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.:
Druk:OWPT Diebko-Biala /l.000/466/82:

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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

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LIST OF REVISIOOS
NOTE:
Place
where
the text
has been
revised
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•arked
with vert ica 1 line on
the
left
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of
text
and with the
ite111
of
revision.
Item
Paga
REVISION
Date
Signature
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Druk:OWPT Diebko-Biala /l.000/466/82:

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Item Page REVISION
Date Signature
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CONTENTS
1. DESCRIPTION OF GLIDER
1.1. General description
1.2. Main technical data
.............
.............
.............
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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 I - Dec. 1984
Druk:OWPT Diebko-8iala /l.000/466/8l.

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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
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1. DESCRIPTION OF GLIDER
a•ma•m••••••••••a•••u•a
1.1. ~!~~r~!-~~~sr!e!!2~
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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 I - Dec. 1984
Druk:OWPT Diebko-Biala /l.000/466/82:

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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

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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,
Ieeue I - Oec. 1984
Druk:OWPT Diebko-Biala /l.000/466/82:

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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