YE-6T AIRPLANE TECHNICAL DESCRIPTION BOOK III DESIGN

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78-03066R000200010001-7
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 287
• Document Creation Date: December 19, 2016
• Document Release Date: September 12, 2003
• Sequence Number: 1
• Content Type: REPORT

Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
4
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
g-r_r_R-V-T
10E-6T AIRPLANE '
Technical Deeoript:ion
Book II/
beeign
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
I 25X1
25X1
-2-
For Convenience, the material is collected into two separate volumes:
First volumes Chapter /. General information
)1A4Ni44
Chapter /I ? Desip of the
Chapter III - Power plant
Second volumes Chapter IV - Take-off and landing devices
Chapter V Air and hydraulic eysteme
Chapter VI - Control of the aircraft
Chapter VII ? Fire-fighting equipment
Chapter VIII Ventilation, pressurization, and
air -tenverature control
s-v-r- R- R-T
25X1
Approved For elease 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
-3 -
CHAPTERI
GENERAL INFORYATION
The* -6T aircraft is a single -seat'light fighter with high performance
characteristics.
J
The craft is powered by one 13F turbojet engine with an afterburner.
Structurallyi the plane is an all-metal midwing monoplane with a delta'
wing controlled by ? stabilizer and normal wing-tip fine. '
The fuselage is divided into the nose and tail sections.
RK1
SE-C-R-E-T
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CLAREIPR7S-9r3066R000200010001-7
Struoturallyb the plane is an all-metal midwing monoplane with, delta
wing controlled by a stabilizer and normal wing-tip'fins.
The fuselage is divided into the nose andtail sections.
On the front part of the fuselage b on the air-intake duct' there is a movable
cone which decreases the plane's resistance and creates optimum working conditions
for the engine during flight.
To prevent disturbances of the air-intake duct, on the fuselage there are
automatically controlled vanes on opposite sides; ahead of the engine inlet on
the sides of the fuselage there are auxiliary air-intake vanes (L.44r_rOvano.).
On the fuselage are three bra ie flares two front and one rear flap.
Approved For Release 2003/12/03 : CIA-RDP78-03066R0002000100017
25X1
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
/ f
Tte cockpit enclosure canopy Is ,streamlined, affording the pilot a good
view ahead and to the sides. The canopy is designed so that the term forward part
can be opened on the groupd, or ejected if necessary during tke flight by means,
of the emergency release handle.
The canopy has a liquid do-jeer.
The plane has a type 'SK". catapult seat which allows the pilot to eject
himself from the plane in an emergency, at high or low flight speeds. The hinged
part of the canopy, during ejection, is used to protect the pilot from the oncoming
air stream; the canopy is not released but covers the seat, which during ejection
retains the canopy.
To keep the pilot from being hit, the plane has armor, consisting of an armor
screen forward under the canopy, ,
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
3g*1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
H
armor plate n frame 6 and 11, and an armor-plated head rest on the /mat.
1 i
The wings of the plane are delta wings with a sweepback Angle of 5713; the
I
trailing edge of the wing forge a 90? -angle with the /Luselage amis.
The wing is
2 '
de of high-speed profiles. Thr is 23 m p the
I
Ja span
is.7.16 in, the chord with respect to the axis of the plane is 5970 mm. The
setting angle is a 0? and the lateral dihedral is ,-2?.
On the wing are ailerons with, axial aerodynamic compensation and "floating- '
type" wing flaps. The "floating-type" design assures a decrease in the flapping
angle of the wing flaps under the influence of impact pressure with increasing epsed.
controlled
The hOrizontal tail section consists of a stabiliser with a sweepback
? i .
angle of 55?.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
The stabilizer consists of two symmetrical halves--the right and left.
The vertical tail section, cons'sting of a vertical fin and a rudder, has
i?
j
a sweepback .angle of 600. The rudder has axial aerodynamic compensation.
1
iThe 37? turbojet engine with controlled boost makes possible smooth regulation
;
of the thruat in boost regimes--from the position "minimum boost" to the position
; ?
t"full boost."
The fuel system consists of the basic system,
including seven tax4rds tanks
inside the fUselage,xxst Dour wing-tank units (?) divided into three groups, and
one suspended tank. There is p syarting system for starting the engine.
on the ground and aloft.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
25X1
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001r7
S-E-C-R-E-T
-8-
The plane has ? three-wheel landing pear which is retracted during flight.
The wheel base is 4810 mm, the wheel track is 2692 mm. The front landing gear is
retracted forward and housed in the lower part of the front of the fuselage. The
main landing gear is housed in the wings. When the main landing gear is retracted,
, t
the mekm wheels turn relative to the strut and are housed in the fuselage, while
the struts are housed in the wing. The main landing gear has 1T-82 wheels with
tires
660 251the front landing gear has a KT-38 wheel with a 500F180A (7) ,tire.
To decrease the landing distance, the plan, has ? drogue chute in the tail
section of the fuselage. The parachute is designed to be released the moment the main
wheels touch ground.
The pnaumatie sputa% consists of two indpandent systems# the main system
and an eelergency one.
S?E-C-R-E-T
wa, e.111.1?1111.11
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
-9-
serves the following purpose
The main system. to brake the wheels, lift and pressurize
the canopy, release the canopy in an emergency, recharging, closing the fuel shut-
off valve, operate the de-icer, releaee and eject the drogue chute, and feed the
anti-0 suit. The emergency syetem releases the landing gear and brakee the wheels
in an emergency.
ihe hydraulic system consists of two different systems. Pressure is
Created in each of them by a variable-output pump which creates a maxinum pressure
of 210 kg/cm2.
The first hydraulic systems serves the cOntrol ayetem (the two-Chamber
DU -51MS stabilizer booster and the BU45A aileron booeter).
The ascend hydraulic ggetem serves the
Approved For
S- E-C- R- E-T
elease 2003/12/03: CIA-R0P78-03066R0002 0010001-7
Approved For Release 2003/12/03 :Ik-IDRP7E8i03066R000200010001-7
Attachment to
landinp,gear, the wing flaps, the ?rake flaps, the adjustable engine nozzle, the
cone at the air-intake duct inlet, e fire-prevention vanes, and one chamber of the
DU-51MS booster (the other chamber i served by the first hydraulic system)) it also
takes over for the first eyatim for the aileron boosters in case of
a breakdown in the first system.
In tho event of a drop in pressurn or a breakdown in one of the two systems,
the BU-51M3 booster continues to operate on one chamber, fed by the system that
still operates
The hydraulic system that serves to control the plane includes an emergency
pumping station which, if the system breaks down or the engine stops, maintains the
required pressure in the hydraulic system to assure ? safe landing. The pumping
station te switched in automatically.
S-E-C-R-E-T
H3E1
II I 25X1
Approved; For Release 2003/12/03 : CIA-RDP78-03066R0002000100014
1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
Attachment to I
The stabilizer is controlled by a control handle using a BU-121 booster
and an ARU-3V automatic device.
The ailerons are controlled by a control handle with the aid of BU4i5A
boosters i /n the event the BU-kA boosters are cut out and both hydraulic syotems
fail, the boosters perform the functions of rigid units of the aileron control
system.
The rudder is controlled by pedals, a system Of rigid connecting rode, and
a.nonlinear mechanism.
The pilot's cockpit is pressurized, affords a good view, and a room enough
for the pilot to work conveniently. The cockpit is ventilated and conditi ns by
hot and cold air taken from the angina compressor. The cockpit has automatic
temperature and oressure control.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25x1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
Attachment to
To assure normal conditions for the Pilot at great altitudes, the plane
has an oxygen feed and compensation system for the pilot.
Electrical and radio equipment. The d-o power source is a 6.5R -ST-12000 VT
generator-starter. As a reserve power supply source theplane has two lfSTsS -45
silver-zinc storage batteries.
The plane has prOvisions fdr starting the engine by means of the on-board .
?
storage batteries. A converter Beeves as the d-o poher source.
n n n n n tt
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
\
3R*1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
.13-
Attachment t
The pla has the following radio equipment'
1. A co posits ultrashortwave receiver-transmitter;
2% An a emetic radiocompais;
3. A low-altitude radioaltimeter;
4. A marker radio receiver;
5. The airplane equivalent of a radar identification
6. An aircraft radio rangefinder.
The aircraft has a fighter course system KSI.
eye tem
P?=111????.=
The technttcal description of the plane is given in four books' I, II,
and IV. In this book we describe the aircraft design.
The general views of the aircraft are given in Figs. 1,
S-E-C-R-E-T
2, and 3 in Book I.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Aplit)roved For Release 2003/12/03 : CJA,-,RADF,'78-03066R000200010001-7
Exploded view of the plan
Attachment to
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-4
S-E-C-R-E-T
Attachment
? ? *.
, si 10. . ? .reir
?
(
4
-erft*
Njdt - '-- . A
1111.011081aV4 L '11 51V32ii13,5.103
1
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
25X1
Approved For Release 2003/12/03 : 9AiRpPR721,3066R000200010001-7
Fig. 4. Exploded view ofthe plane.
1. Drop tank,.
2. Trim tab.
3. Below-fuselage wedge.
I. Valve wedge.
5. Right wing cantilever.
6, Aileron
7. Wing flap.
8. Right half of the stabiliser.
9. Vertical fin. .
10. Tip of vertical fin.
11. Rudder.
12. Cowling.
13i Pylon.
14. Flare on main wheel strut:
15. M in landing-gear strut.
16. Cy inder for raising and lowering main landing-gesr strut.
17. Ca4opy.
18. Note section ofthe fuselage.
21. Air-pressure receiver (Pitot tube).
22. Cylinder for raising and lowering
nose landind-gear strut.
23. Nose landing-gear strut.
24. Flaps on nose landing-gear strut.
25. Air brakes.
26. Flap for main wheel housing in
fuselage. ,
27. Left wing cantilever.
19. Tail section of the fuselage.
20. Lovet half of the stabiliser. '
?
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R00020010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
16
CHAPTER I!
DESIGN OF THE AIRFRAME
1. The Duselage
Oeneral Information
of
TIhe fuselage is a cigar-shaped body elliptical cross section with
cut..avay noes and tail cones.
is a semimonocoque fuselage made mainly of 1)06 and 895 material using
main
SZOKhOSA and S20KhOSHA steel for the
joints.
For mounting, removing, and examining the engine for regulation operations,
the fuselage can be split into two parte- -thenose and tail sections.
assembly
The transverse
of the, nose of the fuselage consistsof,
28 frames , of which Hos. 2, 6, 11, 13, 16, 16A, 20, 22, 25, and 28 are
the main ones.
The longitudinal assembly consists of longerons and trusses with a few
btringers, which
,covering.
is compensated for by using a relatively thick
Such a design makes possible maximum use of the inside of the framework.
The nose section of the plane is aesembled in mat panels.
The traneverse assembly of the tail section of the fuselage consists of 13
Stringers make up the longitudinal
frames, of which 314. 35A, and 36 are the main Ones.
assemblyi
S-E-C-R-E-T
Approved-ForRelease 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
I. Make-up of the Nosexof the Fuselage
(Fig. 5)
The nose section of the fuselage is made up as follower along the forward
section of the fuselage is the air-intake duct with anmextatim inlet section which
canbe regulated using an adjustable three-poeition cone (1).
The upper section between frames 2 and 6 contains ,tbs radio and electrical
Itequipment (2); the lower. part of this section is for access to the nose lan ing-
gear strut.
Pressurised cabin (4) is located between ? frames 6 and 11; the strage
battery section is beneath the cabin.
Behind the cabin, between frames, 11 and 28, are the holders for seven light
kerosene tanker
from frame 11 to frame 13 - tank No. 1 (7);
from frame 13 to frame 16 - tank No. 2 (8), and a second auxiliary tank tem
(14) between frames 11, and 16;
fl'om frame 16 to frame 20 - tank No. 3 (9) consisting of an upper and lower
part;
from frame 20 to frame 22 - tank No. h (11)1
from frame 22 to frame 25 - tank No. 5 (12);
from frame 25 to frame 28 - tank No. 6 (13).
Tanks Noe. 5 and 6 consist of two parts connected together.
The air duct for the engine passes throughthe nose section of the flimflam
Ahead Of the cabin it separates into two parts and circumvents the cabin. Behind the
,S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
-18-
Fig. 5. Airframe and make-tp of the nose section of the fuselage.
a) Pitot tubely b) cockpit canopy, a) all duct, d) engine housing;
e) engine-mount beam, f) air ductA
g) [illegible], h) front i) cockpit floor,
j) left brake flap, k) compartment for second auxiliary tank, 1) cross section A-A,
m) rear brake flap, n) cross seOtion 8-8, o) servine hatch, p) air ducts, q) nose.
' itheel.housing, r) Operi:410.14s) tank No. 2, t) air duct.
S-R-V-R-R-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Appr, ved For elease 2003/12/03 : CIA-RDP78-03066R000200010001-7
S?E?C?R?E?T
*"??741?11Pre.milmee???????
,
, ?144,4434?444'.????-?4,444.
'L.
r
'7 I
40
f.?q+,?
? PP4'"i' 1
11'
0
,
. I '''(' .-.. ''. .. . .,,i ?
v
i i c\t,
. ...7. . ? V Ill J.
?,*-',.4:".;ii .
}
..rc...1.--1v
' c?..7.4i) r ?
..
.....4,...:
t...... 4 4 4
i ' II- ; I , .. i ? I
..;... ' '?.1 1 1 .1t- ?
`t:k?*;
,
44'4 I' ' VI
" -414'4
' , ih - ? 't
, fro0
....qc. 1
? f::?.:..1.1,..a"
A"....,,
?
.1....1'
wren Iea.:---,?..74 as TelCOMO -
is .4. offuwoos AliV40010 111A011 11 II DLL si.........3 0.1 osseseut au
II1Y3S 16111 1SO4
i. I It? Ulf ft!, If ?ft A I, ire t tiii%ot .116 ett" A A et fa ? A e ? ?Tes *Aso :Ls eeffmeelee? etesset ? a alelai i ?
, . 0
- ? ....-.?
A
Vilk ?
Ift;?..'r"-Vallair?
II' ,
IN
I
? ?
.1f
4 n. ? ill.
" ..*1*,,,^1 ?I ? '" '
? ?-? I............??
At.
5 7
' 24 ?
r
S? E?C? R? E?T
?? ? 11,101,??
Approved. For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : 914-Inn8103066R0002000100011-7
.cabin both sections converge into a common duct to feed air to the engine compressor.
011 the aide Panels of the fuselage, on both sides between frames
valves
2 and 3 ars located adjustable anti-surge (16), while between frames 9 and 10
there are two air-duct pressure-relief valves (6).
In the duct ahead of the engine intake, between frames 21 and 22, is located
? the air-air radiatorj for the cabin system.
Between frames 16 and 20, ir the sides of the fuselage, there are housings
for the main landing-gear wheels (10).
The region between frames 22 and 28, along the fuselage axis, is occupied by ?
the power plant.
In the lower part of the fuselage, between frames 11 and lh, are two brake
haps (15), while between frames 22 and 25 there is the rear brake flap (17).
The brake flaps are looked with special locks if there is no preaaurein the
!hydraulic mixture.
nose section of the
There are a number of hatches in the/fuselage for eervicing of the equipment.
r__
All the hatches are zotored? and require daily maintainence to assure that they are
fastened
The placement of the hatches is shown in rig. 6.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
'r .41ZZ
? .1! `L.?
,
?
?
...,4444.4 - ?
?.4. ? )
? !
Crsim;Tx*L
; ? ?
.
..
?????
II
t.
2 ?
????
y
? :?11,
rI
4.?,??
? ?
3t.
.6;
?
r,k-4
%V.^.
;
1 :444'A I
,
? ??
-..:1,..: - )4??
? - 4?:* .... , ?' op ,..- . e +.47:11`. ? ..' : 'I ' . at* t a.?, '''' 1 ' ? /'..,;,P .
,
:Lift. 6--41:-47??: ???;1**1?,:-.?N. 7?r1V-.7 1.14F.41. s7*.411447(?? ?::::;'. 1; .^.!..'5,s:
. ?,1. . . ..-N .,lit --*.o....,,,.: :1.... ,., .- it.,- xf
.,? ? .... -4 A... , , 4( ..., .-.:..., , ..1::,.., , . ? ....,47,-,;;;,... ;r p ,,, ......, ......
-4,?.11;.,". 1 ,1,,,, ..? Fi. ..-," ? ? ? -..,,..1...?' c? , ..t.
k.. .6...4.74.: ?I.7 "?4...t", 0 I ,,?....t ,,..? . -0-.., Iv, 'or.? ? ...4.,?-i,
'` '.. 414.14:i ? t".ILL:..,1 -\.1'.. ,,..--.4.1k-ti -'740/1r" ,
- ? ...
.y...,e...,, _ ...-47,:-,.., --7\ ,..,i'...:; .1.-:f? . . ?na...;:y ; -..-- ? lc .- -:. icAr::4, ,
.1-'-' " . '. ...r .......
4' :71 ? Li.. t. 'r ? ' ? ' ' 71141 r I i i -4
?
?
...
Y111?11111010:10,14 Oft?? TO ?I 110?111111
suaainelli
ma emarte's AMMO 114011 1111 SU 111/3S 11M11 11/40U
TtfirtftfirMITIMIttlInniTMAIMITTIttinttfiltfilittlITItettateletitsaititettilla
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
Pig. 6. Diagram of the location, of the ?Tx rational hatches on the aircraft.
A) left side of fuselage, b) view of wing friss above, a) right. eide of fuselage,
d) view of 'wing from helot/.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
Fig. 6. Diagram of the location of the operational hatches on the aircraft.
install ground lock on emergency
lo Radio equipment; 2. "Open banopy,
cockpit handle; 3, 79. Electrical equipment; 4. Technological hat:"; $.
units
Kerosene system
6. Oxygen-feed reducer; 7. Inspection hatch; 8. Aileron
actuating arm; 9. Wing-tank joint; 10. Tank fill; 11. Float valve and emergency
supply signal; 12, 93. Kerosene tank drain and aircraft control; 13. Gasoline
14. Tank fill; 1$. Kerosene tanks 4, $, and 6; 16, $2, 86, 87. Engine
units
17, 72. Engine mounts; 18. Engine and hydraulic syntem 111,4 ? al
19. Kerosene tank drain, and control' 20, Booster-system pump connection) 21.I
Hydraulic-system tank fill; 22. Kerosene-line joint; 23. ARU-EV; 24. TherroCouple;
2$. ARH-21.1' loading mechanism; 26. Hydraulic accumulator of the booster system;
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
25X1
141-,A
27. NP.27 pumping station. 411p1moulakommuslailiesm.iessmrser and KRP-56P; 28, 351 36,
37. Fastenings for radio wires and slet-ant!enna isseisiebtas driver; 29, 41,
. !
65. Stabilizer control; 30, 31, 32, 33. Actuating arm for control of R.P; 34.
ID-2 transducer (MI); 42, 64. nozzle cylinder; 43. nozzle hydraulic tube;
44, 92. Afterburner attachment; 45. kra Drogue chute lock; 46, 91. Bearing
lubrication; 47. Drain for teleqcoping connection; 48. Drogue chute; 49, 89.
Detachable hydraulic valves; 50. Fuselage butt joints; 51. Kerosene drain;
53, 71, Engine and hydraulic system units; 54. Kerosene drain; 55. Sediment
drain; flti.r njj1tW LLr ,m-ttuhaq 56. Kerosene and hydraulic'
. systems units; 57. Pump for third cerosene tank. Control; 58, 74. Kerouene tank
No. 3; 59. Kerosene system uNits; 60. Kerosene line and line ibr cockpit ventilation;
61, 82. Brake flap attachment;
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
.23-
62, 81. Landing-gear strut axle; 63. Rudder actuating arm; 66. Hydraulid accumulator
'Rot.
for the basil: system; 67. Thermocouple; 68. Hydraulic tank fill; 69. Aelo-tank
safety valve; 70. Connection for ground pump of the basic hydraulic syetem; 73.
Hydraulie units; 75. Dolts for attachment of kerosene tank No. 3j 76. kixakxxlps
tax Charging of oxygen feed; 77. Wing-tank connection; 78. Inspection hatch;
80. Tow-line attachment point, in emergency; 83. Voltage regulator. KAF-I2A
turbocoolers. Connector with catch; 85. Fire-prevention cylinder; 88. itnmmi1 Heat
warning device; 90. EK-48, MP-56P; 94, 97, 100, 103. Attachment for special
suspension; 95. PUS-36. Electrical detachment; 96. Landing-gear strut axle;
98. Nonlinear mechanism; 09. Air cylinders; 101. Kerosene fill; 102. Electrical
Atetts 6.47/VO
separation of carrier; 104. Aileron actuating arm; 105. AsomemAk to ....;
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03: CIA-RDP78-03066R00000010001-7
S-E-C-R-E-T
107. Power-aesiuted control; 108. Wing-flap cylinder; 109. Place for ground
jack; 110. Destruct button; 111. 41cohol fill; 112. Battery hatch; 113. Element
control for AM emf of the storage batteries; 114.eim AccoM memele to RVU(7) units;
115. Airfield powering; 116.Aliee14:111'"s to electrical units; 117. Hatch for .tiegerlai
to front landing-gear strut units; 118k 119. Hatches for examining the bolts of
the control actuating arms; 120. Hatches for ikaigiLis to the bolts that hold the
booste'r in place; 123. ilpeeseetitimilit Accese to aileron axle.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-0306 R0002000100017
S-E-C-R-E-T
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: cl1VIDE7H3066R000200010001-7
Fig. 7. Diagram of teChnological compartments of the nose section of the fuselage.
(ruu.a.h.
1) nose epimmmr; 2) forward* upper compartment; 3) compaitment from frames 6 to
11; 4) side panels; ,5) compartment from frames 11 to 13; 6) bottom panel; 7) side
panels from frames 13 to 20; 8) side panel' from frames 20 to 28; 9) bottom panel;
10) upper panel.
4/ 1,
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
r R-R-T
-26-
Design of Node Section of Fuselage (Fig. 7)
The nose aection of the fuselage, to facilitate assembly, is divided into
the follbwing compartments and panels; the noses xstxmax nacelle up to frame 2
(1); the front upper compartment from frames2 to 6 (2); the compartment from frames
6 to 11 (3); side pane]s from frames 2 to 11 (4); compartment from frames 11 to
13 (5); the upper panel from frames 11 to 28 (10); the lower panel from frames 11
to 20 (CI e iqcle pane). from frames 13 to 20 (7)1 the side panel from frames 20
to 28 (8)i lower panel from frames 20 to 28 (9)1
the inner side panel from
frames 20 to 28; the engine mounting frame; the forward brake f) pa; the housing
far the tigh brake flap; the hcuaing for the left brake flap; and the third brake
flap.
Nose Nazelle (Fig. 8)
The nose nacelle, from the nose to frame 2, is in the form of a '
? sharp leading edge.
/n the center of the air-i4takee duct is radio-transparint cone (2) made of
triplex glass teatoliter two layers are 1.2 mm thlok, and one (illegible).
the cone is attached to three-position cylinder () which moves along tube
(3), whiah is along the axis of the cone. The tube is made of ZOKhOSA material#ando.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
reprira
r ?
? rik? -17""rAW:rllrfrigj"""lr"""Wrj'-e. 411...""Ht .?
,e," I
1.4
?
e
?
Wiii133 %AI mos
e,
miltatfaitittiteittliterittlistiguilTuut tuts thi
s -r -R-R -T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : Clek-11:2P18-03066R000200010001-71
Fig..8. Nose nacelle withtillisyggrectihl. a
(the two outer suites:les aro shown).
diagram Of the three -position con
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
gronvm
-28-
Fig. 8. Nose nacelle with telescoping cone.
1. Nose nacelle, 2. telescoping acme; 3. guide tube; 4. disol 5. three-position
cylinder; 6, adjusting slider; 7. hanger; 8. articulated cantilever; 9. support,
is,
10.spring;11.self-lockingbolts12.. buishingjA
.,rocifor Pitot tube intake.
V V WI V MN
Approved For
Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : Clek-tR9PI8j0p66R000200010001-7
25X1
-29..
One end of
At1at10144 Ala AMA cons-control hydraulic cylinder ( 5) is attached to
frame 3 and the other end is attadhed to adjusting slider (6).
The lover part f the front nacelle oontaine a revolving rod for the Pitt
! tube intake (13). It is attached
to the front nacelle by two steel assemblies--
the front and rear--which are located on the lower spoke.
The front rod-attachment aetembly has a universal bolt joint. The rear
assembly is in the form of a conical pin which is attached by the self-locking
vertical bolt to a corresponding assembly on the fuselage. The rod between the
assemblies has an opening '0h? condensate tran.: and for,exit of the communication
Articulating cantilever (8) ii used to fix the rod in an inclined position;
the rod attachment un't is Covered on the outside with a detachable cowling.
The lower spoke of the front nacelle has a tube for passage of the communi4
cation lines, and a tow unit is attached, made of ZOKhRSA steel.
Frame 2 is' a main)ogalmade of material; in the upper part is
an insert of material. A disc, of t?1. material, is At riveted to the
frame; the cone tube is attached to this disc.
, Thecantilever of frame .2 has an end ',witch which signals that the cone is
extended.
Front Compartment from Frame 2 to Frame 6
The compartment from frame 2 to frame 6 contains,
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIff-Ele_8f0p66R000200010001-7
an upper'hatch for the radioequipment, and a housing for the front landing-gear strut.
The compartment has four Z4shaped stamped trusses made of sheet
duralumin D-16 with tubular spacers, and a horizontal bulkhead (also of D.16dura-
lumin) which separates the equipment compartment from the noes landing-gear housing.
The horizontal bulkhead has ? small hatch for access to the RVU units.
The main longitudinal assembly of the compartment consists of two upper and
two lower W-shaped longerons.
The aide walla of the compartment are made of 1.2-mm sheet D-16. These serve
as the inside walls for the air duct.
so' Compartment from Frame 6 to Frame 11
Frames 6 and 11 form the cockpit and the bottom equipment hatch which are
divided by the cockpit floor.
The main transverse assembly of the cockpit compartment consists of two
main will frames 6 and 11 and 8 intermediate frames. The longitudinal assembly is
formed by the upper and lower W-shaped longerons and the panel butaeath the canopy
With a grooVe for the pressurisation hose. Sheet D-16 is the material for
main elements and the cover,ing.
S-E-C- R- E-T
the
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CLA-RPrTEL-9066R000200010001-7
-31.15
The control cables which pass along the ciOckpit floor are covered by an
auxiliary removable subfloor.
')
The meld cockpit is preesurzed by Means of a U..30M pressurizer.
ihe framework of the lower part of the fuselage under the cockpit is an
assembly of frames made of sheet D-I6.
Tp frame 7 is attached the hanger farmiadiniimsmthm that contains the lock
for locking the front landing gear in the retracted position.
Frame 6 is ? main frame, a mattosemeca partition of D-16 duralumin, is
attached by means of D-16 angular profiles placed along the outside contours of the
frame, by vertical molded angular profiles made of V-95 material, and by two
extruded trusses of V-95T material.
To this partition are attached the forward armor pladng and the unit for
suspension ofthe front landing gear.
The lower part of the frame is cut out for the front landing gear and has
a support for the landing gear in the "down" position.
Ft.eme 11 is a main frame, a partition of V.95 material with an assembly of
profiles made of V-95 and D-16 material. To it are attached the rollers for the
ejection seat, the rear armor plating, the canopy bulkhead, them upper fuselage
panel, and the actuating arms for the aircraft control system.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
The
-32-
Bide Panels from frame 2 to Frame li
side panels from frame 2 to frame 11 form the outside walls of the air
ducts. Prom frame 2 to frame 7 the panels are made of 3.5-mm! -16 sheet duralumin.
On the pane,s between frames 2 and 3 are attached two adjustable anti-surge valves
tvrtikett.t ' itthrturo. 4 0,
Kat ?
Thep4nei frem frames 1 to 11 has two coverings (the outside one from frame
)1 9 and the in or one from frame 8 made of 1.2-mm 0-16 duralumin .
The transverse assembly consists of Z-shaned frames of 1-16 duralumin.
Between frames 9 and 10 on the left and right panels ar0 preosure -relief
valve:1,410othi
alacten inner sheet made of D-16 duralumin.
m....._ ____Le_wt-k?ri:erwwi_t.h_2_,
typ.m(t. ri.
On the right side of the bottom part of the panel is a groove made of
1Kh18N9T -11 steel.
Compartment frcm Frame 11 to Frame 13,
The compartment from frame 11 toframe 13 is made of 0-16 sheet duralumin.
ti serves as the housing fors kerosene tank No. 1 and consists of: panels 11 and
13, uppei removable hatch on the right side, and outside covering on the left side.
The air-intake duct which passes through this compartment isms made of 0-14
sheet duralumin.
S-E-C-R-E-T
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : CeElltN71-.93066R000200010001-7
,-33-
Frame 13 is a main frame, made in the form of a RAt?,1_9 material with
an opening for the air-intake duct.: ?ear tank No. 1 the partition of the frame is
attached by means of extruded profiles; at other places it is attached by moans of
angular profiles made of D-16 material. To the left:and right on the frame ere
the unite for attaching the wings to the fuselage.
IThe bottom arc of the frame is a double T-seotion. To it are attached three
aileron actuating arms. The coupling unite are cast 14L-I Elektron.
! ,
i The Upper Panel from 'reme 11 to Frame 28
The unper panel from frame 11 to frame 28 is in the form of a partition
made of b.iI sheet D..16, to which are attached two main longerons. The longerons
are made of V-95 and are strengthE.ned by anguler et41
The panel at frame 11 is has a flat cutout for the canopy. To it are
attached the unite for coupling the aircraft-control actuating arms.
the
To/longerons from frame 11 to frame 14 awa'attached the rear of the canopy
with its glasswork; to the longerons from frame 1h to frame 28 is attached the
removable1.0._____. which cong'sts of three parts with joints along frames 20 and
tgAr ,
25. Thqtwal is made in the form of a parabolic-cross-sectional second structure,
(0.4? ,
of sheet D-16. TheACU'oe,,c
J. is attached crosswise by extruded frames of 0-16.
The 4.,0,1 contains the !stabiliser meenelesellase and rudder control
,
*tires and also the electrical-anda II , dio-equipment cables.
l -
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
APproved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
The Lower Panel from Frame 11 to Frame 20
The lower panel from frame 11 to frame 20 is attached to the bottom longerons
of the side panels and to frames 11, 13, 16, 16A, and 20. The longitudinal assembly
channel-aeotion
from frame 11 to frame 13 consists of three/trusses on the ripht.and two on the
channel-section
left, made of V-95 material; from frames 13 to 16 it condiete of two/cast trusses
of ML-I.44 material; from frames 16 to 20 the profiles are made of 30khOSA steel.
The panel has a number of intermediate half-frames 12, 14, 15, 17, 18, and
19, the lower parts of '"rames 16 and 16A, and also auxiliary transverse elements i n
the fOrm of two side longerone pausing from the trusses of the brake-flap housings
,
.to frame 20.
To the-cast trusses at frame 15 . is attached the unit for coupling
ernn .
the line for feeding the ' tank. To frame 16 is attached the bracket for
forward attachment of the pylon ofthe
dron. tank.
At frame 16, to the trusses are attached two angle plates made of SZOKhRSA
steel; these extend to frame 20. At frame 20 they are jollied to the bracket for
the rear attachment of the pylon of the drop tank.
The panel covering is of sheet D-16 duralumin.
wheels of the
The housings for the/main landing gear are between frame 16 and frame.20.
The duct from frame 13 to frame 20 is of. round cross section and is made of
riveted D-16 sheets.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
S-R-C-R-R-T
a
Frame 16, a main frame, is in the Shape of a ring formed by/V.95 partition
and angle profiles of V-95 and SZOMOSA materials. In the middle ofthe frame
there are extruded rlatea of V-95 alloy to which are attached the steel assemblies
for coupling the wing and the fuselage.
The Side Panels from Frame 13 to Frame 20.
The side panels from frame 13 to frame 20 are made of sheet 0-16 and V-95.
with
Longitudinally, they are attached by the longerons
hatch framing made of 0-16 angle profiles and bulb-profiles along the contours of
the cutouts for the housings of the main landing-gear wheels.
Inside, between frames 13 and 14, on the rirht is a eleove consisting of
a Z-shaped profile and a covering.
On the left side, between frames 14 and 16, there is the housing for the
second auxiliary fuel tank.
The side panels are fastened to frames 13, 16, and 20. The upper and lower
longerens of the panels are riveted to the upper and lower panels.
Frame 20, a main frame, is a partition of V-95 material in the form of a
ring, and attached by profiles of 0-16.
On the right and left, angle profiles are used to join the walls of the
main wheel wells to the frame.
Approved For
S-E-C-R-E-T
elease 2003/12/03 : CIA-RDP78-03066R0002 0010001-7
1
25X1
25X1
Approved For Release 2003/12/03 : 9.Vprp-,93066R000200010001-7
1 he lower part ofthe frame contains the bracket, for the rear attachment
of the drop-tank pylon. The bracket is drop-forged of AKIA.1 material.
The Side Panels fram `rams 20 to Frame 28
The side panels from frame 20 to frame 28 are made of sheet V.95 and O.16.
They are attached to frames 20, 22, 25, and 28. The upper and lower panels are
fastenedto the longerons of the side panels.
The longitudinal assetbly of each side panel consists of the following: upper
and lower longerone of V-95 material, stringers and molded profiles of D-16 material,
and profiles laid out along the eontourof the wing profile.
Frame 22 is the main frame for attachment of the wing. At this frame the
air-intake duct ends and the engine compartment begins. The rrame consistsof
four sections bolted together. The upper and lower parts of the frame are of
channel *mutt= cross section, extruded of V-95 material.
In the center of the upper part of the Zrame is attached the engine f rame!
to the bottom part are attached the Units for coupling the control actuating arms.
The rignt and left parts of the frames are forged channel-section cross
beams, made of SZOKhOSNA steel
Approved for Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
;
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
.P"
Each has four collar fittings for attaohment to the upper and lower parts of the
frame, and four horizontal e5elets for Junction with the wing-attachment fittings.
The Lower Panel from Prams 20 to Frage 28
The lower panel from frame 20 tOfrage 28 is.a'longitudinal JI-ehaped km; truss
molded of V-95 material.
At frame 22 to the
truss is attached the fitting for
attaching the rear brake flap; at frame 25 is the fitting for attaching the brake-flap
hydraulic cylinder made of SZOKhOSNA steel.
Inner Side Panel from Frame 20 to Frame 28
The inner aide panel from frame 20 to frame 28 can be divided into two partms
the compartment from frame 20 ti frame 221 and the panel from frame 22 to franie 28.
The compartment from frame 20 to frame 22 ,is pairt of the round air4n1 t
duct, made of 0-16 material.
The panel from frame 22 to frame 28 is the inside plate of the housing for
kerosene tanks Not. 5 and 6, on which are installed tracks for mounting the engine.
S-F-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-R-C-R-E.-T
The &One Mounting Trues
The engine-mounting trues is between frames 22 and 28.
The truss is a built-up beam Of V-95 material; it is a wall with a lipped
upper flange and a lower flange made la from a molded T-profile.
At frame 25 a recess is made in the trues for the coupling bolt of the main
engine mount.
A forked fitting it attached to the upper part of the recess for the coupling
bolt; a support fitting of SZOKhOSNA steel is attached to the lower part of theme
recess.
Frame 25 is a main frame. It is in the form of a horseshoe with a lower
aro-shaped tie piece of double-T cross section, forged from SZOKhOSNA steel.
The m&in part of the frame consists of two halves joined to the engine-mounting
truss; they are made of a V-95 partition and flanges made from
V.95 molded angle plates.
On the partition of the frame are a number of reinforcing strut', while
in the middle, from both sides, there are brace plates and profiles of V-95, to
which the steel wing junetion fittinpp are attached.
forrpd
The bottom part of the frame consists of two/Partitions, between which is
attached a truss of ZOKhOSNA steel. To this trues are attached the fitting for the
cylinder of the third brake flap and the engine-mounting fittings.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
err nrm
Housing for Right Brake Flap
The ho sang for the right brake flap, between frames 111 a d 13, ie made in
channel-section ?
the ihrm of three/extruded trusises or V.-95 material which are bo ted to frames 11
and 13.
At frame 13 the universal joint of the brake-flap cylinder, made of SZOKhOSNA
stee10.8 attached to the trusses. At frame it, the trusses have a bulge for the
brake-flap attachment fittings. The trusses are connected by sheet D-16 partitions.
Housing for Left Brake Flap
The housing for the left brake flap near frames 11-13 is similar to that for
the right flap, except that it is made in the form of two extruded trusses. Be-
tween frames 13 and 14 there is an additionaltruss extruded of V-95, andia horizontal
partition made of 0-16.
Half-frame 16A is extruded of sheet D-16 with flanges of 0-16 angle pieces
and with M1,5-T4 fittings for attaching the lower trusses and fittings to support a
special suspension.
Frame 28 terminates the nose section of the fuselage and is the joining frame
;for the nose and tail sections of the fuselage.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
0 0 0 13 V
.140-
The frame is a rim of V..951' molded angle iron.with/:ZOKhOSA reinforcing
angle , 'plate: to which is attached a partition made of sheet D-16. i
The .inner flaw of the frame is made of molded angle plate from V-95
material. To the outer rim are attached supportald.lock washers, made of 1:416T,
for clamp bolts.
To the center of the frame are attached three V -95T fittings for auxiliary
attachment of the engine, and also fittings for attachnent of the rear of the wing,
in the form of telescoping supports with caps of SZOKhOSNA steel.
Joint Pitting (Fig. 9)
The nose and tail sections of the fuselage are joined at frame 28 of the nose
section and frame 28A of the tail section. The fuselage joint is a flange-type,
having three guide pins and 18 joint ....Crest of paragraph illegible)
Wing-Fuselage Hinge Fittings
The wing-111seitige hinge fittings are at frames 13, 16, 22, 25, and 28.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
QVOTZ. VT
. C.
,...
,? ,, ? ? Jr a# ? i . , .
? is
-.' ' .." - '. . ';%"' - . ? ? ..-
-7 ,',.f. tf.
; ,, , - ...1.-- ..?atilb ....).:1,
, .. . , ..., ? 7 .. r ? ? ? a
r.
'
##-.,1;???
-"S j?
e
41- '47)4
'- -'4V'
? 1?01.?
" *"?%. 4?1.. .44. ? 'Jr ? ? ? 1
. .fo. -44" "4\i":. I 4
" SG.: . ?
,
????? ? 1.
A.'s:. ?
- ? . #.
-.11" ?
?
: ? ???*?0:
?
liar* erzasivaiine '? 011#12110 MMUS
1111" 1.11.16". 41111%11103 UM 11 '11 7/41. 311,38 Mill 1401
ataLthaleliallaWIWPATIttnitiTif 1 e1111T111thtfiTI11411114r1lidiMr
S? r... V? V?T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
44 1.*
?
Vig. 9. Butt joint of nose and tail sections of fuselage. 1) frame 28; 2) guide
pintle; 3) frame 291 14) joint pintle; 5) cap; 6) hatch; 7) nut) 8) rubber seal
9) limiter.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
I f
25X1
25X1
Approved For Release 2003/12/03 : Cle-,Rpr78-03066R000200010001-7
25X1
442ft
The joint at frame 13 is a fork-type joint with one vertical bolt.
The joint at frame 16 has an upper and lower fork, in the horizontal plane,
and a nd.ddle lug in the vertical plane. The joint at each fork is
accomplished by a vertical etepped
by a horizontal bolt, fastened in
The
joint at frame 22 is of
bolt. The joint at the middle lug is accomplished
antiiever fashion in the lug of the wing spar.
the collar type, with two vertical clamp bolts'.
The joint atframe 25 is of the forked type, with one bolt and a nut.
The joint at frame 28 is accomplished by a bolt which is inserted and
locked, at the first wing rib, in the telescoping collar fitting.
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-;
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
err ppm
-1!3- -44-
2. Design and Make-Up of the Tail Section of the Fuselage
(Fig. 10)
The transverse main assembly of the tail section of the fUselage consists
of 13 frames the longitudinal main assembly consists of stringers; the covering
is made of D...6ATM- 11, 2, and D-16AT, 115.
Frames 34, 35A, and 36 are main frames, made of SZOKhOSNA steel; joining
I
frame 28A is made of molded D-16 profile, and the other frames are made ot -ahapsd
D-16 sheets.
The stringers are made of molded D-16 angle pieces. The four stringers
that frame the cutouts ror the parachute and the MRN antenna are thicker.
At the bottom left between frames 30 and 32 is the well for the dolma= drogue
chute. Antenna MAN-56P is located at the bottom right between frames 30 and 31A.
The - ventral fin passes along the bottom of the fuselagefrom
frame 28A to the end, along the axis of symmetry.
The front part of the fin is radiotransparent; at the rear of the fib, behind
frame 36, is the drogue chute lock.
The engine cowling is inside the fuselage from frame 29 to frame 34.
The stabilizer is attached to an axle that rotates in bearings mounted on
frames 35A and 36.
The engine afterburner is attached to frame 36.
R. P. 44
plating.
The fueelage terminates in the tail nacelle, made with no inner
There are special air-inlet ducts at frame 31A tm for engine blow-off.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
fmle4o40,,,Vip 4-,,-.10ti ,;)a- -74
404? Z.".R.CtrtS1. k.s?
r?T??
? ? i';.? ?
.
$4-k
;./
.4 4
,
'Vs t? ,`
?
: .4_, 10 to t-
1?1114. i`
.11.11 G="""=?.---
1129 tpi Etta Ix Ci1011
-11"" lartaitatiAtIltteftiatiattaittatta
e,
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
App
oved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
-45-
Fig. 10. Pramlwork of tail section of the fuselage and the tail.
a) Upper rudder fairing; b) rudder; c) back-fairing; d) tail nacelle; e) stabiliser;
. f) stabiliser attachment truss g) joining frame.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001i-7
S-E-C-R-E-T
1
*40'
2. Canopy and Election Seat
The canory and the ejection seat form the system "SK" designed to save the
pilot when he leaves the plane at speeds up to 1100 km/hr, by instrument.
A. Canopy
1. General Information
The canopy of the Ye-6T is designed to cover the pressurized cockpit, pro-
tect the pilot from the air stream, and assure normal vision during flight and when
landing the craft. In addition, the canopy is used to protect the pilot from the
incoming air dumdum stream during ejection.
The canopy (Fig.11) is a streamlined transparent secondary structure on the
upper part of the fuselage between frames 6 and 13. The rear of the canopy forma
a smooth junction with the back-fairing.
The canopy consists f thefellowing basic parts:
--the hinged part,
--the tail rear section, i
--a heat baffle;
^ transparent screen;
--aide flaps.
The canopy has the following systems to fulfill its funotionss
-.pressurization and control systems)
-.emergency ejection system;
-.seat-retention system) .
--de-icing system
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
'6,,t?
. ,
,..1 ? t . .t. 4 i l? i?.?''.
S '4 41:?? f". 11...1. w '.' ,f r? ?,* -1?1" . ke:S., ' ???? ?PE
14:. .7... 4." 1 ' .? s ../ J :ik -., ?? '
r t.i.z? % ? . , ....*:?}
? .- l'"? ,,-,i,t4::t1 ??'. /7 :I^ '''
. '' ' :'. .....
. . r ? '0-?' ?? J
' , , - . f ???? '... ,C
4 ,
? r 11$ ?
0
".." ? r.t
? ' . :. ? ? a
? 'lilt. 710 4.-
.1
"..*;??
-:4?,r4 ?
rf..?
-
:VA!
??44
???
44 ?
..;0? ? .0*,1,. ?
? -
rit ? . pi
1. a?..
' ????
7
kt"7'. ?
QV. trator.rora ?
*41 1?1??? I. t
/WS mamma inn ?rs ?I OM WO 11111106111 11841111411.604 111111n1Pr011 led
al 16.010.0 AtiV11003 11/41011 DU. 31V3S 11111 11/11011
I.
TtrtTlitttfirtilt6t1.1111:ttininTi12171MTIMMitIrItterfttlellenttlirlitt111117Ittilln
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
General view of the canopy.
447.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
n m
When the cockpit is opened, the hinged part of the canopy lifts out and up,
on an axle On frame No. 6. The hinged part of the canooy, is lifted by an air
cylinder.
The canopy* is pressurized after it is lowered and locked in place. The canopy
is depreeaurized either automatically, when the looks are removed, or autonomously,
using the pressurization thumb button. The pressurization hose is located in the
fuselage.
The air oresaure in the pressurization hose is 1.7-2.55 kg/cm2. The pressure
in the hose is less than that behind the reducer due to the pressure drop because
; of resistance in the check valve.
The canopy can be released, in an emergency, by means Of the emergency
release handle on the ripht side of the fuselage. The emergency locks are released
by means of a pyrotechnic system. The canopy is raised by lift cylinders to;which
wog air at a pressure of 130 kg/Cm2 is fed.
and is
During ejection with canopy shielding, the canopy separate from the fuselage
held to the seat; the emergency canopy locks in this ea-se are released by
seat pins.
The
canopy emergency ejection system is interlinked with the seat firii.ng
mechanism; it necessary to eject after emergency ejection of the canopy, part of
K
* Henceforth, in such expressione.we will use the word otanaloy" to moan ita hinged
part.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP/8-03066R000200010001-7
S-E-C-R-E-T
bled off
the gases are from the firing mechanism. This prevrnts the occurrence
system.
2.
due to a decrease in the mass of the
2. Design of theCanopy (Fig. 12)
Hinged Raft of the Canopy
The hinged part of the canopy (I) is designed in the form of a rigid
structure, bearing the convex main glass (1) and the flat front glass (17).
The
f great
frame consists of two longitudinal side trusses (18), attachod together
in the front by a cast bracket made of magnesium alloy itQ (32) and in the back
consist of
by an aro (2). The longitudinal trusses Elektron profile (26),
duralumin profiles and plating (27) riveted together. Rear arc (2) is of rigid
rivited design and has a cutout covered by special cover (3) made of magnesium
alloy. During ejection with the canopy used for protection, the cover of the hatch
is dislodged by the pyromechanism of the seat-stabilizing chwegm parachute.
The main glass (1) is heat-resistant organic glass, brand ST-1, 10 mm thick.
The glass is affixed in the side profiles by means of/Capron tape (20) Failed to the
glass. One edge of the tape is glued to the glass, the other is inserted into a
special groove in the profile (26) and held in place byz rod (21).
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
? 4ong the rear art and the frame of the forward glass the main glass is
held in place by rubber gaskets between theleuteide covering and the inside brace
plates; these Are tightened by bolts.
Zn the longitudinal direction, between the ends of the glass and the parts
of the frame there is a gap to prevent contact stresses in the glass.
The front glass is silicate laminated safety glass 14.5 mm thick in a special
frame (16) which is bolted to the frames of the front glass.
The moving part of the canApy at the joints is pressurized by means of a*
U:I0ni..2 pressurizer (19).
If there is no air in the plane's hydraulic 'system, the canopy can be lifted
manually by means of handle (5) on left truss (10); when not in use this handle is
in a socket in the truss, held in place by knob (6).
The Rear Section of the Canopy
The rear part of the canopy (II) is not pressurized and is removable. It
15 attached to the fuselage by anchor nuts. It is designed in the form of a frame-
work whichcontaine the glass. Olass (30), brand CO, 5 mm thick, is fastened along
the perimeter between the outside? covering of the framework and the inside brace
plate; theme are drawn together with bolts.
S?E?C?R?E?T
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : clilIDE7g37103006R000200010001
-7
-51-
Trig. 12. Canopy design. a) cross ection at "A-A"; b) croes section at
o) cross section at 93-13"; d) arose eection at 'ir-cw; e) crosa section at
f) cross eection at "E-E"; g) cross 'section at "r-)C; h) cover pin; i) shear bolt;
ferlegthael Aza1.4/ /AL "va (' )
S,E-C-R,E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : lik-Q1Z81,03066R000200010001-7
-52-
Fig. 126 Canopy design.
I. Hingdd section; II. rear section of canopy; III. Neat baffle; IV. Transparent
screen; V. Side flap; 1. Main glass; 2. rear arc; 3. Cover.; h. frame for trans-
parent screen; 5. handle to manually open canopy; 6. knob; 7. rubber grommet; 8.
groove for pressurization hose; 9. framework of 1"'rsection
Cd.44-0/1A-
of J410.
Dura (9] pressurized bulkhead sheet; 11. glass of
7
112,
nra ght bracket; 13. de-icer 'collector plate; 14. outside frame; 15. inside
brace plIte; 16. front-glass frame. ; 17. front glass; 18. side truss; 19. U-30M-2
preasurizer; 20. capron tape;
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
21. rod; 22. pressurization hose; 23.
canopy loop; 24.
pintle for operating frame; 25. operating frole; 26. Molded mi Elektron profile;
27 covering
grommet; 32.
28. Dural profile; 29. glascof heat bulkhead; 30. glass; 31. rubber
bracket; 33. blow-off tubs.
S-E-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : Clik-nP708;03,066R000200010001-7
-54-
i ?
To prevent contact maim stresses in the glass, between the covering and the glass
tbere is "UPL-0.4" pagAing take, while the openings in the glass for the bolts to
pars through are made larger than the bolt diameter, and rubber bushinge (7) are
put in them.
.Pressure Bulkhead
pressure
The bulkhead (III) separates the pressurized cockpit from the unpressurized
; region behind the roar section of the canopy. It is attached to the pmol beneath
the canopy to frameg 11. Along the outside edge it is artburicart bolted to the front
end of the rear section of the oanopy. In the center it is attached by bolt e to
the armor plate.
;
1The pressure bulkhead is of hermetically-sealed flat design made of 6qmped
Dural hsets (10) with reinforcing ridges stamped into it, and riveted profiles.
'Above and to the eidee in the pressure bulkhead are small windows for
exantnation of the rear hemisphere. The windows consist of flat glass (29), brand
$ (6?) mm thick.
In front, in the center of the pressure bulkhead, is attached a channeled
profile (8) which contains the canopy pressurization hose (22).
S-V_f? o__1'
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : Cli!k-RDp78-03066R000200010001-7
-55-
Transparent Screen
The transparent screen, of bulletproof glass (TV)f is located directly
beneath the front glass of the movable part of the canopy. It serves
three purposes! 1) it protects the pilot in front from direct hits by bullets,
shells, and shrapnel; 2) the canopy roll. along it during ejection with protection
by the canopy; and 3) it protects he pilot from,the air stream after release of
the canopy.
The transparent screen is t
ee-shoet laminated safety glass 62 mm thick in
a rigid steel frame (4) which is bolted, with 4 bolts, to sight mount (12).
Side Flag!
To the sides oftho transparent screen are two side flaps (V) which have
small windows (11) made of organic glass. The side flaps together with the
, 1
transparent screen form a_sort O'f baffle plata which protects the pilot from the
air stream in the event the canopy is released in An emergency.
3. Pressurisation and Canopy Control System
(Fig. 13)
The canopy is attached to the NeelageIsuspenaion bracket (1) by means of
two bolts which serve as axes of rotation when the canopy is raised and lowered.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
D
Canopy control consists in the opening and closing of the operating locks
and raising and lowering the canopy. The canopy is controlled with a special
handle (7) on the left side of the panel beneath the canopy. The canopy is pressur-
ized with hose (4); pressurization is accomplished by turning button (15) which
is on the sane shaft as canopy control handle (7). On the panel beneath the canopy
and on the fuselage covering, near handle (7), are instructions for the correct
use of the valve.
Canopy control and pressurization are possible both from inside and outside.
aever
kkeor this, the double-arm canopy control . has two handles: one inside (16)
and one outside (13). The outside handle is An a slot in the fuselage and is held
in place by catches and knob (14). In trite position, the outside handle is kine-
matically separated from the inside handle. When knob (14) is pressed, handle (1))
moves out, and when it fa turned down it engages the inside handle, after which the
canopy can be controlled from the inside.
it must be pulled
To retract handle (13)
. from the inside intil the handle
disengages from the inside handle and fits into its housing such that the catches
f the handle drop into place and knob (14) can be turned, looking it in place.
Pressurisation from the outside is accomplished by turning shaft (17) by means of
slot
a screwdriver placed in the at the end of the shaft.
CC(' D V
Approved For
Release 2003/12/03 : CIA7RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
ii
0?11040.40.10,kroth...."1
'73 VIZ:1 UV IOU
m m e.t ma?mmt. itxf
=WIWI INikaililma 0011041rall sma
31106 3/ill 3A1,04
1Ttilennt711/11117t17:11I114
r) T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
?
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S?E?C?R?E?T
Pressurization system
Fig. 13. an d canopy control.
a. diagram of canopy attachment when suspended; b. view at "B"; 0, canopy
loop; d. point "B"; e. gee belog; f. cross section at "104."; g. Zee belog;
h. removal of canopy; i. frame 6.
OpeN
s
\j
re
0 depressurize
'*re 4 depressurized pressurized
I- Sefilel
When lifting the canopy, let
dhSeiled
the air out of the hermetic hoses ,
before releasing,.the lock ? /
s-r.-r-R-F.-T
(Take off only witl
the handle locked
in the extreme
forward position
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : ClfklDr.148;0p66R000200010001-7
Ft
-58-
. 13. Pressurization and canopy control systeM.
1. canopy suspension bracket; 2. canopy lift cylinder; 3. canopy operational lock;
catch diquttLe-A.4.40,1
4. pressurization hose; 5. 6, push-pal rod; 7. (anile
fnT cano4 control) 8. check valve; 9. RV-1.5 reducer; 10. air valve; 11. actuating
arM; 12. pintle; 13. outside handle; 14. knob; 15. pressurization push button;
Seo71/..eits
16. inside handle; 17.4.shaft with apline for pressurizing the zahtm canopy from
thecutoidel 18. swivel lock.
C D V 1'
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
-59-
The c noPyis.affixed in the lowered position by six locka (3) located in
the jbaXmt panol beneath the canopy. Look 3 is a cast bracket with a groove into
which the can py loop fits. Piritle (12), moved by actuating arm (11) crosses this
groove. The ctuating arms of all the locks areconnected by connInting rods, to the
cenopy-contr 1 handle guide. To
Canopy is role sed, the rear left
at the point wlere pintle (12)
e
revent the locks from opening fore the
catch
lock has a " ' (5) which covers the groove
emerges.
When t canopy is released the loop compresses catch (5) and frees
pintle (12).
lowered
The canopy is ' by means of cylinders (2) which get their air from the
lowered
hydraulic system by means of canopy-control valve. The canopy is :by its
own weight, displacing the air from cylinders (2) into the atmosphere.
The double-arm canopy control handle (Fig. i4) is attached to panel (16)
and housing (1). rt consists of rod (4) which has on it inside handle (9),
pressurization button (8), and guide (7). Inside rod (L) is shaft (3) containing
outside handle (2). Shaft (3) is pressed outward by spring (6) and in this position
engages shaft C)4) by means of two screws (5). Screws (5) and the grooves in the
head of shaft (3) ars positioned asymmetrically, so that the outside handle engages
the insida one only in the down position.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIAP18:03066R000200010001-7
r3
. ?
v. ""?
--", ?
tv-Itetk4s...:t.rto, -
cry
' 3.444.11,' 4.spni .16074
.7?11.imer.riiteit iLeystsaf:
r*PlitZta$4184. Ootskr4ct1404
r1-0,410* L4e.tapc9, th.<
?
? er
?;:r ??4.
. .
? ? 4. ?) 4 .k
. .
' , sire ? ?io .4.. . ?,)
.e' 16:4111.f ' e
f,-rr? .
r ?
44 ?e,
',ell %.* A ?
. - "
? ?k-
4.` . , 4:11,..et#'410/0 ? Va
A.
1/4 ?
elb ? .
/iNacc ? .
IV.
t.
MI 0
2411/Alle 1?04,64.1.6U. seureprin mai
1?.1
S.iscosa .U.11,040..1 ]MO 11 DU. nyas 344011
11,...11.01,41iftes
....illinnirri?!!!arnl,11?4v),6444,,,r? 1080 00/0 00e. 01,10-1111.1. 1,1140,4441:110???4,0????...... .0..4. I
NW) V 411.11/101,110
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
25X1
25X1
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
R- F
-60-
Fig. 14. Two-position canopy-control , handle.
1. housing for outside handle; 2, outaide handle I 3. shaN 4. rod; S. screw;
6. sp'ring; 7. ruide; 8. pressurization pueh button; 9. inside handle; 10. spring;
11. nut; 12. connecting rod; 13. bracket; 14. gears; 15. pressurization and canopy
control valve; 16. panel.
S-E-C-R-E-T
1/
ApprOved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
s_r_r_R-V-T
The prevents disturbing the handle whr.n the canopy is closed from the outside.
Guide (nand button (8) have clearance relative to handle (9) and rod (h)
of 300 and 15? respectively. By means of the clearance of pressurization button
(8) the canopy can be pressurized and depressurized when handle (9) is locknd in
the extreme forward position. The toothed sect on of button (8) is connected with
canopy control valve (15), which is also on panel (16). The projections of shaft
(3) and the xx stem of the valve are hermetically sealed by moans of gland packing
and a rubber ring. ihon the outside handle is operated, shaft (3), by means of
connecting rod (12), deflects the inside handle and does not permit it to be locked
in the Arward position.
Canopy Air System (Fig. 15)
The canopy air system is divided into the operating and emergency systems.
The operational air system is designed for pressurization and raising of the canopy.
It includes canopy lift cylinders (5), Pressurization hose (8), canopy control
valve (11)i air valve (12), reducer RV-1.5 (13), and check valve (11.4).
The canopy lift cylinders (5) are located on the aides of the panel beneath
the canopy hear frame No. 7(?). Canopy control valve itg .(i1) is attached to the
panel of the Canopy control handle.
S-E-C-R-E-T
Approved For elease 2003/12/03 : CIA-RDP78-03066R0002
0010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
r_r_ R- T
Yroghwe 9IoJA,a*.e441?
- epowfaut eimitarus oratagooss %part Owl 84assilibe
- ' i,e?nrafre esliwomuesime *ow. i. -: r??
- e Ft fee diVelliNOIN eillOMPAP *Wei
irmaNta
?
.*;1?,41V.. ? :?? ?? P ..:477,'11."7":47141r.
4 fitu- ? 1*.
? .; "
t'?
Z-r,":75,4141
4S..t?
.?.41*C'li%
WegU4.34471'
411-f
?
r-
41,114111414 `,"` r? ?
,
1.,1'?
. . ' --. 4+ '... '7, ?,?OL -.--:;; ?44,' L.--
,
-: 4.- Ill:t- c ,, a ? ..1',
. ' it4'.
, ? t?_, - -%, - -?
-
.1%*
,- to?-* ;
N,-?..#
.
? ?
'
??? 1111 a IA) *4, ON,
14 0 nrywiT1 44404 It *I .4.6 IVA '
lluIflfl auIti llirtabLuTtuskuldAautuldit
S-E-C-R-E-T
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-71
Approved For Release 2003/12/03 : Clt-MPI8E-V066R000200010001-7
Fig. 1. Canopy by4^ 4w? o2ic aystem. a. from cylinders, p ? 130 at b. deeignatione,
system for control using canopy-lift cylinders, p 50 kg/cm2; .
canopy messuritation system, p 17-2.55 kg/cm2; - canopy emergency
removal system, p ? 110-130 kh/cm2.
?
1. chock valve; 2. reducer 111/477; 3. emergency valve; 4. filter; 5. air cylinders;
6. check valve; 7. air cylinder; 6. pressuritation hose; 9. emergency tank; 10.
pipe; 11. canopy control valve; 12. air valve; 13. reducer RV-1.51 14. check valve.
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
no-
The pressurization hose is in a. special groove In the panel beneath the
canopy. Air valve (12), connected into a single unit with AV-1.5 reducer (13),
and cheek valve (1h) are on the left side of the cockpit near frames 7 and lb(?).
Using the emergency air system, the canopy easmkm is cast off when
it is released in an emergency. This air system consist oftcheck valve (1),
located on the right side of the cockpit,
/which separates the campy emcrgency hydraulic system from the 13o-atm aircraft
emergency tank (9), in the forward equipment compartment;
pressure system; emergency
valve (3) on the bracket that holds the right-hand canopy-lift cylinder; filter WI
air cylinder (7), attached to the krankmt canopy suspension bracket and used to
open the time-delay lock during emergency canopy release chock valve (6) Which
separates the emergency air system from the operating system; and air cylinders (5).,
which during emergency release of the canopy serve as ejection cylinders. Pipe
(10)is used to measure the pressur
bleed off the air.
in the emergency canopy air system, and to
R-F-C-R-E-T
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
s-r-C-R-E-T
Hydraulic System Units
Canopy
Pressurisation and - Control Valve
(Fig. 16)
The pre surisation and canopy control valve has two cavities, similar in
body and
design. The valve consists of (3)x/a shaft with cams (1) and valves (6)
and (7). On a shaft (1) is a gear (see Fig. 1h) which turns the tuuthed sector of
the pressurization button.
The gear ratio of the coupling is 3, i.e., when the toothed sector is turned
75? the gear and the valve stem turn 225?. The other end of the shaft passes to
the outai's through the covering of the cockpit and has a slot so that the cockpit
can be nreseurised from the outside using a screwdriver.
(remainder blurred)
S-E-C-R-E-T
Approved For Release 2003/12/03: CIA-RDP78-03066R000200010001-7
Approved For Release 2003/12/03 : CIA-RDP78-03066R000200010001-7
S-E-C-R-E-T
???? ? ? ???????? ??? -?
- - ? ?
? A.'
- ? ^ 417 - .?
??,? -
?
" -1? - .? .1. _ ???:, ' --..f..;?.?:
' 7i' .1" - ,. ? :: , ? -- I,1:::-t?? ;.-
. ? ??????? 4 it? ?-? -- .or?,.? -I( t. ? ir '1...", mit,"a -t f? : ?
?..,,... ,. -.. .: . i .?.. ..;..,; ? . . ??'? ;?:???.- -. : ..t.,?;,-,.? ;
. " ? - ? ; ; , ? ' 4 ' ? ').. :A' '? ?;it . V.-",47
:' . ' .% '4 . . ' . . . . 1
.r, s;; , . -; .s.,...,..f.- 2.....1 .,?1.1."N. .? " _ : 4..`.1.1.3.0?11:r4;',?,....(1, ../.0.; ? ,zt.:4,- e. ? .?.,' ,
? .. .14 I. 'A-C'''''. * *
? ! ?? --.*:,' _,.-.,......,..?.......;:...-,,t.... ?
. , ? ,. -.1-..4-..-.:,7.,-,!--1,
..... . ,..... ... . .. ,
... . . , ... . ..- i,...:,-be.t... .?-z.
1 ? '. er? 4
- ? ? ?-.4 ? :
- - ?
-
i V 1 7 1 1 1100
?- ? ' - 1 2.; W."., 7 3kf.' ft, ? * . ? .-
, 4 ,Z.illtA.:', tr 4 . , ?
4,..` ,... ? 4 , . .4?? ...r. ,......1,
?
,., ?,...?? .? ,- t ? ..,,,, t - ? ,,s ?,-,re-,,,?,,??? ?
' - *--lbl % 4. ( ? ' ?r?? ' ? ? -'
.?
?:?.._ .? ..._? _ . ? ? -. - ....1.? ? ....
?kietilli 4%.1 ?19---ipinotsd Jo ivracria?g`toz?*-',,1/4. -'-.
. ? - ..?,-;,..rt.i????., -.
viti. . -,1..474fr $ ,?-lramir
? P4,,,
ttePa-