Pzl bielsko Szd-50-3 puchacz Technical specifications

TWO-SEATER

SZD-50-3

"PUCHACZ"

GLIDER

F L I G H T M A N U A L

Issue

3

~

Dece~ber

1985

Thia

instruction

is

the

part

of

the

Airworthiness

Certific~te

of

the

glider

of:

Serial

No

E:~Q~3

Reg.No

••••••.•••••

This

ls

the

translation

of

the

original

Polish

Manual

approved

by

Central

Ad~inistretion

of

Civil

Aviation

/pages

1-3

to5-f7

I

Date

Translated

by.

Wieslaw

Stafiej.

o.sc.

Urul<.:OWPT

Uiclako-Diala

/Z000/466/'dZ

r -

1-2

-

50-3

FM3 -

1-3

-

C 0 N T E N T S

1

i>

LIST

OF

REVISIONS

2.

OPERATI~~

LIMITATIONS

2.1.

Permissible

airspeeds

2

•.

2.

Limit

load

factors

2.3.

Colour

markings

of

airspeed

indicator

dial

2.4.

Towing

cable

safety

link

2.5.

Restrictions

2.6.

Masses

2.7.

Permissible

range

of

e.g.

location

2.a.

Table

of

weighing

the

glider

2.9.

Graphical

checking

of

c.g.location

2o10oPlacards

and

inscriptions.

30

PERFORMANCES

4a

GLIDER OPERATION

4o1.

Pre-flight

inspection

4.2.

Cockpits

and

their

arrangements

4.3.

Service

before

take-off

4.4.

Controlling

4.5.

Aerobatics

4.6.

Danger

and

emergency

conditions

4.7.

Assembling

and

disassembling

t.;__~~--------------------------------------------~-

0 r

uk:

OW

PT

Bielako-Diala

/

Z.000/466/82.

-

1-4

-

5.

DRAWINGS

AND

DIAGRAMS

1.

SZ0-50~3

"PUCHACZ"

glider

2.

Instalhtion

of

board

instruments

Glider

with

two

instrument

panels

2a.Instalhtion

of

board

instruments

Glider

with

one

instrument

panel

3.

Wiring

diagram

of

electric

turn

indicator

4.

Speed

polar

5.

Wings-to-fuselage

assembling

6.

Assembling

of

hori%ontal

tailplane

7.

Colour

markings

of

airspeed

indicator

dial

APPENDIX

Individual

loading

plan

50-3

FM3

50-3

FM3 -

1-5a

-

1_ LIST

OF

REVISIONS

2

NOTE;

The

place,

in

which

the

text

has

been

revised

0

is

marked

with

vertical

line

on

left

side

of

text

and

with

the

number

of

revision.

l I

1

2-3V1385

I

1 J

I

2-4

I

l l

l

2-5

t

I i

I

6-2

!

•

I

1

l

I

l

I

J

I

'

•

l

'

J

l

I

1

t

I

l

I

,

I

l

I

r

I

'

i

I

i

1

a

I

a

Replaced

with

~

!

2

-3a/1385,

2-4a,

•14 "09. 1

I 2 I

2-5a

and

6-2a.

1 199 • a

I 1

I I

I

l

I

a

I

•

I

J

I

•

I

l

I

Q

;

I

t

I

a

I

l

I

t

v

l

I

2

j

Druk:OW

PT

IHc:lsko-lliala

/

2.000/

466/

'd2.

-

1.-6

-

===r-.::r:~·=::i:i:.::~:=:::::=

=s.-;:::=-:::::.·:::r::=

==

:::::r.c:::~;::::

:::-::::::::c-:;i:=-=::=:.::::.;!:n: =:::::r.r:

Item

:

Page

~

Revision

:

Date

:

Si.gnat

u

re

:i::u:::

~

:::u::t r

=-QI.

:a

a:n;:~:::

:i::n:..;:::::;:

J:;f

::t

:=c

:i;;

m =

cc:~

:a·=

:::I

:n

::::

'i·=:

zr.

::.::i

::

=··=r

ta

.t::n:::::::::::::::.:::::::::

·:o

~

I I l I

I i ! I

I 1 J I

& t I I

1 I I I

I I I t

1 r a r

I I & I

f I l l

I J l I

I I : I

J l i I

l I I J

I I t l

I l l 1

s r ; 1

' 1 ' '

I ! 2 l

! t l I

I I I I

l l J J

I i I I

I f i I

I I I l

J I a I

l I I J

I I

~

l

J l J '

I I ' I

I I 8 I

I l l I

I I l I

I J I 1

I I D i

I l I f

I t I I

1 I 3 i

I I I I

I E I l

I I I I

; I I I

I I I I

I l I I

l i • J

I I 9 I

I I I I

I I l J

I I I I

I t l l

t I I I

I t I I

I I D I

I J B I

l f i I

I I

~

I

1 1 : I

1 l ! I

I I ' I

! I i I

J • ' J

I I 1 J

! ; t I

50-3

FM3

50-3

FM3 -

2-1

-

2.

FLIGHT LIMITATIONS

_._.

____

_.

..............

_______

...

2.1.

Parmiesibl!

air!peeds

IAS:

kts

VNE

-

max.permissible

airspeed

in

smooth

air

116

-

~ax.perNiseible

airspeed

in

gust

conditions

-

~ano~uvring

airspeed

/speed

of

full

control

surf

ace

deflection/

-

ma~.permissibla

aerotowing

airspeed

-

max.permissible

winch

launching

airspeed

-

maxopermiasible

airspeed

for.

extending

and

flight

~ith

81

59

airbrake

extended

116

~

~ax.permissible

airspeed

for

inverted

flight

/in

s~ooth

air

only/

97

2.2.

Limit

load

fsct~rs

-

positive

• • • • • • • • • • • • • • • • • •

-

negative

•••

0

•••

.,

••••••••••

+

5,3

g

-

2,65

g

-

2-2

-

2.3.

Colour

~arkings

of

airspeed

indicator

dial

v

51

/stalling

speed/

radial

green

line

at

v

51

7 v8

/normal

operation

range/-

green

kts

38

ere

at

from

38

to

06

v8-VNE-

higher

attention

range/yellon

arc

from

86

to

116

VNE

radial

red

line

at

2.4.

!owi~g

cable

safety

link

The

safety

link

of

ultimate

of

1520

lbf.S !

10

%

should

be

on

the

toning

cable.

2.5.

Restrictions

116

stranoth

-

installed

-

SOLO-FLIGHT

ALLOWED

C~

THE FRONT SEAT J

ONLY.

-

GLIDER

NOT APPROVED FOR

NIGHT

FLYING

-

FLYING

UNO.ER

ICING

CONDITIONS

N01

RECOMMENDED

c:.

WINCH

LAUNC.YING

W~ITH

C.G.

HOOK ONLY

-

INVERTED

FLIGHT,

ROLL

AND

ASSOCIATED

AEROBATICS ACC.

TO

ITEM

4.5.2.

ALLOi!ED

IN

THE

SMOOTH

AIR

ONLY

AND

WITH THE

FLOOR BELT

OF

PILOT'S

HARNESS

FASTS~BJ

FLICK

ROLL

ALLOWED FOR

TWO

PERSDUS

CREW

ONLY.

WHEN

PERFORMED

BY

OCCUPANT

OF

REAR

SEAT THE

REAR

INSTRUMENT PANEL

IS

OBLIGATORY.

50-3

FM3

50-3

FM3 -

2-3a/1385

-

2.6.

Masses

kg

-

Max.permissible

empty

glider

mass

with

standard

equipmentxf

••••

:z

I

-where

the

mass

of

fuselage

and

tail

unit

I without

the

moveable

a balancing

weights/

is

, ·

..

• • · • • • •••••

-

Max.permissible

load

mass

/see

page

I

-t1Bx.

permissible

load

mass

in

the

luggage

compartment

/see

page

I

-

Max.per~iseible

load

mass

on

front

seatin:

370

193

-

normal

flight

•••••••••••••••••

110

-

inverted

flightxx/

two

persons

crew

••••••••••••••

95

-

Ma~.permissible

all-up

mass

in

-

normal

fli9ht

•••••••••9••••••

570

-

inverted

flight

···~···········

540

..

..,eD

..........

flDa:a.-cas..

.........

_

-----

--..

......

__

_

x/

The

standard

equ1pment

consits

of:

1.

Instrument

panel

/at

front

seat

only/

with

airspeed

indicator,

altimeter~

variometer

with

compensatorg

slip

and

turn

indicatorg

compass.

2.

Two

towing

books

of

SZD-III

or

TOST

type.

3.

Two

sets

of

four-belts

pilot•s

harness.

4.

Two

sets

of

seat

pillows.

5.

Assembling

wrench

6.

First

aid

kit.

xx/

Inverted

flight,

the

aerobatic

manoeuvres

listed

in

item

4.5.2.

includedo

CJrui<:OW

PT

liielako-Biala

/ 'l..000/

4bb/

H2

-

2-4a

-

LO~D

IN

LUGGAGE

COMPARTMENT

---~-~-~-~---~~~~~---~~-~--

Max.

load

in

luggage

compartment

is

20

kg.

The

above

load

comprises

the

fixed

equipment

/battery,

transceiver

block

etc./

and

a

hand

luggage.

The

mass

of

luggage

uniformly

distributed

in

the

compartment

does

not

contribute

to

the

c.g

location

of

glider

in

flight.

The

hand

luggage

s~ld

be

immobilized

by

means

of

cord

or

belt

using

the

six

removable

lugs

on

compartment

floor.

2.7.

Allowed

range

of

c.g.location

/in

respect

to

wing

root

leading

edge/:

-

empty

glider

without

the

balancing

weights:

o.610

to

0,635

m

-

glider

in

normal

flight:

09

092

to

00

333

m

what

corresponds

to

the

range

of:

23,5

to

44,0

per

cent

of

M.SoC.

-

glider

in

inverted

flight:

o.133

to

0,333

m

what

corresponds

to

the

range

of:

27,0

to

44,0

per

cent

of

M.s.c.

-

for

performing

the

flick-roll:

0.133

to

0.204

m

what

corresponds

to

the

range

of:

27.0

to

33

00

per,cent

of

M.S.Co

-NOTE;~-

To

defirie-th-e

11

r~iaximum

permissible loading mass

11

use

the

formulas given

in

item

2

..

8.

, .

Example:

The

empty

glider

with

standard

equipment

2 /without balancing weights/mass

is:

Qc=370kgi:

Both wings

mass

is

Q

9=172 kg .According

to

the

formula:

[763+Qs-2Qcl

/item

2.8/maximum

loading

mass

~

763+172-740=~kg

50-3

FM3

50-3

FM3

2.8 ALLOWABLE WEIGHTS AND PILOT ARMS

FRONT SEAT:

REAR SEAT:

MAXIMUMPILOT

PILOT ARM

MAXIMUMPILOT

PILOT ARM

110 kg

-1339 mm

110 kg

-247

mm

NOTE! Pilot arms assume a 70

mm

thick cushion

or

parachute

MAXIMUM

WEIGHT OF NON

FL

YING PARTS: 398 kg

MAXIMUM

BAGGAGE Al.LOWANCE: 20 kg

2.9 PLACARD REQUIRE:MENTS

NORMAL CATEGORY:

(1) PLACARD :tvflNIMUM SOLO PILOT WEIGHT

WITHOUT REMOVABLE BALLAST BARS FITTED.

(2) PLACARD :tvflNIMUM SOLO PILOT WEIGHT

FOR

EACH OF 2 REMOVABLE BALLAST BARS WHEN

FITTED

(3) PLACARD

FOR

FRONT AND REARPILOT

CO"MBINATIONS

AEROBATIC, INVERTED FLIGHT:

(1) PLACARD MAXIMUM SOLO PILOT WEIGHT.

(2) PLACARD

FOR

FRONT AND REAR PILOT

COMBINATIONS

10 August, 1994 GFAAD 407 ISSUE 1

2.9 PLACARD

REQUIRE~ffiNTS

{cont)

FLICK

ROLL

(I) PLACARD

FOR

FRONT AND

REAR

PILOT

CO:MBINATIONS

In

this case the AFT CGLIMIT is moved forward making

it most unlikely that a rear pilot can be carried.

2.10 WEIGHING THE GLIDER

2.11

The glider should be weighed

to

scheme 3

on

GFA

weighing form

WI

and the pilot limits computed on form

W2.

Both

of

which should be glued into the back

of

the

log book.

SMAPLE PLACARDS

NOR.i\.1AL

CATEGORY VH-###

FRONT

REAR

kg

.

nun

max

45

75

110

50

60

110

Minimum

Solo

70kg

55

40

110

Maximum

Solo

110

kg

60

25

110

Max fuse load

195

kg

65

10

110

70

0

110

75

0

110

80

0

110

85

0

110

90

0

105

95

0

100

0

95

105

0

90

110

0

85

18/5/90

~

..

0

Ji

"Q

..

"

-

.

,..

0

I

Cl

..

;;

......

....

0

...

.t

,.

·~

11

Ul

3:0

V-l

I

VI

r=coccc~oco=~oa~~~uc~=~=uooao~ocoronoocaccac9=0~c~cmac~~~~o~occ~~mcol

:

Empty

glider

mnsn

with

standard

:

310

.3

: : D

L~~~=~~~~2--~J!l2

__

L_k.9~----------L-----~-~--J

__________

J____________!

I

,.

I I l I

t

Location

or

c

..

g

for

empty

glider1

1 ; r

'

\.Ji

th

a t onda

rd

a

quip

men t

in

~

0 '2 7 r : :

l

re

op

a c t t o r oa t

ch

o

rd

1a

ad

in

g 1 ' 6-J..;) · I 1 1

t t r a

on

L~~~~

__

-------

-~e-

_L!J!..l

_____

--

____

L

_tt·--

----

---

..

~-~

________

J_

__

,_·~-

c.-

__

.,.

__

:

I I A f S

1

Static

womont

of

rnaae

of

ernpty

r 1 1 1

I d d I 1 I

IN

1 g l 1 d

e1

r wi t h ot

an

D r e

qui

pm

e n t 1 2-3

6

/i

1 e 1 1

tin

respect

to

root

chord

r

1,1

1 1

IUl

0 f l f

ltn

1

leading

edge

1 1 i

.~

1

L

___

--

~g

-!:-t21.P_

--

~

_

-L~

g~

L_

--

...

_

..

_L

__________

J

_____

...

____

J_

___

~

_

....

____

:

I I k I

II

:

Maxis3+eQ~:e

2

~i;lo

loadikng

mass

*I

: AqB I : :

21r-------~----~-~-----L_]..l

_______

f----------~----------~----~-u-----:

1

Msx.parmiGeible

loading

moos

' 1 e 1

I

in

inverted

fliQht

"7

l 4b'8 : l l

~--Z~9._+_g§=-~~£-----a-L_kJJ_L

_______

L

...

-----~---J

___

c-

______

...,L.

____

o:»

_____

CJo~

l d l I I f I

Date,

_eignature

an

sea

of

1 ,

~

v

L:~~~~:2:~~-~~~~~~~~~~~~---------U~~~~V:

__

J

__________

L

__________

_1

21

7i}'

Q5-

mass

of.

bath

wings ; :''(-

Qc-

mass

of

empty

glider.

-

2-6

-

2.9.

praphical

checking

of

c.go

loc~tion

/see

diagram

on

page

2-11

f

Before

the

flying

day

or

before

the

every

change

of

loading

condition

the

e.g.

location

of

the

glider-in~f

light

shall

be

checked

acc.

to

the

following

procedure:

1.

Add

the

masses

of

-

empty

glider

m

0

/see

table

on

page

2-5

I

-

pilots

with

parachutes

m

1 + m

2

-

additional

equipment

and

balancing

weights

incorporated

m

3

/see

table

on

page

2-'7

I

The

resultant

mass

of

the

glider~in

f

light

mark on

the

vertical

axis

of

diagram

on

page

m m m

0 + m

1 + m

2 + m3

2.

Add

/algebraical,

respecting

the

sing/

the

mass

~oments

of:

-

empty

glider

M

0

/see

the

table

on

page

2-5

/

-

pilots

with

parachutes

M

1 + M

2

/see

tables

on

pages

2-9

and

2-10

/

-

additional

~quipment

and

balancing

weights

M3

incorporated

/see

table

on

page

2-7

I

50-3

FM3

50-3

FM3 -

2-7

-

~~===:~=====~=~========~~mqaamc==•=::P====~a~===

E q u 1 p m 6 n t

~

Mass

~

Moment

I

kg

I kgm

-------------------------1---------~----------

Ins

t

rument

panel

of

• ' _ 4

rear

seat

: 5 ,.Z :

-------------------------1---------r----------

, I

RS-6101-1

transceiver

1 7 ,,2 1 + 2

TA -

03-A

Oxygen

equipment

I I

+ 1

~~---~--~--~--~~~~~~-~--~~-~~-~~--~L~~-~---~--

1 I

1

balancing

weight

; 6 03 :

-11

~~~~-~-~-~-~~~~~~~--~~-~~J~~~-~-~~...J...~~~-~--~~

I t

2

balancing

weights

:

12,6

I

-22

--~~---~~---~--~~-~-~--~-j~-~-~~~~~~-~~--~~~~

I i

Snow-ski

installed

• 1

on

glider

f

11

"5 I -

o.3

-~~~;;~;:;;;,-:i;d-~~-;h:----1-~~-~----:--:~~-;---1

=~~:::::=:::~:::::::===~=j==~:~===Jn=====:====·

The

resultant

value

of

glider

mass-moment:

M =H0 + M

1 + M

2 + M

3 mark on

the

horizontal

axis

of

diagram

on

page

Druk:OW

PT

liiclako-13iala

/ ZOOO/

4.bb/

HZ

...

2-8

3.

From

the

points

marked

on

the

diagram

axes

on

page

16

draw

the

perpendicular

lines

to

the

axes

and

find

the

point

of

intersection

If

this

point

is

located

in

the

dashed

field

of

the

diagram

e.g.

is

in

the

correct

position.

If

this

point

is

located

out

of

the

dashed

field

the

e.g.

location

shall

be

corrected

with

the

balancing

weights

and

e.g.

location

checked

once

more.

50-3

FM3

c:

..

c:

,.,.

0

-·

"';

'O

>-!

.,,

Ul

3:0

'1-l

I

VI

Mass moment

of

pilot

/parachute

incl./

on

the

front

seat

in

respect

to

the

leading

edge

of

wing

root

chord.

M1

/kgm/

~

m=R=u=~u==~na=====~==ma~==mQ9~~~=,~u=~~=~m=~=~===~=~~=~mua~=~===mapcma=m$

:;

Pi

l t f

t...1

I d i I i I I I I I

~

0 0 mass

•·

1 I 0 11 I 2 D 3 9 4 v 5 I 6 ' 7 I 8 ' 9

~

/parach.incl/kg

1 1 a 1 1 ' 1 1 1 1

~

------------------t----i----t----t----1----~-----f-----~-----i-----~-----

~

50

without

pillow

I • a I I D

-70

I

-71

I

-72

I

-74

I

-75

g h

11

I D I G I I I I I I

":;;:-

Wit

pi

OW

I I B I I I

•741

-75

I

-76

I

-78

I

-79

~

------------------+----+----·----~----~----~-----~----~-----~-----~-----,

-;;-

i h .

11

I

77

G 78 I 7 I 1 t I I 8 I 6 I 8 I D

t>I

60

\.V

t

OU

t

pi

OW.

-a- I - 9 I

-s

I

-82

•

-83.

- 5 '

-a

I - 7 I

-89

with

pillow

•-81

•-82

'-84

I

-95

I

-87

I

-881

-90

'

-91

I

-92

I

-94

I I I I I i I I I I

------------------~----~----~----~----·----~-----T-----~-----1-----r-----

Q

wi

tht0ut

pillow

l-91

:-92

l-93

j

-94

I

-96

:

-97

l

-99

:

-100

:-101

:

-103

1~

7

with

pillotM

•

-95

•-97

•-98

I

-100

•-101

D

-102

B-104

a

-105

•-107

I

-108

u:

------------------t----t----t----~----i----~-----f-----~-----i-----~-----

80

without

pillow1-104u-106r-1011~1os1-11oa

-1111-113

1

-114

•·116

•

-117

. h 11 I I J I I I 0 I I I

-·~

--

~=

;_

-~=-

-~~---!=

=~

~-~

=~

:~i

::::i

=~~~

.::

!:~

-f-=

=~

~

i::

::

.-:..:~~~-J

=~==

J..:~~=-

I 8

I I t I I I I I I I

90

with

out

pillow:

-119:

,..120:-121:

-123

:-124:

-126

:-127

:

-129

:-130

:

-132

------------------~----4----·----~----~----~-----~-----1------~-----~-----

I I 1 I I I I I I I

100

without

pillow:-133:-134:-136:-137:-138:

-1401-141:

-142

:-144

f

-145

.....

-----

...

#

....

--.

..

-.-~

........

~-----..&.

.....

---J.

..,

....

-L

....

...,...,

-""".,.

....

..,

~

...........

A?l-.t

------'--

..

--

..

J--.

..

--1--.

..

oit--

I I I f B I I I I I

110

Without

pillow•-1451

I I I ' I I I

I I I 1 I 1 I I I I

a

Q'

mmi

m.m

i:i

as

eta

a::ar

•am•

aa

L

ma:c

JQ!

r.ri:a

m:a

bn

c

:m:az~

t:s:::i

~:iz

J.i.i

ci::o

=J

i:aia:::

ntn

lrm::a

wi:arl=

:rm

:i:rm:a Jr::s.mss =

:A:u

====

Mass moment

of

pilot

/parachute

incl/

on

the

rear

seat

M

2

/kgm/

aaa~mnm1=mq~ama"=m=r•=a=y====r~===ar~==n,maa~,a~=~~~-~~=~=====y~m=~=r~==~·

Pilot

a f

mass

M

2 : 0 : 1 : 2 : 3 : 4 : 5 : 6 I 7 : a : g

Ipa r a

ch

•

inc

1

/kg

1 1 1 1 r r a 1 1 1

~~~~---~-~-~~~--~~r~~-~+-~-~T•~-~-~~~~~~---~~--~~-t-----~-~-~~~--~--~---~-

50

without

pillow:

: : : : f

-13

;

-13:

-14:

-14

~

-14

With

pillow

I I I 8 I '

-17

I

-17•

-181

-18

I

-18

------------------~----+----~-----~----~----4----+----~-----~-----:------11

60

without

pillow•

·14'

-14'

-141

-14'

-15

•

~15'

-15'

-15

I I I I I I I I 1 I

with

pillow

I

-181

-18•-18

I

-181

-191

-19

I

-191

-19•

-19

I

-20

------------------t----t----t-----~----1----1-----r----i-----~-----r-----

~

70

without

pillow1

-15•

-151

-15'

-151

-15

•

-15

1

-15

•

-15•

-15

1

-15

""""

· h

11

I 8 I I I I a I I I

Wl.

t

pi

OW a

-20

f

-201

-20

I

-201

-20

I

-20

I

-211

-21

I

-21

I

-21

0

------------------t----t----t-----~----7----i----+----~-----i-----~-----

ao

without

pillow1

-151

-161

-16.

-161

-16•

-16'

-16

with

pillow

:

-21:

-21

I

-21

l

-21:

-22;

-22

8

-22:

-22

i

-22

11

------------------t----t----t----~~----1----1-----t----1-----i-----r-----

go

without

pillow

a

-161

-16

r

-16

v

-161

-16

a

-16

1

·16

1

-16

1

-16

1

-16

------------------f----f----t-----~----i----1----+----~-----~-----~-----

100

with

out

pillows

-151

-15

a

•15

o

-15

1

-15

a

-15

1

-15

1

-15

1

-15

8 I I I a I f I I I

------------------T----T----T-----r----,----,-----r----~-----~-----~-----

110

Without

pillow•

-1s• I I • I I I I I

I I I I I I a I a •

===~==a=•=~=Qtamm=L===m&=maa~~~naubmq=a&a=aadm=~m~amnua~aam==~mam==~=====

.,,

tn

3: 0

tH I

VJ

er-------~----~~----~~~~~--~~----~~~~~--~~--~--~~~~~--~~~~~~~~~----------------~~--~--------------

~

r.

~

0

~

GRAPHICAL

CHECKING

OF

IN

FLIGHT

C.G

..

LOCATION

~

Diagram

valid

for

gliders

of

maximum

allowable

empty

glider

mass

~

/with

standard

equipment/

of

370

kg

..

~

ffl !

;;·

;;-

.......

N

0

~

...

C1"

~

""

N 5

f

·e

-.I!\

-0

O>

<.o

CD

<

ru

J-l

f-'·

0.

-h

0 II

,

(Q

f-J

II

f-'·

0..

co

,

(/)

-h

~

,

0

3

II

,,

Q)

0

rt

•

z

0

OJ

I

...,.

Vt

en

LJ1

-

2-12

-

EXAMPLE:

Individual

data

of

empty

glider

/from

table

of

weighing

the

glider

on

page

2-5

/

e.g.

:

m0 a

372

kg

M

0 =

235

kgm

Crew:

Front

seat

pilot

with

pillow

m1 =

60

kg,

M

1 =

-81

kgm

Rear

seat

pilot

without

pillow

m

2=96

kg:

M

2 B

-16

kgm

Additional

equipment

-

Instrument

panel

of

rear

seat

5,2

kg

- 4

kgm

-

transce1%er

------z~g-~g_z_g_~a~--

mw

=

12,4

kg

Mw

= - 2

kgm

Glider-in-fliaht

mass:

m =

372

+

60

+

96

+

12,4

=

540,4

kg

Moment

of

glider-in-fl~ght

mass:

M m

235

-

81

-

16

-2 =

136

kgm

The

perpendicular

lines

from

points

m =

540~4

kg

and

M =

136

kg

on

diagram

of

page2-11

cross

in

point

A

which

is

in

the

dashed

fieldo

The

glider-in-flight

e.g.

location

is

correct.

50-3

FM3

PZL Bielsko SZD-50-3 PUCHACZ Technical specifications

Popular Aircraft manuals by other brands