mach number controller through the AZS (sym. 38M) to the relay Minding
(sym. 126M). The relay functions, closing contacts 2-3.
Positive voltage from the aircraft network.is fed to the electricals
hydraulic valve GA-184 (sytm. 121M) through AZS (s'rn 33M), the' contacts
of the transfer'switch (sym. 120M),
Page 135
contacts 2-3 of the relay (sym. 126M) and contacts 2-1 of the relay
(sym. 141M). The doors open.
In order to provide for stable operation of the aircraft after acceler-
ation to the speed corresponding to a Mach number of about 1.5, and when the
afterburner is cut in, the relay operates (sym. 141M), contacts 1-2 of
the relay (sym. 141M) open and the supply fed to terminal 2 of the electrical-
hydraulic valve (sym. 121M) plug is interrupted. The doors close. In the
event the afterburner is cut out at these speeds the' relay (sym. 141M)
.releases and supply is fed to thj.electrical-hydraulic valve (sym,. 141M)..
The doors open.
The doors open when the aircraft is in manual control and the aircraft Ak,
noses up at an angle of inclination corresponding to'a 200 stabilizer angle
128
SECRET
S0 FOREIGN DISSEM/N4 DIS
SEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
TO rifRFYfrN DISSEM/2Q DISSEM ABROADicuv*.L cvur ~. ~~
(large arm) of 100 (shall arm) and for an aircraft,speed corresponding to
Mach 1.5..
In this /case, the supply is provided to the electrical-hydraulic valve
(sym. 121M) from the aircraft network through the PZS (sym. 33M), the
contacts of the transfer switch (sym. 120M), the closed contacts 2-'3 of the
relay (sym. 126M) and the closed contacts 3-4 of the microswitch;(sym. 114M).
In the event the.do6rs are controlled manually the transfer switch
(sym. 120M) is set in one of the necessary positions: "open" or "closed,".
Page 136
When the position of the transfer switch (sym. 120M) is "open" asupply
a furnished to the electrical-hydraulic valve (sym. 121M). The doors open.
In the "closed" position the supply to the electrical-hydraulic valve
(sym. 121M) is broken. The doors close.
The doors can be opened or closed manually without regard for air-
craft speed corresponding to Mach 1.5-
6. Cone control system and signals.
General information
The system is designed to control the cones, a-change in the position
of-which ensures stable operation of the power plant at super-sonic speeds.
Operation of the cone control system and'signals is accomplished by'`the'
129
SECRET.
.NO FOREIGN DISSEM/NO'DISSEM ABROAD/CONTROLLED DI
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOREIGN DISSEM/N0 DISSEMw:j9R AVIUURTAUbl" N
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NO FOREIGN DISSEM/NO DISSE~11ABROAD JCONTROL DIS.M
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066ROO0200020001-6
50X1-HUM
SECRET
f
1(0 Ft1~>+ Tr?
DISSEM/N0 : I)IS91 PvM A'n /r0NTR LLED DISISTV
The aircraft air intake has a three-position ccce.
Rigging in or rigc;ing out the cone in flight it carried.out auto-
/
matically (depending upon the increase in the velocity head) or manually,
by setting the transfer switch to the-corresponding -)osition.
When the switch is set for automatic control, aid when the aircraft
speed is equal to that worked out by a special controller for the first
position of advance of the cone, electrical-hydraulic valve GA-185 operates..
The cone advances to the first position.
When the aircraft attains a speed equal to that worked out by the special
controller for the second position of advance for the cone, a second
electrical-hydraulic valve, GA-185, functions.
Page 132
In this case both electrical-hydraulic valves ha"e current supplied
them. The cone moves out to the second position . to full speed.
With a reduction in the velocity head the controller for moving the
cone outward to the second position is cut out. The Lane moves inward to
the speed value for the second position.
With a further speed decrease the controller for-roving the cone out-
ward to the first position is cut out. The cone is caipletely rigged in.
Electrical system o eration
When the SZS (sym. 38M) is?cut in and the tranafex switch (sym- 54m) is
to the "automatic" position tt b-`voltage from the aircraft network is fed
to contact 5 of the relay'(sym. 126M) and contacts 5 and 2 of relay symbol
127M.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABRO1'?!D/CONTRO LED DISS
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
? qL' V Rl'l l _
NO FO1 E1? N DISSEM/1 O DISSEM ABRuAp/UUVTiVLLrjv lli
]33
SECRET
NO FOREIG14 )ISSEM/NO DISSEM ABROAD7CONTROLLED DI M.
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
When the controller (sym. 66M) contacts close the.supply.is fed to the
winding of.the relay (sym. 126M) through terminal B of the filter (sym. 50M)'
from the AZS?(sym. 33M). When the relay operates'it closes contacts 5-6
plug for the electrical-hydraulic valve (sym. 72M). The circuit supplying,
terminal.2 is opened. The supply through closed contacts 5-4 of the relay''
and a voltage from the aircraft network is. supplied to terminal 3 of the
(sym. 127M) is delivered,to terminal 2 of the plug
Page 140
for the electrical-hydraulic valve (sym. 128M). The circuit supplying'
terminal 3 is broken. The cone moves out to the first position.
When the controller contacts close (sym. 124M) a supply is furnished
the winding of the'relay (sym. 127M) through terminal B of the filter
(sym. 125M) from the AZS (sym. 38M). The relay functions, closing contacts
5-6 and 2-3 and the voltage from the.aircraft network is fed to terminal 3
circuit supplying terminal 2 is broken. The cone moves out to the second`
of the plugs for the electrical-hydraulic valves (symbols 72M, 128M). The
position.
symbol 128M. The supply to the'1e4ectrical-hydraulic value symbol 72M remains
circuit supplying terminal 2.of,,the plug for electrical-hydraulic valve
-break the circuit supplying terminal 3, while contacts 5-4 close the
When the controller contacts are opened (sym. 124M) the current i's
remgved from the relay (sym. 127M) winding. In this case contacts 5-6
. unchanged.
The cone moves back to the first position.
 _6V1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001NO FOREIGN DISSEM`JNO DISSEM_ABR inn7CUBTrViiw JJIS~uM
When the controller (sym. 126M) contacts are opened current is removed
From the winding df the relay (sym. 126M). In this case contacts 6-5 break,
,,he circuit sipplying terminal 2 of the plug for electrical-hydraulic valve
symbol 72M. The cone returns to the initial position.
Page 141
Manual control of the outward movement of the cone is accomplished by
setting the transfer, switch (sym. 54M) in the "manual", position and transfer
switch symbol 57M in one of three positions:
"Rig IN".
"Rig Out 1.5," "Rig Out 1.9,"
The supply to the terminals of the plugs for the electrical-hydraulic
valves (symbols 72M, 128M) is, in this case from the AS (Nym. 33M) and the
r osed contacts of the transfer switches (symbols 54M, 57M).
'he alternate sources of supply to the terminals of the electrical-
hydraulic valve plugs (sym. 72M, 128M) are the same as those for automatically
rigging out or rigging in the cone in the following cases:
closing of the
(rigging out);
closing of the
(rigging out);
opening of the
(rigging in);
controller (sym. 66M) contacts - la~t cone position
controller (sym. 12414) contacts - 2nd cone position
controller (sym. 12414) contacts l.st cone position
opening of the controller (sym. 6614) contacts - initial cone position
(rigging in).'
When the cone is rigged,out;to the first position: the terminal switch
(sym. 105M) operates and closes its contacts, feeding a voltage from the
aircraft network to-the pilot light (sym. 10414) through the AZS (sym.'33M)
and the, relay contacts 16-17 (sym. 86). The pilot light "cone rigged out"
).fights.
131
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSZS(
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 : CIA-RDP78-03066R000200020001-6 )X1-HUM
terminal switch open and the pilot light-(sym. 104M) goes out.
When the cone is returned to its,initial position the contacts of t
135
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DI ,.,,
? V 1''VMJ!iLtiry V100MM/MV V100bM A1jJUADfUUN't?JSVLIJLJJ VLLNv J
Page 142
7. Engine flight speed control lever interlock system
General information
Operation of,the engine control lever .(RUD) is provided for by the'
devices indicated in,the table.
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 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
IYU N9 fNN J f'N J)15bi M fe1VU D1o p;M ARR 4..+.
r
00 N -4 11 14
U L Qt
01 O t0 3i Q1 R~pj1l
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w
0 w 4J
W4 I
OU4 V
to 0
41 M 4J 4! N O Q k :~
0 -0
93 a dl d eOl) f+ .4J1 N
Z0
W -
a
Q 0
6 Est
.Z x
W" in P~'1
/w . 1. 0 M r4.
- .4
1#6
SECRET
RO,FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSIMM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
00
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO VAPVT(N DISSEMYNO DISSEM ABROAD/CONTROLLED DISSEM,
designed to prevent engine surge
of the cane contr?l system and the compressor anti-stalling flaps and is
The operation of this system takes place in parallel with the operation;
which can occur during high flight speeds at small engine revolutions.
the RUD is removed.
automatically, thanks to which the above indicated limitation of travel of'
Page 143
The engine control lever, interlock system is a stop device which is
moved forward with the aid of an electromagnet at speeds corresponding to
M ~ 1.5 and prevents the shifting of the RUD towards the "low gas19 stop-
under flight conditions such as these.
When the speed drops :(at M < 1.5) the stop along the sector is selected
In case of emergency the stop is selected by pushing the botton on
the sector, which is mechanically connected with the stop.
Page 144
Electrical system operation
When flight, speed corresponds to M k 1.5, and MR-1;.5 controller'
(sym'. 66M) causes the relay (sym. 116M) to operate. Through contacts 5-8
this relay feeds terminal 2 of the plug forthe.eledtromagnet (sym. 75M)
from the AZS (sym. 38M). Contacts'5-4 break the eircruit supplying'
terminal 1 of.this same plug..
The electromagnet functions pi}d,.moves the atop forward.
Y. .
When speed'is reduced (M < 1.5) no current flows in'relay
and the supply circuit to-terminal 1 is,broken.
electromagnet pulls the-stop inward.
137
symbol' 16M
NO FOREIGN DISSEM/NO DISSEM ABROAD /CONTROLLED DISST
--- -.--- --. _ -_. r _.
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
No 14PORFTGN DISSEMhO DISSE tA}3R(}AD uva-
)IR
Page 1,,
8. Engine fuel supply system and a gnats
General information
The system is designed to supply fuel to the engine and to signal fuel
depletion.
The devices indicated in the table are involved in the operation ofthe
system.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD'/CONTROLLED DISSE1
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
lfn rnnrTnTT' DISSEM'(NU DI55L';P?1 ASRUW/C;ULVInVVLML L.-ae:,xi
No. No, of posit. Name OfItem Type Quan..
ion in electr- tity
14M Circuit breaker, "Pump 1" AZS-5 1 Switchboard, port
console, cockpit
5M Circuit breaker, "Pump 2" !AZ5-5 1 same
188 Relay TKYe-21PD 1 Relay box, frames
Green
Page 146
6M Contactor KM-50D - 1 Contactor block, star,
board side, frames
12-13
1495A?2
frame 16A
5K Pressure signal SD-3 1 Port side fuselage,
lOM Filter J F-37VT 1 Port s isle _ fuselage,
12M Contactor ILM-50D 1 Same
4K . Pilot light, "Pump 3" SLTs-5T .1 Instrument panel,
Green starboard section
9M Circuit breaker,' "Pump 3" IAN'S-S 1 same
6K Pilot light, "Pump 1" SLTa-S1 1 Same
3K Pressure signal SD-3 1 Fuselage, lower,
17M Contactor KM-50D 1 Same
15M 1 1. Filter I 1F-37VT 1 Lower section fuse
lage, port, frames.
12-13
16M Pump for tank group 1 f422A 1 Fuselage, underneath,
Lower section fuselag
between frames 18-19
422A 1. Fuselage, port side,;
frames 21-22
.13K Circuit brea1 "tank press-AZ'S-S, 1 Switchboard,. port
s
'
ure signal
cockpit
139 console,
7M Filter ~F-37VT I Same
NO FOREIGN DISSEM/N( aISSEWAB'RQAD CONTROLLED i7T rcy
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
IM Fnutr.Ta'u DISSEM/NO''biSSF11 ARnr1A11TiCONTRO L DIS `'VT
19 1116K Pilot light "depletion
suspended tank'-
20 115K
21
23 '14K Float transmitter
Pressure signal
4 5
SLTs.51
Green
middle section of
instrument panel
SDU2.0.35 1 Port, lower section
fuselage, frames 20.
Port side fuselage$
f ramp 16A
22 12K Pilot light "Tank in use" Red 1 Display T-6, instrum.
21 1K Pressure signal .SD-3?
t z
24 48K Pilot light "500 liters
remaining"
Page 148
;27 21K Consumption gage; ;trans
mitter rY.?.
consumption gage
26 f20K Thyratron cutout
i (or interrupter)
25 19K Indicating instrument,
140
ent panel
SE-16 7 1 Upper fuselage, port 1
side, frames 16-17 li
RrS16A.?4 1
PT.501
RTS16A?4 1
Instrument panel
Starboard side fuse.
lage, frames 12-13
Port, lower section
fuselage, between
frames 20.?22
SECRET
NO FOREIGN DISSEM/NO DIS
SEM AfROAD/CONTROLLED DISS^x
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
Fuel is'stowed in the aircraft in seven fuselage kerosene tanks, as'
well as in one suspended tank and in the wing tanks - aeotiona.
' _ SECHL'T'
NO FORETGN DISSEM/,NO DISSEM ABRnnn/C 1`RULLdU Drr
Page 149
Electrical system operation
The pump (sym. 16M) for the ist group of fuel tanks is energized from
the aircraft network through terminal 2 of the pump plug and a fuse (sym.
24E) in the. power unit/through the closed contactor (sym. 12M).and a filter
(sym. 15M). The contactor (sym 12M) operates and closes its contacts when
a supply is furnished to its winding from the aircraft network through the
AZS (sym. 14M) and when the aircraft network is connected to the airdrome
supply or to?the generator (in this case the supply is furnished to the
,relay (sym. 18E) winding, the relay operates and closes contacts 3-2).
The pump (sym. 8M) for the 2nd group of'fuel tanks is energized by the
delivery of a supply from the aircraft network to terminal 2 of the pump
plug through a fuse (sym. 20E), the contactor>(sym. 6M) and the filter
(sym. 7M)?
The contactor contacts close when the AZS (sym. 5M) is closed and
voltage from the aircraft network is supplied to the contactor winding.
The.pump (sym. 11M) for the 3rd group of fuel tanks is energized by
141
SECRET
NO FOREIGN DISSEM/1tO,DISSEM !L ROAD./CONTROLLED DIS Z$
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
(sym. 17M) and the filter (sym. lOM).
the delivery'of a supply from the aircraft network to terminal 1 of the
pump plug through a fuse,(sym. 18M), the closed contacts of the contactor:
. from the aircraft network is supplied'to the contactor (sym. 17M) winding.
r,... 'Pa e 150
The contactor contacts close when the AZS (sym. 9M) is closed and voltage
 ___ 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
LW r'tJN.;tfDN 111751~M/N1J ll155?M ABROAD /C ,..,.
When the fuel is exhausted (whin there is a drop in pressure in the
fuel line) from the tanks in the lot group the transmitter contacts in the
pressure signal-transmitter SD-3 (sym? 5K) close and "negative" is supplied
to the pilot light (sym. 6K). The pilot'light lights.
When the fuel in the 3rd group of tanks is exhausted the SD-3 ,(sym.
3K). transmitter contacts close 'and the pilot light (sym. 4K).lights.
When the fuel in the tank suspended from the fuselage is gone the
pilot light (sym. i6K) lights because the SDU2-0.35 contacts (sym. 15K)
close and "positive" is supplied to the pilot light from the aircraft
network from the AZS (sym. 13K).
When the pressure in the line between the engine and the service
tank drops below 0.3 kg/cm2 the SD-2 (sym. 1K) contacts close and "positive"
from the. aircraft network is supplied to the,signal pilot light (sym. 2K)
through the AZS (sym. 13K) and contacts 16-17 of the relay (sym. 15Y'e). The
pilot light lights.
When 500 liters of fuel remain the contacts in the float transmitter
(sym. 14K) close and feed "negative" to the pilot light (aym. 18K). "positive"
is supplied to the pilot light from the AZS (sym. 13K). The pilot light
lights.
Page 151
A cumulative fuel consumption meter, RTS 16A-4, is installed in the
aircraft to measure the amour t? .of fuel consumed by the engine.
The indicating instrument''t the uonsumption.meter permits visual
observation of the amount of fuel remaining in the aircraft tanks with
properly operating fuel lines.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLUID DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOREIGN DISSEM/N0,DISSEM ABRUAD/UVa
. k,
The consumption meter complex consists of a transmitter (sym. 21K),
the indicating instrument (sym. 19K) and the thyratron cutout PT-56M (sym.
20-K).
The indicating instrument (sym. 19K) and the transmitter in the con-).
(sym. 21K) are electrically connected with the thyratron
'cutout (sym. 20K). -
The thyratron cutout (sym. 20K) PT-56M supplies 115 volts, 400'cycle
alternating current from the converter PO-750A (sym. 1R) through contacts
13-14 of the relay (sym. 32R) and fuse SP-5 (sym. 30R). In emergency opera
tion the supply is from the PO-750A (sym. 2R) converter.
Switchboard, port
console, cockpit -
J
Nose section fuselag
port, underneath,.
frames 20-21 -
Switchboard,'port
I console, cockpit
11
SECRET
NO FOREIGN DISSEMII30-'tISSEM ABROAD/CONTROLLED DISS79
Symol `_.Name of item Type Quan
In order to shut off the main fuel line supplying the engine (when
dismounting aggregatesand in cases of emergency)-before fuel enters the
engine, (there is a shut-off with an electric.-pneumatic valve,?`(sym.
va lve!1
52M Electrical pneumatic
Button 01EinginiR shutr&o[:
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 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
'Page 153
Electrical system operation
The electrical pneumatic valve to cut in by pushing the button (sym. 33M). In
this case a supply to terminal 1 of the valve plug flows from the aircraft netowrk
through the AZS (sym. 9K) and the closed contacts inothe push button (sym. 53M)
144
nt GxT SSFty[ A 2Fr A", ^,T ,: }E~ 1 TSSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R0002000200016'1X1-HUM
NO FOPP.TRN DISSEM/NQ DTIZcFe3 At~nn a n--nn~tTRnT,T.
10. Fire protection system equipment
General information
The sy,stem is designed to warn of fire in the engine compartment and
Type
Quan-
tity
Tail section fuse-
lage, frame 29
Switchboard, port
console, cockpit
. Page 1551,
Electrical system operation
The I0-2Ms ionization fire signal device Is to signal the appearance
to put the fire extinguisher tank in operation.
The.eleckrical devices given in the table ensure operation of the
fire protection system equipment...
and disappearance of flame 'in ',tbe aircraft engine compartment.
.The signal device's. transmitter is a heat-resistant metal tubed The
transmitters are,installed on special ceramic insulators.
The operating_;p .ncipls of the IS??2MS is based on the property of
chemical reaction..'. 145
conductivity of flame resulting from 1 ization which accompanies a flaming
fiECRI, '~
110 FOREIGN DISSEM/NO iISSEM j.'ROAD/CONTROLLED DISC
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 tifX1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/NQ DISSEM ABR6AD/CONTROLLED SSIM
The IS-2MS signal device functions only when flame appears in the
space between the transmitter and the aircraft masse The IS-2M3 signal
device will/not react to a rise in temperature. The IS-2MS signal device
is an electronic device and operates practically instantaneously.
The primary
winding of the transformer in the IS-2MS electronic
amplifier (sym. 24K) is connected to pins 2 and 5 of the plug connector
shR2OP5NShlO and is supplied with a 115 volt, 400 cycle alternating
current from the PO-750A converter (sym. 1R) through contacts 1~-14 of
the relay (sym. 32R) and fuse SP-5 (sym. 55R).
The grid leads of the IS-2MS device's twin triode are connected to
the aircraft hull.
"Positive" rectified, stabilized voltage is fed to the leads to the
transmitters via terminals 1 and 2 of plug ShR20P2NGC. LT-N: The plural
"transmitters" is translated exactly
Page 156
In the event flame appears in the space between the transmitter and
the mass of the aircraft the air space becomes electrically condutive.
This is equivalent to connecting a resistance on the order of 5 to
6 megohms between the grid and the plate of the tube. A positive potential.
is supplied to the grid. The plate current rises and reaches a value
such that the relay functions. When the relay functions a supply is furnished
to the "fire" pilot light (syn. 25K) from the aircraft network through the
AZS (sym. 9K), the closed contacts of the amplifier relay (sym. 24K), and
contacts 1-2 of the relay (sym.' 15K).
l6
SECRET
NO FOREIGN DISSEM/NO DISSEMABROAD/CONTROLLED DISSE31
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
%A VAPr+'T(i DISSJ!M/NU V1SSSM ABHUAD/UVIV"lnv?J M a+.aUuu.J .
The button.(symn. 22K) must be pushed in order to put the fire
om
is
4...,
fr
extinguisher tank into operation. in this case the supply
aircraft neiwo.rk to the tank (sym. 23K) via the AZS (sym. 9K) and the
closed contacts of the push button.(sym 22k).
Page 157
111, System' for measuring pressure in the"main'snd bbestet_hydtaulic_
systems and ~ fiignels
General information
A remote electrical pressure gage, 2EDM-250,,.serves'.to measure
the pressure: of the hydraulic fluid in the hydraulic system.
Included'in the 2EDM-250'electrical pressure gage complex is:
the DV-250' electrical pressure 'transmitter (sym. 12K) in the
'main hydraulic system; '
the DV-250 electrical pressure transmitter (sym. 17K) in the
booster hydraulic system;
the remote electrical indicator 2EDMU-250 (sym. 11K).
The DV-250 transmitters (sym. 12K, 17K) are installed between
frames 21-22 starboard, below, and at frame 20, port, respectively.
The 2EDMU-250 electrical indicator'(sym. 11K) is located beneath
the starboard movable section of the instrument panel.
The transmitter and indicator are electrically interconnected. In
addition, the indicator (sym;..'11K) is supplied with a voltage from the,
,aircraft network through the AZS (sym. 13K) "EDM, gidr. ost, gor. sign.
podn.'rash. bakov" (T.N.: "EDM" is the remote electrical pressure
gage; "gidr" is hydraulic; "sign." is signal; "bakov" is "of tanks"; the
others are uncertain and can not be fully reconciled with that function.
of 13K shown in the table on text page 147.)
147
SECRET
NO FOREIGN DISSEMLNO DISSEM ABROAD/CONTROLLED DISS1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 50X1-HUM
NO Fnnrr.N DI: ;EM 00 DISSEM ABROAD
The way in which lack of pressure in the booster and in the main
P ..p
hydraulic systems is signa]led results from the operation of the
devices incyicated in the stable.
Page 158
t- No.
Symbol
Name of item
Type
Quantity
Location
l
83M
Circuit breaker "booster
system cutout, hydraulic
signal"
5
1
Cockpit, starboard
rear switch. I M1 i
board
2
43K
"Booster" pilot light
SLTa-51
Ye:` low
Instrument pan.
el, starboard
section
44K
"Main" pilot light
SLTa-51
Ye! Low
1
Same
4
85M
i
Relay
Relay box be-
hind Instru-
ment panel,
starboard,
frame 6
45K Relay
Pressure relay
TKYe.21PD 1 Relay box,
frame l1, in
cockpit
Fairing,
between frames
31-31A
Electrical system operation
When the pressure in the main hydraulic system drops to 16S kg/cm2
relay GA-135T (sym. 46K) operates and supplies "negative" to the pilot
light (sym. 44K), while "posit%ye is supplied from bus number 3 of the
rear electrical switchboard of the starboard conso'+a through the AZS
(sym. MD. The lamp lights.
1148
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONT)tOLLED DISS
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '1X`1-HUM
the GA-135T hydraulic relay (sym. 60M).
of the relay (sym. 45K) TKYe-21PD winding is broken by the contacts in,
supplied to it through contacts 1-2 of the relay and the nagative circuit
n FnFrC.N `fi~S
Page 159
When the pressure in the booster hydraulic system also falls to
165 kg/cm2 the pilot light will burn (sym. 43K) because "negative" is
D
booster hydraulic system drops, the contactor winding (sym. 70M)circuit.
When the switch (gym. 89M) is cut in and the pressure in the.
O-NZ of the hydraulic relay (sym. 46K). The pilot light (sym. 441() goes out.
the negative circuit to the pilot light (sym, 44K) is broken by contacts
When the pressure in the main hydraulic system rises to.195 kg/cm2
NP-27 (sym. 7914) begins to operate*
is closed and the contactor functions and supplies current from the bus
of the power unit to terminal 2 of the pump station plug. Pump station
contacts O-NZ in the hydraulic relay (sym. 60M).."The contactor carries
the negative circuit' to the contactor (sym. 70M) winding is broken by
When the lressure in the booster hydraulic system rises to 195 kg/cm2
no current and the supply to pump station NP-27T (sym. 790 is opened.
to the winding of relay symbol 45K through' contacts O-NR.
The relay (sym 45K)' operates and opens the negative'circuit to
the pilot light (sym. 43K).-,,The pilot light (sym. 43K) goes out.'
At the same time the hydraulic relay (sym. 60M) furnishes "negative"
Page 160
Operation of the system for coit:ro,lling the cutting in and cutting
12. Pump station control system
General ini rmation
out of the pump station is provided for by the devices shown.in the table.
SEC: ~T
NO FOREIGN DI3SEM/NO DISSI.i ADROAD/CONTROLLED DISSZf
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6'1X1-HUM
NO FOREIG t DISSEM/NO DISSEM .1` v j~1.==o
Symbol Name of item Type Quan- Location
tits'
Pump station
Forward fairing of
fin, frames 32A.
33 ti
Contactor block, star.
board side fuselage,
frames 12-13
60M
Pressure relay in
hydraulic system
GA-13ST 1
89M
Switch, "P6mp
Station"
87K 1
IP-75M 1
110M
, , Fuse
IP-5 1
Back fairing
frames 30-31
Forward switchboards
starboard console
Starboard side fuselage,'
frames 11-12
Pump station NP-27T is installed in the booster hydraulic system
to ensure landing with a locked (zakiinennyy) engine. It is cut into
the system automatically when the pressure in the booster system drops
to 165 kg/cm2 and cuts out when the pressure builds up to 195 kg/cm2.,
Electrical system operation
Pump station NP-27T (sym. 0 79M) is cut in when a supply is provided
from the aircraft network to terminal Z of the plug for the NP-27T via.
the fuse (sym. 71M) and closed contactor contacts (sym. 70M). The
contactor contacts (sym. 70M),close when the switch (sym. 6914 is cut
in and the pressure in the hydraulic system drops to 165 kg/cm2. In
this case contacts ('0"-"NZ") in the relay (sym. 60M) close and supply
current from the aircraft network to the contractor (sym. 70M) winding
through the fuse (sym. 110M), the transfer switch (sym. 69M) contacts and
the relay (sym. 60M) contacts.
1:50
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTPOLI,ED DI8 F
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1 -HUM
NO FOREIGN DISSEM/NO DISSEM ABR
When the pressure increases to.195,kg/cmZ contacts "0"-'!NZ" in the
relay (sym. 60M) open and the supply circuit to station NP-27T is broken.'
The devices which r ensure system operation are given in the table.
'Page 162
Symbol Item ( Type quantity Location
General information
Page 163
83M Circuit breaker, AZS-5 .1 After electrical switch
'Stabilizer and aileron booster control system
,cutout, hydraulic cockpit
booster system board, starboard console,
system signal'
90M Push button 204K 1 Horizontal section,
TKYe- 1 Relay box, frames 31A-32,
I 52PD , dorsal , section of fin
hydraulic. valve
Back fairing, fuselage,
between frames 32-32A
26M Transfer switch 88K 1. Horizontal section port
console, cockpit,
TKYe- 1 Relay box,''between
52PD frames 15-16, port side
27M Electrical- GA-1905 "I Lower section fuselage,
hydraulic vai'v~. between frames 20-22
hydraulic valve
Longitudinal and transverse control of the aircraft is carried out
from the control stick through non-reversible boosters supplied from the
151
..izer.is controlled with the aid.
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CQNTROLLED DISS^Jj
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
NO F( . RFTc N DISSEM/NQ, DISSEM ABR6ADjCOFT#UbbrjV Z.L-
of a two-chamber booster, BU-51M and an ARIJ-3V automatic device. The
,ailerons are controlled by two BU-45 boosters.
Electrical system operation
The stabilizer booster, BU-51M, is cut in with the aid of the
electrical-hydraulic valve (sym. 81M). When voltage from the aircraft
network is present there is a supply to terminal 3 of the valve (sym. 81M)
plug via the fuse (sym. 112M0 and the relay (sym. 8514) contacts 1-2.
Page 164
The aileron boosters, BU-45, are cut in when the transfer switch
(sym. 26M) is set to the "on" position.
In this case the aircraft voltage issupplied to termimaWi 3 of the
electrical-hydraulic valve (sym. 27M) for cutting.in the BU-45 booster
which operates-off the main hydraulic system, the supply coming through
the fuse (sym. 113M) and the switch (sym. 26M) contacts,
The aircraft voltage is, simultaneously, fed
o terminal 3 of the
electrical-hydraulic valve (sym. 82M) for cutting in the.BU-45 booster
which operates off the booster hydraulic system, the supply coming through
relay (sym. 84M) contacts 1-2.
V
When the push button (sym. 90M), which cuts in the AZS (sym. 83M),
is pressed the stabilizer and aileron boosters, which operate off the
booster hydraulic system, are cut off.
At the same time, supply-is provided for the windings of the relays
(sym. 85M, 84M). The relays function. Contacts 1-2 break the supply
circuit to terminal 3 of the plugs for the electrical-hydraulic valves
(sym. 82M, 81M) and contacts 6-S close the circuits supplying terminal 2.
The BU-45 aileron boosters are cut out by setting transfer switch
(sym. 26MI) "off". This opens the supply circuit to terminal 3 of the plug
for electrical-hydraulic valves (sym. 27M, 82M) and opens the supply circuit
152
to terminal 2. SECRET
NO FOREIGN DISSEM/NO DISSER ABT?OA.D/CONTROLLED DIS
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1u1_ 1 . IRA
62M
14. Stabilizer control system
Page 16
Genera,]. Information
Operation of the stabilizer control system is carried out by the devices given
in the table.
No. Symbol Name of Item Type Quantity
3
Laqe 166
rC
WO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED PI ' M
SECRET
ARt1-33-2N
series
73M Execution mechanism ARU-3V
ElectfUcal mechanism MP-100M
Circuit breaker, "AIU
automatic control"
AZS-5
Circuit breaker "~ARI.T
manual control
AZS-5
Transfer switch,
Manual-Automat Lc"
2SP-46
Transfer twitch, high
speed--low speed"
PN-154
Switch
Switch
Relay,
87'K
Location
Cockpit, starboard
side, frames 10-1].
Back fairing, fuse
lage frames 29-30'
Instrument panel
Back fairing, fuse-
lage frames 30-31
Starboard console,
cockpit, after
electrical switchboard
Starboard, after
electrical switch-
board in cockpit
Port console, cohkpit
Port console, cockpit
Forward- switchboard,
starboard console,
cockpit
PI{-4
WO-52M
I
1
Control stick'
Relay box, tail section
153
fuselage, frames 3LA-32
NO FOREIGN DISSEM/NO DISSEM ABROAD'/CONTROLLED DI
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R0002000200016'1X1-HUM
NO F0RFIQN DIS:uTM/NQ DISSEM ABROb/CONTAULLEW 4
5 6
86M Relay TKTe-56M 1
Relay box behind
instrument panel
frame 6
valve GA-1905 1 between frame 32.#
81M/ Electricai-hydraulic Back fairing fuse
15 78K
Display T-4, instrument
panel
ARJ-3V-2 series (green) 3. same
Pilot light for signal-
ling neutral position SM-30
of trim effect (green)
Pilot light for signal-
ling the large arm of the SM-30
Longitudinal control of the aircraft is obtained with the aid of the
control stabilizer, through booster BU-51M, wh1ch controls both positions
of the stabilizer simultaneously.
Page 167
The stabilizer control system includes the ARU-3V automatic device,
which automatically changes the transmission ratio. from the control stick
to the stabilizer and, at the same time, to the spring loaded mechanism.
The adjustment law carried out by the ARU-3V is a function of the
velocity head and the altitude and is determined by the aircraft. aerodynamics.
A spring loaded mechanism is installed in the stabilizer control system
to duplicate the aerodynamic forces on the control stick. The mechanism
duplicates the forces on the control stick in proportion to its deflection
and to the position of the arm in the ARU-3V aggregate.
The ARU-3V automatic device consists of theacuating mechanism,
the control block, and the position indicator.
At low instrument flight speeds at elevations of more than 10,000 meters
the position of the coupling rod is not dependent upon the instrument speed.
The load on the control stick is minimum, while thetabilizer deflection
1.5
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
i. JX1-HUM
SECRET
N1) Trmim(W DISSEM/N0 DISSEM ABR~rlm7cum~TOAa~D~~sw
At high instrument speeds and at elevations of from 0 to 5,000
'
is minimum.
meters the load
. on the stick is maximum, while the stabilizer deflection
Page 168
At intermediate altitudes of from 5,000 to 10,000 meters, the
rod stops, despite any further increase in the speed.
adjustment is achieved at an intermediate altitude, the actuating coupling
In the event an instrument speed less than the speed at the end of the
automatic device functions in accordance with the velocity head,'as
well as with the altitude.
the AR(J-3V automatic device. When the switch is thrown to the "automatic"
A switch, installed on the cockpit's port console, is used to control
ment panel,
initial position this is done ly a green pilot light installed on the 3nstrui
pulses and is'signalled by the ARU position indicator, while, in the extreme
The manner in which the automatic device carries out the adjustment law
is not a smooth one but, rather, takes place intermittently, in short
block. When the switch .s set in the "manual" position the actuating mechanism
position the actuating mechanism functions automatically from the control
manual pressure switch'is used.
is reset from the large arm to the small arm, and vice versa when the
The spring loaded mechanism, nerves to feed the aerodynamic forces.to the
stick in proportion to the angle of inclination, speed and flight altitude,,
The more the stick is displaced, the greater the spring compression
1;5
SECRET
NO FOREIGN DISSEM/140'DISSEM 18ROAD/CONTROLLED DISSIJj
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
and force loading the stick.
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R0002000200016 1X1-HUM
NO F(? R ;N DTSSEM/NO DISSEq AB
The MP-100M trindeer effect mechanism performs the aerodtiynam:b function
Page 1
of a trimmer, shifting at the desire of the pilot, the neutral position
of the loading meYism, which permits the in-flig:t longitudinal
balancing of the craft with respect to forces.
The rotational movement of the electric motor in the MP-100M is
converted into forward motion of a screw. The screw is retracted or
run,out, depending upon the direction of movement of the electric motor
rotor and moves the body of the loading mechanism which is connected
with it. When the body of the loading mechanism is displaced by the
amount of compression of the springs in the loading mechanism the load
acting on the stick is completely removed.
When the screw is in the limit positions microsvjitches function.
These switches are installed in the electrical mechanism and cut out the r-
electric motor in one of the positions.
The mechanism is controlled by pushing the transfer switch on the airy`
craft stick. When the transfer switch is pushed to the "dive" position,
and with the boodter cut in and normal pressure being delivered to
the hydraulic system, the forward end of the stabilizer is tilted
upward (with a free control stick).
In the neutral position the screw in the electrical mechanism MP-100M
operates a mieroswitch which cuts in the green pilot light "trimmer neutral"
on the instrument panel.
P. age IY0
Electrical system operation
The BU-51M stabilizer booster is cut in when voltage is present in the
aircraft network and when it is supplied to terminal 3 of the electrical-
156
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLL:SD DI-SSIJI
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
L - oriGttL'1
NO FO1 thN DISSEM/~p DISSEM ABROAD CO TROLLED DISSZ
hydraulic valve (sym. 81M) plug through a fuse (sym. 112M) and the closed,
contacts 1-2 of?a relay (sym. 85M).
The spring loaded mechanism duplicates the forces acting on the contr&]...
stick. Longitudinally acting forces resulting from pitching or diving
of the aircraft are removed from the stick by the MP-100M (sym. 58M)
electrical mechanism. Voltage is supplied to terminal B or terminal A
of the MP-100M (sym. 58M) plug through a fuse (sym. hUM), the closed
contacts of the switch (sym. 55M) and the correspondingly closed contacts
of the button switch (sym. 56M) in the "dive" or "pitch" positions.
Displacement of the neutral position of the loading mechanism occurs"
simultaneously with this above indicated action. The pilot light
(sym. 69M) which signals the neutral position for trim effect lights
up when the contacts. in the terminal switch for the electrical mechanism
MP-100M (sym. 58M) close at that instant which corresponds to the position
of the stabilizer and the, electrical mechanism MP-100M for the specified,
Page L71
When the AZS (sym. 87M) is cut in and the transfer switch (sym. 67M)
is set to the "autcmtic" position aircraft network voltage is fed through
terminal 4 of the control block (sym. 62M) plug to the voltage divider,
,the contacts of relay RS-3 end the armature "Ya" of the RPS relay.
The RPS. relay operates either according to t he altitude (Ya
closes with contact r-1 or according to speed (Ya closes with contact L),
according to:.the. misv : tch voltage from the potentiometric bridges,,
formed by the potentitnetricaltitude transmitters, the potentiometric speed
transmitters and the '.'edback pptentiometric in the actuating mechanism
157
SECRET
NO FOREIGN I CSSEMINO DISSEM AB'I.OAD/CONTROLLED DISSISM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
NO FOREIGN"DISSEM/NOtDISSEM ABROAD/C0NTROLLE DISSEM
of the ARU'-3V (sym. 73M) automatic device, which flows in windings 1-2,
3-4, 5-6 of the BPS relay in the control block (sym. 62M).
Winding 11-12 is a positive feedback element auddserves to stabilize
the operation of the BPS relay.
When contacts Ya and P close aircraft network %vvoltage is
supplied to the winding of relay RS-3 "BP" (large arv), while, when contacts
!Ca and L close, the voitagec is supplied to the "MP" (small arm) winding
of relay RS-3.
Relay RS-3 functions and, when the contacts are closed, supplies
a voltage from the aircraft network to the reverser winding of the MP-100M
electric motor through the AZS (sym. 87M).
Page L72
The microswitches for the run out and retracted positions of
the coupling rod in the actuating mechanism (sym. 73M) are the terminal
switches for the extreme positions of the mechanism.
Connected with the position of the coupling rod in the actuating
mechanism is the position of the slide in the potentiometer for signal-
ling stabilizer position in the, actuating mechanism AIU-3V (sym. 73M).
The slide picks off the voltage, some, or all, of the aircraft network
voltage(the AZS symbol 684 must be cut in) and supplies it to the indicator
(sym. 74M) arms.
When the transfer switch,,(eym. 75M) Is set in the "manual" position,
and the transfer switch (sym. 64M) for "high speed - Low speed" is set
to the desired position a voltage is'supplied to the corresponding winding
in the reverser of. the MP-100M electric motor in the actuating mechanism
v
(sym? 73M)
158
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD /CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
N0 FOREIGN DISSEM/NO. DISSEM APTIOAD/CONTMULMU ``'.
shaft arm in t4e ARtJ-3V (sym. 73M) actuating mechanism.
through the contacts of the actuating mechanism (sym.13M) microswitch.
At "la?cge arm", the pilot light (Gym. 78M) positive circuit closes
The pilot light (sym. 78M) burns.
Page 1-7a
15. Landing gear control system and signals
General Information
Thus, it is possible to?manually change the position of the coupling
2 3
.35M Transfer switch, "land-
ing gear retracted,"
"lowered" PPN-45
36M
Electrical-hydraulic
valve GA-1421
76M Relay TKYe-52PD
1:: 1
43M Microswitch KV-9A
Flight-landing
indicator
Pilot lights:
"nose wheel retracted"
No. Symbol Name of item Type Quantity . Location
The system is designed to lower and to retract the landing gear and
to indicate the position the landing gear is in.
The control and indication system.operation is carried out by the
devices listed in the table.
Circuit breaker; "land- AZS-5
ing gear control, housed"
34M
6
After electrical switch
board, starboard con-
sole, cockpit
Instrument panel,.
port section
Lower starboard section
fuselage between
frames 23-24
Port wing, rib 1
Relay box, cockpit,
frame 11 ?
Instrument panel, port
section
159
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSE1'
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 NO Fnp1 T(91 DISSEM/ O DISSEM ABROAD/CONTROLLED DISS7.4
Page 174
"nose wheel down" Green
"landing gear release"c. Red
"starboard down" , Green
"starboard retracted" Red
"port down"
port retracted" Red
$ 103
Pilot light "landing gear
release" SLTs-51
Red
Instrument' panel,
amidships section
3S
Terminal switch VIC-44
Port removable wing
section, between iribs
4-5
Terminal switch VK-44
Port removable wing
section, ribs 1-2
Terminal switch VK-44
Starboard removable
wing section, between
ibs 1-2
Terminal switch VK-44
Terminal switch VK2-14OR
r
Starboard removable
wing section, between
ribs 4-5
Frame (Possibly 6),
bottom
14
Terminal switch VK2-14OR
Pilot light MIS-39
.,...Page 175
Frame (Possibly 7A)s
bottom
Port landing gear panel
Pilot light W-39
Starboard landing gear
panel
17
13S Pilot light Kh3-39
Receptacle, nose wheel,
landing gear.
160
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS2
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 r-OX1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
_l
18
19
20
switchboard, star-
board console.
Page 176
Electrical system operatialf
in the "lowered" position.
The landing gear is lowered by setting the transfer switch (sym. 35M)
~r,unciJ
NO Fns? r4N DISSEM/NQ DISSEM ABROAD
b !,
-3
2S
Circuit breaker; "Landing
After electrical switch-
gear indicator, ANO"
A2;S-5
1
'."board, starboard con-
sole, cockpit
15S
Relay
TKYe-53PD
1
Relay box behind
instrument panbl
413
Circuit breaker
AZS-25
1
Fcrwara electrihal
This causes a voltage from the aircraft network at terminal 2 of the
electrical-hydraulic valve (sym. 36M) plug, the supply coning through the
contacts of closed AZS symbol 34M and the contacts of the transfer switch
(sym. 35M).
vvalve Plug ~(sym: 36M), while, at the same time) the supply to terminal
This results in a voltage at terminal 3 of the electrical-hydraulic
The landing gear is retracted by setting the transfer switch (sym.
55M) in the "retract" position.
2 is broken.
switch'symbol 5s- Pilot lights "nosewheel down," "port down," and "starboard
during take-off the landing gear is down, contacts 0-1'in the
The landing gear indicators operate as follors:
terminal switches (sym. 3S,'70 are closed, as are contacts 0-N3 in terminal
161
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD-/CONTROLLED DIS,-.
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
v~+C+itL' 1'
NO FORETGI DISSEM/N0 DISSEIt ARRUA NT Lhv Dr
in flight tae landing gear is retracted and pilot lights "part down,"
"starboard down," and nosewheel down" do not burn; that is, contacts
0-1 in the terminal switches (sym. 3S, 7S) and contacts O-NZ (sym. 58)
are interrupted. The pilot lights "port retracted-" "starboard retracted,"
and "nosewheel retracted" burn; that is contacts 0-1 in the terminal
switches (aym. 4S, 88) and 0-NR (sym. 68) are closed. The pilot
lights "landing gear release" on the P2S-2, symbols 118 and 10S are out
since the
Page 1
negative circuit has been broken by contacts
4 of the microswitch
(sym. 43M) when the flaps are returned to neutral.
NOTE. When the flaps are deflected from the neutral position the "landing
Upon
gear release" lights will not burn either because the circuit
-..A&ibh connects them to the aircraft network through the AZS
(sym. 2S) and contacts 0-2 of the terminal switch (sym. 75)
will be broken by the 1-2 contacts in the relay (sym. 76M)
which is in the self-feed position thrbagh contacts 5-6.
landing the landing gear is down, the pil tt lights "port down,"
"starboard down," and "nosewheel down" burn since tae contacts 0-1 in terminal
switches (sym. 3S and 78) and 0-NZ in terminal switch symbol 58 are closed.
The pilot lights "port retracted," "starboard retracted," and "nosewheel re-
tracted" ' on the PPS-2 (sym. are extinguished.
The "landing gear release" pilot lights will nxt be on. These lights
will burn if, during the landing, the flaps are det`'_ected Pram the neutral
position and the lending gear is retracted. In this:, event "negative"
is supplied to the lights through the closed contacts 3-4 of the microswitch
162
SECRET
iiO FOREIGN DISSE1i/NO DISSEL,t LEROAD/CONTR(LLED DISS J
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 I. -HUM
tt SECRET
CONTDAT.T.ED DISS ri
NO FARE?t N DISSE11l4A DISSEM AB
ROAD
closed contacts 1-2 of the relay (sym. 76M).
(sym. 2S), cont4ts-0-2 of the terminal switch (sym. 7S). and the normally
(sym. 43M),, while voltage from the aircraft network comes through the AZS
.The pilot lights (sym. 123, 1381 14s) for external indication of land
Page 18
ing gear being down will burn only when the AZS (sym. 41S) is cut in and the
relay (sym. 158) has operated. Then contacts 8-9, 5-6 and 2-3 in the relay
while contacts 0-NZ and 0-1 in the terminal switches (syin. 5S1 38, 7S)' close
(sym. 158) close the negative circuit to the external indication pilot lights,
the aircraft network supply circuits.
The devices.indicated in the table provide for the operation of the
Page 17
16. Automatic landing gear wheel brake release system
General information
automatic landing gear wheel brake release system.
163
SECRET
NO FOREIGN DISSEM/NO >OISSEt.ArnAen/CONTROLLED DISSEM.
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET 50X1-HUM
NO FOREIGN DISSEM/NO DISSEM ABROAD/UUMMAXV 4.,,tt
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1614
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS^j
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
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165
SECRET
a)
NO FOREIGN DISSEM/NO DISSEM Al.DAD/CONTROLLED DISSEM
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SECRET
SO FOREIGN DISSEM/1' j DISSEM ABROAy/uutiL ++~ ars~?~
Page 181
Electrical 8 stem Operation
Whhen1the brake lever on the aircraft control stick is pressed the air
enters the UP-22 (syti. 21M) from the pneumatic system. The electrical air-
cuit contacts are closed.
When the AZS (sym. 20M) is cut in aircraft network voltage is fed to
the terminals of the pneumatic valves UP-53/1-2 (sym. 22M, 23M) 92M) and to
the relay windings (sym. 93M, 134M).
Should there be a sharp reduction in speed, or should a "lock" occur
in one, or in both wheels of the main landing gear, true electrical-pneumatic
valves function (sym. 2214, 23M) as a result of the closing of the negative
circuit in one or both of the inertial transmitters (xym. 24M, 25M). The
air is purged from the brake chamber, releasing one or both wheels of the
main gear.
At the same time that the port wheel is releascithe relay (sym. 93M
unctions, the result of supply of negative voltage to its winding through
the closed contacts of the inertial transmitter (sym. 24M).
The circuit supplying the electrical-pneumatic valve (sym. 92M), is
through the 3-2 and 5-6 contacts of the relay (sym. 93Y4). This relay
operates and releases the nose wheel brakes.
Page 182
At the same time that im,,starboard wheel brakes; are released the
relay (sym. 134M) functions since it is supplied with a negative voltage
at its winding through the closed contacts of the inertial transmitter
(sym. 25M). The circuit ' supplying.. the electrical-pneumatic valve (sym. 92M)
is through contacts 3-2 and 5-6 of the. relay (sym. 131W). The valve functions
and the nose wheel brakes are released
!A6
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSI~Fy
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO FO1ETGN DISSEA/N0 DISSEM ABROA~NTRULLLD D1SbIM
Thus, the nose wheel brakes are released when the.brakes on either. the
,F
port or starboard wheel are released, as well as when both wheel brakes on the.
main landing gear are released.
Should there be a sharp reduction in the angular velocity (or in. the
gent. a "loc1`forms) of the nose wheel alone the electrical pneumatic valve
(sym. 92M) operates since the contacts in the inertial transmitter (sym. 91m).
negative circuit are closed and only the nose wheel brakes are released.
Page 183
17. Speed brake control system and signals
General information
The system is designed to extend and house the speed brakes
provide an"indication as to their position.
The devices which carryout the operation of the system for controlling.
the '.speed brakes, and providing the signal. indications, are given in the table.
167
SECRET
X0 FOREIGN DISSEM(NO.DISSEM,AB$OAD1CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 lX1-HUM
NO ;FOREIGN DISSEM/NO DISSEM AB SE
No. Symbol
22S Circuit breaker, AZS-5
"Speed brakes"
2 30M Transfer --switch KV-9
3 31M Push button 204KS
133M Microswitch KV'-9A
122M Electrical-
hydraulic valve
GA-184
6 32M Electrical- GA-140
hydraulic valve
Quan-
tity
After electrical
switchboard, star-
board console,
cockpit k
Aircraft control
stick
Suspended fuel tank
pylon, frames 17-18
Lower, starboard sect-
ion fuselage between
frames 25-26
Lower, starboard sect-
ion fuselage between
frames 20-22
9S Terminal switch VK2-14OR 1. Fuselage, between
frames 12-13, port,
underneath,
Page 184
Speed brake control is accomplished with the electrical-hydraulic valves
GA-140 and GA-184, with the aid of the push button set in the aircraft control
stick, or with the transfer switch set in the throttle control lever. The
push-,button and the transfer switch are connected in parallel in the circuit.
~ihen the button is not held down, and with the transfer switch open, the brakes
are housed.
When the button is depressed, or the transfer switch is closed, voltage is
upplied to the electrical-hydraulic valves, the brakes are extended and
deflected to the determined angle. The "speed brakes
flight and landing indicator PPS-2 goes on.
168
extended" light on the
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R0002000200016 1X1-HUM
-
NO ' 1iETCW ISSEM/NO DISSEM ABROAD/ CUB TA"Ju
Extension of the lower brake is blocked by the suspended fuel tank (the
lower brake is emended only when the suspended fuel tank has been jettisoned).
button is depressed or when the transfer switch is cut in, the supply circuit
Electrical system'operation
Closing the AZS.(sym. 22S) supplies voltage from the aircraft network to
the push button (sym. 31M) and to the transfer switch (sym. 30M). When the
/
The light is not on when tie, gipped brakes are housed.
169
SECRET
I'O FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED. DISSEM
it closed to terminal 2 of the electrical-hydraulic valve (sym. 32M)'plug.
valve (sym. 122M) plug. The lower brake is also extended. If the suspended
s supplied through these contacts to terminal 2 of the electrical-hydraulic
Page 18
The wing brakes are extended. Should the suspended fuel tank be
,Jettisoned, contacts 1-2 in the microswitch (sym. 133M) close and a voltage
fuel tank has not been jettisoned the lower brake remains housed.
applied to the pilot light which indicates "speed brakes emended." The.
aircraft network through the AZS (sym. 2S) and the closed contacts now is`
operates, losing its contacts O-NZ. The voltage which is supplied from the
When the brakes are in the extended position terminal switch (sym. 9S)
When the button is released, or when the transfer switch is opened the
supply circuit, to terminal 2 of the valve plugs (sym. 32M, 1224) is broken
and the brakes retract.
light goes, on.
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NOTOREICN DISSEM/kO DISS! ABROAD/CONTROLLED-DISC!
Page 186,
18. Flap control system and signa,"_s
The system is designed to extend and retract the flaps when taking off
and landing.
The devices indicated in the table provide for system operation.
No. Symbol
34M
Name of item Type fan- Location
t:", ty
Circuit breaker, AZS-5
"flaps, landing
gear""
2 39M Flap control mech- MZ
anism
3 43m Microswitch KV-9A
After electrical
switchboard, star-
board console
Horizontal sec-
tion port console
Port removable
section of wing,
after section of
wing rib, No. 1
44m Electrical-
hydraulic valve GA-185 i Lower starboard
section fuselage
between frames
22-23
Page 187
The flap control system is electrical hydraulic. The flaps can be
housed and extended by pressing the corresponding buttons in the flap con-
trol mechanism.
Electrical system operation
When the +extend" button in''`the flap control mechanism (sym. 39M) is
pressed the aircraft network voltage is supplied to terminal 2 of the
electrical-hydraulic valve (sym. 44M) plug through the closed AZS (sym. 34M)
and the closed contacts 4-3 of the terminal transfer switch in the flap
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS-42
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 ,;,,
SECRET
NO r+*f1RFTGN DISSEM/NO DISSEM ABROAD/CO tI
control mechanism (sym. 39M). The circuit supplying terminal 3 of the
electro-hydraulic valve. plug isinterrupted by contacts 1-2 of the terminal
transfer switch in the mechanism (sym. 394).
The electro-hydraulic valve functions. The flaps extend. The pilot
light indicating "flaps extended" on the PPS-2 (sym. lls) lights up since
the closed contacts 3-4 of the microswitch (sym., 43M) complete the circuit.
When the "retract" push button is pressed the supply is to terminal 3
circuit supplying -terminal 2 is interrupted by contacts 4-3 in the terminal
of the electro-hydraulic valve (sym. -4M) 'plug and comes through contacts
1-2 of the terminal transfer, switch of the mechanism (sym. 3914). The
Page 188
The electro-hydraulic valve functions, and the flaps are retracted.
The pilot light indicating "flaps extended" on the PPS-2 (sym. 118) is out
because contacts 3-4 in the microswitch (sym. 4314) are open.
If, when the flaps are extended, the landing gear is not dawn, pilot
lights indicating "lower landing gear" on the PPS-2 and the pilot light
e
symbol lOS?light up (the voltage from the aircraft network to the pilot
light is supplied from the AZS (sym. 2S) through contacts 0-2. of the
terminal switches (sym. 3S, 7S) and contacts 1-2 of the relay (sym. 7614).
relay (sym. 7614) winding through the AZS (sym. 2S). The relay (sym.- 7614)
(sym. 4S) close and a voltage?rpm the aircraft network is supplied to the
.When the landing gear is released contacts 0-2 of the terminal switch
the pilot light "lower landing gear" and the light goes out.
functions blocks itself and,.with contacts 1-2, opens the circuit supplying
a 171
SECRET
1O FOREIGN DISSEM/NO DISSEMM ABROAD/CONTROLLED DISSEJ,
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
110 rnRrTr-N DISSEM/NO DISSFW AR
General information
The system is designed to release the parachute in order to shorten
the aircraft's landing run.
The devices shown in the table ensure system operation.
?? t SECRET
x ar,e 1:39
19. Drag-chute control system
No. tame of item Type Quan- Location
tity
1 46M
Circuit breaker AZS-5
"Drag-chute"
1 After electrical switch-
board, starboard con-
sole, cockpit
2 129M Push button 51GS
"release para-
chute"
131M? Push button 204KS
"drop parachute"
1 Port upper section
instrument panel
1 Port console, cbekpit
4 130M Eleetro-pneu- 695000/A 1
matic valve
132M Electro-pneu- 695000/A 1
matic valve
Tail section fuselage,
between frames 3C-31,
underneath, starboard
Tail section fuselage,
between frames 30-31,
underneath, starboard
Page 190
Electrical system operation
The system controlling the drag-chute is an electrical and air one.
Release of the drag-chute` *a, accomplished by push .ng button symbol 129M,
whereupon a voltage from the aircraft network is supplied via the AZS (sym. 46M)
to terminal 1 of the-electro-pneumatic' valve (sym. 13014) plug. The valve func-
tions and opens the air inlet in the flap control system. The, flaps open.;.
172
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISS^Y
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
vrti,nu i
NO-x'OR1r,Tt;N DISSEMy!NO DISSEM EIROA1)7UUN'1RVbLJW P1 . M
The parachute,, of its own weight, falls out of its container and deploys.
Jettison action occurs when the push button (sym. 131M) "drop parachute"
is pressed. Tice aircraft network voltage is supplied from the AZS (sym. 1+6M)
to terminal 1 of the eleetro-pneumatic valve (sym. 132M) plug. The valve
.1(0m. 132M) functions and air is, by-passed from the air system into the
coupling lock cylinder. The drag-chute is uncoupled.
I Page 191
20. System for controlling' landing lights, UFO, ANO, cockpit and port-
able lights
General information
The system is designed to illuminate the take off and landing strips
during landing and taxying, to illuminate guage scales, the cabin, and
certain places in the aircraft.
The devices contained in the system are indicated in the table.
No. Symbol Name of item Type Quan Location
x+18 Circuit breaker, "land- AZS-25 1 Forward electrical
ing lights, external switchboard, star-.
landing gear signal" board console,
173
MPRF-lA 1 Starboard re-
movable wing
section between
ribs 1-2
,SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
cockpit
Transfer switch "land- VTZ602020SP 1 Port section of
ing lights," "landing," Instrument panel
"retract" "taxi"
MPRF-3.A 1 Port removable
wing section
between ribs 1-2
ry:~ ?
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET oUX1-HUM
p0 1hn4rrr_rt :hISSEM/Nt? DIe. ?qrd navnATV1r0V'PhVJ~bMv Di.sCvY
Page
1 2 4 5
5 48S Relay TKD-12PD 1 Relay box be-
tween frames
11-12
49S Relay
16s Transfer switch, "ANO," PEPN-2O 1 Port console,
"law, " "med ium, " "high" cockpit
2S Circuit breaker land- AZS-5 1 After electrical
ing gear signal,INO" switchboard
starboard con-
sole, cockpit
17S 'Resistance P2P-25Kh-15 2 Relay box,
cockpit, frame 11
10 19S Side light BANO-45 1. Port side, port'
removable wing
section, between
wing rib tips
nos. 18-19
11 20S Tail light KhS-39 1 Tip of tail fin
12 216 Side light BANG-45 1 Starboard re-
movable: wing
section, between
wing rib tips
nos. 18-19
15
35S Circuit breaker AZS-5 1. After electrical
"ARU FOSh, switch switchboard,
for lamp for illum- starboard con-
inating KKO, AGD" sole, cockpit
Rheostat.
39S Rheostat
violet illumina-
tion
TKYe -56P]) 1 same,
RUFO-45 1 Starboard con-
sole, cockpit
RUFO-45
Starboard con-
sole, cockpit
37S Light for ultra- ARUFOSh-45 1 Aircraft con-
17I
SECRET
NO FOREIGN DISSEM/NO DISSEM ABRQAD/CONTROLLED DISS M
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAn7CON'T'ROLLJi1) 1)i M
2 3
When,the switch (sym. 42S) is thrown to the "landing" position voltage
36S Receptacle . 47K
17 4OS` Light for ultra-
violet illumination
19
Port side cabin,
frames 7B-8
Starboard side,
cockpit
Electrical switch-
board, port con
sole9 cockpit
Circuit breaker
"sig. gen. ZUP,
KLS"
. IS Cockpit light
45S Receptacle
Starboard side
cockpit
Port wing
The landing lights (sym. 44S and 43S) are controlled with the aid of a
ARUFOSh445.
KLSRK-45
47K 1
page 194
Electrical system operation
transfer switch (sym. 42S) ante two relays (sym. 48s and 498).
from the aircraft network is supplied from the AZS (sym. 41S) switch to the
windings of the relays (sym. 488 and 493), and the relays operate.
the fuse IP-30 (sym. 50S), terminals 2-6 and 1-5 of the transfer switch (sym.
42S) and terminals 2-3 and 5-6 ~o i"th:e relay .(sym. 48S). The lights go on,
Voltage from the AZS (sym. 41S) is supplied to terminal 2 of the lights
(sym. 44s and 43S) through terminals 12-11 and 9-8 of the relay (sym. 49S)
and the lights are extended.
Voltage is supplied to,terminal 4 of,the lights (sym. 443 and 43S) through
burning on the "high beam."
When the transfer switch (sym. 42,5) is set in the "taxi" position the
aircraft network voltage is fed from the AZS (sym. 41S) switch to the relay
winding (sym. 49S). The relay functions and the lights are extended.
17.,
SECRET
AIO'FOREIGN DISSEMINO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6'1X1-HUM
W , W r M _ i f DTSSEM/NO%DISSEM ABRO.ADY/C011TROL S
The voltage path is from the IP-30 fuse (sym. 50S) to terminal 5 of the
lights (sym.44S and 43S) through terminals 5-4 and Z-1 of the relay (sym. 48S)
and terminals 18-17 and 15-14 of the relay'(sym. 495). The lights go on,
burn i,ng on the "low beam."
When the transfer switch (sym. 42S) is set to the "retract" position the
aircraft network voltage is supplied either from the AZ.S (sym. 41S) switch"
or from the IP.30 fuse (sym. 50S) to terminal 3 of the lights (sym. 44s and
3S) through terminals 2-4 and 1-3 of the transfer switch (sym. 42S). The
lights are retracted.
The ARUFOSh-45 lights (sym. 37S and 40S) are designed to illuminate the
dials of the measuring instruments and control levers with ultraviolet rays.
the dials and levers are covered with a phosphorescent material which reacts
temporarily.
The voltage is supplied to the lights from the AZS (sym. 35S) through the
rheostats (sym. 38S and 395). The intensity of the light from the A UFOSh-45
lights can be'changed by these rheostats, whichin addition, can either cut
the lights in or out.
The navigation lights - AN0 - (sym. 195, 20$, 21S) are cut in by setting
the transfer switch (sym. 16S) to one of the three positions, "high," "medium,"
"low," depending upon the light intensity required. In this case the voltage
supply from the aircraft network is from the AZS (sym.2S) switch through the
transfer switch (sym. 165) con-apts,and the resistance (sym. 173).
The receptacle (sym. 36$) for connecting the portable lights receives its
supply from the AM (sym.- 35S) switch.
176
SECRET
NO FOREIGN DISSEM/NO DISSEN ABROAD/CONTROLLED DIS$31
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
oUX1-HUM
SECRET
NO 'tfREIGN DISSEM/NO`DISSEM ABROAD/CONTROLLED DISM
The light KLSRK-15 (sym. 1S) provides illumination in the cockpit.
Voltage from the`aircraft network is supplied the light through the AZS
ti
(sym. 3t.K) switch. A rheostat is provided to change the light intensity
in the cockpit, as
a short period of time. When the button is pressed full voltage from the
aircraft network is supplied to the light through the closed contacts.
Pae17
A push button is provided Iin the event the light is required for only
Pane 196
well as to provide a means for cutting the light on and off.
/
21. System for heating storage batteries the airtight helmet GSh-4m KK?-
clocks, PVD and TP-15 M
General information
The system is designed to provide a normal operational temperature regime
for the storage batteries, to provide against fogging of the window in the.
`'airtight helmet, to provide for accurate clock operation, and to prevent the
PVD and TP-156 M receivers from icing.
System operation is provided for by the devices given in the table.
No.
3F.~
Symbol
Type ? Quan- Location
3 -4
207, Switch "ground heat- 87K 1 Horizontal see-
ing storage batteries," tion, starboard
"on-offconsole
42T Relay
13T . Heater jacket
1 Is placed on
the storage
batteries
177
SECRET
No FOREIGN DISSEM(NO DISSEM ABROAD/CONTROLLED DISSEM
TKYe-52PD 1 Relay box, be-
tween frames
11-12, port
side
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOREIGN DISSEM/Nb DISSEM ABROAD/ cza
31 Fuse
Page 198
5 35S Circuit breaker AZS-5
"AR.tJFOSh" trans-
fer switch lights,
heater KKO, AGD"
5 6
1 Frames 9-10,
under cock-
pit floor
18T
a
Rheostat
RKO-45
204KS
8
7T
Circuit breaker
AZS-10
8T
"heater PVD,
clocks"
Heater element,
clocks AChKh
AChKh 1
Heater element,
IXJAS-8M 1
11
11T
PVD
Circuit breaker,
AZS-10
"TP-156 heater"
.
12
10T
TP-156M heater
TP-156M 1
element
tween frames 3-4
Page 199
1ectrical system operation
The storage battery 15STsS-45 heater element (symm~ 13T) is'cut in by
setting the switch (sym. 20T) i&-'the "on" position.
When the switch (sym. 20T) is set in the "on" pos"tion voltage is sup-
plied to the heater element from the ground supply source through the KPA-4~
(sym. 30E), the fuse (sym. 34E), the closed contacts :)f the tranBfer switch`
178
SECRET
NO FOREIGN DISSEM/N0 DISSEM ABROADJCONTROLIED DISSIM
SECRET
A
After electri-
cal switch-
board, star-
board console,
cockpit
Port console,
cockpit
Instrument
panel
Instrument'
panel, clocks
End of PVD
rod
Instrument
panel
Starboard side
fuselage, be-
max. -
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1-HUM
Nff "mPP I bISSEM NO DISSEM AB
O
D
4 +J
A
R
sym. 20T) and contacts 2-3 and 5-6 in the relay (sym. 12T)..
The relay (s3+m. 12T) operates automatically when the contacts in the
thermal switch close as a result of a drop in temperature.
NOTE: The heater jacket has a thermal relay, T-50, which is set to
Heating of the GM-4M KKO-3 airtight helmet is accomplished by supnlvina
open its contacts at a temperature of 120 t2?C.
voltage from the aircraft network through the AZS (sym. 35S) switch to the
hea ec element In the pelmet, or through the rhec
the.closed contacts of the push button (sym. 21T).
Page 200
The filament in the heater element is adjusted by the use of the rheostat,
which also is. used to.either supply full voltage from the aircraft network,
.or to cut out the supply.
When the push button is pressed rapid heating of the helmet is cut in
(full voltage from the aircraft network is supplied to the helmet heating
element).
Heating the PVD, the AChKh clocks and the TP-156M dynamic pressure re-
ceiver is accomplished by cutting in, respectively, the circuit breakers
(sym. 7T, 11T). When the breaker is cut in voltage from the aircraft net
work is supplied to the'PVD heating element (sym. 9T), the AChKh (sym. ST)
heating element, and the TP-156M (sym. lOT) heating element.
1.79
]CRET
NO FOREIGN DISSEM/NO DI:,'E1d ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
+. t SECRET I
NO FOREIGN DISSEM/NO 1 .SSEM ABROAD/CLjj2? Dim#SEM
Page 201
22. Cockpit heating system
General information
The devices contained in this particular system are given.in the table.
No.
Symbol
Name of item
Type
Quan-
tity
Location
1T
Circuit breaker "Cock-
pit heat"
AZS-5
1
After electri-
cal switch-
board console,
cockpit
Transfer switch
P2NPN-45
1
Horizontal see-
"automatic-hot-cold"
tion, starboard
console, cabin
3T
Temperature regulator
TRTVK-45M
I
Cockpit, frame
11, port
4
14T
Relay block
BRTRTVK-45M
1
Same
5
4T
Electrical air dis-
525 aggre-
1
Lower fuselage,
tributor
gate
frames 20-22,.
port
The temperature regulator is designed to automatically maintain the air
temperature in the cockpit within fixed limits.
The electrical air distributor is designed to receive air from the engine
compressor and to distribute it over the hot or cold ducts, or over both ducts
simultaneously.
Page 202
The relay block is designed to switch the electrical supply circuits to
the electrical air distributor.
Electrical system operation
In order to automatically maintain air temperature in the cockpit within
act (with the aid of a dial) limits, the AZS (sym. 1T) is closed and the trans-
fer switch (sym. 2T) is set to the "automatic" position.
180
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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I oUX1-HUM
SECRET
NO FOREIGN.DISSEM/N0 DISSEM ABROAD C SM
metal helix in the air regulator (sym. 3T), which is.in contact with the air
If the air temperature is below the "normal" Set on the dial the bi-
through terminals "B" and "D" of the temperature regulator (sym. 3T):j1ug and
terminal "V" of the relay block (sym. 14T) plug. Positive voltage is supplied
from the AZS (sym. iT) through the closed switch (sym. 2T) contacts and ter-,
minals "L" and'"Zh" of relay block (sym. 14T) plug to the relay windings
and contacts. The relay operates and distributes the voltage from the air
craft network to the electric motor in the electrical air distributor (sym. 4T)
through closed contacts in the relay block (sym. 14T), terminal "Ye" of the
in the main duct; is deformed so that the first fixed and the movable contacts
close and feeds negative to the relay winding in the block (sym. 14T)
{
block (sym. 14T) plug; through terminal "A" of the electrical distributor
(sym. 4T) plugs the closed contacts of the terminal switch and the.winding
of the air distributor (sym. 4T) reverser. The electric
Page 203
motor begins to run and opens the dampers in the main duct delivering hot air.
If the temperature in the cockpit begins to exceed the temperature bet on
the dial, the bimetal helix, in the air regulator (sym. 3T) is deformed and the.
movable and second contacts closed and cut in the air distributor (sym. 4T)
the cockpit.
electric motor through the contracts in the other block relay (sym. 14T).
The electric motor turns the damper in the main duct to deliver cool air,to
In'order to'reduce.the fluctuations in temperature, the electrical air
distributor has a feedback electromagnetic coil which is-connected at both
ends to the potentiometer in the-electrical mechanism for distributing the aair
181
SECRET
NO FOREIGN DISSEM/NO 3)CSSEM ABROAD/CONTROLLED DISSEI1
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SE,13ET I I
NO"FOREIGN DISSEM/NO DISSI;,A ABROAD /CONTROLIED-DISSS134
(sym. 4T). One end of the potentiometer and the feedback coil have voltage,
from the aircraft network; the other end of the potentiometer has "negative"
while the potentiometer slide is connected to the other end of the feedback coil. AW.
The potentiometer slide, which moves with the distribution valve dampers,
changes the voltage in the feedback coil. The lower the slide on the poten-
tiometer, the higher the voltage in the coil, and vice versa.
The movable contact in the air regulator (sym. 37) is, correspondingly,
a
pulled up to the coil core or moved away from it, closing the circuit for
cutting in the cold air
Page 204
supply and opening the circuit for cutting in the hot. air supply, and vice
versa.
Thus, the air temperature in the cockpit is.autotnatically stabilized.`
If the pilot is not satisfied with the temperature established by the
dial on the temperature regulator (sym. 3T), the transfer switch (sym. 2T)
can be set to one of the required positions, "cold," or "hot."
In this case the automatic air temperature re
for in the cockpit is
cut out and the aircraft network voltage is supplied directly to the air
distributor electric motor (sym. 4T) from the transfer switch (sym. 2T)
through one of the reverser windings. The motor turns the damper in the
main duct to supply either cold or hot air.
When the required temper& ure has been established the electric motor
can be cut out with the transfer switch (sym. 2T).
182
SECRET
NO FOREIGN DISSEM/NO DISSEbt ABROAD/CONTROhLED DISS M
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SECRET
NO FOREIGN, DISSEM/NO DISSEM ARROAD/CONTEVbbhV V1b51M_
Page 20
3. Seat position control system
k
General information
Symbol
Name of item
Typ
47M
Circuit breaker "Seat
control"
AZS-15
48M
Transfer switch "seat
control -.up - dawn"
PN-45M
-9M
'Terminal switch
VK2-141
61M
Terminal switch
W2-14.1
45m
Electric motor
W-1O0AP
Lower trans-
verse girder,
seat framework
Seat position control, depending upon the size of the pilot, is carried
out by shifting the seat bucket,up or down on the guide rails of the seat
frame
can be rotated either way,
screw rotated by the MU-100AP'motor. Since the motor is reversible the screw
Page 206
work. Raising and lowering the seat bucket is carried out with the aid of a
Travel of the bucket up or..down is limited by the terminal switch
183
SECRI
NO FOREIGN DISSEM/NO DISSEMBROAD/CONTROLLED DI'
mechanisms.
supplying the electric motor (in event ..,.e seat must be taken out).
The electrical plug ShR20-PK4NSh8 is installed underneath the seat'on
the starboard.' rail of the seat framewor-: and serves to disconnect the circuit
Quan- Location
tity
1 After electri-
cal switchboard,
starboard con;
sole
1 Port console,
cockpit
Upper section,
port rail,
seat framework
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6'1X1-HUM
NO FGT SIGN DISSEM/N0; D1 f SEM ABROAD /CONT
Electrical system operation
When the transfer switch (sym. 4814) is set to the "lower" position
(circuit breaker sym. 4714 is cloned) the supply from the aircraft network
is fed to the winding in the electric motor (sym. 4514) reverser through the
normally closed contacts of the terminal switch (sym. 9M).
The MU-10QAP motor turns left, lowering the seat to the position in which
the terminal switches (sym. 4914, 6114) operate.
Terminal switch(sym. 4914)opens the.normally closed contacts, interrupting
the flaw of current.to the reverser winding and the motor stops. Terminal
switch sym. 61M closed its normally closed contacts, preparing the circuit
supplying the reverser winding for
Page 207
right rotation of the electric motor.
When the transfer switch (sym. 4814) is set to the "raise" position the
supply from the aircraft network is to the motor reverser winding (sym. 45M)
through the normally closed contacts of the terminal switch (sym. 6114).'
':tithe MU-100AP electric motor turns right, raising the seat to the position at
which the terminal switches (sym. 6114, 4914) operate.
Terminal switch sym. 61M opens the normally closed contacts, interrupting
the current supply to the reverser winding and the motor stops. Terminal
switch sym. 49M closes its normally closed contacts, preparing the circuit
to supply the reverser windingk't9r.,left rotation of the motor.
1814
SECRET
NO FOREIGN DISSEMJNO DISSEM ABROADJCONTROLL.D DISSJ
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
NCB FnRrT(fl DISSEM/NO DISSEM ABROAD
Page 208
211. Canopy anti-icing control system
General information
The system is designed to prevent icing of the canopy glass.
System operation is provided for by the devices given in the table.
1 Switchboard,,
port console
.Port, upper sec-
tion instrument
panel
1 Fuselage,:
lower, 'frames
5-7
Electrical system operation
The system is cut in by the push button (sym, 5T). When the contacts,
Page 209
25. Aerial' navigation equipment system
General: information
Included in the aerial navigation equipment system are:
50X1-HUM
No. Symbol Name of item Type Quan- Location
tity
close voltage from the aircraft network is supplied through the closed AZS
(sym. 9K) to terminal 1 of the electro-pheumatic valve plug (sym. 6T). The
valve operates and compressed air is started into the tank in the anti-icing
system. Air pressure inthe tank ejects alcohol.which is sprayed on the
canopy glass through a manifold.
9K
Circuit breaker "fire AZS-5
equip., canopy anti-
ice"
5T Push button "glass 5KS
anti-ice"
6T Electro-pneumatic 695000/M
18,5
SECRET
A0. FORJU. D-US_EM/NO : )ISSEM ABROAD/CONT.R?LLED DIS MM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1-HUM
% SECRET
NO FORE t ff DISSEM/N6 DISSEM ABROAD/CON RT LLED DISSI
Symbol
Name of item
Type
1
2
1
iN
Circuit breaker,
AZS-5
S
PT-500;s
3
3H
Inc'icator
4
4N
Fuse "converter
IP-50
PT-500Ts for KSI,
AGD, VRD"
6N
Turn indicator
EUP-53
7N
KSI matching mech-
MS-1
anism
7
8N
KSI gyroscope aggre-
GA-2
gate
Page 210
8
9N
KSI indicator
UGR-4U
9
1ON
Circuit breaker
AZS-5
10
11N
KSI correction
KM-3
mechanism
11
12N
Correction switch
VK-58R6
12
13N
KSI amplifier.,
U-12
13
14N
KSI induction trans-
ID-2
mitter
14
15N
KSI matching push
5KS
button
186
SECRET
NO FOREIGN DISSEM/N0 DISSEM ABROAD/CONTROL
L Forward electrical
switchboard, star-
board console,
cockpit k
Upper equipment
hatch, frames -5
Instrument panel
Power unit, star-
board side, frames
12-13
Instrument panel
Upper equipment
hatch,'frames 3-4,-
starboard
Upper equipment
hatch, frames 3-4
Instrument panel
Forward electrical
switchboard, star-
board console,
cockpit
Starboard side fuse-
lage, frames 10-11
Cockpit, port side,
frames 6-7
1 Cockpit, frames 6-7
1 Tail fin
I Instrument panel
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
.k SECRETI I
IVN'E~7ir'+f"1# ' 16TSSEM/110 DISRrM .ARR(1A.n MLLrav L110CLA
2
15
16N
16
17N
17
18N
18.
19N
20N
Relay
belay
3
TKYe-53PD 1 Relay box, upper
instrument hatch,
frame 4, starboard
TKYe-53PD 1 Same
KSI amplifier U-18
Relay
Cockpit, port side,.
frames 6-7
TKYe-21PD 1 Relay box, upper
equipment hatch,
frame 4, starboard
Fuse SP-2 1: Upper equipment
hatch, starboard
side, frames 4-5
hatch, starboard
side, frames 4-5
21N Fuse SP-2 1 Upper equipment
Page '211
22V Fuse
22 23N. Fuse
(blur) Circuit breaker
hatch, port side.,
25N .KSI,control panel PU-2
frames 5-6 . ,
23 24N Gyro transmitter AGD-1 1
25 30N Relay block
"indicato'Ps' for
generator;:
(blur)"
SP-5
SP-5
.AZS-5
358 Circuit breaker. AZS-5
"check display lights,
fuel remaining; trim
effect indicator"
Upper equipment
Upper equipment
hatch, port side,
frames 3-4
Starboard side,
frames 4-5 .
Cockpit, port con-
sole., vertical sec-
tion
Cockpit, after elec-
trical switchboard.,, starboard console
187
SECFPT
NO FOREIGN DISSEM/NO`DISSEh 1BROAD/CONTROLLED DISS^M
ter..-
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
t SECI.,;T, 1
0 FOREIGN DISSEM/NO DISSEIL ABROAD/CONTROLLED DISSS1.14
The purpose, the make up, as. well as the electrical supply for
the fighter pl.ne course system KSI, the gyrohorizon AGD-l, and the
electrical( turn indicator EUP-53, are described in the chapter titled
"Instrumentation" in the present volume.
Page 212
26. Armament system
General information
0
The following units are contained in the armament system:
No. Sym- Name of Item Type Quan- Location
bol tity
1P Circuit breaker, AZS-20 1 Cockpit, Starboard for-
"Sight, sight ward electrical switch=
heater" board
2 2P Circuit breaker AZS-10 1 s
"Sight n
3 3P. Relay for cutting TKYe-52PD
in PO-500A for "SS"
supply
4 4P Filter
Lower equipment hatch,
radio relay box,
frames 8-9, starboard
side
F-14A 1 Cockpit, frames 10-11)
on Starboard beat rail
5 5P Distribution box ASP-5ND 1 Upper special equip-
(block No. 5)
meat hatch, frames 5-6,
port side
6 6P Null gyroscope. ASP-5ND 1 s
amplifier (block
No. 4)
7P
Automatic altitude
input (block No. 6)
rw.,
ASP-5ND 1 Upper equipment hatch,
frames 5-6, along axis
of symmetry
188
SECRET,
NO FOREIGN DISSEMINO DISSEM ABD07!D;'CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
30 FOREIGN DISSEM/NO DISSE:d ABR D
Page 213
1 2
8 8P
---3-
Damping button
Sight head (block ASP-5ND
9 9P Electronic relay ASP-5ND
block (block No.8)
10
10P
11
11P
12
12P
Computer (block ASP-5ND
No. 2)
Circuit breaker) AZS-5
"gun, SS, RS, FKP"
Firing control butbori ' '2O4KS
Circuit breaker AZS-5
3-4a port side
Null gyroscope ASP-5ND
(block No. 3)
No. 1)
13 13P Voltage stabilizer 1SN-4 of
(block No.9) ASP-5ND
complex
14 14P Fuse in "SS" AC SP-5
circuit
.'15' 15P Manual range input ASP-5ND
potentiometer
16 16P Sight transfer ASP-5ND
switch panel
Page 214
'04n
Cockpit, on control
stick
Upper special equip-
ment hatch, frames
5-6, starboard side
Upper special equip-
ment hatch, frames .
Upper special equip-
ment batch, frames
2-2A, along axis of
symmetry
1 Cockpit, fram 7b, above
instrument panel
Cockpit, frames 6-7,
on floor
Radio relay box,
frames 8-9, under
.cockpit floor
'Cockpit., throttle lever
Cockpit, block No. 1,
above instrument panel
Cockpit, starboard after
electrical switchboard
Cockpit, starboard for-
, board
189
SECRET
NO FOREIGN DISSEM/NO DISSEN ABROAD/CONTRA -DISSN3j--
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 'X1 -HUM
110 FOREIGN DISSENT/CIO DISSEM ABxvAv/van==,~~
20
24P
21
25P
22
26P
23
27P
24
28P
25
37P
.26
38P
27
39P
28
40P
29
41P
30
42P
31
43P
32
44P
33
46P
3 5
Transfer switch for VT3602006 1 Cockpit, vertical see-
r+&nge only radar
modes and firing
tion, port console
circuits '$S, 33"
Circuit breaker AZS-10 1 Cockpit, starboar6 for-
"Gun'" ward electrical switch-
board
Switching relay for TKYe-21PD 1 Relay box behind
control of gun firing
sand "5S" launching
pLot's seat, frame 11
Electric trigger gun 1 Gun
Relay for cutting in TKYe-52PD
gun and FKP circuits
Gun ready signal SLTs-51
light (red)
Gun ready signal TKYe-21M
relay
1 Relay box on instru-
ment panel, frame.6
1 Instrument panel,
middle section
Z Relay box behind instru-
ment panel, frame 6
Page 215
Gun reload button 5KS 1 Port upper section
ini;trument panel
Electropneiamatic EK-48 1 1 Frames 14-15, lower,
valve for reloading
gun
Relay for cutting In TKYe-52PD 1 Relay box behind pilot
seat, frame ].l
Gun camera Ssh-45- 1 Cockpit, on sighthead
1-100-03
Timing mechanism VM-2 1 -Cockpit, starboard side
NO FOREIGN DISSEM/N0 DISSEM ABROAD/CONTROLIE'aD DISSEM
SIV-52 supply block SIV-52 1 Cockpit, behind pilot
seat, starboard
Circuit breaker "SIV" AZS-5 1 Cockpit, starboard for-
ward electrical switch
board
190
SECRET
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO rt1RrTtN DISSEM/Nb iDISSEM ADROkD/CONTRDLLEIT DISS M
1 2
3 i
54, 1B
Circuit breaker "RS,,
A)?,,U suspension
indicator"
' AZS-5
35 Ku')
Relay for cutting
in FKP circuit
TKYe-53PD
Page 216
38 5B
Suspended tank lock
BDZ-56-Ye
40 7B
Suspended tank
signal light
SLTs-51
(green)
41 8B
Beam pylon
BDZ-60-
21U
42 9B
Circuit breaker
"Emergency drop RS,
tank, APU. Emergency
launch It
AZS-20
44 11B Beam pylon
BDZ-60-21U
4512B Signal light, zero
SLTs-51
position PUS
(green)
46 13B 'Signal light, zero
SLTs -51
position PUS
(green)
47 14B Circuit breaker 'BS"
AZS-10
5
1 Cockpit, starboard after
electrical switchboard
1 Relay box behind pilot
seat,) port, frame 11
Fuselage "pylon, frames
17-18
1 same
1 Starboard wing
1 Cockpit, starboard, after
electrical switchboard
43 lOB' Push Button for drop- 5K3 l Port section instru-
ping tank meat panel
1 ..-Port wing
1 Cockpit, starboard foi--
ward electrical switch-
board
1 same
1 Cockpit, starboard for-
ward electrical switch-
board
switch
48 15B RS salvo transfer r?v.V Omsp l Port console, vertical
'Page 21
49 16B RS'fire control PUS-36 1 Port wing, tips nos.
14-15 wing ribs
50 17B RS fire control PUS-36 1 Starboard wing, tips
instrument nos. 14-15 wing ribs
191
SECRET
No FOREIGN DISSE1!/210 DISSEM ABROAD/CONTROLLED DISSMY
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
51
19B
52
20B
53
21B
54
22B
55
23B
56
24B
57
25B
NO FORLTGN )ISSEM/NO DISSEU ABROAD/CONTROLLED DISSI
3 T+
"SS" audio signal SPO-0.5- 1 Port console
volume regular.-)r VT-33K-a1L3
Relay for bloc king TICYe-53PD 1
RS, SS launch t tau
of landing gear
Relay for cutting in TKYe-21PD
overload signal
Push button, emer 204KS
gency launch "SS"
Push button, emer.-_ L.. 205KB
gency dump RS, APU-S8
Signal light indica-b-,SLTs-51
ing suspension RS, (green)
APU on port wing
Relay box, frames 11-12,
port side
Relay box behind inatru-.
meant panel, frame 6
1 Instrument panel
l Port upper section
instrument panel
1 Instrument panel, middle
electrical switchboard
1
Signal light indicat- SLTs-51 1 same
ing suspension RS,
APU on starboard wing
58 26B Altitude signal vs-14500 1 Equipment hatch, frames
device 2-a, port
Page 218
59 27B Overload signal SLTs-51
light (red)
60 28B Circuit breaker AZS-20
"SS heat"
61 29B Circuit breaker "SS AZS-10
filament"
62 30B Circuit breaker
launch"
Above instrument panel
on sight bracket
1 Cockpit, starboard for-
ward electrical switch-
boa:rd
l Cockpit, starboard for-
ward electrical switch-
board
IN AM -10 1 same
""88
63 31B Signal light, sus- SLTs-5l , 1
pension port SS" (green)
Instrument panel, upper
starboard panel
64 '32B Signal light, sus- - sus-51 1 same
pension starboard
192
SECRET
NO FOREIGN DISSEM/NO DISSELc ABROAD/CONTROLLED DISC(
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
N() 1~nu~rTr.N DISSEIt/NO DISSEMA13RJ xn, UL L "", W z,X0Q.,X
.65 33B "SS" 'Launch switch 87K 1 same
'salvo - s ingle,'
34B Relay for transferring TKYe-21PD 1 Relay box behind pilot
-- -+ r,.,,+ P"6-- ?
overload signal
circuits
67 '35B Overload mechanism MP-28A
68 36B Transfer switch, 2PPN-45
separate launch S3 .
69 37B
70 4oB
71 41B
74, 6R
Relay for cutting in TKYe-52PD
83 launch circuits
V Page 219
APU suspension lock DZ-57
APU suspension lock DZ-57
Circuit breaker AZS-5
"range only radar"
75 15R Converter for suppler:.,- PO-500A
ing A8P, SIV, SS
76 20R. Fuse SP-5.
77 25R Signal light, with- SLTs-51
draw from attack
79 47R Fuse
78 26R Signal light) permis- SLTs-51
sible range (green)
8P-5
in S1V-52
of fuselage
193
80 48R Relay for. cutting TKYe -52PD
Relay box, frames 8-9,
starboard side) bottom
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Back fairing of fuse-
lage, frames 11-12
1 Instrument panel, upper
starboard panel
Relay box behind pilot
seat, port, frame 11
Port wing pylon
1 Starboard wing pylon
1 Cockpit, starboard for-.
ward electrical switch-
board
Upper equipment hatch)
frames 4-5, starboard
side
Relay box, frames 6-9)
starboard side, bottom
of fuselage ..
Above instrument panel,
on sight bracket
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
ur~tlLlrl
NO FORLTCN DISSEIt/N0 DISSEMM A AR 2 ,L D DISS''Ii
61 24s Relay for checking
signal lights
62 33E Relay for cutting
out power consumers
63 17E Relay for cutting
in power consumers
Page 220
TKYe-56PD
1
Relay box behind instru-
merit panel, frame 6
TKYe-53PD
1
Cockpit, frames 6i-7,
starboard side
TKD-203DT
1
same
The aircraft network serves the armament system with electricity
as well. The armament system consists of the gun ane. rocket installa-
tions, as well as the sight, the range only radar infrareds viewfinder
and the gun camera.
Distribution of electric power from the aircraft network busbars
to the consumers in the armament system is done in the following way:
-the gun, rocket and gun camera circuits are supplied from bus
number 4 on the forward electrical switchboard of the starboard con-
sole through the respective circuit breakers:
gun (sue. 25P); "R8"
(sym.14B), "8S heater" (sym. 28B), "SS filament".(sym 29B), "88
launch" (sym.30B), FKP (sym. 19P);
the aggregates used for emergency jettisoning of the "RS" and
"APU" blocks, and for emergency launching of the "S8" are supplied
from bus number 2 on the forward electrical switchboard of the star-
board console through the."emergency jettison" (sym. 9B) circuit
breaker;
Page 221
- the aggregates for. jettisoning the RS and the tank, and the
firing button are supplied from bus number 3 of the after electrical
194
SECRET
NO FOREIGN DISSEM/N0 DISSEM ABROAD/CONTROLLI DISSE7d
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
switchboard of the starboard console through the "RS, APU suspension
,Indicator" (sym. 1B) and the 'Sgun, RS, FKP" (sym. 17P) circuit breakers;
- the sight and the infrared viewfinder Sly are supplied from bus
number 4 of the forward electrical switchboard of the starboard console .
through the "sight heater1 sight" (sym. 1P), "sight" (sym. 2P) and "SIV"
(sym. 46p) circuit breakers, respectively.
The 115 volts alternating current for the sight, SIV and the EPU-13.
in the K-13 system is supplied from the PO-500A (sym. 15R) converter
when the AZS (sym..1P, 2P) 46P, 30Bh) are cut in.
The switching gear in the armaments electrical system is the
common firing button (sym. 18P) for all types of`armament and the
transfer switch on the sight control panel (block number 1), the
setting of which determines the type of armament, as well as:
- the relay (sym. 28P) for cutting in the electric trigger
'(sym. 27P) for the NR-30 gun, the electric motor for the gun camera
SSh-45 1-100-0S (sym. 42P), through the VM-2 timing mechanism (sym, 43p);
- the relay (sym. 26P) for switching the "SS" firing and gun con-
trol circuits;
- the, transfer switch (sym. 24P) - "RS - gun" -"SS3"
- the relay (sym. 38P) for indicating readiness of gun to'fire;
Page 222
- the push button (sym.`.3 ;O,for reloading the gun;
-the relay(sym. 41P)?for cutting in the "RS" and the SSh-45-1-
.the relay (sym. 20B) far--blocking "RS" and "SS" launching be-
of the forward landing gear strut;
195
SECRET
1a0 FOREIGN DISSEM/N0 DISSEM ABROAD%CONTROLLED DI9
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1-HUM
Ftf14ETGN DISSEMJ'KO DISSEM ABI vAv/waj-
the relay (sym. 37B) for cutting in the "SS" launch circuits;
the push button (sym. 23B) for effecting emergency jettisoning
of the "R8" and APU-13;
- the push button (sym. 10B) for cutting in the circuit to
jettison the tank;
-the push button (sym. 22B) for emergency "SS" launch.
A more detailed description of the MIG-21F (with the K-13 system)
armament, and of its, electrical circuits providing for operation of
the aggregates in the armament system, is given in book II on "Armament
Chapter II
Page 223
Radio Equipment
1. General information
1. Aircraft radio equipment composition
The radio equipment in the aircraft consists of the RSIU-5G ultra-
short wave radio set for communications, the ARK-10 type automatic,
medium wave radio compass, the type MRP-56P marker radio receiver, the
type RV-UM low elevation radio altimeter, the SRO-1 aircraft responder
in the radar recognition system, and the SRD-5MK range only radar.
The schematic showing the placement of the radio equipment in the
aircraft is given in figure 26. The schematic showing the placement
of the radio equipment with 'r9,spect to the framing is given in figure
27
The upper equipment compartment is shown infigur?e 28.
2. Tasks accomplished by the aircraft radio equipment
The radio equipment installed in the aircraft provides:
196
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSI1
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 in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
2~6 F"ISE>`t~N DISSEAt/N0 DISSE'.f A)3?ROAD/CONTROLL IS~E~!
'
? ~. ; ' ? 1 `T mac' .j . , . st
+'ice 4t. - 1~ ~Y 3'
w s
~
y
mot, t
[
+
iT.
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
140 FOREIGN DISSEM/N@ DISSEM ABnuAD~caaiunvJ.~ a2,s-~..~
1. Two-way radio telephone communications between the aircraft
and ground stations (over the RSIU-5G ultra-short wave radio set).
Page 224
Figure 26. Placement of radio equipment
Page 225
Specifications for the schematic showing placement of radio
equipment (fig. 2b)
Block Posit-
No. ion num-
ber on
schematic
Block name
RSIU-55G
12
Transceiver with supply
block - blocks A, B, d
Upper equipment compart-
ment, between frames
and 5
55
Control panel) P-1
Cockpit,
port
frame&?
vertical section
console, between
8 and 9
57 Button for cutting the
radio set on for transmit
operation
4 31 Combined whip antenna,
RSIU-5G and ARK-l0
5 30 Separation filter AF-1,
for combined whip antenna
for RSIU-5G and ARK-10
6 54 Ampiifiei':;UK-21, series
53 Separation transformer
198
Cockpit,, port console,
aircraft control stick
handle
After fixed section of
canopy, between frames
13 anw 14
After fixed section
canopy, between frames
13 and 14
Cockpit, port console,
frame 10
Cockpit, port, between
frame., 10 and 11
SECRET
NO FOREIGN DISSEM/N0 DISSEM ABROAD/CONTROLLED DISSEf
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO Fn1FTh?N'DISSEM/Nb DISSEM ABROADICONTRO L I 8T, '
whip antenna RSIU-5G and
ARK-10
199
Upper equipment compart-
ment, between frauds ,5
and 6
Upper equipment compart-
ment, starboard, between
frames 3A and 4 1'
Cockpit, middle vertical'
panel of starboard con-
sole, between frames 8
and 9
Cockpit,. vertical section
port console, between
frames 8. and 9
Cockpit, instrument panel
Cockpit, horizontal sec-
tion starboard console
,Cockpit, instrument panel
Cockpit, behind instrument
panel, starboard
After fixed section canopy,
frame 13
Nose section fuselage,
underneath, between
frames 2 and 3
After fixed section
canopy, between frames
13 and 14
After fixed section canopy,
between frames 13 and 14
SECRET
15'
Receiver
Page 226
ARK-10
10 Supply block
Control panel
56 Remote wave transfer
switch
61 Course indicator UGR-1+U
(in the KSIcomplex)
24 Tuning indicator
60 Transfer switch "short-
long"
All-purpose automatic
device for UAP-1 trans-
fer switch
Directional sloop antenna
block ,
Combined (nondirectional)
whip antenna, RSIU-5G and
ARK-10
30 AF-1 filter for combined
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO FOREIGN DISSEM/NO DISSEMM ABROAD TCONr Lam' DlsS''
Page 227
Equivalent feeder (5m) in
the directional antenna
channel
Equivalent feeder (18M)
in the combined whip
antenna channel for the
RSIU-5G and ARK-1O
65 "ARK-BPRS" indicator
light
74 Transceiver - PP-U
block
43
3 75
62
63
Transmitting antenna.
Receiving antenna
Altitude indicator,
UV-57
"Dangerous altitude"
signal light
664 Transfer switch for
dangerous altitude,
PSV-U
73 Filter VChF-3
Upper equipment compart-
ment, starboard, between
frames 2A and 3
t
After fixed section
canopy, between frames,.
13 and 14
Cockpit, instrument panel,
port
Upper equipment compart-
ment, between frames 3
and 4
Port wing, underneath,
"between tips of wing
ribs 23 and 24
Starboard wing, under-
neath, between tips of
wing, ribs 23 and 24
Cockpit, instrument panel,
port
Cockpit, instrument panel,
port
Cockpit, instrument panel
Upper equipment compart-
ment, between frames
4 and 5
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
1P FORtIGN DISSEM`/N0 DISSEM ABR.~4~TR LLED DISSEM
36 Receiver, MRP-56P Tail fin fairing, between
frames 33 and 33A.1
Tail section fuselage,
between frames 30 and
31A,.underneath
Cockpit, starboard console,
T-4 signal panel
NO FOREIGN DISSEM/NO DISSEM ADR)AD/CONTROLLED DISSEM
201
'Marker" signal light Cockpit, instrument panel,
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOREIGN DISSEM/Nd DISSEM ABROAD/CONTROLLED DISSEN
j
Page 229
SRO-1
68 Transceiver
25 Code panel
72 'Inertial contactor
0
59 Exploder push button
32 Antenna
16 Exploder circuit check
panel
58 Transfer switch "Distress"
SRD Range Only Radar
I Combination antenna and
waveguide tract
4 Transceiver block RB6-2M
8 Receiver-range meter
block- RB6=3 block
9 Supply block - block
RB6-4
7 Speed block - block
RB6-S
Up3er equipment compart-
me't, between frames
5 and 6
Cockpit, vertical section
starboard console,
frame 9
Upper equipment compart-
ment, between frames 4
an:; 5, port side
Cockpit, horizontal section
of starboard console
Nose section fuselage,
between frames 21 and
22 (sic), on top
Upper equipment compart-
ment between frames 5
ano b, port side..
Cockpit, horizontal section,
board console
Forward section fuse-
lage, cone
Upper equipment comport-
ment, between frames 2A.
and 3
Upper equipment compart-
ment, between frames 2A
and 3, starboard
Upper equipment compart-
ment, between frames 2A
and 3, port.
Upper-equipment compart-
ment, between frames 2A
amd 3
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X17HUM
NO FORET.CN DISSEM/NO DIS.SEM 14 Rp p/ t3Yt;i`xp ~x;~'
Page 232 :
Check `and adjustment
panel - K-6 block.
11 Comparator block
K-8 block
a 0` ,.
ter, VRD-2A
22 Range indicator, D ? D ' -
Permissible. range ce
Air speed transmitter,
!Permissible: r4nge"
signal light
Withdraw from atta~+i:k1?
signal light
Page 241
Figure 27:. Schematic of placemetrt of ray".,eq+iame, $ t}
aircraft with respeet . to. framing
Page 2.32
Figure 28r. Upper equipment
Figure 28 Upper equi} i at
Service plug for range only radar.
Speed block -,block RB6-5 - .x~a b Qn
r p e r e Ae iptnent :c rt
inept, batwe is es 2A
d 3, sta -a.
Upper equipment coqertw
Ott,: between games 2A `.
and 3 port' ,
Aff
equi pmeit ce
E t teen i'ire $
kpit0: ir~stmnt pang
.tj eg ` eqt iptnent ? sump t.
meaty etwee 9tb s .' ,
and 4,' part.
Lower equ . Zment??. comps r"t.
heath
Cp t, ins;lrar?um t
Cockpit . k t: 'ttm t3 pane
Upper equipment. `+ t
ant, between. names
An- 2A
ompartmeut
ompartinent
teen
- 13O FOREIGN DISSEMM/NO..DISSEK A$RpAT J INS` C~1 LElt
DLI
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 ,,D n 50X1-HUM
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"~- SECRET
NO FORFIGtN DISSEM/NO DTS ' =CALLED DIS' K
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 hCC:i
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
` ?' 91 -` fir' r;'ri ~yl. M1PT-. s'.~{~_Ytii ~~.: ??''?,tr -F~~ ..a^...r~ -.,
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
LW f'UL 1! L(N D166EM/NO DISSEM
ABkAV/UURTItVWZV sm
 C
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NO FOREIGN DISSEM/N ~
0 DISSEM ABROAD/CONTROLLED DISelry
3. Check and adjustment panel - block K-6 - range only radar.
4. Reciever-range meter block - block RB6-3 - range only radar.
5. Supply block - block RB6-4 - range only radar.
6. Supply block for automatic radio compas$ type ARK-10.
7. Comparator block - block K-8 - range only radar.
8. Inertial contactor for the responder in the radar recognition
system, SRO-1. !
9. Transceiver and supply block - block ABV - ultra-short wave
radio set for communications.
10. Permissible range computer VRD-2A of range only radar.
12. Transceiver of automatic radio compass type ARK-10.
Page 234
15. Transceiver of aircraft responder SRO-1.
16. Panel installation for checking the exploder circuit in the
aircraft responder SRO-1.
17. DVS-5 air speed transmitter for range only radar.
18. Transceiver of radio altimeter for low altitudes, type RV UM.
19. Transceiver - block RB6-2M - range only radar.
Page 2
(Ti: the following text is a continuation of that interrupted
on page 223)
2. Piloting the aircraft ;in accordance with homing radio, broadcast-
ing radio stations, and radio beacons (automatic medium-wave radio compass
type (ARK-10)
3. Signalling the passage of the aircraft over a radio beacon marker'
(marker radio"receiver installation type (MRP-56P)
206
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 : CIA-RDP78-03066R000200020001-6 )X1-HUM
NO ropr'TGN DionO DISSEM AiiX0ApJGU1vi
.the earth's surface and signalling with sufficient warning the given
"dangerous" altitude (radio' altimeter for low altitudes) typr.RV-UM).
1. Determination of the true flight altitude of the aircraft above,
5. Provide answering coded signals to aricraft, ground and ship-
as well as relative target speed; delivery to the sight computer mechanism.
system, SRO-1).
6. Automatic and cOntinuqus determination of distance to target,
board interrogating.devices (aircraft responder in the radar recognition
of voltages which,are proportional to'fixed values. Determination of the
instant for effective launch of the K-13 "air-air" homing rockets (air-
craft range only radar).
Page 236
In order to reduce radio interference and-to provide for reliable
All the large units and parts in the aircraft are bonded.
.electricity dischargers on the wing tips) the stabilizer and tail fin.
operation of the installed radio equipment the aircraft has static
The antenna location schematic is shown in figure 29.
The schematic showing the location in the cockpit of instruments for
checking and controlling radio equipment is given in figure 30.
Pa e 237
Figure 29'. Antenna location schematic
',Page 238.
`Figure 30. Schematic'showing the cockpit location of instru-
ments for radio equipment control and checking
207
SECRET
NO FOREIGN DISSEM/NO DISSEtd ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 17.1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
SECRET
NO FORETCN DISSEM/NO DISSEU ABPl1dT~7t.`~'NTROLLED DTS!
-'? _ SECRET
NO FORFTMT DISSEM/TTO DT"" ;IM Ai rAN( TROLLED DT ' ? M
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
0
SECRET
NO FOREIGN DISSE: /NO DISSE'If ABROAD [CONTROLLED DISc7-!,1
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
ECii::P 50X1-HUM
NO FOPEI:rT DISSEM/NO,DIss .: ABPOAr/CCmTTR- DISSTY
Pace 239
`. qure 30. Schematic showing cockpit location of instruments for radio
equipment control and checking
1. P-1 control panel for communications radio set.
Remote wave transfer switch for ARK-10 automatic radio compass.
3. Push button for cutting in the RSIU radio set to transmit.
4. UV-57 altitude indicator of the RV-UM radio altimeter.
"Short-Long" ARK-10 transfer switch.
;. UGR-4U course indicator (of the KSI complex) ARK-10.
I, T-4 indicator panel.
3. Dangerous altitude indicator light of.RV-UM radio altimeter.
9, "ARK-BPRS" signal light.
10.. "Withdraw from attack" signal light, range only radar.
U. UD-l range indicator, range only radar.
"Permissible range" signal light, range only radar.
L. "SRD" circuit breaker.
20. "Marker, RV-U" circuit breaker.
=1. "Radio set" circuit breaker.
?2. "PQ-750,11 'IRV-U, MRP" cutout circuit breaker.
24, "Emergency converter transfer" circuit breaker.
2S. ARK-10 control panel.
26. Responder control panel, SRO-1 radar recognition system.
27. SRO-1 "Distress" transfer switch.
Page 240
1TO FOREIGN DIS5EM/NO DISSEM ABROAD/CONTROL D DISSESf
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOREIGN DISSEM/T;0 DISSEMM ABROAD/CONTROLLED ISSEM
29. ARK-10 tuning indicator.
31. SRO-1 Exploder" push button.
32. PSV-U dangerous altitude transfer switch, RV-UM radio altimeter.
Page 241
II. Communications System
The RSIU-5G Ultra-Short Wave Communications Radio Set
1. Purpose
The RSIU-SG ultra-short wave receiver-transmitter is designed to carry
on two-way radio telephone communications between the aircraft and com-
munication stations on the ground, as well as between aircraft.
2. Composition
The RSIU-SG communications radio set installed in the aircraft includes:
.1. transceiver and supply block (blocks A, B, V);
2.: P-1 control panel;
3. push button for cutting in the radio set to transmit;
4. combination whip antenna for RSIU-5G and ARK-10;
5. AF-1 filter (separation), for the combined whip antenna for the
RSIU-SG and ARK-10;
6. UK-2M amplified, series "B";
7. separation transformer;
8. Plug with locking screws;
9K - 17K. cable runs and feeders.
Page 242
The schematic showing the lc,--ation, and the manner in which the blocks
211
SEC"RET
NO FOREIGN DISSENT/PTO ABROAD /CONTROLLED DISSIM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1-HUM
NO FOFr^.T(?T DTSSE!f,/ ) DTr1"7-' ~?; AD 1 ; ;
aircraft, is,given in Figure 31.
3. Brief technical data and methods of carrying on communications
The ultra-short wave receiver-transmitter radio set provides for
carrying on two-way radio telephone communications in the 2 - 3 meter wave
band (150 - 100 megacycles). The communications waves are uniformly
distributed over the band indicated and are stabilized by quartz crystals
installed inside the AB block. Quartz crystal stabilization ensures the
,possibility of establishing communications without searching and carrying
on such communications without the need for making fine tuning adjustments.
For operational purposes the set is tuned preliminarily on the ground
to a definite number of previously selected communications channels, any
one of which can be used in flight. The RSIU radio set is capable of
operating against the background of high aircraft noises.
Page 243
Used with the radio set for carrying on communications is either the
( 5h-4M sealed helmet with TA-56M headphones and DEMShh-1 microphone (the
transfer switches on the UK-2M, Series "B" amplifier in the "GSh" and "M"
)ositions) or the helmet phone with LA-S throat phones and TA-56M head-
?hones (the transfer switches on the UK-2M, Series "B" amplified in the
104" and "L" positions) .
Page 244
Figure 31. Schematic showing the connections, and the location in
--Ie aircraft, of blocks in the ultra-short wave radio set used for
communications.
212
J DI ..'? 11
_-B'1 CSD,/C0NTIWL "D DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 : CIA-RDP78-03066R000200020001-6
0
P0TT;T( PT3S '?i/?i0 TJSS,r:i r^~ll!~ iii1.~ .n' Ivti .~~
U
U i7
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M W
C1 o
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W
00 0
- $4
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NO r017TC ' DTcr;T.`d II C T, ', ^"^n,-r'
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
; EC13ET
tv`0 +'()Pr..T(;T.T DISSEM/110 DT DISELM
Page 245
1. Transciever with ABV supply block.
2. P-1 control panel.
3. Push button for transmit mode for the radio set.
4. Combination whip antenna for RSIU and ARK.
5. AF-1 filter (separation) for combination whip antenna for RSIU
,And ARK.
6.
UK-2M amplified, series "B"
7. Separation transformer.
3. Plug with locking screws.
9K - 17K. Cable runs and feeders.
Page 246
The UK-214 amplifier, series "B," is set to match the parameters of
~e DEt9Sh-l microphone in the GSh-4M sealed helmet wit?, the input of the
transceiver of the radio set. This is provided for by setting the UK-2M
amplifier transfer switch to the "M" and "GSh" position. The UK-2M
amplifier does not function in the "L" and "KM" positic.ns. At the same
time, the throat microphone circuits in the helmet phone are connected
directly to the input of the radio set's transceiver.
i?cure 32 is aschematic showing the connections ox' the helmet phone
or the GSh-4M sealed helmet to the P-1 control panel for the radio set,
. well as the electrical cable schematic.
The P-i control panel of the communications radio set permits connec-
Ling either the receiver output,'the automatic radio compass output, or the
output of the automatic radio compass in series with tie receiver for..
271.E
U ,
3,) r: .. G1 :/':0 DT 71C )U O Lam) DTSS~'.1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
NO wn'PPrnV DISSEM/NO DISS7-11f ABrO.:4.D/CONTROL ISSZ
simultaneous listening, to the telephone in the helmet phone circuit (or
the GSh-4M sealed helmet).
The noise suppressor in the radio set eliminates the need to listen
to the noise and interference which might come through during standby
reception, that is, when there is no signal carrier frequency at the
receiver input.
When the noise suppressor is cut in the receiver tract automatically
opens up with the advent of such signal carrier frequency.
Page 247
Figure 32. Schematic showing the connection of the helmet phone or
the sealed.helmet to the P-1 control panel for the radio set and the
electric cable schematic
Page 248
3. Pushbutton for cutting the radio set in to transmit.
6. UK-2M amplified, series "B"
7. Separation transformer.
8. Plug with locking screws.
Page 249
It closes (cuts out) when the signal carrier frequency disappears.
Operation with the noise suppressor cut in results in some reduction in
the range for the set (receiver range is reduced).
The radio set used for communications purposes provides for the
following cycle of operations when forced air cooling (forced scavenging
of the hermetically sealed casing of block A, B, V)' is. present: "transmit"
1 minute, "receive" 3 minutes; standby reception can be obtained over a
24 hour period. Should it be necessary to "transmit" for as long as 20
2:.5
SEC I ET
NO FOREIGN DISSEM/NO DISSE'. ABROAD/CONTROLLED DISSIM
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 50X1-HUM
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199 N; R-1-11,
411W ffllkl~
216
xCZ
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
minutes, the following 30 minutes must be used as a cooling interval.
With normal airtightness for the transceiver (blocks A. B, V) operation
at altitudes of up to 25,000 meters is ensured for the communications radio
When operating with a ground station of the RAS-UKV type the communi-
cations radio provides a range for two-way radio communications at full power
(on the order of 18-20 watts) of at least 350 kilometers at flight altitude
of 10,000 meters; when operation is between aircraft the radio provides
a range for two-way radio communications of at least 120 kilometers at
flight altitudes of from 500 meters up. For lower power (on the order of
3 watts) the ranges indicated are correspondingly reduced 2.5 times.
Page 250
4. Cooling the transceiver in the radio set
In order to ensure normal operation of the radio sets,, forced scavenging
of the hermetically sealed casing of the transceiver is used. The air
forced through the casing is at a temperature of not more than +50?C.
Figure 33 shows the arrangement for transceiver scavenging.
Air is drawn in from the port duct through a cutoff valve (sym. 9) and
a hose (sym. 8) and is supplied to the,Pi-shaped connection (sym.7), welded
to the bottom of the hermetically sealed casing, and flows through the con-
nection into the radially positioned ducts along the rear, inner wall of
the casing. The air then flows into longitudinal ducts on the upper side
walls inside the casing and discharges through holes at the forward panel.
The ducts are formed by channel bars (sym. 3) welded to the inner wall of
the sealed casing. These channels, in addition, provide rigidity to the
217
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
-asing design.
When air temperature in the intake duct is increased because of an
increase in the Mach number (M 1.5), that is, when the air temperature
used for scavenging the transceiver rises above 50'C, scavenging is
automatically discontinued.
Page 251
Figure 33. Transceiver scavenging diagram
Page 252
Figure 33. Scavenging diagram, radio set transceiver
1. Transceiver
i. Outer wall of hermetically sealed casing
3. Channel bars
4. Inner wall of hermetically sealed casing?
7. Pi-shaped connection
3. Ho s e
9. Cutoff valve
10. Electrically operated valve, EK-69'(1401')
33M. AZS-10 "Cone, throttle interlock"
50M. Filter in the Mach number controller Circuit
66M. Mach number controller
116M. TKYe-52PD relay
Page 253
when a Mach number M > 1.5 is attained, 27 Volts is fed from the Mach
number controller (sym. 66M) to terminal A of the relay winding (sym. 116M).
The relay operates and 27 volts from the aircraft; network is supplied to
SECRET
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 -1X1-HUM
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SECRET
rrt~ FOT?FTGN T7551),1/1?n PfFS",t ~, nn TTTROLLED DP'
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOREIGN DISSEM/NO DISSEM ABR
terminal i of the electrically operated valve (14OM) trough the normally
>,:en contacts 2-3 of the relay (sym. 116M). EK-60 ope ates and, under air
?essure of 50 atmospheres, the piston moves the valve disc, which covers
tae opening providing air intake from the intake duct.
Page 254
5. Controlling operation of the radio
Control of the ultra-short wave radio set for com;-,unications has been
rc,duced to a minimum number of operations:
1. Start the set by cuttir.,; in the AZS stencilled "Radio" on the
i.o)rward electrical switchboard of the starboard console.:_ Operational
zo;adine-ss of the set is provided for in not more than 1.5 to 2 minutes
after the supply is cut in.
2. Select one of 20 prO-tuned communications charnels by setting
:1;e "Channel" transfer switch on the P-1 control panel to the position
-orresponding to the given channel (the number of the channel selected
i11 be set in the window in the control panel cover). The transfer time
rrom channel to channel is 4 seconds.
3. Switch the set from "Receive" to."Transmit" by pushing the button
or energizing the transmitter mounted on the handle of the engine control
.ever (gas sector or throttle). The time.to switch from receive to transmit
:.: v.. -e versa takes not. more than 0.5 second.
Page 255
Additional Operations
Adjust the phone volume by turning the "volume" adjustment knob
s,.n the P-1 control panel.
220
U-E-C-R-E-`I
',D) WGREIGN DISSEM/NO DISSEM. ABROAD/CONTRO!,LED DISSE '
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO FOREIGN DISSE3,4/Y0 D?Crr,t l~ rn Ts7G~~IrtoL~ l '
The amplified and automatically regulated sensitivity of the
receiver tract which is available in the set permits a reduction in the
change in the receiver output voltage connected with the change in field
intensity as the aircraft recedes from or approaches another aircraft or
ground stations. The amplified and automatically regulated sensitivity
of the receiver tract frees the operator from making repeated volume
adjustments for the phones when communicating.
2. Cut the noise suppressor in and out by shifting the tumbler switch
for the noise suppressor on the P-1 control panel to "Noise Suppressor" or
"off" positions.
3. Shift the transmitter power by switching the tumbler switch for
power on the P-1 control panel to the "Full Power" or "Reduced" positions.
Page 256
4. Connect the automatic radio compass output in series with the
output of the radio and connect both to the phones in order to hear both
simultaneously by shifting the tumbler switch "Radio Compass" on the P-1
control panel to the "Compass" position.
6. Electrical supply for the radio set
The communications radio set is supplied with 27 volts direct current
from the aircraft network and with 115 volts, 400 cycle, single phase
alternating current from the PO-750A converter, which converts the aircraft
network direct current into the 115 volts, 400 cycle single phase alter-
nating current.
The Communications ultra-short wave radio set takes single phase
221
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSCM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIC 1 DISSEM/lT0 11ISS,73. 1S.8i64.i.
alternating current at 115 volts, 400 cycles, from the network:
(a) whe,n transmitting at rated power, 400 volt amperes;
(b) when transmitting at reduced power, 270 volt amperes;
(c) when receiving, 200 volt amperes.
The weight of the operational radio set complex is 32.7 kilograms.
Page 257
7. Installation location and methods of securinr* blocks
Transceiver (blocks A. B, V) - installed in the upper equipment
compartment (directly under the equipment hatch cover) between frames
.,umbers 4 and 5. Shock mounting for the blocks A, B, V is accomplished by
the placement of four damped shock mountings (two type AD-7, two type AD-8)..
The shock mountings are secured to block."V." Block,-; A, 3, V are set
in a frame secured directly to two subframes with four screws which screw
into anchor nuts of two brackets which are fastened to th+ sheathing of the
intake duct.
11
-1 control panel (figure 34) - installed in the cocl.pit on the vertical
section of the port console between frames 8 and 9 on a bracket riveted to
she sub-canopy panel and frame number 9. The panel is secured to the
Bracket by two screws for two bosses on one side'and by a boss which is
u:hreaded into the bracket impingement on the other.
Page 258
The push button for cutting in the RSIU radio set to transmit is
installed in the cockpit, on the port console, on the thrcttle.
The combination whip antenna for the RSIU and the AR}-10 is installed
-_in the after fixed section of the canopy, between frames numbers 13 and 14
: ECRE T
4
110 F07777 T DISSEII/IIO DIn''17.1 ABROAD/CONTROLLED DISSE}6
50X1-HUM
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 I
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SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/ XIMLL D 1)1 6~jl.
and is secured to an insulated panel made of Mark AR-4 press (board)
material by/four bolts. The panel is secured to the anchor nuts of two
diaphragms riveted to the upper fuselage panel by four screws.
In order to prevent breakage of the high frequency feeder for the.
RSIU and ARK-10 antenna in the event the tail section of the canopy is
removed two warning stencils have been mounted. One, at the site of the
first fastener for the antenna feeder (frame no. 13) reads: "Feeder
length, from antenna to first fastener, must be 320-mm." The other, on
the fuselage (between frames nos. 13 and 15, port side), reads: "When
removing the tail section of canopy disconnect communications radio set
feeder."
AF-l Filter (separation) fox the RSIU and ARK-10 combined ..:.ip
antenna - installed on the after, fixed section of the canopy, between
frames 13 and 14, and secured to the RSIU and ARK-10 combined whip antenna
by screws, from underneath. The AF-1 filter is screened in order to
eliminate interference, as well as to improve bonding.
Page 259
Figure 34. P-1 control panel for the ultra-short wave communications
radio set
Page 260
The UK-2M series "B" amplifier (figure 35) is installed in the cockpit,
on the port console, at frame no. 10 and is secured by 3 ears as follows:
two of the ears are fastened to a runner welded to the horizontal
section of the port console framework; the third ear is secured to a bracket
which is mounted on the-face of frame no. 10.
223
SECRET
NO FOREIGN DISSEM/NO DISSTEM ABROAD /CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECIET o0X1-HUM
h10 FOREIGN DISSEM/N0 DIP""''.f A3;.0.A.D/CONTROLLED DISSEM
The separation transformer is installed in the cockpit, port side,
between frames nos. 10 and 11, on a bracket to which it is secured with
two bosses. One of the bosses is secured to the bracket channel, the other
is fastened to the bracket by a screw.
Page 261.
Figure 35. UK-2M series "B" amplifier
Page 262
III. Blind landing system
1. Medium wave, automatic radio compass, type ARK-10
Pur 2-0 S-0
The medium wave, automatic radio compass, type ARK-10 is designed to
guide the aircraft bya-homing radio station,.a broadcasting station, or
by a radio beacon and ensures continuous computation of course angle (the
angle between the longitudinal axis of the aircraft and the direction to
the radio station)and the solution to the following navigational problems:
1. flight to and from the radio station, with visual indication of
course angle;
2. automatic determination of radio station bearings from the course
indicator;
A%
3. handing by instruments using the OSP blind landing system; -
3. determination of distance to the homing radio station by the route
integration method;
4. reception of and listening to signals from radio stations trans-
mitting on medium waves in the frequency band 120 to 1340 kilocycles.
SECRET
470 FOREIGN DISSEM/NO D1SCEM ABROAD /CONTROLLED DISSE!i:
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
m E^ 4
i10 FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
SECRET
N a
NO FOREIGN DISSEM/NO DISSEM ABROAD CONTROLLED DISSEM
I
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
NO FORFT(N DISSEM/NO
Composition
i
The mecum wave, automatic radio compass, type ARK-10, as installed
Page 263
craft, includes the following;
1. receiver;
2. supply block;
3. control panel;
4. remote wave transfer switch;
5. UGR-4U course indicator (part of the KSI complex);
'6.' tuning indicator;
7. "Short-Long" transfer switch;
8. UAP-1 transfer switch all-purpose automatic device;
10. "ARK BPRS" indicator light;
11. antenna amplifier;
12. AF-1 filter for the RSIU and ARK-10 combined whip antenna;
13. RSIU and ARK-10 combined (non_directional) whip antenna;
14. directional antenna block;
15. feeder equivalent (SM) in the channel of the directional antenna
(two) ;
16. feeder equivalent (18M) in the RSIU and ARK-10 combined whip
antenna channel;
17K - 26K - runs and feeders.
Figure 36 is the schematic of the connections and the location in the,
aircraft of the blocks which make up the ARK-10 radio compass.
227
SECRET
NO FOREIGN DISSEM/1,0 DISS~.:.i ABROAD/COIN'T'ROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
aJ ~"
i; o
W .^I +.1 y+
W
g 49 p 0
4
w
V
'm
r- 0
~y L_~:14+to j.
ihT^ T~ R?>T'r1Ar/f ,{ i`t )Lt D CCI
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 CIA-RDP78-03066R000200020001-6 V1 U, IRA
SECRET
NO FORr7GN DISSE?,1J1?;0 DTSSF:??f ABROAD/CONTROLLED DISS"EM
Page 264
Figure 36
Page 265
Figure 36. Schematic of connections and location in the aircraft of
the automatic radio compass ARK-10 blocks
1. Receiver
2. Supply block
3? Control panel
4. Remote wave transfer switch
5,, UGR-4U course indicator (part of the KSI complex)
6.,. Tuning indicator
"Short-Long" transfer switch
.";UAP-1 transfer switch all-purpose automatic device
10. "ARK BPRS" indicator light
11. Antenna amplifier
12. AF-1 filter for the RSIU and ARK-10 combined whip antenna
13. RSIU and ARK-10 combined (non-directional) whip antenna
'14.' Directional antenna block
15. Feeder equivalent (SM) in the directional antenna channel
16. Feeder equivalent (18M) in the RSIU and ARK-10 combined whip
antenna channel
17K - 26K - runs and feeders
Page 266
Operating principles
The ARK-30 automatic radio compass operates on the principle of con-
verting a signal from a radio station, picked up by two antennae (a direc-
229
SE;,a:'i
NO FOREIGN DISSEM/NO DISIM ABROAD/C0:4TROLLED DISSE~j
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FORF? M.1 DISSEM/1T0 DT Stir +!"'nen/rO TTPOLL O DZSS!
tional loop antenna for the ARK-10 and a non-directional RSIU and ARK-10
combined whip antenna), and using it for automatic rotation of the loop
Lntenna to the position of zero reception (the direction of the axis of~
the loop antenna coincides with the direction to the radio station) and
to track this position for any aircraft course changes.
The automatic rotation of the loop antenna to'the position of zero
reception (in the event of its deviation from this position after tuning
to the radio station being received) and automatic trackir. , by the loop
rntenna, of the zero reception position for any aircraft course changes, is
;:accomplished by the use of an automatic servo system (circuit for automatic
rotation of the loop antenna) which is part of the radio compass. It
consists of a control circuit and an electric.motor for rotating the loop.
"he servo is controlled by law frequency voltage from the output of the
-adio compass superheterodyne receiver.
Paige 267
rile phase of the control voltage is determined by the direction of the
leviation, while the amplitude is determined by the magnitude of the
':.eviation of the loop`,antenna from the direction to the radio station.
The selsyn system contained in the radio compass transmits the angular
..isniacements of the loop (automatically established by thy:- plane of the
_a~.. in the loop perpendicular to the direction to the radio station) to
:he pointed indicator for the radio compass, the UGR-4U indicator of the
:SI compass.
The feeder for tfe directional antenna and for the ARab-10 receiver, as
,ell as the antenna arjplifier cable, is covered with braided shielding to
230
Si,C EI
NO FOREIGN ;ISSEM+ NO D11-S-1'!1 AE ROAD/C0NTROLLLD DISm_7L:
50X1-HUM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEI,I/t;0 DISs AIM
D/COr THUL ~ ISS M
eliminate interference in the ARK-10 radio compass resulting from other
stations.
Operating "Modes
The medium wave, automatic radio compass, type ARK-10, is designed
for three modes of operation:
1. Automatic direction finding - "Compass" - in which a signal
voltage is
Pale 268
taken from the ARK-10 directional loop antenna, as well as from the non-
directional, RSIU and ARK-10 combined whip antenna. In this mode, when
the radio compass is tuned to the frequency of the radio station sending
the beam, the course angle to this radio station is automatically set on
the UGR-41J course indicator of the KSI complex.
2. Acoustic direction finding - "Loop" - in which a signal voltage
is taken only from the directional loop antenna (the non-directional an-
tenna is disconnected). In tl~is mode, and when tuned to the frequency of
the radio station sending the beam, the radio compass enables the operator,
by rotating the. loop antenna (using the transfer switch for manual rota-
tion marked "L-P Loop") and listening, at the same time, to the station
signal, or, at the same time, observing the signal strength on the tuning
indicator, to determine the loop direction corresponding to minimum (or
zero) reception. The UGR-4U course indicator will show either the course
angle to the radio station, or the angle which differs from it by 180?.
3. "antenna" - in which a signal voltage is taken from the RSIU and
ARK-10 whip antenna (the compass section is disconnected).
23 J.
SECRET
NO FOREIC?i DISSE:d/NO DISC-?:.4 AEROAD/CONTROLLED DISSSM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 JX1-HUM
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED UIb liM
Y
Page 269
In thi's mode the radio compass functions as an ordinary medium wave
communications receiver and is considered to have a sufficiently high degree
sensitivity and interference resistance.
In the "Loop" and "Antenna" modes the type ARK-10 radio compass permits
listening to modulated, as well as to unmodulated, signals.
Controlling radio compass operation
Remote electrical control of the operation of the automatic radio
compass is carried out from the control panel installed or the vertical.
section of the starboard console in the cockpit between frames nos. 8 and
J, and includes the following operations:'
cutting in the radio compass by moving the transfer switch from
the "Off" position to the type of operation, that is, to one of three
:ositions - "Compass," "Antenna," or "Loop." First, however, the AZS
a:arked "ARK" on the after electrical switchboard of the starboard console
in the cockpit must be cut in.
2. remote tuning of the receiver to the selected frequency:
or tuning to any frequency in the operating band, by means of setting
w:e knob of the band transfer switch and the "Coarse tunin" knob and
"Fine tuning" (first haying pressed the push button marked with the letter
+i"YJ .l the corresponding
Page 270
Fosition;
or tuning to a fixed frequency, by means of pressing the push botton
corresponding to the previously assigned frequency. Frequencies for the
232
SECRET
1;O FOREIGN DISSEM/N) DISSZM ABROAD/CONTROLLED DI c1SQ
I
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SCR.LT
NO FOREIGN DISSFM/]WO DISSFM AB_: A N ii m t.;;.
closest'radio stations are fixed by the push buttons with the even numbers
(2) 4, 6, 8)'., while the frequencies for the distant radio stations are
fixed by the push buttons with the odd numbers (1, 3, 7, 9). The closest
station, and the most distant corresponding to it, have the proximate
numbers.
The even.numbered push buttons on the control panel, that is, all the
close-by radio stations, have been set on the remote wave transfer switch
which is installed on the vertical section of the port console in the
cockpit.
When turning to a landing the shift from the distant homing radio
station, set by having pressed the push botton on the control panel, to
the close homing radio station, set by the position of the remote wave
transfer switch, is done automatically by the all-purpose, UAP-1 transfer
switch automatic device.. The ARK BPRS indicator light on the instrument
panel lights up.
Manual tuning of the radio compass by use of the "Short-Long" transfer
switch in the aircraft is retained. (When the UAP-1 transfer switch is
operated the "Short-Long" transfer switch must be set to the "Long"
position).
Page 271
3. Switching the radio compass band pass by switching. the tumbler
switch with the inscription "Broad - Narrow" to the corresponding position.
4. Switching the "Telephone" and "Telegraph" operating modes by
switching the tumbler switch with the inscription "Tlf - Tlg" (Telephone-
Telegraph) to the corresponding position.
233
SECRET
NO FOREIGN DISSEM/PTO DIO?~ ADROAD/CONTROLLED DISSI!d
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NO FOREIGN DISSEM/NO DISS!M ARM') n. /CONTROLLED-1
5. Adjusting receiver gain in "Antenna" and "Loop" modes and ad-
justing signal volume in the phones in the "Compass" mode by rotating the
volume control knob with the inscription "Volume Control."
u. Remote rotation of the directional antenna to both sides, used
wren operating in the "Loop" mode, by using the tumbler switch with the
inscription "Loop L-P." Loop antenna rotation will.continue as long as
tile tumbler is held down.
Electrical Supply for the Radio Compass
The electrical supply for the type ARK-10 radio compass is obtained
from the aircraft's network, 27 volts direct current, as well as from the
PO-750A converter, which converts the network direct current into 115
volts, 400 cycle alternating current.
Page 272
Power requirements from the direct current network:
{1) with the heating circuit, the drum-type transfer switch motor,
and the automatic tuning equipment operating, the requirement is almost
450 watts;
2) with the heating circuit cut in, but with the control mechanisms
cut out, the requirement is about 250 watts.
The demand on the 115 volts, 400 cycles, alternating cirrent network
~>ut 150 volt-amperes.
Installation Location and Method of Securing Blacks
The ARK-10 receiver is installed in the upper equipment compartment,
Between frames nos. 5 and 6 (under blocks nos. 4, 5, 6 and 3 of the ASP-5ND
:ss;ht; above the SRO transceiver), on a shock-mounted frame, with the
234
SECRET
NO FOREIGN DISSEM/N0 DISSEU ABROAD/CONTROLLED DI3SCH
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/730 DISSEM A,BRQ] / a . SS;,.,
front panel facing to starboard. The frame is secured to a bracket which
is rigidly connected to frame no. 5 and the inlet duct sheathing. On this
side catches are used. On the other side the frame is set in a recess for
two special bolts which are, at the same time, used to secure the armor
plate to frame no. 6.
Page 273
The supply block is installed in the upper equipment compartment,
between frames nos. 3 and 4 (closer to frame no. 4), to starboard, directly
under the equipment hatch cover and is, on the one side, secured by two
screws to the bracket anchor bolts. The brackets are secured to the upper
longeron. On the other side the block is secured by toggle bolts set in
a clip secured to a stringer.
The ARK-1- control panel (figure 37) is installed on the middle, ver-
tical panel of the starboard console in the cockpit, between frames nos. 8
and 9 and is secured to the console frame by lug bolts on one side and by
the installation of two other lugs under a bracket-welded to the frame on
the other side.
The remote wave transfer switch (figure 38) is installed in the cockpit,
on the vertical section of the port console, between frames nos. 8 and 9.
The t1GR-4U course indicator is installed in the cockpit, on the port,
movable,, section of the instrument panel, and is secured to the instrument
panel by four bolts which screw into a flange.
Page 274,
Figure 37. Photograph captioned "Control panel for automatic radio
compass, ARK-10"
Figure 38. Photograph captioned "Remote wave transfer switch for
automatic radio compass, ARK-10"
23.5
SECRET
-14O FOREIGN DISSEIII/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
iC FOREIGN DISSEM/PTO DISSEM ABROAD/CONTROLLRD DI_SS94
VOLUME --- L.LOOP-P
MOW A rVart Norcaor?
ar,' 9? R Y
Figure 37.
;i-; `';U i}13 ;EM A!-T0AD/:'O'IT
Remote wave transfer switch for
automatic radio compass ARK-10
ILLUM.
MARROW
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
.
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
50X1-HUM
SECRET
NO FOREIGN DISSEM/N0 DISS.E .1 ABROAD/CONTROLLED DISSEM
Page 275
Tuning,indicator (ammeter) is installed in the cockpit on the hori-
zontal section of the starboard console (figure 39).
The "short-long" transfer switch is installed in the cockpit, on the
port, movable panel of the control panel.
The UAP-1 all-purpose switching device is installed in the cockpit,
behind the instrument panel, to the starboard side.
The antenna amplifier is installed in the vicinity of frame-no. 13, on
the after, fixed section of the canopy and is secured by four screws which
pass through the base and which are held by anchor bolts to the bracket
secured to the fixed section of the canopy.
The antenna control block is installed in the nose section of the
fuselage,, between frames nos. 2 and 3, underneath, in a special hatch,
along the aircraft's axis of symmetry and is secured by screws to anchor
bolts on the hatch frame.
Attention! In order to do away with the possibility of breaking the
feeder to the combination antenna in the course of removing the tail section
of the canopy, the feeder is installed so as to have a length of 320 milli-
meters between the. antenna and the first point where it is secured to
frame no. 13.
Page 276
Figure 39. Photograph captioned "Tuning indicator (ammeter)"
Page 277
2. Low altitude radio altimeter, type RV-UM
Purpose
2.37
71
140 FOREIGN DISSE?4/NO DISSE"S ABROAD/COI:TROLLED DISSZYJ
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
w.. ECRFT r;?=.
t"ORETGN DISSEM/NO DISSENT ABROAD/CONTROLLED DISSEM
SFCRFI'
GT1 DISSFY/--,10 DISSFru?1 A3T,^_,AD./''0TT
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
1"0 POIET1?T DISSEII/2o0 DI:S`" ~`?TnAT) C
The type RV-UM low altitude radio altimeter is designed to determine
the true fl~ght altitude of the aircraft above the ground surface and to
ensure signalling of the dangerous altitude previously set by the pilot.
Composition
The type RV-UM low altitude radio altimeter, as installed in the air-
craft, includes:
1. the transceiver - block PP-U;
2. transmitting antenna;
3. receiving antenna;
4. UV-57 altitude indicator
5. Indicator pilot light (red)
6. PSV-U dangerous altitude transfer switch
7. VChF-3 filter
7K-19K runs and feeders
The schematic of connections and location of the RV-UM radio altimeter
blocks in the aircraft is shown in figure 40.
Page 278
Figure 40. Schematic of connection and location of RV-UM radio
altimeter blocks in the aircraft
Page 279
Figure 40. Schematic of connections and location of RV-UM radio
altimeter in the aircraft
1. Transceiver - PP-U block
2. Transmitting antenna
3- Receiving antenna
4. UV-57 altitude indicator
239
SECRET
NO FORPTCrI DISSEM/IT0 DIES t,, ABP0. D/CONTROLLED DISSEIY
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
NO FOREIGN DISSEb4/?d0 DISSI'::'t ABROn.?~7CUt~ s
5. Indicator pilot light
6. PS'-U dangerous altitude transfer switch
7'. VChF-3 fliter
7K-19K - Runs and feeders
Page 280
Operating principle and brief technical data
The type RV-UM radio altimeter operates on the basis of the phenomenon
that radio waves are reflected from the earth's surface. In order to deter-
mine the altitude at which the aircraft is flying the frequency modulation
of a radiated signal is used (as time passes the frequency of the radiated
signal changes in accordance with a fixed law; the amplitude remains con-
stant). The frequency used to modulate the signal radiated by the trans-
mitting antenna of the radio altimeter is 70 cps * 10 cps. The width of
the modulation band is 17 megacycles. The altitude measured is from 0 to
600 meters with an accuracy of t 5 meters to within t 8 percent.
The signal radiated by the transmitting antenna of the radio altimeter
reaches the ground and is reflected by it, to be picked up by the radio
altimeter's receiving antenna and fed to the receiver input. A special
feeder inside the radio altimeter transceiver supplies a direct signal,
directly from the transmitter to this same, input. The path of the return
signal (it will depend upon the flight altitude of the aircraft above the
ground) lags behind the path of the direct signal, so that the reflected
signal is fed to the receiver input later than the direct signal. Because
.of the use of frequency modulation, the frequency of the reflected signal
will be different from that of the direct signal by a value which is directly
241
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET I
1d0 FOREIGN DISSE!1/11O DISSr:.1 ARRO1D/CONTROLLE.) DISS Vf
uruportional to the altitude of the aircraft. As a result of the struc
cure of the direct and reflected signals, a voltage
Page 281
occurs in the receiver which is the beat frequency between these two
i;nals and is proportional-to the altitude above the ground.,
Radio altimeter operation
Radio altimeter operation reduces to three basic tits:
1. radiation of high frequency oscillations from th-- SVCh .(super-
114
1.7,11 frequency) generator, frequency modulated, from the transmitting an-
tenna;
2. reception of signals reflected from the ground b;~ the radio al-
timeter's receiving antenna;
3. measurement of the time between the moment of radiation of the
`requency modulated signal and the moment it is received, by measuring
he beat frequency of the direct and reflected signals which depends upon
_1.e aircraft's altitude. (The beat frequency is directly proportional to
:h altitude, the modulation frequency, the modulation band and is inver-
eiy proportional to the radio wave propagation velocity). The beat
Frequency voltage is converted into a direct current in the transceiver
_rt the RV-UM radio altimeter proportional to the beat frequency. The
t obtained passes through the UV-57 altitude indicator and delfects
Page 282
r the current is proportional tp the beat frequency, and the beat
r>quency is proportional to the aircraft altitude, the scale is graduated
242
SECRET
'O FOREIGN DISSEMINO )ISSEM ABROAD/CONTROLLED DISS:N
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
1vv i' Uil 'llrz~ L.LJ ~=~:,. 1VU 1J .L ~i ' S.a.
50X1-HUM
directly into altitude in meters.
In order to avoid false indications on the UV-57 altitude indicator
at altitudes in excess of 600 meters, the RV-UM radio altimeter transceiver
has an interlock circuit which moves the indicator needle into the right
stop.
The transceiver also has a signal circuit for dangerous altitude
which provides alight and sound indication for the pilot when the air-
craft descends to one of the previously fixed, and set by the pilot,
(dangerous) altitudes. The signal of dangerous altitude sounds (a 400
cycle signal which is interrupted every 2 to 3 seconds) in the pilot's
helmet, and he is, at the same time, warned visually (a red pilot light
on the port, movable panel on the instrument panel in the cockpit, lights
up). Signals for dangerous altitude occur at the following altitudes:
50 meters, 100 meters, 150 meters, 200 meters, 250 meters, 300 meters,
400 meters, in accordance with the position of the dangerous altitude
transfer switch.
When the radio altimeter is cut in on the ground the sound signal
functions and the red pilot light lights up and it will burn until such
time as the aircraft climbs to an altitude which is higher than the setting
on the dangerous altitude transfer switch.
Page 283
Radio altimeter electrical supply
The supply for the type RV-UM low altitude radio altimeter comes from
the aircraft direct current network through the PO-750A converter, which
converst the network direct current into single-phase, alternating current
213
SECRET
NO F0flI";1 DISSE2. /A,O DIS;'T5;M AB2,0AD/CONi'ROLLED DISSE1f
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
110 FOREIGN DISSEM/NO DTSSEM ABROAD i T F ULLED-DI
at 115 volts, 400 cycles. The 115 volts, 400 cycles voltage is fed to
.he PP-U transceiver and delivered to the supply circuit installed in it
nd which consists of the anode-filament transformer, a rectifier with a
Iwo-section pi-section filter made up of chokes and condensers; it is
stabilized.
The type RV-UM low altitude radio altimeter is cut in by closing the
AS bearing the nameplate "4arker, RV-U" on the forward electrical switch-
hoard on the starboard panel in the cockpit.
Installation Location and Method of. Securing Blocks
The transceiver of the RV-UM radio altimeter is installed in the upper
ouipment compartment, between frames nos. 3 and 4 on a horizontal stiffener
)low the nosewheel on the frame and secured by two screws and anchor bolts
i:o a bracket. Four shock mounts are secured to the frame which carries the
Transceiver block panel.
Page 284
The transceiver is secured to the shock-mounted panel by lugs which
re inserted in special openings in the panel on one side and by catches
r'sd;eh the clips fit into and tightened to the panel by screws on the other
The transceiver is installed with its front panel facing frame no. 4.
_cccss to the block is through a special door.
:The receiving antenna for the RV-U radio altimeter is installed on
the starboard wing, underneath, between the tips of ribs nos. 23 and 24.
antenna is secured by four screws which pass through the flange and
re held by four anchor nuts on the lower wing sheathing. The receiving
..bhtenna is positioned along the direction of flight (with. an accuracy of *-2?) .
244
SECRET
NBC 70RETGrN DISSEM/:;O DISS EM AB1 03_D/COFTR0LLED DI SS:4;
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
110 FOREIGN CSEL /,, 1!'x'7^^D/COi1TP SS59
The transmitting antenna for the IWV-U radio altimeter is installed on
the port wiry? underneath, between the tips of ribs numbers 23 and 24. The
antenna is secured by four screws which pass through the flange and are held
by anchor nuts on the lower wing sheathing. The transmitting antenna is
positioned along the direction of flight (with an accuracy of t2?).
The UV-57 (figure 41) altitude indicator is installed in the cockpit
on the port, movable panel on the instrument panel and fastened to it by
four screws which pass through a flange.
The PSV-U dangerous altitude transfer switch (figure 42) is installed
in the cockpit on a side panel of the instrument panel and secured to it by
four screws
Page 285
which pass through a flange.
The dangerous altitude indicator light is installed in the cockpit on
the port,. movable panel of the instrument panel.
Page 286
Figure 41. UV-57 altitude indicator of the RV-UM radio altimeter
Figure 42. PSV-U dangerous altitude transfer switch of the RV-UM
radio altimeter
Page 287
3. Radio receiver marker installation, type MRP-56P
Purpose
The type MRP-56P radio receiver marker device is designed to indicate
the passage of the aircraft over points located at fixed distances from the
245
SECRET
NO FOREIGN DISSEM/NO DISS '.' ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
71
w " V7 - 7Z
r f
SECRET'*
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM!
c = -~rT+w - yam:?t- r
-'Figure 42. PSV-U dangerous altitude transfer switch
SECRET
;O FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '1X1-HUM
NO FOREIGN DISSE14/I.TO DISS,1!,,14 i13:ROAD/CO11,TfOLLED DISC y
landing strip by receiving radio beacon marker signals.
Composition
The following units, which make up the MRP-56P radio receiver marker
installation, are installed in the aircraft:
1. the receiver;
2. an antenna inside the fuselage;
3. an indicator block;
4. a "Marker" pilot light;
5. the runs and feeders.
Figure 43 is a schematic of the connections and the location in the
aircraft of the blocks which make up the MRP-56P radio receiver marker
installation.
Operating principle and brief technical data
The type MRP-56P radio receiver marker installation is part of the
system for
Page 288
Figure 43. Schematic of connections and location of type MRP-56P
radio receiver marker installation in the aircraft
Page 289
Figure 43. Schematic of connections and location of type MRP-56P
radio receiver marker installation in the aircraft
1. Receiver
2. Antenna inside fuselage
3. Indicator block
4. "Marker" pilot light
Page 290
247
SECRET
NO FOREIGN DISSEYr
/NO DISSE:,f APROAD/CONTROLLED DIS, .y
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
.J ~ J V RL 1
!i FO TGN DI S"JM/NO D1. S -rri
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
NO r MMU('_+T PISS D.i/y Q OTSPT-f hfir
simplifying the process of landing the aircraft blindly, on instruments.
The principle of operation involves the reception of pulses radiated from
a marker radio beacon and converting them into light and audible signals
of the same duration.
The. type MRP-56P radio receiver marker installation operates. on a
frequency of 65 megacycles. The modulation frequency has an amplitude of
3,000 cycles, while the percentage modulation is 30%.
The supply for the filament circuits of the tubes in the radio
receiver is 27 volts from the aircraft on-board network. The anode circuit
supply for the radio receiver comes from the receiver of the type RV-UM
low altitude radio altimeter and is 220 volts direct current. 115 volts,
400'cycles, alternating current, and 27 volts direct current, are used for
the signal circuits.
Purpose, operation, location, and methods used to secure the blocks in
the aircraft
The antenna inside the fuselage, used with the MRP-56P radio receiver
marker installation, from an electrical point of view, is an unsymmetrical,
very short, dipole located inside a metallic cavity and tuned to resonance
using loading condensers.
Page 291
On the forward side the cavity is covered by an organic glass lid. The
antenna is installed in the tail section of the fuselage, between frames
nos. 30 and 31A, underneath, on the starboard side, next to the drag-'
chute compartment, in a special hatch. The antenna is secured to the hatch
frame by catches. The hatch cover is installed flush with the skin of the
fusllage.
249
S -, n Rr T
NO Fc T::";t Apf{O D/CONTROLLED DISSJM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
r ri
NO FOREIGN DISS M/1+TO DISSE 1 ADRO,AD/CONTROLL DISS:N
The receiver in trig type MRP-56P installation is designed to amplify
a stage of uhf voltage taken from a section of the dipole of the antenna
inside the fuselage and deliver it to the receiver. A three-stage, low
frequency amplifier is used to rectify the voltage and deliver it to the
low frequency amplifier input, the circuit of which contains the winding
of relay RE-53-V. At the same time, its contacts close tr,e 27 volt, direct
current, circuit which serves to indicate passage of the aircraft over
the marker radio beacon;
The receiver is iistalled in the tail fin fairing, between frames nos.
33 and 33A, on four shcek mounts which are secured to the panel.
Page 292
The indicator blocc in the installation is designed ti provide an
audible signal (at a fitquency of 400 cycles) in the helmet phones for the
pilot when the aircra?t,passes over the marker radio beacon.
When a signal is present at the receiver input, and relay RE-53-V
operates as a result ofthis signal, 27 volts is fed to terminal 2 of the
indicator block.
This voltage is su,blied to terminal 1: of relay windi7Lg in the indica-
Lor block. The relay f.,ctions. Contacts '.3-2 and 6-5 in the relay, normally
open, close, and, at thesame time, close the 115 volts, 4(0 cycles, single
alternating currenncircuit as well.
An audible signal i'fed to the pilot'sjhelmet phones.
The indicator block installed in the `cockpit, on the starboard
console, at frame no. ll.t
The pilot light, stetiled "Marker," is installed in the cockpit, on
20
FOREIGN DIS11!? 0 DiSSE'i ABROADl;ONNTROLLED D ^S 'q
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
~E(;tlL' 7'
NO FOR IG i Di5'Hmt /n ?r ~e rte.
the T-4 signal panel which is secured to the instrument panel by two screws
which pass through toggles.
Page 293
Figure 44. NIRP-56P receiver
Page 294
Figure 45. MRP-56P antenna
Page 295
I.V. Airborne responder in the identification radar system,'SRO-1
Purpose
The SRO-1 airborne responder in the identification radar system is
designed to identify the aircraft with elements of its own forces by sending
coded responses, in the form of signals, upon interrogation by air, ground
or seaborne elements.
Composition
The SRO-1 system, as installed in the aircraft, includes the following:
Page 296
1. antenna
2. transceiver
3. code panel
4. inertial contactor
5. exploder circuit control panel
6. exploder push button
7. remote transfer switch for "distress" signal
8. F14A filter
9. runs and feeders
2 1
SECRET
NO FOPEICIT DISSEM/fiO DI ;~^ Oa1D/CO~~T.IO ._ DISS
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
STAT
Man-
710 FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
-
SECRET DISSEM
N ROLLID
DISSEM/NO DISSEM ABROAD/C0
O FOREIGN
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
NO FOPrTOT? DIS"B'g/]'^ .PT"": I.^ 0.11)/CONTROLLED DISSE4
The schematic showing the manner in which the airborne responder in
the SRO-1 radar recognition system is connected is given in figure 46.
[page 305)
Page 297
Principle of operation
The airborne responder in the SRO-1 radar recognition system is con-
nected with a series of interrogators which can operate on different
frequencies. In order to provide the possibility for responding to any
interrogator, there is a provision in the SRO-1 responder for a smooth
change with respect to time in the frequency to which tuned, ensuring
coverage in the frequency range between 160 and 170 megacycles. The tuning
process takes place automatically.
The smooth change which occurs in the frequency tuning is attained by
changing the inductance in the high frequency circuit by varying (with a
special mechanism) a short-circuited loop inside the leg. The time to chance
the frequency, within the limits indicated above, from the minimum to the
maximum value, and return, is the time for one cycle of variation, and is
equal to 0.64 second. The variation cycle consists of the forward and back
movement of the loop. Reception of the interrogating and the transmission
of the answering signals occurs only during the forward
Page 298
movement of the loop. During the return movement the responder is blocked.
(The high frequency circuit is common to the receiving and transmitting stage
in the responder. Consequently, reception of the interrogating and trans-
mission-of the responding signals takes place, for all practical purposes,
25
SECRET
NO FORI'TC'' T Iss:::'/idfl AI3TO D/CONTROLLED DISS2'd
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
NO FOPP-7-7I DISSE'M/NNO DTSST M iET)o, D/CONTROLLED DISS1M
on one and the same frequency of circuit tuning).
The coding of the response signals is in accordance with the Morse
alphabet. The "dot" corresponds to a pulse of short duration, while the
"dash" corresponds to one of long duration (2.5 to 3 times the width of
the short, or narrow, pulse).
Each code in the given coding system is a letter in the Morse system,
and consists of a maximum of four signs(pulses). In order to keep the
letters from merging into each other while reading the code, the-letters
are separated by pauses. Thus, the code consists of a collection of pulses
and pauses within 5 tuning cycles (so that the fifth cycle is always used
for the pause) which requires 3.2 seconds for its transmission.
Page 299
The airborne responder in the SRO-1 radar recognition system has four,
one-letter codes. In addition, a special distress signal is incorporated
in the SRO-1 responder - a broad pulse, the length of which is considerably
longer than the length of the ordinary pulse in any of the codes. The
distress signal is transmitted on that cycle of the tuning which is used as
a pause, so that the transmission of the code which is set up is unchanged.
The responder contains a detonator for blowing up the transceiver
installation. The detonator is set off either by the pilot himself by
means of the exploder button in the cockpit on the horizontal section of
the starboard console, or by automatic operation of the inertia contact,
which functions in the
Page 300
event the aircraft falls.
255
SECRET
NNO FOREI N DISSE21 /ITO DI: :': APROAn,'cON`PROLLED DISSTM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 I
'.O rOREIGN DISSE;a/1TO DIS ; , A32 AD /CON? E ISS-~d
Purpose, brief description of characteristics, and the methods used
to secure the SRO-1 responder blocks in the aircraft
The SRO-1 responder transceiver is made up of the transceiver proper
and supply block which, from the design standpoint, is made in two chassis.
Both blocks are fastened with screws and covered with individual covers.
The transceiver is installed in the upper equipment compartment, bet-
ween frames nos. 5 and 6.
The antenna, common to the receiving and transmitting sections of the
responder, is designed to receive high frequency interrogation pulses and
to radiate answering, coded pulses from the SRO-l's radar responder.
Page 302
The antenna, with its tuning cells (segments of a long line, made in
the form of a cylinder, with a movable plunger in it, serves as the tuning
coil) is a stub dipole with a conveniently faired section 260 millimeters
high.
The antenna is installed in the nose section of the fuselage, between
frames nos. 21 and 22, on top, along the axis of symmetry of the aircraft.
The code panel is designed to replace change codes, control and monitor
the operation of the SRO-1 responder.
The code panel is installed in the cockpit, on the vertical section of
the starboard console.
Page 303
The inertial contactor is designed to automatically close the detonator
circuit in case of emergency.
The intertial contactor is installed in the upper equipment compartment,
256
M FO7 :,7. i1 LI ' /::O L' ' ' A CL /CC i;O L L DISSIM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
SECRET
r Pr (?7 TSSEM N TCr']?. A. ~UALIIUOIIIIL
between frames nos. 4 and 5, on the port: side.
The exploder circuit control panel is installed in the upper equipment
compartment, between frames nos. 5 and 6, on the port side.
The exploder push button is designed to deliver a voltage from the on-
board network to the detonator which, if exploded, will destroy the trans-
ceiver installation.
The exploder push button and the "(distress" signal transfer switch are
installed in the cockpit, on the horizontal section of the starboard
console.
Page 3 )4
The F14A filter is installed in tho upper equipment compartment,
between frames nos. 4 and 5, close to the starboard side.
The remote "distress" signal transfer switch is installed in the cock-
pit, on the horizontal section of the starboard console.
Page 30.!
Figure 46. Schematic of block connections. Responder in the SRO-1
radar identification system.
Page 306
Figure 46. Schematic of block connection. Responder in the SRO-1
radar identification system.
1. antenna
2. transceiver
3. code panel
4. inertial contactor
5. exploder control circuit
6. exploder push button
257
panel
SECRET
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 CIA-RDP78-03066R000200020001-6 V1 U, IRA
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
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" rTC1 7'(lt?T"T('?T DIS` 'i/.'.`(1 II1 ,. r `)A'1/( i'VtI >....
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7. Remote "distress" signal transfer switch
8 7 F14A filter
Page 307
Figure 47. The code panel
Page 308
Figure 48. Exploder push button
Page 309
V. Airborne range-only radar SRD-SMK
1. Purpose
The airborne range only radar is designed to determine the instant of
effective launch of "air-air" homing missiles, as well as for operating
with the gunnery sight,.and ensures, in the first instance:
(1) automatic, and continuous, determination of true range to the
target and transmission of this true range value to the UD-1 range indica-
tor which is installed on a special bracket fastened to the sight range
indicator;
(2) automatic comparison of true range with permissible range for
launching the K-13 air-to-air homing missiles and delivery of permissible
launch signal - a green pilot light for "permissible range" lights up. It
is installed on a special bracket;
(3) indication of reaching the range at which the attach is to be
broken off (turn away), eliminating the possibility of the pilot being
hit by fragments of his own missiles - a red pilot light "withdraw from
attach" lights up. It is installed on a special bracket;
in the second instance it ensures:
259
Ll a..iL 11L' 1
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 ? _.
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170 FOREIGN DISSEM/1N10 DISSEM ABROAD
continuous input to the computer for the gunnery sight of
voltages proportional to the range and relative speed of the target.
Page 310
2. Composition
The following components are installed as part of the range-only radar
system (see figure 49):
1. combination antenna - block K-1 - and waveguide tract;
2. transceiver - block RB6-2M;
receiver block - block RB6-3;
4. supp'y block .. block RB6-4;
S. speed block - block RB6-5;
monitoring and control panel - block K-6;
7. comparator block - block K-8;
8. permissible range computer VRD-2A;
9. range indicator UD-1;
10. air speed transmitter DVS-5;
11. temperature receiver P-5;
12. "permissible range' indicator light;
13. "withdraw from attach" indicator light;
14. "RS, Cannon-SS" mode switch
15. push button for dropping target;
16. control plug;
16K - 27K. runs and feeders.
The schematic for the connections and the location in the aircraft of
the blocks which make up the radar system are given in figure 49.
2o2
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NC FOPJI N DISSFI,t/?I0 D. c1. n ? r 'r
.1.~.. . P ran irn ? r;1ZL T)TS`lTV -1 A
A. Instrument panel
The instrument panel is installed in the plane of frame no. 7B.
'`ounted on the instrument panel are the most important,, and necessary,
instruments used by the pilot in constantly controlling the attitude
of the aircraft in space, as well as the operation of the power plant
n flight. The instrument layout, a: as the 1a rout of other
rlcments used for control, or the instrument panel iti sho-~.:i in
figure 6.
The instrument panel consists of five duralumin stampings,, two
of which are shock mounted. The other three are rigidly secured to
the sides, as shown in figure 57..
Cr F:T
It FOREIGN DISSEM/ i0 DISS ':; AL??OA-)/CO:T TOLLED D.:.SSIM
50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
2. Cockpit layout
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 : CIA-RDP78-03066R000200020001-6 )X1-HUM
VO F0PEICN DISSL?,,,/NO DISS; "?,M ATrOAD,fCO', utiI.
. Panels 1 and 15 are mounted in a tubular steel framework and are
secured by special nuts 5 to screws 6'. The steel framework is, in
turn, suspended through four shock mounts 2 from brackets.
Page 351
Figure 56. Instrument panel
Page 352
Figure 57. Instrument panel design
1 - Panel B; 2 - Standard rubber shock mounts; 3 - Panel A; 1. - Tubu-
lar framework; 5 - Special nut; 6 - Screw; 7 - Sight head bracket;
8 - Panel G; 9 - Support; 10 - sleeve; 11 - dowel; 12 - guide; 13 -
stop ring; 11. - Panel D; 15 - Panel
Page 353
When the nut 5 are unscrewed the panel is easily removed inside
the cockpit,
providing an access to the electrical plugs, the hose connections,
the instruments and the equipment located on the instrument panel.
In addition, Panel 1 is made so that it can be pulled out on two
dowels, or pins, 11.
The tubular dowel, or pin, can be moved in the guide 12, its move-
ment limited, however, by stop ring 13. If this latter is pulled out
the panel can be completely removed.
Panels 3, 8, and 14 are rigidly secured in place along frame num-
ber 7B with screws and are made so that they can be removed. The loca-
tions of panels 3, 8, and 11i are clearly shown in figure 57.
A white, painted stripe in the middle of the instrument panel is
used to determine the neutral position of the stick in the transverse
direction for aileron control.
305
SEi;i:I
0 I1?. 3U'i =.' !-'To Z'`"? /C NT1 OLLL+'D DISS^g
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/NO DISSEM ABROAD/C4)NT - 01611'
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78 03066R000200020001-6
'SECRET
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
'O 'OFETGPT DISS%tii/.ilk DISS ?1 C ; , ? ; ~i'. JbIj .
B. Middle panel
The middle panel is set underneath the instrument panel along the
",`-craftu axis and is tilted towards the pilot at an angle of 350 dram
the vertical.
Figure 58 shows the location of the equipment elements on the
Pa.-;e 35L.
Figure 58. Middle panel
page 355
figure 59. Middle panel design
I - Channels; 2 - Tubular steel framework; 3 - Threaded tube; 2+ - Panel
screw
e 356
T'',-,e panel is a stamped duralumin piece (see figure 59) which is
s cured in place with four self-locking screws 5 to the frame 2.
The frame 2 is made of welded steel tubing and is Sc; in the than.
rzcl 1 on the cockpit floor.
Four steel sleeves 3, threaded to take the screws 5, are welded
t frame 2. This installation makes for a secure fastening of the
:nel to the aircraft structure.
C. Port console
The port console is positioned along the port side of the cockpit,
7c.;;ueen frames nos. 7B and 10. Mounted on the console are the units
to control the engine, fuel system, fire extinguisher, armaments,
otter eq_uipent. instrument placement on the console is shown in.,
YU T1.1 /_.~S s...,, q ITiO
50X1-HUM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
'50X1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
50X1-HUM
TO FOREIGN DISSEM/2110 DISSEM ABROAD/ .. "..
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRE'2
r()r '!7rT7 D7SS E"'/T?(? D 4Sr ,r nn, ~^ nr, err, TTROI,T Fit) P.' ' ..
~n
The console consists of a vertical and a horizontal section (see
figure 61)./ The vertical section includes three removable duralumin
panels (2, 3, 4) which are fastened to the side along the frame with
special screws.
Horizontal section 1 is made as a fixed section and is secured
in place with ordinary screws to the tubular steel frame installed on
the side of the cockpit. A sufficiently clear outline of the console
design is shown in figure 61.
D. Starboard console
The starboard console is posi-~ioned along the starboard side of
the cockpit, between frame nos. % and 10. Mounted on the console are
the forward and after
Pa-;e 357
Figure 60. Port console
Page 358
Figure 61. Port console design
1 - Horizontal panel; 2 - after panel; 3 - middle panel; 4 - forward
panel; 5 - electrical switchboard
Pane 359
Figure 62. Starboard console.
Pa, e 360
Figure 63. Starboard console design
1 - After panel; 2 - Middle panel; 3 - Horizontal panel; 4 - forward
panel; 5 - forward electrical switchboard;'6 - ARK-10 control panel;
7 - SRO control panel; 8 - after electrical switchboard
311
SECRET
NO FOREIGN DISSE:: /Ro DIssJ;:d ABROAD/C0_' Ru.L ED. DI S:,:~1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/NO DISSEM b.3RO.AD7C0_ TROLLED DIS4:,.
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Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
5UX1-HUM--. - ---I
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
SECRET
NO FOREIGN DISSEM/NO DISSEM AB'6 ..
50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19 : CIA-RDP78-03066R000200020001-6
SAC i1; i
X -O FOREIGN DISS V'J O DISSEM.ABRO07CONTR .
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
c Sri(.
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NO FOREIGN DISSEM!NO DI SCI pr ~r: s
Page 361
electrical switchboards, the control panels for the radio equipment,
ansfer switches, valves, and other apparatus. The in,trument layout
the console is shown in figure 62.
The console consists of a vertical and a horizontal section (see
=:_g 0 63). The vertical section contains three renova.)le duralumin
w..els (1, 2, 4+),, which are secured to the side along tae frame with
racial screws.
There is, on panel 1, a t.:?ansparent, hinged cover hioh serves
~o protect the circuit ::,w ewlers on the after electrical switchboard
.r on being accidentally moved by the pilot in flight.
The horizontal section 3 is made up of three fixed,duralumin
anels which are secured to the tubular steel frame by ordinary screws.
Figure o3 shows the console design quite clearly.
Bage 362
3. Piloting and navigating instruments
The piloting and navigating instruments permit the pilot to use,
o;:;rrectly and completely, the flight and tactical capabilities of the
aircraft.
All instruments which .ssist in checking the attit ade of the air-
wa?t in space, relative tothe ground, and which are t.:ed in navigat-
belong to the piloting; and navigating instrument grouping.
included in this group jf instruments are:
the :SUS-2500 cctnbi nation speed indicator;
the ACID-1 mas {r attitude indicator (gyrohorizon)
3 iC
i3 FOR 113 D:r si..'! io DIS < AM';O".~J/CONTROLLED '-)ISSZ!A 1
Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 50X1-HUM
'D F, T;,l
NO FOT?EIGNT DICSI?/?l0 DI.r!'3'J1! AT t)An/Co'?TIOILED PTs":.v
C. the KSI fighter plane course system;
D. the.VD-28 two-needle altimeter;
the EJP-53 electrical turn indicator;
F. the ACM 3 aviation clock;
G. the VAR-500 climb indicator;
II-. the "m" number indicator (P4-2.5)
1. the UV-57 indicator of the RV-UTM4 radio altimeter;
J. the ARU-3V arm position indicator;
K. the overload indicator for the .AM-lo accelerometer
The instruments operate on various p.: inciples . Some of air
navigation instruments operate of the PZD system, on the prin-c'ale
of the measurement of dynamic and static pressures in flight.
operation of others is based on the radio engineering, electrical
and gyroscopic principles for the particular device.
Page 363
A. The KUS-2500 Combination Speed Indicator
The instrument is designed to measure the forward speed of the
aircraft relative to the air mass and is expected to indicate within
the range from 200 to 2500 kilometers per hour at flight altitudes
from 0 to 25 kilometers. Instrument operation is bass. on the measure-
ment of the difference between the absolute dynamic and static pressures
of the air in flight, that is, the velocity head and the pressure of
the ambient, together with the introduction of methodical corrections
for air density for altitude, determined with the aid, of an aneroid
device.
3 i_7
SEE C .'R T
1v0 FOREIC:'T DI`'SI%/:INO 'DTI ^T"d ABFOAD/CONTROLLED DIS`"IM
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L4.i{L L
t0 FOREIGN DISSELf/ '0 DIS"r's 1'{`'r" Tl..S,..7.
For reading purposes the instrument has only one scale, calibra-
ted from 200 to 2500 kilometers per hour with divisions every 20 kilo-
meters per hour up to 400 kilometers per hour, and ever.,- 50 kilometers
{
,,er hour from 400 up. The meter has two needles. One needle (the broad
one) indicates indicated flight speed in the range from 200 to 1800
ii l ometers per hour, while the other (the narrow one) indicates true
air speed in the range from 400 to 2500 kilometers per hour. See
-Li; ure 64.
Figure 61+., KUS-2500 speed indicatcr_
P^ e 3614
D. The AGD-l Remote-ii1 icatingMaster Attitude Indicator
A new master attitude in icwt-or has been installed in the aircraft.
The AGD-1 master attitude indicator, with slip indicator, is
designed to deterr:ine the attitude of the aircraft in state relative
to the plane of the true horizon when the ground is not visible. In
addition, the master attitude indicator determines the presence of,
and the direction of, lateral slip of the aircraft.
In the well-known AGI-l master attitude indicator the indication
elements are mechanically linked to the gyroscope, makin,: it difficult
to obtain an indication which visually simulates the actual position
_.a the aircraft. in flight. For example, the AGI-1 master attitude in-.
aicator simulates the horizon by a white line on a spherical scale,
distinguishing the "sky" (the blue background) from the
brown background). At the same time, however, t he "sky" is below,
and the "ground" is above, u_e horizon line, making it neaessary for
J~V
C iET
C FO EDn.r .
~y DIJ ~SE`t1/'d0 ,'AIS~7Mt r,~~^-`1/COiT OELED r''Sr7G1
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SECRET
TO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
3rd ~-~i'-==
ip uIp II}N~ 'Sbs~I I*$M: t** ao'!tea.'1s._+
.(p('e nil ASV.tsrr OT001 $M?ti W t,: 3ij90K W *0 s
!_ @more ?i w A@$ IF ijit'
?~~~t!* 4d0rh"C0 ?'! i11/Vi ? o M~Q lej? ?
7Y: - ! us "Aw. 0.186 Midi f ' ,
3F% s!: 't
c~~is~[~ R# -rte i+ # IQMag
.ea.~ax ? OtIltUCliU .r&LL4LJI b a f>D1 13i1~, .
s~swl~lia l if 9014013 SO t012t4fl aCIA -
JA X& WW sMQs'lr.c~s +l~l~le! C welr~lat ?
W AA ZS.t Q/sc., ?
, e law a
l,0!'EIGN DISSEM/NO DISSEM ABROAD IC ONTROLLED DISSEM
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RhT
r,, C .i i~.Jl
ITO FORT'?Tr'T I~.J i S '4 NM DIr'I, , 11 1 ?i 1 C..
tlie: pilot to reorient himself when shifting from visual flight to in-
struments. A material deficiency in the AGI-1 master attitude indica-
tor is its property of kicking out (the matching of the external axis
of the cardan ring with the axis of the horizon) when the aircraft is
doing complicated maneuvers involved in piloting. In addition, the
AGI-l has large post-takeoff and post-turn errors.
These errors,,in the AGD-1 master attitude indicator, have been
eliminated, or have been reduced to a minimum.
In the AGD-1 the visual indicator for the horizon is a fallow-up
system which reproduces the bank and pitch angles in accordance ...th
electrical signals _:Jrovided by the remote gyro transmitter. This has
permitted the provision of the most rational, large-scale system of
indications with the "ground" and the
Page 365
?sky" in their natural positions.
Complex Composition
The AGD-1 master attitude indicator complex contains:
the gyro transmitter;
the horizon indicator (figure 65).
The /27 volt supply for the master attitude indicator comes from
the aircraft network, while the alternating current, 36 volts, 400
cycles, three phase, comes from the PT-500Ts converter.
A correction cut-out switch, VY.-53RB, is connected to the gyro
transmitter in order to cut out the transverse correction when the air-
craft is turning.
320
SECRET
EtEEO FOT?Ti`TMT SEM 7 Tc?nr,ir
._: T~T.S /r,0 T, T
,?.:,?, ^t?nr~~^/r02TROLLED DISSIM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
50X1-HUM
'"he P -500Ts converter and the VK-53RB correction cu:-out switch
..et a port of the AGD-1 complex.
ACD-1 Master Attitude Indicator Operatin ;
2rinciDles
kinematic diagram of the transmitter and indicator is given in
66.
The ;rgiro transmitter is a yroscope with three de4>re: s of freedom
consists of the gyro unit 16 and a cardan ring 20 installed in
inns in the follow-up gimbal! 22. The follow-up LI::=s-.._, with the
of the fine adjustment motor 1-, constantly maintain. exter-
;xis of the cardan ring 20 Q_ae axis of rotation) in a position
__ah is perpendicular to the ... axis of the gyroscope -y.
i;---;UTe 65. _GD-l indicator
367
Vine adjustment of the gimba:' is made in accordance with a signal
.. ? r. r: tie induction transmitter 13, the armature of which is fixed to
_._v shaft of the gyro unit, while he stator is fixed to :he cardan
;siren the external axis of t 1i, cardan ring is disp"aced from
?_-- osition perpendicular to the i lin axis of the gyroscope 19, the
.. ,i on transmitter sends an AC s tial to the amplifier input. The
si"ns! is amplified and delivered to lie type DG-l motor-generator 14,
:c i, through a reduction, makes the .ine adjustment of gimbal 22,
,.,___ , at the same time, restoring peo'ndicularity of the external
t ,e cardan ring and the mil g;?oscope axis. At the same time,
21
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
;>ECREJ'
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
Figure 65. AGD-1 Indicator
w N
322
SECRET
r,r'OPEIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
"fO FO JT( r'n 50X1-HUM
this fine adjustment takes place at a rate known to be greater than
the -oossible rate of change in the banking of the aircraft. As a're-
sult, for any aircraft maneuver, the gyroscope rotor axis does not co-
incide with the cardan ring axis and the gyro transmitter tak
4
es on the
property of "not kicking out."
In order to damp out oscillations in the gimbal 22 in the cource
of making the fine, adjustment, a tachosignal from the motor-generator
(that is, a voltage which is proportional to the rotation rate of the
gimbal) is fed to the amplifier in the form of a negative speed feed-
back where it is summed with the signal from the induction transmitter.
In the event the pitch angle of the aircraft is greater th_;- - 900, and
in order to Provide for correct movement of the gimbal to make the fine
adjustment, the phase of the control signal from the induction trans-
mitter to the motor-generator 14 is switched by the commutator 17.
The commutator 17 is located on the external shaft of the cardan ring.
Owing to the presence of the commutatorthe follow-up gimbal has two
operating positions relative to the gyro rotor axis: a main position to
which it is adjusted by a remote caging systemand position rotated
1800. Normal tracking of the gyro axis by the gimbal is assured in
both posit ions.
The vertical position of the gyroscope rotor shaft is c:.::rolled
by a pendulous,, liquid corrector (not shown in the diagram) secured to
the lower surface of the gyro unit. The corrector acts on two correction
motors, the longitudinal correction (21)located on the internal shaft
of the cardan ring, and the transverse correction (18), located on the
i.O ~OT T(x, DISSE. /:70 DID" , /r0JIL l] uIS~~~,1
! 1
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;50X1-HUM
"OREIGN DISSEd/N0 DISSEvf A .r'OAD/C d.' ...,. s.. A
:.e, pal shaft of the cardan ring. 'Roll and Ditch signals are provided
the plane selsyns. The Ditch selsyn transmitter (S,,) is located
t o external shaft of the carc?an ring, while, the roil selsyr. trans-
,ter (S1,) is located on the gimbal shaft.
.,hen the position of the gimbal is upset the zero positions of
_e roll and pitch selsyn rotors change, relative to the stators,
t` 160?. In addition, the direction in which the pith. selsyn rotor
_rns relative to the stator for changes in pitch chan es in the opposite
~ection. In order to Drovide a correct position for the horizon
r=:iicator when the position of the gimbal is upset, the sib... '..s from
gyro transmitter for the roll and pitch selsyns arc svttc __c'.
ye switched signal is supplied by the cc :utator 26 lc :~ated on the
369
?igure 66. Diagram: showing kinematic principle a1 t^e AGD-1.
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
OT T''T' T DJ ) r.fDO .DIG ':
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
J S-E-C-R-E-T 50X1-HUM
NO FOREIGN DISSEM/NO DISSEM ABROAD/CC1xTROL1D 00P
'age 370
;are bo. Diagram showing kinematic principle of the :_GD-1
- :etch motor-generator, D0-0.
Friction clutch
ard
? Aircraft silhouette
5 1cI1 motor-generatorDG-1
_j-3 ca ,irg device motor
VK-1 terminal switch
etent or cam
caging device cc j.in, rod
- - -
Jetent or cam.
- dzc i ~cn transmitter
G-- .,rotor-generator for fine adjustment * of the follow-up gimbal
unit
o rnut at or
_.sverse correction motor (for pitch)
s haft of TsGV gyroscope
a dan ring
;itudinal correction motor (for roll)
cw-up ;gimbal
- Vii terminal switch
- Plun er
- ~ )inale
- Return spring
oiler
S-E-C-R-E-T
CVO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISE M
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 i
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r
'
.itli
l
EEC
INT0 FOREIGN DISSM"JO DTSS.E1.1
Page 371
Switching of signals for the selsyns is accomplished throc.-h the
use of special relays in the gyro transmitter and in the horizon
a
indicator.
Cutting out the gyroscope correction has been anticipated in order to
increase the accuracy with which roll and pitch are indicated in the course of
the evolutions carried out by the aircraft;. .-Then the aircraft is turning the
transverse correction is cut out by series conrcai c switch VK-53RD.,
Cutting out the longitudinal correcti : ' :;h a for 2
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEt
r_ --
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
NO 1` 11"'1 T P1TT
2. The iQ'1-3 correction mechanism is installed in the frame zone, to
/
starboard and upirard with respect to the line of flight.
3. The ID induction transmitter is installed in the tail fin in the rib 10
Page 390
KSI,Electrical Supply
Supply for the KSI system comes from the aircraft network in the form of
+27 volts DC, and from the PT-500Ts converter in the form of 36 volts, 400 cycles,
The electrical schematic for the supply circuits is shown in figure 70.
When the AZS-5, symbol 1014, located on the starboard panel, is cut in 27 volts
is supplied from the aircraft network to:.
relay symbol 16M;
5KS matching pushbutton, symbol 15N;
U-18 amplifier, symbol 18N;
UG:R-4U indicator, symbol 9N.
After the Fr-500Ts, symbol 2N, is started alternating current at 36 volts and
400 cycles, three phase, is taken from the converter and fed to the following
blocks (phases 1 and 2 through fuses SP-5, symbols 22N and 27N, and the closed
contacts of the relay, symbol 16N; phase 3 directly):
f
GA-2 gyro aggregate;
GG1t-4U indicator;
:`'NS-l matching mechanism;
PU-3 control panel;
1i-3 correction mechanism;
344
T-'C E
F'Q lGii DISS '.il 0 i~IS: =i 9I3> 0~: /COi~`i':dOL ED 1]TS },f
1M
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 IX1 -HUM
.tJl DIc,~. -n~. }'rrc, x n- r,
?' f `T
u,.:_,E:.urI/J. .,, .., ....._.. ::ia ~~~. ~.~J... l,li,
ID induction transmitter;
U-12 amplifier.
The +27 volts DC from the aircraft network is used to supply the switch-
ing apparatus in the semiconductor amplifier,.
The 36 volts, 400 cycles, 3_p!- -a AC su plies the GA-2 gyroscope motor,
the selsyns in the trackir._-,- c motors in the correction sys-
tams, and the induction. u._~'_ m tt?r (see
No. No. of posit. Designation
ion in c:iv
trical~c.c;atic____
Upper equipment hatch,
fran;es 4 and 5
2
side, frames 12-13
3 7N Matching mechanism Up?, .r equipment hatch,
4 5N
6 ION Circuit breaker AZS-5
7 11N Correction mech- KM-3
anism
the block :.char;. ' _c in figure 69).
Type Cw- -
tity
Fuse "PT-500Ts Ir-50 1 Power unit, starboard
converter fo_-
KSI? AGD, VRD
Gyroscope aggre- GA-2
gate
Indicator UGR_4U
8 13N Amplifier U-12
Induction trans- ID
mitten
:;tL.board, frames
J-w
1 U?.-,,ter ee_uipt-,ent hatch,
frames 3-4
1 Instrument panel,
zone "B"
Starboard console,
zone "K"
Cockpit, to starboard,
frames 10-11
1 Cockpit, frames 6-1
1 Tail fin
LLLD DT"7-9f
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
3
15N
Matching pushbutton
1
Instrument panel, zone
$ -, N
IAN
Relay
1
Relay box, upper equip-
ment hatch, frame 4,
to starboard
".8N
Amplifier
U..18
I
I
Cockpit, to port,
rams 6.7
J _ cr equipment hatch,
w~d od side,
_.,.~ 4-5
23N
Control panel
PUa3
1
li ~_. L ,~ ant hatch,
>;~t,___ fr3~:s 3-4
BR-4
1
Upper equ:pmcnt hatch
393
Figure 70? Electrical schematic
chnical Data for the KSI S,istern
n ss for operation after supply is cut in
_~- n determining magnetic course whan flight is
Z ad horizontal, not more than
final error after 30 minutes of operation
directional gyro mode
ror from remote transmission of course angle from
r.c io compass:
Lro marling on scale, not more than
par Markings, not more than
angles for rcJ. d ditch
- 2050
360`
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
I
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 tifX1-HUM
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. -..:rc is, for pitch angles of 50=50 and 270 0
, a zone of irdet:r-
dos tuns along the course which is fixed by the characteristics of t
h
e
.tin : vG?:ica1 gyro TsGV (AGD-1 transmitter).
I o : rao ayatem operates without fi.*3". ovstr thus C'.e aggregateb haV,
le for 1cn8 periods of time i c: o 0
in outside t,.~;~~p;,.~ta:ra~ ,ing frc~ Std to -6,0C.
itude
pply:
direct current, volts
ulterrating current, volts
vyc:.~:s veco-.d
'ower racuirementc '."..::a running steady
direct cur:- .r., watts
current, volt-4::;perec
OTE: Starting current:
d__ect current, amperes
_ . 1 t r:ar current, amperes
The start system aggregates withstand a landing
,C'VO meters
VD-7g, Dki ;?.-'.'ee;die Altimeter
~?? VD-28 altimeter (figuat+e 71) serves to fix relative altitudes for air-
flight from 0 to 28 kilometers above the flight ar=, the landing s!te, or
- =t ve= ocher points, the barometric pressures for which a-a icno,rn.
in tr?.:ment has two, dials. The outer scale, or
has a range of
cations from 0 to 1,000 :ret~.. _ -..th div--.. every 10 meters, and a
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 oUX1-HUM
170 FOPEIG.PT DI SS-J /loo ~~~ S -~ :..Si:..,ti u ?ri.t .'_ll.i 1J ; :i
needle for marking the indications. The inner dial has a range of indications
from 0 to 28 kilometers in divisions of one kilometer each. A.small needle marks
the indications on this scale.
The small needle moves one division for every rotation of, the large needle;
that is, the small needle moves one kilometer. The instrument has a dial setting
knob and rack arrangement to make eo rections in accordance with outside pressure
_: ^^ 396
in flight, or when setting the large needle to "0" b Zza-,. (the small
needle should be on "+3").
Figure 71. AA-c- 4er
Turri kedicator
The EUUP-53 turn ..__.-v:etor, with slip it.. icator, serves to indicate the
deviation of the ._.._~_..,.t from st:._-a-,:ht..linc flight (to po_., c .,_-.rboard), as
well as correct e: ecution of turns of the aircraft
relative to the vertical axis with a transverse roll of up to 450 at a flight
speed of 500 kilometers per hour. Figure 72.
The joint operation of the ball and needle makes it possible for the pilot
to properly bank the aircraft without skidding when weather conditions-are good,
as well as when they are not.
P ge 397
The sensitive element in the turn indicator is a gyroscope with two degrees
of freedom.
Supply for the gyro motor comes from the aircraft'~6 direct current network.
The electrical schematic is sown in figure 73.
When the AZS-5 (sym. ,a the port cor uole switc:::;yard is cut in +27 volts
,leg
,;0 T"PCAD /co TRoLLLV L D IS (27,!
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SECAT
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DI5
Figure 71. VD-28 Altimeter
Bus #1
Fig. 73. EDP-53 Electrical Supply Schematib
350
SECPET
NO FOREIGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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5UX1-HUM
7j ~.. ;r
nTSS1}F/j`:C i r ZT"?i ? ; ' ) ,-11 !c
the gyro motor starts up.
Figure 72. EU?-53 Turn Indicator
from bus number 1 is supplied to terminal ?'A"of the EUP-53 (sym. 6N), whereupon
.J JV
Figure 73. .:ic__ . _ -y W.:vr...__jc
No. No. of pos-
ition in
electrical
6N Electrical turn
indicator
2 34( Circuit breaker AZS-5 1 E1e .cal switch-
boa port con-
F. Aviaticn Clacks A.ChKh
The aircraft Qs aviation chronometric clocks, AChKh, equipped with electrical
heaters (figure 74) provide accurate time readings. When. the cock springs are
P.: 399
fully wound the clocks will run continuously for 6 days. However, for norval
operation it is recom.mcended that they be wound once every 5 days. The supply to
the heater element is shown in figure 75. 4hen the AZS..20 (sym.
Type Quantity
on the instrument panel is cut in +27 volts from bus number I is supplied to the
heater element (sym. 8T) for the clocks.
Figure 74. A ChKh Clocks
Figure 75. AChKh heater electrical schematic
No. No. of position Designation
in electrical
schematic
7T
87
rument panel
7T) "PVD, clocks,"
Location
Circuit broker AZS-5 Instrument panel
:.rater element AChL:h
)j.
Di 0 `.1 l:i;1?Oi:D/CCid' tU%uLD- DIS~` !S
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 ~v, HUM
1 J -
V2.h-3'30 variometer serves to -.ieasure the vertl,al climb or dive rate.
. i::g the vertical climb or dive r position fo:
: 3. ge ar:1)
indicator which haz z2 -AadL~,_W-d in -p
ilctet_.s a_ _ and in
o altitude t t o : _`atad by the Dtuat] 1c ':...:t of the
/
..._..poi (cf? ti hurt i,~3:. ..ti c _......,.._~v.: .. ordinary V
i71t,,..--..
in speed and u, _ _ ude units.
j? ARU-3V Arm 'tsv' tic,n nd' cator. For
Automatic Device
~wt- X c3; rating conditions the indications shown cz the ar:-,l
.he flight instrum>ants for speed and altitude.can be sc P ew 4a
b cause of the deviations in atmospheric conditions from st .d-
well as because of fluctuations in the supply voltage from the
b3 borne in mind that the position indicator - the indicator for
of 27:.0,5 volts to 27 I -n-1 volts.
d... ,. :.v _ the Lutomatic device - ,~c::ves to, in c?enera , :_ccuaint t :e pilot
is fu:. n n sat'i :fectori? y?
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
Lr FO_J:Icj. DISili'~?_
?!U
~FX
iFG L~ s -- ---' '. i.`-L; CON I .'OLLLrt IUIE " \(
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
accelerometer (fig, 3} se:"~' to deter.ni _a the arou:it of ova--r-
on the aircraft Perpendicular to the plane othe winos the air-
carrying out the flying maneuvers rcuuir d in tl.: air as well as dur zg
...r. .=y?4s of movements with velocities involve.
,verto d, occurs when tension in the structure haJe incr?a sk::d somewhat
a_ed with those which would occur in horiZ,o.~tai f when :here is only
cc of gravity acting. The meter s c.., _u:;. .~? r-age from -4d
yne) to +10d, with each ``,o 0.5 a. ._-- ~:~~.?:....
.:wo :zc9d
~les,
c:.a main needle, used to aver lcad, and the other to ,mot maximum
'.a J
k-Z3b v i the face of the mete- s. h, i:?n :sod
_1, rczr~
i-:dicato ---.idle to the original '30--ftion.
+'_ use 80. C1: -b Accelerometer
- aneroid and diaphragm instrument system in the a~rcraft suaolies the
_ struments with absolute and static pressures.
=yot is supplied from the D TA5_8P4 air pressure receiver installed on
~: >7ar which extends out into an undisturbed flow of air. The spar
~v on a nylon, underneath, in the nose section of C- fuselage. Vne:a th .6 ;a
o- ---__ ~._~ vr~. a.~r+ucu c.i 3wr:3SU5 6.J ~Jiev :u ore~1:^Ca e rD' f
:."uc the sped indaca.:Cr, t :.. resolver block
device jr t the Mach mot'er Ott j Jvc J-J, w --lie K2_7_/
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
nrz~p!wjYr DT.~sr M ARFOATI,/COr.TRUlLEll DIC771?1
Fig. 80. AM-10 Accelerometer
NO FOPETGN DISSEM/NO DISSEM ABROAD/CONTROLLED DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 )X1-HUM
J
D.i-St)1 DLL,---
and the transmitter in the core control system receive both types of air press-
ure, while others of the instruments, such as the variometer, altimeter, altitude
6
and pressure drop indicator, the automatic device for introducing altitude in
the ASP?5N sight, the ARD-57 pressure regulator, the VRD-2 and the VS-14500 are
supplied with static pressure only.
The principle schematic, as well as the installatic-a for the system
is shown in figure 81.
in the event the main air pressure rec;a_vcr (1) breaks down t . ,::c: is an
emergency receiver, TP-156M, instal 4:: on starboard side of the :'u ;elage,
upper, near frame number 3, :-eh ies a E.; i : rur,: nts with dy.d~:n c Y,_essure.
=.11
Figure 81. Aneroid-Diaphragm lr ;; run;~:3t Supply System
Pn-~_ Z1,12
I'iurc us. AneroidrE)iarshr,m Instrument Supply Syl;t:~_m
1. DUAS-8%1 reciver
2. Spar
3. TP-156., receiver
4. VRD-2 permissible range computer (SRD complex)
5. DVS-5 air speed transmitter (SRD complex)
6. Block Number 6 (ASP complex)
7. Condensate trap in the TP-156M main line
8. MR?1.5 and MR-199 transmitters
Mach number indicator
10. Variometer
11. Speed indicator
12. Valve 623700M for switching dynamic pressure from the mLis _cceiver, DUAS?8M,
')u2
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
50X1-HUM
-_Cy LP-156
c e, flow a, _ t'tl is charged the
aircraft connection is
The detachable ce .noct c~^s make posr.ible to bring the pipin- 1-..:o the
cockpit, as well to tale the system apart when the wing cantilevera mist be
unj ointe_da.
i cssure devlce. The device is designed to fill the air
chambers of .,'hc anti-overload apparatus in the VKK compensating flight Suit,
depe di~.g u.-.on the overloads. The AD_5A device is not connected with the o:,:y?en
p8.
V'.C altitude c? ,apcnsatin,- f? ~. ht suit is designed to compensate for the
i.::?:c.sa pressure in the pilot?s lungs, and to reduce the harmful effects of over-
The VKK altitude compensating flight suit consists of the following main
parts:
the coverall;
the tensioning dev,ee;
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
,._..ut ..nom:: .. ?. - -- -
~~~ : y or i~~ lt::s
r7 'iYbi V.: c
C7 7
uip-_7::U W'..;h .3
v.. vi U6?aw a*..
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
rO TTG1`f 1`T5 R/ jl cc F n ?1~f
I, f I...
50X1-HUM
The position of the rheostat knob will depend upon the temperature of t1e
surrounding medium.
A button, located on the port console, and marked "fast heat for helmet" can
be pushed if rapid heating of the sight glass is necessary to remove moisture or
rost..
Since, in this case, heating takes place with maximum power,
Px o,e 451
the button should be held down for a short period of time only (not for longer
than 2 or 3 minutes). When the buttcA is re-Teased the electric heater will
function in accordance with the position of L_e RK0-45 rheostat knob. If the
_c!:
rheostat fails in flight the window c be :ic_;c.~ ,iod cal y pressing the
button indicated above. .
The KP-2711 arach etc t Y ~W ~_ ... at is an equipment for ~;.uu l use and
has a continuous oxygen flow.
This equipment supplies the pilot vs.- ...tee . f? r
oxygen during eject': ,a or in the event the KP-34 .installed equ ipm; ,: b ea . ; down
during flights at high altitudes (to descend to safe altitude).
Under nomr,,l flight conditions the oxygen, which is contained in a bark :,f
tanks, is not expended and the pilot breathes oxygen, or a gas m1xt,ur.~e, com.:.g
from the K.P-34 equipment in the aircraft.
NOTE. More detailed information concerning the oxygen equipment units
is provided in the descriptions and instructions compiled by the manufacturers
of the KKO-3 oxygen equipment complex.
Paige 452
0'iA. =TEP V
photo^},eohi?' -"au ?er:,?:"t
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 1X1-HUM
~..c n croup of MiG-21F-13 a.i'_c:'aft have been vkcl;rcted for the ina.ziill-
the ArA-39 aerial cammra, which is a completely automatic camera with
control . from the cemrnand device and is design.cd E. r ma ng aerial phcto-
:: reconnaissance in the daytime.
_he camera can be used at altituces --'--cam 500 to 51i.;00 meters (with ~30
use up to 10,000 maters) at f l s ::`~ ss
vim. a pig'
t 30 km/hour to obtain
i 50 0; made by co
of from I :o i:l0000 made by opt:':cal (or -,: o_ ect on)
FA-3 camera L; installed in the of the .:.t."....' .::33r wIn- c.._nti1ever
-I:.d the r e 2jr the landing gear bcttie ribs No. and No.
':ns enclosed in a special fairing with shutti.rs.
device and the cutout switch for controlling the cease a..*e i a-
i :e cockpit on the middle panel, while the, : ircuit brc..i
- ;ard electrical switchboard of the starboard co nst'le.
length
o2, d across picture diagonal
,y e :utter
ate :peed (effective)
-~ :i. filters
54`'
Curt- ::.h
1/700; 1/1400/; 1/1800 see.
YeS-id 0S-14
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 50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 20.12/04/19: CIA-RDP78-03066R000200020001-6
A.17,0 t, n
Picture size 7 x 8 cm
Number of pictures 200
Size of load of aerial film 8 x 1900 cm
Duration of cycle
not over 0.7 sec. for o
temperature from +15 C
to + 25?C;
9.8 sec - for -60?C.
Current requirements for:
temperature +20?C without heating u t:: ac pyres
temperature -60?C L ;. eres
Voltage 27-107.
L.eii ?.c`:: CC~,r),~t,Yt1Qn
Included in the as zaI camera complex are the:
A. acr :al camera;
B. command device
C. cut out switch
D. electrical runs and plugs.
1 _:2e 1. t
4. Puri:>ose of .the aggregates In the AFA-39 aerial camera instal tire:
and location in the aircraft
The schematic showing the location of the camera equipment making up the
AFA-39 inst lation is given in figure 102.
A. Aerial Camera
The aerial camera is designed to photograph objects which will be sLbjected
to interpretation and study.
The camera is installed on the cover of the hatch in the root of the star-)card
wing cantilever, behind the landing gar reQe_. :, ribs I and 2, and is
secured by the ears of its the d sci~ bracket by four bolts. An
D]'FSE',f
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '1X1-HUM
the camera c -se
has bacn cut is the hat s. cover. The cover is
to the wing by four nuts.
. v ens of the camera extends outside the wing end cure and is protected
action of the wind stream by,fairin , installed ;:z the lower wing cov-
aer.missible displacement of the optical a-xis'c:f the camera with re-
.o the hatch axis in the fairin is not more thaw millimeters, while the
ssible deflection relative to the aircraft irk all directions, not
t1, 3"
l f ir '
..ens
. i
-":_.~ t..w.._._.-~... ,.. ..- 2.. Set..= the. ..v"O[.-~ and aEter
3
to the 8+.-3_^..r by :. e. 3> a:,,! .....i:ho ti"Lt:;? The M c d ,_ s secured to
~hutch cover ~:._o can be dismounted .1lonc ;with the hats -.l cover - ` h.4 camera.
102. Schematic Of AFA.39 location
aircraft
1,56
plug (ShR-2)
t rrninai switch for interlock
_a 1 camera AFA-39
._ :: 2P 8. M3 plug
J
-l54 plug (Shit-7)
plug (Shit-7)
_'. `t -ht plug (ShRG-7)
i4 Sh?-25)
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6
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 Declassified in Part - Sanitized Copy Approved for Release 2012/04/19: CIA-RDP78-03066R000200020001-6 '1X1 -HUM
.wit} circuit breaker
r.:ds hips panel (instrument panel)
device
: 32 AU c3 plug
,i..-,'out switch for onaratincc A:3
After curtain
_` 1l s:'od (2 pieces)
7ward curtain
s `rein
.twtutn1
lever (2 pieces)
vn ;u_ar
lever
rvo panel of the landing ;ear s,!_-rut
is, in the middle section of the fairing, a ca-;:era hatch circ..G:. :n
-`; is closed by two curtains which move apart and which ar: oy.a
.:s c': ~ermits the light ima a of the object Co eni tr. the cam;~r. l n The
ce troj mechanism mounted in the forward and middle sections of the f :a
interlocked with retraction of the land.r_ , Year struts..
landing gear strut flap, upon retracting, presz _. on the extended
.
:i
in the after the ~- n is the V_9.A terminal snitch
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 50X1-HUM
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far interlocking operation of the camrma::ra installatt.on with thw curtains on the
camera hatch. It eliminates the possiblity of exposing film when the camera
h curtains are closed (or not fully open).
Four bolts fasten the terminal
switch to the fairing by the ears on the switch housing.
:`OTEP When night flights are made the camera apparatus can be removed from
the hatch and the lens fairing can also ba removed. In their place there can
be installed an extension-type land1n liUit (_n the same hatch).
4c
The command device for the is c,:siyned to control v'r. camera remote
ly and to perm2t the of intervals bet.,7eer 'Aures equal
to 2, 4, 8, and 16 as well as to cut in the camera so it v).l operate
continuously at intervals equal to the operating cycle for the ca ; _a (0.7 sec-
ond). The device permits monitoring - film rewinding (a green pa"sot light
burns) and (',y a counter) the number of frames remaining in the camera.
The con?:~,"-nd device is installed on the middle section of the instrume. t
panel and the casing is secured to two duralumin brackets by screws. Four
screws and anchor nuts secure the brackets to the panel of the middle suction.
C. Switch
Switch 871