(SANITIZED)UNCLASSIFIED POLISH BROCHURES ON MOTOR VEHICLES AND AIRCRAFT(SANITIZED)

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP81-01043R001500060005-0
• Release Decision: RIPPUB
• Original Classification: C
• Document Page Count: 55
• Document Creation Date: December 27, 2016
• Document Release Date: February 12, 2013
• Sequence Number: 5
• Publication Date: October 28, 1957
• Content Type: REPORT

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PROGRAM POKhZU
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POKAZ POLSKIEGO C' ILNEGO EKSPORTOWEGO SPRZETU LO1 ` L ., I
Uory odbed:le sly na lomisku Goclaw w dnlu 15.X. 1957 mku o godt
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~~LIEAIfEI~t ArNS~1Et~A-T~ACiEN:r
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IREUIE BE LANCEMENT POUR PEAHEURS i U B R-3
Foncttonnenmcnt sur, simple, facile d I'entre-
lien, nu minlmmn do frals d'exploltatlon.
IREUIE AUXIEIAIRE RTC POUR IREUIE BE EANCEMENP
Grande Economic de temps au rbcupdrage du cable.
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The TS-8 "Bies" aircraft
Short Teohnioal Bescri,p12n
1. General ihf orma ions
The TS-8 "Bies" aircraft is designed for basic
and acrobatic training. it can be used for training of
air crew prior to jet flying coursed
The aircraft is suitable for instrument flying
training while the special version of TS-8 "Bies" can
be used as a trainer for instrument landing.
The TS-3 "Bies" is a cantilever low wing two seater
with tricykie retractable underoarriage. The two seats
are placed, in tandem in a spacious cockpit equipped
with dual controls.
Ventilation of the cockpit is ensured by means of
special intakes.
The transparent plexiglass canopy ensures good
visibility from the cockpit. Ths canopy comprises two
0
independent sliding hoods /one over each pilots
compartment/ which can be slided backwards to improve
visibility in bad weather conditions. The hoods can be
ejected in emergencyo
Lighting of the cockpit consists of ordinary and
of ultra violet lamps,-
The aircraft is equipped with standart navigation
lights and with set of visible from the ground green
lights indicating that the undercarriage is fully
lowered.
The position of the undercarriage is shown by
means of indicating lights placed both in front and in
the rear oompartment azno by visual indicators fitted
in wings and in the fuselage9 the latter are well
visible from both seats of the aircraft.
The aircraft is of all metal, stressed skin
construction. The wing consists of three sections.
Ailerons, elevator and rudder are of metal construction
covered with fabric. The pneumatically retracted under-
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carriage is equipped with pneumatic brakes on the main
wheels and with a shimmyCdamper on the fully castoring
front wheel.
The aircraft is powered by the type WN-3 four
stroke, seven cylinders, air cooled, radial engine,
without supercharger and reduction gear, developing
320 H.P. take off power? The aircraft can be equipped
with variable pitch, constant speed air screw type
WRC1 of the 2,2 m diameter or by two blade, fixed pitch
wooden air screw of the same diameter,
? Lead indata
2.1? Dimensions
Span 10? 50 m. /34 ft. 5ins, /
Length 8?50 m. /27 ft, 10 ins./
Height /oockpit/ 2?25 m./7 ft. 4 ins./
Height /fin/ 100 m, /9 f t.10 ins./
Main wheels track 2?35 m?/7 ft.8 ins.!
Wheel base 2.05 m./6 ft. 8 ins./
Wing area 19?1 m2./212,2sq.ft./
Fuel tank capacity 215.1/47.25 imp.gaL/
Oil tank capacity 20 1. /4.4 'imp. gal. /
2? 2? aleig_htt o?f aircraft
All=up weight /full
acrobatics allowed,
overload ooeffi=
oient ? 3 / 1550 kg. /3410 lbs,/
All~up weight /no
acrobatics allowed/ 1760 kg? /3872 lbs,/
The weight of trainer
version comprises:
aircraft with power
plant 1070 kg, /2354 lbs./
basic radio equipment 90 kg, /198 lbs./
fuel and oil 160 kg? /352 lbs./
crew 180 kg. /396 lbs./
Total ..1500 kg? /3300 lbs./
2?3. Performance /trainer version/
Maximum speed at
sea level
Cruising speed.
310 km. /h. /192 m.p.h./
/75% power/ 270 km. /h. /168 in. p. h. /
Stalling speed /no
power, flaps up/ 120 km. /h. /75 in. p. h. /
Stalling speed /no
power,flaps down/ 100 km. /h. /62 m.p.h./
Speed for best rate
of ,limb 175 km. /h. /109 in. p. h. $
Maximum diving speed 500 km./h. /310 m.p.h:/
Maximum speed with
flaps down
Initial rate of climb:
with fixed pitch air
screw
with variable pitch
air screw
Ceilings
with fixed pitch air
screw
with variable pitch
180 km. /h. /112 m.p.h./
5.4 m? /sec. /1064 ft./min./
6.8 m,/seo./1340 ft./min./
5000 in. /16400 ft.!
air screw 6500 m, /20992 ft./
Take off run 390 in. /426 yds./
Landing run, flaps
down brakes on 200 in, /219 yds./
Flight endurance
/235 H.P. , 2100 r. p. m. / 2.5 h.
Range
20 4, Power plant
675 km. /420 miles/
Number of cylinders 7
Swept volume 114 1.
Compression ratio 6.3 : 1
Flight at .fhx~ power:
power developed 340. HG Po .
engine speed 2500 r, p. m,
speoifio fuel 0011=
sumption 270 g. /H. P. h.
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Flight at take off power:
power developed
engine speed
specific fuel , on-
sumpt ion
Flight at continous
rated power:
power developed
engine speed
specific fuel con=
sumption
Flight at cruising
power /75% take off
power/:
power developed
engine speed
specific fuel con.
sump tion
Fuel
320 h. p.
2350 r. p. m.
250 g. /h. P. h.
285 h. p.
2250 r. p. m.
250 g. /H. P. h.
240 H.P.
2100 r. p. m.
210 g. /Ha P. h.
aero=engine petrdl
72 ootanes
Specific oil consumption
/cruising/ 5 ge /H. P. h.
Weight of engine 240 kg. /528 lbs. /
3. Airframe eonstxuction
3.1. The outer LYing
The outer wing attached to the wing centre
section is of a stressed skin construotion
with leading edge torsion box, formed by the
wing nose and the front face of spar located
approximately at 30% chord.
The skin of the leading edge box is of thick
metal sheet and is stiffened by means of nose
ribs and spanwise .stringers.
Rear part of the outer wing taking ailerons
and flaps loads hay thin metal sheet skin.
The whole skin is fastened by means of
countersunk rivets. The outer wing is attached
to the wing centre section by means of flanged
oonneotion.
12. The wing oentre section
The wing centre section is of stressed skin
construction similar to that of the outer wing
but with gradually increasing thiJokness of the
spar booms. Right and left side of the centre
section are slighty inclined downwards; they
are fastened to the central part of the spar
which forms the main member of the wing construc-
tion. The lugs for fuselage attachment to the
wing are on the central part of the spar and on
the front and rear part of the No. 1 rib.
In the rear part of the wing oentral section
are the main wheels bays and the space for
special equipment. The landing light is located
on the left hand side in the wing nose of central
section.
3.3. Fuses
Fuselage is of a stressed skin construotion
with dural sheet skin stiffened ny means of
frames and Z=section longerons.
In the front section of the fuselage is
located the cockpit equipped with two seats and
separated from the engine by a fireproof bulkhead.
The engine mounting is attaohed to the fuse-
lage by means of four bolt joints. In the lower
section of the fuselage are plaoed three inter-
connected,fuel tanks.
3.4. Tail unit
The tail plane is attached to the fin by
means of four joints. All the. control surfaces
and flaps are of similar construction. It
comprises a tubular steel spar and light dural
sheet ribs. The tubular spar is in each case
located in the nose and its additional purposes
is to mass-bairoe the control surface.
All the control surfaces and flaps are fabric
covered.
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The control surfaces are aerodynamically
balanced.
15. Undercarriage
Tricycle undercarriage with nose wheel is
pneumatically retracted.
Main wheels legs turn on bearings located
in wing centre section between the third and
the fourth ribs and retract into bays in the
wing centre section; the nose wheel retracts
into the fuselage. When the undercarriage is
retracted the bays are covered by special
fairings.
The nose wheel unit is attached to the
bracket of lattice construction fitted in the
front part of the fuselage.
The uderoarriage comprises oleo pneumatic
legs; the nose wheel damper unit is of a two
stage type.
Wheels are made of magnezium alloy and are
equipped with differential pneumatic brakesn
The front wheel is fully castoring and is
fitted with shimmy=damper.
16, Controls
The aircraft is equipped with dual controls
If or pupil and for instructor/. The control
system is of rod and lever type while all the
linkades are fitted with ball bearings.
The engine is controlled by means of push=
pull rods.
The pneumatically operated flaps are linked
to the actuating unit by a series of rods.
3.7. Power plant and air screw
The WN-3 seven cylinder' air cooled engine
developer 320 H.P. at 2350 r. p. m.
The engine drives a two blade wooden fixed
pitch air screw or a variable pitch constant
speed air screw.
The engine cowling consists of two parts
which can be easily removed for maintenance or
repair works Cowling gills in front of the
cylinders enable control of the air flow during
the flight. The engine is equipped with a rad
diator and a compressed air starter.
18. Cockpit acoessoriee
Seats are designed for back type paraohute
and each of them can be adjusted by the pilot.
Strong harness attached in an ingenious way does
not hamper movements of the pilot.
Both compartments are equipped with a full
set of instruments. The instrument panels are
mounted on rubber lord blocks,
30 9o Instruments
The set of instruments comprises:
= magnetic compass
air speed indicator
= altimeter
rate of climb indicator
artifioel horizon and turn indicator
engine controller
rev meter
clock
30100 Basic radio egui went
The aircraft is equipped with the VHF radio
set' automatic radio compass with repeaters in
each compartment and an'intercom.
3011. Additional equipment for instrument flying
For instrument flying the aircraft is
equipped with radio altimeter, approach receiver
and gyro magnetic compass with repeaters in both
compartments instead of ordinary magnetio compass.
The remote control of radio equipment are
located only in the front compartment. All the
switches and knobs of radio equipment are
grouped on a special panel on the pilot's
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right hand side in the front compartment On
both sides of eaoh compartment are placed other
oontrols and indicators suoh as extinguisher
lever, switches of electrical and pneumatioal
system, manometers etco
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The Jakm12M aircraft
--------------------
Shoat technical desar~tion
prrrMrrrrrrrrrrrrrr rr-i
10 General information
The high wing monoplane Jak=12M powered by the
AZ=14R air cooled engine driving the variable pitch
W~530=D11 air screw may be used in three versions: as
passenger aircrgfty as ambulance and as agricultural
aircraft: Conversion from one version into any of the
two others can be carried on an aerodrome /that is in
field working conditions/o
The Jak=12M aircraft is equipped with the blind
flying instruments, radio set and automatic radio
compasso
The spacious and well lighted cabin is ventilated
in summer and heated in winter: Easily detachable in=
spection panelsn covers and cowlings as well as com~
Portable access to the accessories of the aircraft
simplyfy the maintenance and the operation of the
airorafto
The take off and landing characteristics of the
Jak='12M allows operating the aircraft outside aeroW
dromes in summer and in winter: The conversion of wheels
into ski landing gear can be carried on an airfield:
Good stability in the air and easy control of the aix=
craft guarantee full safety of the flight:
The passenger version taking full fuel supply can
carry two passengers with hand luggage:
Removing the ARK=5 radio compas and filling tanks
with 115 litres /2503 impogallons/ of fuel only allows
the aircraft to carry three passengers with hand luggage
at the distance of 450 kmo /280 miles/0
At short distances the aircraft can carry in the
cabin 300 kg. /660 lbso/ load on the conditions that
the weight of fuel in tanks does not exceed 50 kgo
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/110 lbso/ and that the ARK-5 radio oompas as well as
right hand side front seat are removed
The ambulance version can carry one patient on
stretchers and a medical attendant or three sitting up
patientso The medical equipment of the ambulance version
ensures an adequate care of the patients during the
whole flight.
The agricultural version is equipped with
accessories for spraying fluids or spreading dusts,
fertilizing chemicals and seedso The equipment comprises
the hopper, the feeding device, the
and the spraying devioeo
fan with
the pump
20 Leading_data
The k1~14R__engine
Number of cylinders
9
Continus rated power
220 H0 PO
Take off power /maximum/
240 H0 Po
Cruising power
165 H0 PO
Specific fuel consumption at
continus rated power
240250 go /Ho PO h0
Cooling
by air flow
Engine weight
200 kgo/440 lbso/
Length
Dimensions
9 m0 /29 f t0 .6 ins0 /
Span
12.6 m0/41 ft0 4 inso/
Tail plane span
403 m0/13 f t0 3 inso /
Wing area with ailerons and
closed extension flaps
2386 m20/256o5 sqo fto /
Wheel track
20 2 m/7 f t0 4 ins?'/
Performance and _!_-
version and the ambulance version of the
------------------------------------------
dak=12M aircraft
Performance
Maximum speed in level flight 179 kmo /ho /111 mo po h0 /
Rate of climb at sea level 401 m0 /seoo /807 f to /mind /
Time of climbing:
to 500 ino /1640 f to / 20 2 mind
to 1000 mo /3280 f to / 40 7 mind
Take off from concrete runways
at take offs powex, 2350 x0 p0 m0
and 20? lowered flaps:
take off run 126 mo/138 ydso/
take off speed 80 kmo /ho /50 mo p0 ho /
take off length to clear
25 mo /82 f to /
Take off in similar conditions
as above but at conti nus
rated power and 2050 ro po mo :
450 mo /490 ydso /
take off run 150 m0/1605 5 ydso /
take off speed 80 kmo /ho /50 mo po h0 /
take off length to clear
25 m0/82 ft0/
Landing on concrete runway with
flaps lowered 40? and brakes
on:
535 mo/587 ydso/
landing run 190 m0/207 ydso/
touch down speed 73 kmo /h0 /45 m0 p0 ho /
length of landing from
25 m0/82 ft0 /
Landing in similar conditions
as above but with flaps up
and brakes off:
390 mo /425. ydso /
landing run
465 m0/507 ydso/
touch down speed
82 kmo/ho/51 m0poho/
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length of landing from
pilot
80 kg. /176 lbso/
25 mo /82 f to /
765 mo /834 ydso /
passengers
240 kgo /528 lbso/
Service ceiling
4160 me /13650 f to /
fuel
87 kgo /191 lb$0 /116 1
Time of climbing to the
oil
14 kg. /31 lbso/.
service ceiling
4001 mina
hand luggage
12 kgo /27 lbs. /
Still air range at 500 m0
Weights for the ambulance version
/1640 f to /
765 km0/473 miles/
/stretchers and medical attendant/
Flight endurance at 500 m0
Empty weight
1014 kg. /2251 lbso /
/1640 ft0/
6 h~ 29 mine
All up weight
1374 kg./3023 lbso/
Weights of the passenger version
Useful load
360 kgo /792 lbso/
fli
ht
i
ts
l l
d i
U
f
Empty weights:
cons
s
se
oa
n
u
g
aircraft converted to carry
two passengers
aircraft converted to carry
three passengers
Maximum weight in flight with
two or three passengers
Normal weight in flight:
with two passengers
with three passengers
Useful lead in normal flight:
with two passengers
with three passengers
Useful load in flight with two
passengers consists of the
following weights:
pilot
passengers
fuel of specific
weight 0,750
oil of specifio
weight 0,893
? hand' luggage
Useful load in flight with
three passengers consists
of the following weights:
of the following weights:
1026 kg/2257 lbso /
pilot
80 kgo
/176 lbs. /
patient
80 kgo
/176 lbs0 /
1002 kgj/2205 lbso/
medical attendant
fuel
80 kgo
92 kgo
/176 lbso /
/202 lbso /
1435 kgo /3170 lbso/
oil
14 kg.
/31 lbso /
luggage or stretchers
14 kgo
/31 lbs./
1428 kgo /3141 lbs0 /
the
of
Performance and wei~hts
_
_
----------- --- ---
/
/3170 lbs
k
43
o
go
1
5
402 kgo /884 lbso/
a~ricultux_-___al _version_of_Jak_12Y
Performance
433 kgo /952 lbso/
Range of economical speeds
Rate of climbing at sea
130-140 kmo/ho/81-87 mopoh./
80 kgo /176 lbso /
160 kgo /352 lbso/
136 kgo /299 lbso/180 l0
14 kgo /31 lbso /
12 kgo /27 lbso /
level for the all-up weight
of 1450 kgo/3190 lbso/
at continus rated power
dust spreading version 2,6 m./seoo /512 ft./mina/
spraying version
at cruising power and
1860 r0 p0 m0 dust
spreading, version
spraying version
32 nb /seoo /630 f t. /mine /
1 m0/seo0/197 ft0/mina/
1.2 m./sec./2.36 ft0/min./
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The lengtx of grass take off
run for the all-up weight of
1450 kgo /3190 lbso /, with
flaps lower: 22?, at take
off power:
dust spreading version 1~4 mo/139 ydso/
spraying version 110 mo/120 ydso/
The lengtb'of grass landing
pilot 80 kgo. /176.lbso/
cheraioals 300 kgo. /660 lbso/
oil /supply for two
hours flight/
10 kgo /22 lbso/
fuel /supply for two
hours flight at sea
level with the speed
of 135 kmo /ho /84 mo po he / 73 kgo /161 lbso /
run for the all-up weight
of 1450 kg. /3190 lbso / with
3d Construction and accessories
==========_===_=============
flaps lowered 22? and with
brakes on:
dust spreading version
spraying version
180 mo /197 ydso /
The fuselage structure comprises welded steel tubes
and Dural ribs covered with fabrioo
The front part of the cabin, covered in the upper
section with transparent panels, is equipped with
~i~e ight s
Empty weight:
doors on both sides while in the rear compartment the
door is fitted on the left hand sided The doors are
bi
i
s
n
equipped with emergency ejecting device0 The ca
dust spreading version
978 kgo /2152 lbso/
equipped with ventilating and heating system0
spraying version
987 kge /2171 lbso/
The wing and control surface structure is made of
All up weight
1450 Mtge /3190 lbs0 /
Dural and is covered partly with Dural sheets and
Useful load:
partly with fabric0
dust spreading version
472 kgo /1038 lbsd/
The tricykle undercarriage with the tail wheel
spraying version
473 kgo /1019 lbs0/
is of non retractable typed Main wheels are equipped
Useful load of the dust spreading
with brakess The undercarriage is fitted with rubber
version consists of the
rope shook absorbes and the hydraulic dampers The tail
following weights:
wheel is fully castorings
pilot
chemicals
80 kgo /176 lbso /
300 kgo /660 lbso/
The ailerons, elevators and rudders are controlled
by means of cables while the flaps are pneumatically
oil /supply for
two driven0 The air screw is of a variable pitchy
hours flight/
10 kgo /22 lbso / The aircraft is equipped with the pneumatic
fuel /supply for two system for engine starting, wheels braking and for
hours flight at sea flaps controllingo
level with the speed of Fuel tanks are of 180 litres /40 imps gallons/
135 km0 /ho /84 m0 p0 ho / 82 kgo /180 lbs0 /
capacity while the oil tanks contains 25 litres
Useful load of the spraying
/50 5 imps gallons/ of 0110
version consists of the
following weights:
Electrical installation supply the energy to
lighting and navigation lamps, to instruments, radio
equipment, heaters and to wiper0
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MOTOIMPORT FOREIGN TRADE OFFICE
National Enterprise
26 P,rzemyslowa, Warszawa. Poland
P. O. Box 365. Telegrams: MOTORIM WARSZAWA
POLISH FOREIGN TRADE PUBLICATIONS - WARSZAWA
Printed in Poland
in Warszawa -
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ACHIEVEMENTS OF THE POLISH CIVILIAN AVIATION
The purpose of today 's lecture is to acquaint the
Representatives of foreign Embassies and Legations
accredited in Poland as well as the press represent-
atives with the history of development and with modern
problems of aircraft design in Poland after the World
War II0 The Polish production of both gliders and engi-
ne aircraft of low and medium power has reached a stage
of technical perfection which together with achieve-
ments in both the field of pilotage and record perfor-
mance enables us to speak today of an export of a
number of products of our aircraft industry working
under the trade name of Polskie Zaklady Lotnicze /PZL/.
The continuation of this name known since pre-war
years is meant to couple with the good technical, pro-
ductional and commercial traditions of the pre-war
Polish aircraft industayo For a number of PZL aircraft
knwon then like the fighter Super P-24,0 the light bom-
ber "Sum", the bomber "Lod", the diver-fighter "Wilk",
the reconnaisance aircraft "Mewa" and the training
aircraft "Wyzel" have won a good name in the world
flying opinion and a credit on a number of Internatio-
nal Exhibitions of Paris, Milan, Belgrade and Stockholm;
This resulted in efforts'.of , oommencing export of these
planes to a number of countries as for instance to
Bulgaria, Greeoe, Roumania and Turkeyo
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As a natural effect of military airoraft export a
considerable export of sport aircraft and gliders was
notedo This latter was influenced by the fact that both
the glider and sport aircraft designs have achieved in.
the meantime a number of successes whereas the PZL air-
craft9 and especially the RWD ones have won world repu-
tation by establishing many'a world re.oord and winning
the Challenge de Tourisme'Internationale competition
of 1932 and 19340
The Polish aircraft industry has also specialised
in the production of light sport free balloons of high
class which have achieved a number of-successes in the
past in the International Gordon Benett Balloon Competi.~
tionso
In the field 'of aircraft combustion engines a
number of original successful designs were developed in
the same time such as the radial engine G-1620 and the
bank engine PZL=Poka which as to their idea of construo.-I
tion and elaboration of detail have been rated among
the leading in the worldo It is also worth to be mention
ed that in the field of designing oompressorcandcturbine
jet engines a suitable experimental engine was developer
qualifying considerably in advance of contemporary work
conducted in other countries respectivelyo
The Polish aircraft industry of that time was
marked for high class'of designing on the basis of
original ideas9 own standards and methods of high
quality industrial production which won common reoognii
tiono On the other hand with regard to the production
of low and medium power aircraft engines based on
foreign licence the Polish aircraft industry has fre, j
quently reached achievements superior to those noted
abroado
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The outbreak of World War II has brought Poland
further development of the Polish domestic aviation
but also in its outcome a nearly complete destruction
of aircraft industry and research establishments as
well as complete devastation of airfields and flying
schools. The gre-atest losses were suffered in the form
of casualties among flying specialists, designers,
pilots, mechanics and technologists.
In the field of motorless aviation the situation
was favourable since already during the period follow-
ing immediately the war a suitable specialist personnel
was recruited and trained whereas it was possible to
commence the production of prototypes and series of
gliders despite primitive and hard conditions with
regard to the design and production of a glider being
relatively simple as compared with those of an engine
powered aircraft.
The general situation in the field of engine avia-
tion was complicated by the lack of own aircraft engine
production upon which the development of various types
of utility aircraft could be based. Since the needs
of both civilian and sport power 'aviation were great
since the beginning efforts were made, for obvious
reasons, to meet them directly by rapidly launched
production based on licences or even by foreign pur-
chases. Thus the production offered today for export
includes first of all aircraft based on lic,enoes pur-
chased by Poland from the Soviet industry, and re=
presented by the aircraft "J'akm 12M" and the helicopter
SM-1, of high utility values and good performance
factors. These products, owing to various possibilities
of their application can be used for service in nu-
merous fields of economy.
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and economic coefficients but also owing to the
correct pilotage and good flight properties at low
and high speeds and to the possibility of performing
full acrobatics# to represent top achievements in its
class.
Most interesting developments are noted in the
field of the Polish motorless aviation.
The Polish gliders are marked for extremely quick
and efficient assembly and dismantling which in case
of the "Jask6lka" takes only a few. minutes of time.
The number of loose parts is reduced to the minimum
some of the gliders being equipped with special
devices serving the elimination of play occuring in
fixings following long lasting use.
To the best known Polish gliders belongs the
"Jask6lka" high performance single-seater of which
the following versions have been developed: Albatross,
"Jask6lka-M", "Jask6lka-W", "Jask6lka-Z" and "Jask6l-
ka-L".
Next very successful glider presenting a two-sea
version of the "Jask6lka" is the "Bocian", type SO-9
bis, also holder of many national and world records.
An interesting design development presents the
single seat training and performance glider Mucha
presenting various improvements of glider technique.
An advanced design displays the "Czapla" two-
seater for both primary training, dual control flying
instruction and first solo flights as well as for
acrobatics learning;
The SZD-18 "Czajka" training two-seater capable
of flying with or without cabin is fitted with a
wheel undercarriage of extremely soft shock absorp-
tion.
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It is worth to be mentioned that the sohool
glider craft including the 18-3, ".ABC" and "Salamandra
gliders have found very wide application not only in
Poland but also in the Chinese Peoples Republio.
Sales agents for the Polish aircraft industry
are the "Motoimport" responsible for advertising, in-
formation and trade.
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 Main rotor diameter
Rotor blade number
Length without rotors
Overall length
Overall height
Track
Weight empty
All-up weight
Useful load
Maximum speed in le-
vel flight
Maximum rate of climb
Time of climb to
1000 m.
14.00 m. (46 ft.)
3
12,11 in. (39.7 ft.)
16.95 m. (55.6 ft.)
3.30 m. (10.8 ft.)
3.30 m. (10.8 ft.)
1785 kg. (3935.2 lbs.)
2250 kg. (4960.3 lbs.)
465 kg.(1025.1 lbs.)
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Time of climb to
3000 in.
12 min.
Absolute ceiling
5000 m. (16400 ft.)
Maximum range
385 km. (239 miles)
Maximum endurance
3 h. 24 min.
Take-off power
575 h.p.
Cruising power
323 h.p.
Fuel consumption
225-240 g./h.p.h.
(4.86-5.29 lbs./h.p.h.)
Fuselage structure - welded steel tube lattice.
Tail boom structure - semi-monocoque.
Rotor structure - mixed, steel and wood.
Rotor blades - articulated with friction
dampers on vertical hinges.
FOREIGN TRADE OFFICE
MOTOIMPORT
NATIONAL ENTERPRISE
26 PRZEMYSLOWA, WARSZAWA, POLAND
P. 0. Box 365. Telegrams: MOTORIM Warszawa
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rryKr~?+Gr~,. pf'Y'y K ',i~~'4~,?i~'. W
~t fir. fi? .~
ry~"e .4a,r~w 1. .,
^J.,~aba'.+~' :`r~.'i`z~.?:~i"r.n.~f'v'r?:,? ..'~"7rnr-:.d:'+...a-+.A t',?a't'$.C~}ra~r' ~d _. a' !. ~'~!
 EQUIPMENT:
The "JAK-1211" aircraft has a full set
of instruments.
The radio equipment includes a radio-
compass and a V. 11. F. radio-station.
The cabin has normal and ultraviolet
lights. The aircraft is provided with
navigation lights and a landing light.
All elements of the plane and the power
plant are well accessible and easy in
maintenance. A two part engine cowl-
ing can be easily Laken off when ser-
vicing the engine. A shutter in front
of the cylinders allows to regulate air-
passage during the flight.
A metal frame work with fabric co-
vering and, where clanger of damage
exists, sheet dural covering - is re-
sisLant enough to atmospheric effects.
The slotted and strut-braced wings can
be easy dismounted.
Owing to the trimmer at the elevator,
which is regulaLed by the pilot during
the flight, the aircraft is easy to fly
at full range of speeds and various
loads.
The sLeerable Lail wheel can be coupled
with the steering mechanism allowing
easy manoeuvering on the ground.
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 The "JAK-1211" aircraft can be used for the transport of
3 passengers in a comfortable, well ventilated cabin, which
assures extremely good visibility for the pilot.
The aircraft is equipped with instruments which allow flights
in bad visibility and M. night; it can start even in difficult
ground conditions.
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- sowing chemical manure
- sowing seeds
15-20 in. (16-21 yards)
18-22 m. (19-24 yards)
IC IiIA.- ot: th,a,,iiecui-o
The "JAK-1211" aircraft can be used for crop and forest (lusting and
spraying purposes and for sowing chemical manure and seeds.
The spraying installation, provided with a container of approximately
300 kg. (600 ctw.) capacity for spraying or sowing material, reliable in
operation and serviced by the pilot during the flight, allows during one
passage to dust or spray strips of following widths:
- dusting forests, fields and gardens 60-90 m. (65-98 yards)
- spraying fields and gardens 40-60 in. (43-65 yards)
Small surface needed for starting and landing (Lake off and landing dis-
Lance appr. 120 in (180 yards) permits operation bases to be located
in the neighbourhood of areas to be sprayed.
A Light wall-plate mounted"for this purpose between cabin and spraying
installation protects the pilot against harmful effects of the chemicals.
STAT
The "JAK-12 Al" aircraft can be used as a sanitary aeroplane
for transporting a sick person on a stretcher, accompanied
by a doctor or an orderly, who have full possibility to look
after the patient during the flight.
The cabin is easy accessible and the sick person can be placed
in and Laken out of We cabin by two orderlies in a very
short time.
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The Polish gliders of most modern construction are known all
over the world.
During 1955 only the Polish pilots won 22 golden badges with
3 diamonds for 46 golden badges with 3 diamonds totally award-
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The SM=1 helicopter
Short $echnioal description
10 General igormation
The SMc1 helicopter is designed to carry two or
three passengerso The machine can be used for various
special purposes such as xescue action in inaccessible
terrain /mountains, forests, marshy.grounds/ and water
ors after introducing certain modifioations9 for agri-
cultural application /insecticide spraying and dusting
of fields, forests, and orchards, topdressing and seed
spreading/o
The helicopter is suitable for operation In
various climate conditions- the machine is equipped
with special antifreeze devices which enable its opera-
tion in artio clianateo
The helicopter is powered by the Al-26 W seven,
cylinder, radial piston engine cooled by forced air
flown
The SM=1 helicopter employs three bladed lifting
rotor, tricycle undercarriage and a motocar type cabin
for pilot and passengers. In the cabin is mounted the
seat for a pilot and the bench type seat for two
passengers with parachutes /the bench can acoomodate
three passengers without parachutes/, The helicopter
is equipped with accessories enabling day and night
flyingo
The machine can hover and It is capable of vertical
take off and vertical landing, The hoverning enables
passengers to get on board or to alight by means of a
rope ladder in inaccessible places where landing is not
possible,
20 Leann data
2010 Dimensions
Main torot diameter 140 3 mo /47 fto /
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Number of main rotor
blades
Disc area
Length of fuselage
Maximum sweep
Wheel track
Wheel base
Height
Ground clearance
Range of main rotor
collective pitch
3
160.5 m? /1726 sq. ft. /
12.11 m./40 f to 9 ins.!
16.95 m. /56 fto 7 ins./
3.3 m./10 ft. 10 ins.!
3.75 m./10fto5ins./
13 m. /10 ft. 10 ins,/
0.4 in. /1 ft. 4 ins. /
control from + 1? to + 13?
Tail rotor diameter 2.5 m./8 ft. 3 ine./
Number of tail
rotor blades
Range of tail
rotor pitch control from = 6o to + 11?
2.2. Weights
All up weight 2250 kg. /4950 lbs./
Weight empty 1785 kg. 13927 lbs./
Usefull load:
pilot
two passengers
fuel
oil
de-icing fluid
Total...
80 kg.
/176 lbs. /
160 kg.
/352 lbs./
175 kg.
/385 lbs./
25 kg.
/55 lbs. /
25 kg,
/55 lbs!
465 kg.
/1023 lbs./
Maximum vertical climb
rate at continious
rated power:
at sea level 4 m. /sec, /788 f t. /min. /
at 1000 m. /3280 ft. /4.6 m. /sec. /906 ft./min./
at 2000 in.
/6550 ft.! 5.1 in./sec./1005 ft./min./
at 3000 in.
/9840 ft.! 3.5 m. /sea. /690 ft./min./
Maximum' vertical
climb rate at maximum
power:
at sea level 6.5 m. /seo. /1280 ft. /min. /
Economical speed
for climbing 90 km. /h. /56 m. p. h. /
Climbing time:
to 1000 m.
/3280 ft.! 4.3 min.
to 2000 in.
/6550 ft.! 7.8 min.
to 3000 m.
/9840 ft.! 12.0 min.
Hovering ceiling 3000 in. /9840 ft./
Service ceiling 5000 in. /16400 ft./
/normal equipment of
the helicopter does
not comprise oxygen
2.3.
Performance
system o the machine
Maximum speed /level
flight/ at sea level
200 km. /h. /124 m. p. h. /
should not operate
above 4000 in.
/13120 ft.!
at 1000m. /3280 ft.!
185 km. /h. /115 m.p.h./
Maximum stil ait
at 2000m./6560 ft.! 185 km. /h. /115 m. p. h. /
range at 1000 in.
above 2000 in.
/3280 ft./ with speed
76560 ft.!
175 km. /h. /109 m. pa h. /
of 140 km. /h.
/87 in. po h. / 385 km. /239 miles/'
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Endurance of flight,
at 1000 m./3280 f to /
with speed of 90 km./h.
/56 m.p.h./ 3 h. 24 min.
2.4. Power nt
Numbest of o7lin4era 7
Swept voluae 20.6 1.
+Compr.seion rsti. 6.4 s 1
Flight it teko aft
po~Yx
poror d.nlop*d 379 &P.
~ngins spood 2200 r.p.a.
boost 890 rs. fig /35 ias. xg/
speotfio fuei
oonsusption 290-320 g./LP b.
?light at Oontiaoue
rand power at sea
1*sl$
p0wo= dmloped 430 b. p.
ongins speed 2050 r.p.a
boost 760 mm.Hg /30 tns.8g/
speoifio fuel
ooaaumption 260-275 g./E.p.b.
Flight at oontiuous
rand power at
2200 mo/7216 ft./t
power developed 460 H.P.
engine speed 2050 r.p.m.
boost 760 mmHg /30 ins.Hg/
Flight at cruising
power /75% of ' r
oontinoui rated
power/ at sea 1lvel:
power developed 322 b.A.
boosts
at 1960 r. p. m. 630 mm. Hg /25 ins. Hg/
at 1860 r. p. m. 960 mm. Hg /38: ins. Hg/
specific fuel
consumption: '
at 1960 r. p. in. 230-255 g. /H. P. h.
at 1860 r. p. m. 225?240 g. /H. P. h.
Flight at cruising
power /50% of
continous sea level
rated power/:
power developed 215 H.P.
engine, speed 1860 r. p. m.
boost 575 mm. Hg /22.5 ins. Hg/
specific fuel
consumption 240270 g. /H. P. h.
Maximum time of
engine running:
at take off power 5 min.
at continous rated
power 60 min.
at cruising power unlimited
Fuel 9ero engine 92 ootane
petrol
Maximum oil specific
consumption 15 g. /H. P. h.
Dry engine weight 445 kg. /979 lbsd/
2.50 Gearin
Reduction ratio
between main shaft
and engine 1 : 1.295
Reduction ratio
between main rotor
and engine
Reduction ratio
between tail rotor
and engine
Reduction ratio between
cooling blower and
-engine
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: 8.85
1.52
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3.
3010 Fuses
The fuselage is made of chrom-man-sil steel
welded tubes; the construction is covered with
nonCstressed skin Dural panels while the trans-
parent sections are covered with plexiglass.
The cabin is located in the front part of the
fuselage@ The transparent sections of the cabin
ensure good front and side visibility while two
special bulged side windows enables oertain
visibility backwards0 The cabin is equipped with
a motocartype doors
Engine and engine cooling blower are mounted
in engine compartment placed in the centre section
of the fuselage. Main gearbox is mounted in the
upper part of the fuselage above the engine.
In the rear section of the fuselage= behind
the engine compartment, is mounted a Dural fuel
tank of 240 litres /53 imp.gallons/ capacity.
The adjustable tail plane and the tail skid
with rubber foot are fitted at the end of the
fuselage rear section which is of tranculated
cone shape.
Inside the fuselage rear section and the
tail bq?m run transmition shaft of the tail
rotor drive, push~and-pull rods controlling
tail plane position and oable of tail rotor
pitch control systems Leading edge of the tail
plane is made of Dural and the remaining part
is fabric covered.
3? 2. Power
The engine is equipped with a clutch engaging
the transmission and with axial flow-cooling
blower comprising flow steering baffles. The air
filter of the engine is mounted on the right hand
side of the maohine$ Exhaust gasses run through
the exhaust manifold comprising two parts ending
on both sides of the machine.
The fuel system comprises special oil valve
for oil dilution when the helicopter is operating
in low temperature conditions. The oil tank is
of 32 litres /7 imp.gallons/ capacity. The oil
is cooled by means of two radiators.
The engine is equipped with compressed air
starting device comprising compressor and two
bottles of 4 litres /0.9 imp. gallons/ capacity
each,
The firefighting system consists of two
bottles with carbon dioxide and of an alarm
device warning the pilot about the increase of
temperature. Engige cooling can be controlled
by means of a set of adjustable gills.
303. Transmission
From the engine the drive is taken up to
the main rotor and to the transmission.
The transmission comprises: the engine re-
duction gear fitted on the engine, the main gear
box mounted above the engine, the intermediate
gearbox located 'in the rear section of the
fuselage' the tail rotor gearbox mounted near
the tail rotor and various shafts connecting
the gearing.
The vertical main shaft connecting the
engine reduction gear with the main transmission
gear is att~ohed to the gears by means of two
elastic clutches dumping the torsional' vibration.
The main transmission gear employs a pair of
spur gears for reduction of main rotar speed and
a pair of bevel gears for reduction of tail
rotor speed.
The main transmission gear is oonneoted with
the intermediate transmission gear by means o
a shaft rotating in five bearings ans fitted
with four universal joints compensating any
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strain of the shaft.
The intermediate transmission gear does not
change the speed of the shafts and its sole
purpose is to alter the direction of the shaft
oonneoting the main transmission gear with the
tail rotor transmission gear. The latter finally
reduces the speed of the tail rotor.
304. Flyins controls
The control of the helicopter flight is
obtained by means of changing the magnitude and
the direotion of the main rotor lift and by
ohanging the tail rotor thrust.
The flying controls of the helicopter
consist of:
lever for control of pitching and roll ng,
- lever for mixed control of rotor pith and
thrust and of tail plane position,
- pedals for yawning control,
? sieering wheels for balance device control.
305. Main rotor ting rotor/
The three blades of the main rotor are
connected by means of vertical and horizontal
toggle joints to 'the hub mounted on the main
transmission gear shaft. To prevent the ground
resonanoe special friction-dampers are fitted
on the vertical toggle joints. Near the hub
the blades are rectangular while the parts
nearer to the blade tips are of the trapezium
shape. The blade oomprises tht steel spar of
varying section and of ribs rivetted to the
spar. The blade is covered with plywood and
fabric.
To the leading edge4 of the blades are
attached special fittings with openings through
which the antifreezing fluid flows on the blade
surface.
:306.
Tai
The variable pitch tail rotor comprises
three wooden blades with metal fittings. The
blades are also equipped with the *ntifreezing"
device.
3,7. Undercar_, lags
Trieykle undercarriage allows taxying on
the ground and vertical as well as runway take-
off and landing. The legs are of a oleo-pneuma-
tic type.
The tyres are of low pressure type, the
front wheel is fully castoring.
3.8. Antifreezing ystern
The antifreezing system prevents the forming
of ice on main rotor blades, tail rotor blades
and on the windscreen by means of washing their
surfaoes with special antifreezing fluid. Beside
that the windscreen is heated from the inside
of the cabin by means of a hot air flow. Anti-
freezing fluid is spread on the windscreen
surface by means of a wiper. The main tank
containing antifreezing fluid is of 28 litres
/6 imp.gallons/ capacity and the auxiliary tank'
can take 2.5 litre /0.6 imp. gallons/.
3.9. Electrical equipment
The eleotric energy is supplied by a genera-
tor and 28V batterieso They supply the energy
to instruments, electric motors, heating units/
lighting points, signaling devices and to radio-
equipment.
'
'1
The lighting of the helicopter comprises
the ceiling lamp in the pilots compartment,
the instrument panel lamp, the compass lamp,
landing and taxying light and navigation lights
fitted on both sides of the fuselage aril on'-he
tail. -
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 110. Radio equipment
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The radio equipment comprises a receiver-
-transmitter radio set, radio compass and
radio altimeter.
111. Auxiliary accessories
The auxiliary accessories oomprise the
flare pistol and flares and the first aid
equipment.
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MOTQOW FQREiGN TRADE OFFICE
Natlou! Enterprise
FlZemya ows. Warszawa. Poland
P. O. l 363. ftegum: MOTORIM WARSZAWA
POLISH FOREIGN TRADE PUBLICATIONS - WARSZAWA
Prinfed in Poland
in Warszawa
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MOTOIMPORT
Central Foreign Trade Office of the Motor
Industry National Enterprise
Warsaw, Poland P.O. Box 365
Telegrams: MOTORIM - WARSZAWA
W. H. Z. 330!IV 56
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"JASKOhKA"modern high performance glider designed
for training flights both for thermal soaring and flig i clouds
without visibility. The construction `his~li er meets all
demands of modern aviation owing to e- odynamic design
acilities.
as well as to its excellent pilo
;ing
The additional advanta e e JASKOhKA' glider co sists
of the automatic c ng devices for the control system which
allow fork g it in small hangars ensuring its very rapid
and preparation for flight (within 3-10 minutes).
SKOLKA" is outfitted with a complete electric equipment
including lights and lightning protector.
This glider can be.equipped on request with oxygen
apparatus and total energy variometer
The standard equipment of4 strument panel consists
of airspeed indicator, variometer, altimeter, compass,
and electric turn and slip indicator with cross level
Moreover, the plane is equipped w th.a set of tools
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
"JASKOhKA" is a cantilever mid-body mounted wi,'hder of
wooden construction. The monospar wings are,covered with
plywood. The ailerons are in two parts, of splif type, differen-
tiated and aerodynamically compensa ed, The Fowler flaps
may be set in three positions for 0 , 12o,and 250,
The diving brakes are of scis or Type,
The fuselage of oval cross-section is entirely covered with
1ywoodyt has in its front portion the pilot's cockpit with plexi-
glass canopy
A single-wjel un ereant e is provided, half-retracted in
This-wheel is provided with a mechanical brake synchronized
with the air brakes. r
Further, the fuselage is provided with a short front skid, front
and bottom tow-hooks for aero-tow or winch-launching, front
and rear tow-hooks for launching by means of rubber rope
when in slopes.
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
 "MUCHA 100" an unexpensive glider is perfectly suited for,
thermal and slope-soaring, as for flights in clouds.
Good aerodynamic features, simple handling, perfect finishing
and comfort are the characteristics of th machine
Owing to its up-to-date construction the "MUCHA 100" glider
meets all modern requirements It is to be added, that neither
tools nor additional elements are necessary for assembling
and dismantling the "MUCHA 100"
The instrument panel is fitted with airspeed indicator, altimeter,
variometer, electric turn and slip indicator with cross level,
? longitudinal clinometer and compass
Further this glider is outfitted with electric installation, lightning
protector as well as with covers for canopy and Venturi tube
protection On request this glider can be equipped with oxygen
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
"MUCHA 100" glider is a single-seater with cantilever wings,
entirely built of wood. The monospar wing with oblique auxi-
liary spar has a ply-covered leading edge stiff against torsion
Air brakes are of scissor type
Longitudinal oval cross section fuselage is entirely plywood-
covered. The cockpit with the streamlined plexiglass ca ropy
is outfitted with a comfortable seat, with safety-belts and tarpau-
lin covered back-rest, which declivity can be regulated on
the grouna. This glider is outfitted with front and bottom
tow-hooks as well as with a starting hook for the launching by
means of rubber rope
The transport wheel and short front and rear skids are located
under the fuselage The skids are shock-absorbed by means
of rubber pads The skids facilitate the take-off and ensure
a smooth landing A folded grip located before the tail unit
is provided for carrying the tail when manoeuvring on the
ground
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
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 MOTOIMPORT'
Central Foreign Trade Office of the Motor
Industry National Enterprise
Warsaw, Poland P 0. Box 365?
Telegrams: MOTORIM - WARSZAWA
W H Z 33CIIV 55
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
"SALAMANDRA" is, a strut braced high wing glider with
framed body' made out entirely of wood
The monospar wing in two parts rear auxiliary spar has diffe-
rentially operated ailerons and air brakes.
The- framed body hes in its rear-portion the crossed pianowires.
The cockpit, open type with a small windshield is situated in
the front portion of the fuselage.
The wooden landing skid, shock-absorbed with two tyres is
situated under the cockpit. The instrument panel is fitted in
three basic flight instruments,
airspeed indicator, variometer and altimeter. The knob of the
front releaser is located close by the instrument panel.
SPECIFICATION:
Total max. weight in flight 225 kg (495 lbs )
Weight of pilot (equipment included) 85 kg. (187 lbs.)
Wing loading 13,30 kg /m2. (2,73 lbs /sq. ft.)
Max gliding ratio (at 49 km./h) (30,45 in ph) -12,2
Min. sinking speed (at 47 km./h.) (29,2 in p.h ) 0,85m /sec.
(2,79 ft./sec.)
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0
 Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043R001500060005-0
The winch " ZUBR 31r is mounted `on sfee1 framin
-located on a bi-wheeled undercarriage provided=
with an independent ' suspension' and shock" absor p= Y
by means of spiral
springs:
The winch when working is put four fixed egsby,_
means of a special jack.
The winch "ZUBR 3" is provided with a 6-cylinder,
four stroke, top valve, water cooledpetr61 engine'
of "S-42" type, arranged a unit with clutch and,
gearbox. The winch-launch set consists of* a cable
drum with drop type brake, rope reeling. device,
on the drum and security scissors.
The winch "2UB.R" is provided. with-signalling"-lights,
for the launching. A speedometer, indicating, the-
speed of the drum reeling the towing cable, as well.
as the instruments controlling the engine's work
oil pressure gauge, cooling water thermometer-
and an amperometer are located on the' instrument'-
panel in the cabin. -
MOTOIMP.QRT=
Central Foreign Trade Office of-1 lo
h -`Nfor
Industry -National' Enferprise" - - ?
Warsav,, Poland P.O. .Bo x? '365..
Telegrams: MOTORIM =14ARSZAWA ^
W. H. Z. 33011V. 56
SPECIFICATION:
Engine power (at 2.800 r.p.m.) 85 h p. (83,8 b.h.p.)
Cylinder capacity 4188 ccm. (255 cu. in.)
Length of the towing rope on the drum 1200 m. (3940 ft.)
Overall dimensions:
Length (shaft excluded) 2760 mm. (9,05 ft )
Width
1810 mm. (5,94 ft.)
Height
1280 mm. (4,18 ft.)
Weight
1440 kg. (3168 lbs.)
Declassified in Part - Sanitized Copy Approved for Release 2013/06/11: CIA-RDP81-01043RO01500060005-0