PZL Bielsko Junior SZD-51-1 Technical specifications
PRZEOSI~B
IORSTI'IO OOSl'I IAUCZl\LNO-PROOUKCY:::JNE
SZY8CJ.'INICT1IA
"PZL-81
ELSKO"
SZD-51-1
"::JUNIOR"
GLIDER
FLIGHT
MANUAL
Issue
I -
Oecember
1984
Reg.
No
•••••.••
This
is
the
translation
of
Folish
text
approved
by
Central
Administration
of
Civil
Aviation
Translated
by:
W.Stafiej
D.Sc.
Iseue
I -
December
19f1.:
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J
51-1
FLIGHT
MANUAL
No
inscriptions
or
supplements
are
Page:2
allo~ed
to
be
introduced
to
this
Manual
if
not
approved
by
the
Authority.
In
case
this
M•nual
haa
been
lost
the
Authority
shall
be
infor~ed
i••ediately.
Everyone
who
finds
this
Manuel
is
asked
to
~ail
it
to
the
Ministry
of
Com~uni-
cation,
Central
Ad~in1strat1on
of
Civil
Aviation.
In
this
Manual
the
revisions
contained
in
Bulletin
No
BE-001/85
~JUNIOR"
have
been
introduced.
Iesue
l -
Dec.
1984
·-·
-. --- -
szo- FLIGHT
MANUAL
Page:
51-1
3
LIST
OF
REVISIOOS
NOTE:
Place
where
the
text
has
been
revised
is
•arked
with
vert
ica
1
line
on
the
left
side
of
text
and
with
the
ite111
of
revision.
Item
Paga
REVISION
Date
Signature
1 7
2eplaced
with
page
7A
accordill6
to
i;ho
85-07-1p
'
-~
Bulleti:1
!lo
3K-002L65
1;--.;
;,,.;_
'
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UJ~NlOR"
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sue
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Dec.1984
Druk:OWPT
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sz.-0-
FLIGHT
MANUAL
Peg•:
51-1
4
Item
Page
REVISION
Date
Signature
I
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--------··-
·-
Iesue
I -
Dec.19B4
szo--I
51-1
-·--·---··--------------..------.
FLIGHT
MANUAL
CONTENTS
1.
DESCRIPTION
OF
GLIDER
1.1.
General
description
1.2.
Main
technical
data
.............
.............
.............
Paga:
5
Page
7
7
9
1.3.
Instrument
installation
•••••••••
9
2.
OPERATION LIMITATIONS
•••••••••••••
10
3.
PERFORMANCES
......................
14
4.
OPERATION
OF
GLIDER
•••••••••••••••
15
4.1.
Pre-fligrt
inspection
•••••••••••
15
4.2.
Operations
before
flying
••••••••
15
4.3.
Pilot
in
cockpit
••
•• ••
••••
••
••••
18
4.4.
Procedures
before
take
off
••••••
20
4.5.
Controlling
.•••••••.•••..•••••••
20
4.6.
Operations
after
flights
•.••••••
26
4.7.
Assembling
and
disassembling
••••
26
4.8.
Road
transportation
•••.•••••••••
27
4.9.
Directions
for
Mc
Cready
ring
29
5.
DANGER
AND
EMERGENCY
CONDITIONS
30
5.1.
Landing
in
high
plantation
••••••
30
5.2.
Break
off
or
unintended
releasing
of
towing
cable
•••••.•••••••••••
30
5.3.
Emergency
exit
and
use
of
parachute
••..•..•••....•••.•.•••
30
Issue
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1984
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szo-
51-1
FLIGHT
MANUAL
Page:
5
5.
FIGURES
Page
Fig.
l.
SZ0-51-1
7~UNIOR•
glider
•••••••
33
Fig.2.
Instru~ent
installation
•••••••••
35
Fig.3.
Mc
Cready
ring
for
SZ0-51-1
glider
•••••••...••••••••••...••.
36
Fig.4.
Speed
polar
for
SZD-51-1
glider
•
37
Fig.5.
•Ying
assembling
....•••..••••••.•
39
Fig.6.
Horizontal
tailpane
assembling
.•
41
Fig.7.
Colour
marking
of
airspeed
indicator
dial
•..••••.••.••••.••
43
Fig.8.
Adjustment
of
pilot's
back
rest
and
seat
•.•••.•.••••••••••••••••
45
Fig.9.
Allowed
range
of
empty
glider
e.g.
location
...•........•......
47
Fig.10.
Operat~on
of
elevator
trimming
........................
49
Fig.11.
Displacement
of
placards
••.••••
51
7.
PLACAA
OS
• • • . • . • • • • • • • • • • • • • • • • • • • • •
50
8.
TABLE
OF
GLIDER WEIGHING
•••••••••••
57
Issue
I -
Dec.
1984
szo- I
51-1
FLIGHT
MANUAL
1.
DESCRIPTION
OF
GLIDER
a•ma•m••••••••••a•••u•a
1.1.
~!~~r~!-~~~sr!e!!2~
I
Page:
7 A
SZD-51-1
•JUNIOR•
is
the
school
and
training
one-seater
built
on
base
of
JAR-22
Requirements
in
·u·
category.
Glass-fibre/epoxy
structure.
WING
-
in
two
panels
of
double-trapez
planform
Double
T
spar
with
longerons
and
web
of
glass-fibre
composite.
Sandwich
coverings
glass-fibre
/foam/glass-
f
ibre.
Rear
web
of
glass-fibre.
ribless
structure.
AILERCN:
undivided
at
20
%
of
chord,
mass
balance.
suspended
on
Spoints,actuated
in
one
point.
Glass-fibre
structure.
AIR BRAKE:
Plates
of
duralurainium
sheet
extended
on
upper
surface
only
equipped
with
caps
fitted
to
wing
contour.
FUSELAGE
integral
with
fin,
glass-fibre
structure.
The
central
part
comprises
the
steel
framework
to
which
the
wings
and
undercarriage
are
attached.
UNDERCARRIAGE:
fixed,
no
shock
absorber.
Wheel
of
~
400x140
size
with
disc
brake.
Tu.be
pressure
of
0,15
MPa
Fixed
rear
wheel
of
~
200
diameter.
The
wheel
brake
and
air
brake
controls
are
independent.
COCKPIT
covered
with
one-piece
cenopy
aide
opened.
Nearly
sitting
pilot•s
position,
adjusted
on
ground
by
means
of
folded
pillow.
Pedals
adjusted
in
flight.
Instrument
panel
supported
on
column.
Issue
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1984
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SZD
'51-1
FLIGHT
MANUAL
Page:
a
Adjustable
air-conditioning.
airflow
directed
on
canopy
front
part
and
pilot•s
face.
TAIL
UNIT:
·T·-arrangement.
Rudder.
stabilizer
end
elevator
of
glass-fibre
structure.
Elevator
divided
on
two
parts,
each
one
suspended
on
three
points.
Both
elevator
half~
are
equipped
with
fixed
glese-fibre
tabs
to
increase
the
hinge
•oment.
Tha
rudder
covered
with
fabric,
mess-
balanced,
suspended
on
two
points.
EQUIPMENT1
instruments
/listed
in
item
1.3/
sanitary
installation
and
first-aid
kit.
The
aerial
incorporated
into
fin
structure
to
enable
the
use
of
transcei~er.
HOOKS:
The
glider
is
equipped
with
front
and
bottom
hooks
in
one
of
the
following
combinations
/ace.to
user's
order/:
a/
Both
hooks
of
SZD-III
A
56c
type
without
the
self
-
releasing
mechanism.
or
bf
Front
hook
of
TOST
E72
type
without
the
self-releasing
mechanism
and
bottom
hook
of
TOST G72
type
with
the
self-releasing
mechanism.
The
kind
and
type
of
hook
is
related
on
the
placard
in
cockpit.
The
hooks
are
accesible
from
cockpit:
the
fror1t
::ine -
when
the
instrument
panel
and
its
column
are
removed,
the
bottom
one
-
when
the
seat
pan
is
removed.
Both
hooks
are
released
by
means
of
pulling
the
common
control
hand-grip.
When
the
hand-
grip
is
released
the
hooks
are
closed
due
to
the
return
spring
action.
When
wj,1,h-launched
using
the
bottom
hogk
of
TOST
type
with
self-releasing
mechanism
Issue
I -
Dec.
1984
SZD- I
<il-1
FLIGHT
MAAUAL
the
glider
releases
the
cable
auto111aticaly
when
the
cable
reaches
the
maximum
release
angle.
MOVABLE
EQUIPMENT:
assembling
lever,
screwdriver.
wrench
for
wheel
brake
adjustment
canvas
cover
for
canopy.
1.2.
Main
technical
data
-------------------
Sp;in .............................
15,00
'"
length
·~·····-····················
6•69
~
Height
• . • • •
..
. . • • • . . •
..
• .
..
• • . •
...
• • • .
..
1.57
m
Dihedral
of
wing
..••••••.••.••••••
3°
Wing
area
•..•••.•••.•.•••....•.•••
12.s1
m2
Aspect
rat
lo
.......................
18
Root
chord
.••••••••.••••••••••••••
1,115
m
Hean
Standard
Chord
• . . • • • • • • • • • • . •
0,88
m
Wing
section:
l'/ortmann
502-196
//502/1-158
Mass
of
emotv
alider
with
standard
equipment
is
441
+
529,2
lb
see
Fig.
9
All-vp
mass
...................
~
...•
;.~;:~.
M.
i Ill i I
05
in
mu
w
ng
mass
••••.•..••••••••.
The
installation
comprises:
-
1nstru~ent
panel,
837,9
lb
231,5
lb
-
total
pressure
heed
located
at
fuselage
nose,
- 2
static
pressure
ports
located
on
front
fuselage
part,
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I -
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/l.000/466/82:
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o;1
-1
FLIGHT
MANUAL
-
ducts.
drainage
units
and
four-way
connector.
Pogo:
1
()
-
nest
for
the
additional
pressure
head
on
the
f
J.n.
The
instrument
panel
is
attached
to
its
column
by
~eans
of
screw
located
in
face
wall
of
panel
end
shielded
on
top
with
the
cover
fixed
to
the
cockpit
board.
The
"standard"
equipment
comprises
the
following
instruments:
-
airspeed
indicator
PR-250-S
-
altimeter
W-10S
or
W-125
-
variometer
WRS-50
with
KWEC-2
compensator
and
bottle
-
slip
and
turn
indicator
EZS-3
-
Compass
BS-1
The
place
for
installation
of
special
instruments
provided
on
instrument
panel
and
on
its
column.
2.
OPERATION
LIMITATIONS
•csaEasa•a••a••a~•o•••
1.
Maximum
permissible
mass
of
empty
glider
with
standard
equipaent
.•..........•.•.•..
.
1:t'~
529,2
lb
2.
Per11issible
loading
mass:
•••••
H·c.
308,7
lb
where:
mini11um
cockpit
load
···~·
121,3
lb
maximum
cockpit
load
••••
,
10
i'.~
242
,6
lb
3.
Maximum
all-up
mass
•••••••••••
"f~K'a
837,9
lb
4.
Limit
load
factor
..••••••••
+5.3g;-2,65
g
5.
Ultimate
load
factor
•••••..
+7.95g:-3,97g
Issue
I -
Dec.
1964
szo-
51-1
FLIGHT
MANUAL
Page:
11
6.
Distance
of
c.g
of
empty
t
glider
with
standard
equip•ent
aft
of
wing
root
see
Fig'
leading
edge
/glider
in
attitude
ace.to
item
6
of
Technical
Service
Manual/
7.
Allowable
range
of
e.g.
location
in
flight
referred
to
Hean
Standard
Chord
6.
Loading
plan
22.7
to
44.9
per
cent
of
Hean
Standard
Chord
Correct
val11e
and
location
of
load
masses
is
listed
on
LOADING
PLAN
placard
/see
page
53/.
N 0 T
ES:
l.
The
location
of
balancing
mass
B
in
instrument
panel
for
pilots
of
mass
below
125,7
lb
is
not
obligatory,
when
the
glider
is
equipped
with
RS-6101
transceiver
or
TA-03A
oxygen
equipment
or
additional--
equip11ent
of
mass
more
than
2,2
lb
in
instrument
panel.
2.
In
case
the
oxygen
bottle
is
installed
on
the
framework
of
central
fuselage
part
/ace.to
Annex
No
2
to
this
Manual/
the
•aximum
allowable
additional
loading
mass
8
in
instrument
panel
is
11
lb
in
the
full
range
of
pilot
•s
mass
up
to
242,6
lb
3.
Installation
of
load
E
other
than
oxygen
bottle
of
TA-03A
equipment
on
the
central
fuselage
part
framework
should
be
accepted
by
the
Authority.
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1964
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FLIGHT
MANUAL
Page:
51-1
12
,__:.._
_
__,'-----------------------'--~---!
4.
When
flying
without
the
parachute
the
additional
beck-cushion
of
~in
9
cm
thickness
/when
pressed/
should
be
used.
5.
In
case
the
glider
is
loaded
in
way
other
than
stated
in
Loading
Plan
/e.g
for
pilot's
mass
other
than
allowable
cockpit
mass/
the
mass
value
of
all-up
glider
and
e.g.
location
shall
be
defined
by
weighing
the
glider
with
full
load.
9.
Flight
li~itations
£~_!!!!:!E!!!!g~
knots
a/
Take-off
and
aerotowed
flight
up
to
• • • • • • • • • • • • • •
VT
"81
knots
b/
Winch -
launching
with
airspeed
up
to
• • • • • • • • • • • •
Vw
"70,2
knots
c/
Diving
with
airspeed:
in
smooth
air
••••..••••.
in
gust
conditions
•••••.
d/
Extending
of
and
flight
with
airbrake
extended
VNE'
118,8
knots
VB.
83,7
knots
in
smooth
air
.••••••••••
VNE•118,8
knots
in
gust
conditions
• • . • • •
VB=
83,7
knots
~/
Manoeuvring
airspeeds
up
to
. • . • • • • • • • • • •
..
• . • • •
VA=
83,7
knots
f/
Maximu~
load
factor:
nA
•
+5,3
g
at
airspeed
••
VA=
83,7
knots
g/
Maximum
load
factor:
n0 •
•4,2
g
at
airspeed
••
VN{i118,8
knots
Issue
I -
Dec.
19B4
szo- I
51-1
-------~---~
FLIGHT
MANUAL
h/
Asroba
tic
manoevv
res:
•
looping
•
stall
turn
Page:
13
•quick
half-roll-half-
-loop
,
spiral
•
spinning
i/
Altitude
flying
allowed
providing
that
the
glider
is
equipped
With
efficient
oxygen
equipment.
j/
Bungy
take-off
allowed,
10.
Restrictions:
The
glider
is
not
allowed
for:
-
night
flying
-
winch
-
launching
on
front
hook
11.
Additional
statements:
a/
When
aerotowing
the
cable
safety
link
of
+
690-
10
%
daN
shall
be
used
/Standard:
BN-65/3833-45/
b/
Before
the
first
flight
the
pilot
should
be
familiar
with
Flight
Manual.
c/
When
towed,
the
flight
below
the
airplane
level
is
not
recommended
since
the
cable
contacts
the
fuselage
surface.
d/
Flying
in
ice-condition
should
be
limited
only
to
unavoided
cases.
e/
At
VNE=
118,8
knots
airspeed
the
rudder
and
aileron
deflection
is
allowed
as
1/3
of
full
deflection.
The
small
gentle
elevator
deflections
are
allowed.
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1984
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FLIGHT
MANUAL
Page:
51-1
14
f/
At
VA
•
83,7
knots
airspeed
the
full
control
surfaces
deflection
is
allo_.ed.
3.
PERFORMANCES:
/fig.
4/
-------------
GLIDER
Al
all-up
111ass
of
~
573.3
lb
I
734,3
lb
837,9
lb
At
mass
4,3
lb/ft
2
5,5
lb/ft
2
6,2
lb/ft
2
loading
of
Minimum
sinking
speed
...........
105ft/min
112,7ft/min
124,4ft/min
at
airspeed
of
..
33,5knots
37
,8
knots
41,8
knots
Maximum
L/O
.....
35
35 35
at
airspeed
of
..
37,Bknots
43,2
knots
45,
9
knots
Sinking
speeds
at
airrspeeds
of
v
ft/min
ft/min
ft/ain
knots
54,0
209,9
186,6 175,0
59,4
254,7
225,5 210,0
64,8
305,2
266,3
248,8
70,2
371,3
311,0
291,6
75,6
447,1
365,5
340,2
81,0
534,6
431,6
398,5
86,4
630,0
519,0
470,4
91,8
734,8
606,5
548,2
97,2
882,6
699,8
631,8
Issue
I -
Dec.
1984
~
-
·-------~---
.....
szo-
51-1
FLIGHT
MANUAL
4.
OPERATION
OF
GLIDER
aaa2aa=•••aD••=••=•
4.1.
~r~:!!!9~!-!~~P~S!!~~
Paga:
15
Before
the
flights
it
shall
be
inspected:
-
integrity
of
structure
and
covering~
•
securing
of
assembling
elements
anJ
control
system
joints.
-
operation
of
control
systems.
-
operation
of
hooks/front
and
bottom.
if
installed/.
-
undercarriage
condition.
rollability
of
main
and
tail
wheels,
operation
of
wheel
brake,
-
air
pressure
in
tube
and
tyre.
cleaness
of
undercarriage
housing,
-
pilot's
safety
belts,
-
total
and
static
pressure
ports
/clean
if
necessary/,
-
operation
of
instruments.
4.2.
2e~re~!2~~-~~!2r~_f!~!~g
4.2.1.
Opening
and
locking
of
the
canopy
The
Canopy
is
side
opened
and
fixed
on
two
hinges
at
right
board.
In
emergency
the
hinges
are
released
when
the
emergency
jettisoning
levers
are
moved
forwards
/red
ball
at
right
side/.
On
left
side
opposite
to
emergency
jettisoning
lever
is
situated
the
canopy
locking
lever
accesible
from
outside
through
the
window.
Issue
I -
Dec.
1984
Druk:OWPT
Diebko-Biala
/l.000/466/82:
szo-
51-1
FLIGHT
MANUAL
Page:
16
4.2.2.
Inserting
of
towing
cable
/1/
Pull
the
releasing
grip
full,
/2/
Insert
the
small
ring
of
cable
end
into
the
hook
and
release
the
grip.
/3/
CHECK
THE
CORRECT
CABLE
LOCKING PULLING
IT
SEVERAL TIMES I
Two
hooks
can
be
installed
on
the
glider
/see
page:
8/.
4.2.3.
Transportation
on
airfield
The
glider
with
locked
canopy
can
be
towed
by
motor-car
or
tractor
with
speed
up
to
5,4
knots
The
towing
rope
not
shorter
than
4
m.
NOTE:
THE
~IANOEUVRING
IVITH
GLIDER
ON
MUD
STICKY
GROUtJO
ESPECIALY
BACK.<AROS
MAY
CAUSE
THE
MUD
TO
JAM
THE
TYRE
TO
FENDER
ANO
RESTRICT
THE
WHEEL
ROLLABILITY.
CLEAN
BEFORE TAKE-OFF !
4.2.4.
Anchoring
of
glider
1.
Put
the
glider
into
position
to
have
the
side-back
wind
2.
Anchor
the
glider
on
the
following
points:
Ninq:
the
wing
tip
directed
toward
wind
should
be
supported
on
30-50
cm
height,
wrap
with
seat-cushion
and
attache
with
anchoring
cord
to
the
picket
or
anchor-rod
in
distance
of
about
50
cm
from
wing
tip.
.
Issue
I -
Dec.
1984
szo-
51-1
F'
LIGHT
MANUAL
Page:
17
Fusela~e:
Fix
the
tail
part
to
the
picket&
or
anc
or-rods
sticked
to
ground
on
both
sides.
Wrap
the
fuselage
tube
near
the
fin
with
anchoring
cord.
Avoid
the
contact
of
pickets
with
fuselage
surface.
Anchor
the
fuselage
front
part
by
means
of
front
or
bottom
hook.
The
aileron
and
elevator
shall
be
immobilized
by
means
of
right
pilot•s
back
belt
joined
with
right
abdomen
belt
on
the
control
stick
hand
grip.
Rudder:
should
be
immobilized
by
means
of
clamp
/for
fin
and
rudder/
made
of
two
wooden
slats
joined
on
ends.
Air
-
brake:
should
be
extended
and
secured
by
means
of
immobilizing
the
hand
grip
in
cockpit
using
the
left
pilot•s
back-belt.
4.2.5.
Procedures
with
wetted
glider
In
respect
to
structure
/glass-fibre/
the
glider
is
moisture
and
meteorological
influences
resistant.
In
case
of
heavy
wetting
e.g.
landing
on
water
or
long
standing
on
field
when
country
landed,
the
structure
inside
should
be
ventilated
by
means
of
opening
the
inspection
holes.
canopy
and
extending
the
air
brake.
When
driec
the
glider
should
be
wiped
with
a
flannel.
4.2.6.
Drainaging
of
instrument
pneumatic
installation
After
flight
in
prolonged
rain
/or
in
cloud/
it
is
necessary
to:
1.
Dry
the
drainage
units
and
remove
the
drain
plugs.
Issue
I -
Dec.
1984
Druk:OWPT
Diebko-Biala
/l.000/466/82:
szo-
51-1
FLIGHT
MANUAL
Page:
18
/2/
Disconnect
the
ducts
of
total
end
static
pressure
out
of
the
instruments.
/3/
Slow
through.
if
necessary,
the
ducts
of
total
and
static
pressure
heads
/by
means
of
pump
for
inflating
the
wheel
tube/.
NOTE: i3EFORE
BLOWING
THE
DUCTS
BE
SURE
THAT
THE INSTRUMENTS ARE CORRECTLY
DISCONNECTED
OUT
OF
THE
BLO.VED
PART
OF
INSTALLATION -THE
DANGER
OF INSTRUMENT
DAMAGE.
/4/
Screw
in
the
drainage
unit
plug,
connect
the
installation
end
check
the
tightness.
4.2.7.
Slip
and
turn
indicator
supply-
inserting
of
batteries
Electric
slip
and
turn
indicator
is
supplied
with
direct
current
of
4,5
Y
taken
from
three
round
batteries
of
R20
type.
The
batteries
are
contained
in
round
housing
which
is
inserted
into
the
bracket
on
right
side
of
instrument
panel.
NOTE:
THE
NEGATIVE POLE
OF
THE BATTERY SET
SHALL
BE
DIRECTED
AHEAD
!
NOTE:
THE
USED
BATTERIES
SHALL
NOT
BE
LEFT
IN
THE
NEST
!
4.3.
~!!2l_!~-f~S~E!!
The
cockpit
allows
for
pilots
up
to
1.95
~of
height
with
back
parachute.
To
adjust
to
pilot•s
position
the
glider
is
equipped
with
two
part
folded
cushion
Issue
I -
Dec.
1984
----
----
--------------------~-----.
szo-
51-1
FLIGHT
MANUAL
Page:
19
of
various
thickness.
The
different
position
of
the
pillow
on
seat
or
back-reet
acc.
to
Fig.8
ensures
the
multi-step
adjustment
of
sitting
position.
For
extremely
high
pilot
the
folded
cushion
is
stored
behind
pilot's
back-rest.
The
pilot's
position
should
be
adjusted
so,
to
allow
for
easy
acces
to
hook
releasing
handle
and
all
control
levers.
When
flying
without
a
parachute
the
additions:
cushion
of
thickness
no
less
than
9
cm
in
pressed
condition
should
be
used.
Upholstering
the
seat
pan
with
rubber
avoids
the
back-slip
of
pilot
when
winch-launched.
The
pedals
are
adjusted
in
flight
/5
location~/.
Pulling
on
the
brown
hand-grip
/at
right
side
of
instrument
panel
column/
the
pedals
can
be
moved
back
or
when
pressed
with
both
legs
can
be
moved
forwards.
When
the
leg
force
is
released
the
latch
locks
the
pedals
in
selected
location.
The
control
systems
of
control
surfaces
and
air
brake
are
operated
conventionaly.
The
wheel
brake
lever
is
located
on
air
brake
control
lever.
The
spring
trimming
device
is
actuatedy
by
means
of
hand-grip
on
the
left
board.
Operation
of
this
device
acc.
to
Fig.
10
is
the
following:
-
Press
the
hand-grip
/release
the
locking/
and
put
into
the
desired
location,
than
LOCK
/pull
upwards/.
The
canopy
opens
when
the
left
lock
is
released
/red
hand
grip
put
forwards/.
In
full
opened
position
the
canopy
is
retained
by
means
of
limiting
cable.
Issue
I -
Dec.
1984
Druk:OWPT
Diebko-Biala
/l.000/466/82:
szo-
51-1
FLIGHT
MANUAL
4.4.
Procedures
before
take-off
--------------------------
Page:
20
/1/
Check
the
completation
of
bo2rC:.
equipment
/glider
log-book.
Flight
Manual
tools.
anchoring
facilities,
covers,
rope
for
ground
towing/.
/2/
Check
the
parachute
rubber
tension
members
and
put
the
parachute
on
beck.
/3/
Adjust
the
cushion
and
take
place
in
the
cockip,
adjust
the
pedale
and
fasten
the
safety
belta.
/4/
Check
the
full
movements
of
control
surfaces
and
air
bra~e.
Adjust
the
trimming
spring
handle
on
position
from
"6"
/for
light
pilot/
to
"8"
/for
heayy
pilot/
counting
from
front.
For
winch
launching
from
"6''
to
"8"
respectively.
/5/
Check
the
operation
of
slip
and
turn
indicator.
/6/
Close
the
canopy
and
check
the
good
locking.
4
.5.
f~~~~~!~~09
In
school-flight
the
long
towing
cable
should
be
used
/minimum
40
m/.
Before
take-
off
adjust
the
trimming
spring
handle
into
position
from
"6"
/light
pilot/
to
"8"
/heavy
pilot/
counting
from
front.
During
ground
run
till
to
airborning
control
the
glider
to
roll
on
the
main
wheel.
The
recommended
aero-towing
airspeed
when
climbing
is
no
less
than
54
knots.
Issue
I -
Dec.
1984
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