Grob TWIN-ASTIR Flight Handbook

GROB

N8485W

3250

Utah Soaring Association

GROB-FLUGZEUGBAU

8939

Mattsfes

Flugplatz Mlndelhelm-Mattsies

Telefon

FLIGHT HANDBOOK

08268/411

-,-

Registration:

Owner:

German edition of LuftGerPO.

""-'

This handbook must

I

IV

Jt

refers

of

operating instructions are approved under § 12/2.

-

1-~J:::':I}

be

carried on board

to

the TWIN ASTIR Sailplane

• ,

Factory

Serial Number:

I

at

atl times.

11?

Published

Approval of translation has been done by beat knowledge and judgement - In any case the

original text In German language Is authoritative.

·

GROB

GRO~-FLUGZEUGBAU

8939 Matts!es

FJugplatz Mindelheim-Mattsies

Terefon

08268/411

FLI"GHT

-.--~I

ThJs

handbook must be carried on board

lt refers

Registration:

Owner:

HANDBOOK

I'J

to

- I I

TRAINER

the TWIN-ASTIR

.!*S·

TRAINER

Factory

•

at

Sailplane

Serial

I

all times.

Number:

..........

<~1

German edition of

LuftGerPO.

Pub

fished

Approval of translation has been done original

text

In

of

operating instructions are approved under § 12/2.

German languag& Is authoritative.

by

beat knowledge and judgement - In any caea the

FLIGHT HANDBOOK

Updates

TW~N

ASTIR

1

Current number

1

2 17

\

3

4

5

6 1, 28

7

Page

Sa

18

25

25a

1,25,25a

Reference Date

TWIN ASTIR TRAINER 1.4.78·

New

Control

New

Control

Check

Fittings

Service Butletin

315-50

TM 315-58

Levers

Levers 1.10.78

of

wing

1.10.78

28.09.92

04.11.96

Signature

LBA-

Approval

1,

7,

1, 7,

1"1

11

8

9

14 September 2004

As

·a 315-64

Envelope

MSB 315-64/3

Revised

Operation

Limitations

Limits

of

30.06.2003

14.09.2004

-

~

/

t(_~

/.~~

~

_..

t-

..-

·

1

2.

f2\

~

DKr.

2aa~

FLIGHT

Contents

HANDBOOK

TWIN

ASTIR

2

I.

1

•.

I.

11.

ll. 1 Airworthiness Group

11.

General

1

Updates

2 Contents 2 3 Photograph 4 4 Drawing 5 5 Description 6

Operating limits

2 Permitted operating conditions

Minimum equipment

3

Maximum Speeds

4

Flight envelope

5

Weight limits

6

Centre of gravity position

7

Load scheme

8

Tow hooks

9

Weak link strength

10

Tire pressure

11

Cros:swlnds

12

Required placards

13

Symbols

14

1

6 6 6

7 7

8

10

10 10

10

11

13

Ill.

1

Ill.

Ill. 2 Ill. 3 Ill. 4

Ill. 5

Emergency procedures

Exit from a spin

Emergency canopy jettisoning and exit

Landing with a retracted undercarriage

Others (Rain, ice, stall, groundloops}

Instruments specifications

15 15 15

15

16

FLIGHT

IV

. Normal operation

HANDBOOK

TWIN

ASTIR

3

IV.

IV·

IV.

IV. 5 Free Flight

IV. 6

IV.

IV

..

IV.

IV. 10 Approach and landing

IV.

V. V.

V.

Cockpit and controls (Picture) 17

1

2 Daily preflight inspection 19

3 Control checks before

4 Take

Slow High speed flight

7

Cloud flying

8

Simpre Aerobatics

9

11

off

flying and stalls 22

Flying with waterballast

Rigging and derigging

take

off

1 Rigging, derigging

Storage

2

3 Transport

4 · Maintenance

of

the

glider

21

22

22 22 23

24

25

26

27

VI.

1

VI.

2

VI.

3 ·_Reference 4 - Reference

Vl.

5

VI.

Appendices

Flight performance

Service and Maintenance instructions

to

repairs

to

release hooks

Determination

of

the

center

of

gravity

29

30

31

FLIGHT

HANDBOOK

TWIN

ASTIR

5

I

'

FLIGHT

HANDBOOK

TWIN

ASTIR

5a

The sailplane TWIN-ASTIR TRAINER is derived from the TWIN-ASTIR. The differences are fixed sprung undercarriage with disc brake, and the deletion of the wing ballast tanks.

Therefore, the remarks

In the flight handbook and the maintenance handbook concerning retractable undercarriage and water tanks do not apply to the TWIN-ASTIR

The wheel brake

of

the TWIN-ASTIR TRAINER is a disc brake. The

brake cylinder with the storage tank for brake fluid Is mounted

TRAINER.

on

the

undercarriage box. The marks for minimum and maximum reserve must be observed.

For refilling use brake fluid DOT 3 (amber).

1.

10.78

FLIGHT

I.

5

Description

HANDBOOK

TWIN

ASTIR

6

The TWIN

ASTIR

Is a high performance two seater sailplane with a

T-tail, fitted with a retractable undercarriage, upper surface airbrakes

and water This

sailplane is manufactured using the latest techniques in industrial

ballast tanks in the wings.

Glass fibre construction.

it is designed

for

training, high performance and simple aerobatic

flying.

Technical

Span 17.5 m (57.4 ft.)

Length Height 1.6 m

Aspect

Ratio

11.

Operating

11.

1

(U,

Utility, LFSM}

The

segler) published 23. the licensing of a new type of glider

Data:

8.1

m (26.6 ft.)

17.1

Limits

Airworthiness

LFSM

(Lufttuchtigkeitsforderung fUr Segelflugzeuge und Motor-

(5

.2

ft

Group

10.

.)

1975

Wing Area 17.8 Maximum Flying Weight

m•

(191.6ft.

650

kg

2

(14351bs)

Maximum Wing Loading 36.5 kg/m

(7.841bs/ft.

are the basic rules and requirements

or

motor glider in Germany.

}

1

2

for

)

11.

2

Permitted

operating

conditions.

The plane is licensed for:

1· Flight in

VMC

2. Simple Aerobatics (Loops, Stall turns, Lazy eight, Chandelle and

SpiA).

3. Cloud flying {When fitted with suitable Instrumentation as defined

in section

11. 3 Minimum

1. 2 Air speed Indicators reading

2.

2 Altimeters.

3. Full Harness

4. Parachute

5.

Loading limit plaque in front and back cockpit.

6.

Flight Limits plaque.

7.

Flight Handbook.

11. 3).

equipment

to

300 km/hr (162 kts, 187 mph)

Straps in front and back cockpit.

or

back cushion at least 7

cm

(3

inch) thick.

FLIGHT

HANDBOOK

TW-IN

ASTIR

Cloud Flying.

For

cloud

flying

the

additional instruments listed below must be

installed. ·

1.

Variometer.

2.

Electric turn and

3. Magnetic

Compass (Compensated inside

slip

indicator.

the

7

glider).

11. 4 Maximum

Maximum permitted

speed

in

calm

-Speeds

air

• ·

VNE

=

250

km/h ( 135 kts, 155 mph} I

Maximum permitted

speed in

Maximum Manoeuvring speed

rough

air

Maximum winch launch speed Maximum Aerotow speed

Conditions· in rough

air

are similar

Vs

VM = 170 km/h ( 92 kts,

Vw

VT

= 170 km/h ( 92-kts, 105 mph)

= 120

= 170 km/h (

to

km/h

( 65 kts, 74 mph)

92

those encountered in rotors,

cJouds, whirlwinds and when overflying mountain ranges.

Manoeuvring speed tions should

Air

105-155 mph

may

be restricted

speed

51-105

be

used.

indicator

mph

=

==

at 155 mph = 135 kts =

at

65

m

ph

= 55

Position

The

Pitot head

Errors

airspeed

in

indicator

the

is

the maximum · speed at whi

At

maximum speed (VNE) the control deflections

to

1/3

of

the full range .

markings

44-

92-135

tail

kts

fin.

92

kts = kts =

= 102

must

static

82-170

170

-----

250

km/h

km

/h - Yellow

(recommended minimum appr. speed}

be

connected

vents

side

ch

full

km/h

250km

/h

-Green

-Yellow

(MSB315-64/3}--

to

the foUowing sources:

of

the fuselage between the

Red line

two seats.

Using a

or 1 kt

cal-ibrated

or

1.2 mph. A

ASI

the

calibration

posaion

curve

error

is

not

greater

is

therefore not necessary.

1-05

mph)

kts, _105 mph)

control deflec-

arc

arc I

triangle

than ± 2 km/h

If

. 5 Flight envelope.

The sailplane design

At

manoeuvring speed + 5.3 -

At

VNE + 4.0 - 1.5

(Brakes

14. September 2004

closed

and

limit load factors are as follows:

calm

air}

2.65

FLIGHT

11.

6 Welghtllmlts

HANDBOOK

TWIN

ASTIR

8

Maximum permitted weight without water ballast Including water ballast .

Maximum permitted weight of non

11.

7 Centre

of

gravity position

lifting parts •

650 650

470

kg

(1435 lbs)

kg

{1435 lbs)

kg

(1036

lbs)

The approved range of centre of gravity positions during flight is

260

mm

{10.24 inches) to 460 inm (18.11 inches) behind the reference

to

point, equivalent

24.7%

to

43.6%

of

the

M.A.C.

of the wing.

The reference point is the front edge of the wing at the wing root. The approved centre of gravity range does not get exceeded by the

11.

payload distribution specified in the loading plan The exact position of the centre

VI·

calculated according to

5.

of

gravity at flying weight can be

8.

11.

8 Load scheme TWIN ASTIR

70

kg

Minimum load in the front seat for all flight . Maximum load in the front seat Maximum load in the back seat Maximum load ln both seats Maximum load in the baggage compartment .

110 110

220

10

(154 lbs)

kg

(242 lbs)

kg

{242 lbs)

kg

(485 lbs)

kg

( 22 lbs)

Ballast must be used on the front seat to compensate If the front seat load is lower than

The maximum flying weight

70 kg (154 lbs).

of

650 kg {1435 lbs) must not be exceeded.

Waterballast may only be taken on until the maximum flying weight

is reached.

lf

Water ballast can not be used to compensate

seat

Is

too low·

the load in the front

F

LIG

H T

HANDBOOK

TWI

N

ASTIR

9

Date

of

wetghlng: list

carried out

by.

~.

-

Equipment

for weighing

...

used

(dale)

---

--

Empty

(Weight

kg!lb9

Position

cg

empty

} behind

rence

mm/ inches

of

refe-

Maximum

r--

total

payload

kg/lbs

·

-

1--

-

--

----

"-

-

,-

...

~

._.....,_

--

-·

-·-

FLIGHT

11

. 9 Tow

For

Ae r

For

Winch launch: Safety back release hook

H A

ND

hoo

ks

otow: No

BOOK

se

hook "E

TWIN

75''.

AS

TIR

"G

10

73".

The E installation are

11.

Winch launch and aerot

(ie. Tost weak link colour code black-red)

ll. 11

Tire size

11.

The maximum crosswind component approved for fake

Is

75

and the G

or

2000 launches

to be

10

recertified

Wuk

Tire Pressure

link ttrength

5.50-

12 Crosswinds

20

km/h

{11 kts, 12 mph).

5

73

Tost hooks are lim ited

which

by

the manufactu re

recomme~~

ow

to

ever occurs first, at which time they

r.

~~~

·

if'f

,) .!.:AI

~0

2,5-2

.8 atm.

kg 1323 ± 66 lbs

rrt-1~~)-

36

months after

/t~

·

)"Z

J

-

:1'/

35.6-39,8

off

and lan

t.A

din

:;

PSI

g,

FLIGHT

HANDBOOK

TWIN

ASTIR

11

U ~ 13 Required placards front

Maximum flying weight

Without

With Waterballast

Airspeed limits.

Never exceed

In

Rough

On Airotow

On Winch

Airbrakes Open

Manoeuvring

Payload (Pilot

Waterballast

Air

or

Auto Launch

and

Parachute).

and

rear cockpit

V

Ne

Vs

Vr Vw

V oF VA

650

kp

650 kp

km/hr

250

170

"

170 120

250

170

1435

1435 lbs

knots

135

92

92 64

135

92

lbs

m

ph

155

105

74

155

105

·

Minimum in Front

for all flight

. Less ·must be compensated with

ballast secured in the seat

Maximum load

Simple aerobatics·

Recommended

entry speed

Loop Stall turn

Spin

Chandelle

aerobatics with waterballast is

cockpit

front

back

air

speeds

.km/hr

180 180

80

170

not

70

kg

110 kg

knots

97 97

43

92

allowed

154 lb

242 lb

m ph

111

50

105

14

September 2004

FLIGHT

HANDBOOK

Required placards

TWIN

ASTIR

12

Check before

Full and free movement

launch

of

controls?

Parachute secured?

Straps

tight

and locked?

Pedals adjusted and locked?

Brakes closed and locked?

Trim correctly adjusted?

Altimeter adjusted? Canopy locked?

Cable on correct hook?

Beware: - Crosswind! -

Front Cockpit

Cable breakt

Canopy Jettison and Emergency Exit

- Pull red handles on right and left of canopy fully back together

- Push canopy up and away with the left hand

- Release safety harness

- Stand up and get out over left altitude

- When using a manual parachute full extent after

1-3

seconds

or

right side depending on the

grip

release and pull firmly

to

By canopy release front and back

Tire

Pressure

39,8 PSI 2,8 atm

Maximum weak

link strength

1323 lbs

Left

undercarriage

600

kg

door.

Baggage maximum

22

lbs

Baggage compartment

10

kg

F L J G HT HA N D 6 0 0 K

11.

14 Symbols

TW

J N

AS

T I R

13

Undercarriage retract

Canopy open

CanopyJeUson

Waterballaat

Jetlson

.Trim

Airbrakes

Wheel brake

IOJ)

F

Ll G HT

Symbols

HA

N D B 0 0 K

TW

I N

AS

T t R

14

t

Cable

i

Air-vent.

Top left

Instrument panel

Pe~al

Top right

QQ

Instrument panel

release

of

front

adjustment

of

front

Total energy

compensation tube

FLIGHT

Ill.

Emergency

HANDBOOK

procedures

TWIN

ASTIR

15

Ill. 1

Exit

from a spin

Exit from a spin can be accomplished by

- Full opposite Rudder

--

Neutralise Stick

- Ailerons should be central

-

When

Ill. 2

rotation stops centralise rudder

Emergency

canopy

Jettisoning

and

exit.

pull out gently·

The spacious cockpit allows unhindered exit in an emergency.

lt

Is

advisable

a)

Pull red handles

to

keep to the following order:

on

left

and

right back together and push canopy

upwards and away with the left hand.

b)

unlock safety belts

c)

Stand

up

and get out over left

or

right side depending

on

attitude.

d) When using a manual parachute grip release handle and

firmly"

Ill. 3 Landing with retracted undercarriage

to full extent after 1 - 3 seconds.

the

pull

lt

is possible on hard and soft ground without risk

Approach as normal and touch down

Ill. 4

Flying

Wet ice deposits

10

Stall

Stall out of straight flight

Others

·In

rain

or

lightly iced wings have little noticeable effect

on

the wing increase the stalling speed by about

km/h = 6 kts.

or

a turn: Neutralise stick

on

two points.

der to any turn.

Ground

The glider

However

Loops

has

no tendency to ground loop whilst taking off.

if

a wing touches

or

the direction changes·by .more than

degrees during a take off release immediately.

of

overturning.

on

flying. Thick

and

opposite rud-

15

FLIGHT

HANDBOOK

TWIN

ASTIR

16

Ill. 5

Instruments

specifications

Basic equipment: Airspeed The installation error of an airspeed Indicator

or

1 kt.

or

1,2 mph using the pitot tube In the tail fin and the static vents

of"the cockpit.

side

Is

not greater than 2 km/h

The original certification was carried out using a Winter

a

PZL

PR

400

S Airspeed indicator.

similiar

A

to

300

km/h

FAA

approved airspeed indicator to meet TSO C 2 reading

(162

kts,

187

mph) may be used.

Altimeter The original certification was carried out using a Winter

a

PZL

12

S Altimeter.

A

simillar FAA approved altimeter to meet

35.000

feet may be used.

TSO

C 10 with a range

6FMS4-2 and

4FGH

10

and .

to

Nur USA-Export

FLIGHT

IV.

Normal

VI.

1

Cockpit

Front Seat.

HANDBOOK

operation

and

controls

TWIN

ASTIR

17

Stick 5 Undercarriage lever

1 2 Rudder pedals 6 Release knob

3 Airbrake lever and wheelbrake 7 Canopy jettison 4

Trim-lever 8 Water ballast jettison

Ventilator top of

Instrument panel left side·

Rudder pedal adjustment top of instrument panel right side.

FLIGHT

IV.

1 Cockpit and controls

HANDBOOK

Back seat.

' .

TWIN

ASTIR

18

1 Stick 4 Trim lever

2 Rudder pedals 5 Undercarriage lever

3 Airbrake lever and wheelbrake 6 Release knob

7 Canopy jettison

F L I G H T H A N 0 B 0 0 K T W l N AS T I R

IV. 2 Daily preflight Inspection

1.

a) Open canopy. b)

Check the 4 wing fastenlngs Inside

c)

Visually check all controls inside the cockpit. Check for foreign bodies.

d) e)

Te~t

controls for full and free movement.

f) Check tire pressure

g) Check condition

h)

Check fUnctioning

2.

a) Check top and bottom of wing for damage·

2.5 -2.8

of

both hooks.

of

releases and wheelbrake.

the

atm. =

b) Check ailerons for condition, freedom

c)

Check alrbrakes for condition, locking and fit.

fuselage If locked.

35.6-39.8

of

movement and play.

PSI

19

3.

Check fuselage for damage especially on the underside.

4.

Check tall unit for correct assembly and that safety lock Is in position.

5.

Check condition of the tailskid.

6.

Check the pitot tube, total energy venturi and static vents are clean.

7.

Repeat step 2 for right wing.

B.

Check static vents.

After heavy landings

or

excessive flight loads the entire glider should be checked. The wings and tailplane should be removed for these checks and

if

any damage is found

an

inspector should be consulted.

The plane should not be flown before any damage is repaired.

FLIGHT

HANDBOOK

\

TWIN

ASTIR

Preflight Inspection Checkpoints

compare

IV.

- 2

20

N

I

FLIGHT

HANDBOOK

TWIN

ASTIR

IV. 3 Control checks before take off·

1.

Check all the controls for full and free movement.

2. Check undercarriage lever

3. Check that the ballast limitations are being adhered to.

Is

fully forward and locked down.

4. Check safety straps and parachute are firmly fastened.

5. Check altimeter is adjusted to zero

6. Check that transmitter is switched on and set

7. Check trim is neutral.

8.

Check canopy is closed and locked.

9. Check airbrakes are closed

IV.

4 Take off

Winch launch

and

or

airfield height.

locked.

to

airfield frequency.

21

Trim lever should Maximum winch launch speed is

be

in central position.

120 km/h (65 kts,

74

mph). The glider has a release hook in front of the wheel. Winch launches cause no difficulties at positions

and

wing loadlngs.

The plane has no tendency to balloon up

One should push forward slightly on the stick below about

(330

ft)

in the case of fast launches from a powerful winch. When the

all allowed centre

or

to swing on the ground.

100 metres

of

gravity

cable slackens pull the release firmly to its limit.

The undercarriage should not be retracted during a winch launch.

Aerotow Trim lever should be in central position.

Maximum aerotow speed is

170 km/h

{92

kts, 105 mph).

Aerotow should preferably use the nose hook. The recommended length of tow rope is

40-60

m

(120-

200ft.).

The glider can be controlled with coordinated rudder and aileron

using full movements

if

required.

There is no tendency to swing In a strong crosswind.

The glider can be lifted off at about The glider lifts off without ass.lstance at a speed

(43 kts, 50 mph)

if

the stick Is kept

70

km/h (38 kts,

in

the neutral position.

44

mph).

of

about 80 km/h

The undercarriage can be retracted during aerotow at a reasonable height. .

The yellow release handle is mounted on the Instrument panel a.

nd

must be pulled to its limit when releasing.

•

FLIGHT

IV.

5 Free flight

lt

Is possible

titudes. Full

co11trol 170 km/h used with the appropriate care.

IV.

6 Slow flying and stalling

The glider gives clear warning when about

shaking The

stalling speed depends on the wing loading and

of

the plane. The following are guidelines:

Single seater

470· kg = 1034

HANDBOOK

to

fly the glider over

movements are only allowed up to the manoeuvring speed

(92

kts,

105

of

the elevator.

Weight

lbs

TWIN

mph).

Without Airbrakes

{36 kts,

ASTIR

At

higher speeds

66

km/h

41

the

entire speed range in all at-

mph)

the

controls should be

to

stall by a distinct

the

condition

With Airbrakes

75

km/h

(40,5 kts,

47

22

mph)

Double seater

Weight

650

kg = 1430 lbs

If

the stick is .pulled back further high rate of sink, during which rudder and aileron turns can be at up

returns After the stick

the bank can IV. 7 High speed flight

There is no tendency

range. Above be under VNE

IV.

The minimum Instrumentation required

to

15 degrees

to

a normal flying attitude immediately.

Is pulled back quickly the glider pitches nose down and

still

be controUed with aileron.

170 km/h

restf1icted

8 Cloud flying

Air Altimeter Compass

to

1/3

In a 45° dive even

speed indicator Variometer Turn and Slip

Without Airbrakes

80

km/h

(43

kts, 50 mph)

the

glider

of

bank. When

for

flutter

(92

of

full range. The airbrakes

to

kts, 105 mph) control movements should

at

maximum flying weight.

the

stick is released the glider

develope within the permitted speed

for

flying In cloud is:

goes into a controllable

With Airbrakes

90

km/h

{49

kts, 46 mph)

limit

the speed to

flown

FLIGHT

HANDBOOK

TWIN

ASTIR

23

Experience icing.

If

the manouvering speed ·is exceeded · unintentJonaJiy,

airbrakes In

emergency open brakes and leave cloud

105

mph).

IV. 9 Simple Aerobatics

The gJider is

1.

Loop Entry speed

Maximum g

exit speed

to

date shows that the

to

avoid overstressing.

licenced for the following aerobatics (no waterbaUast):

•

ASJ

does not get affected by

at

about

180

km/h

ea.

3 g

ea.

180 km/h (97 kts, 111 mph)

170

(97

puiJ

km/h

kts,

out the

(92

111

mph)

kts,

2. Stall turn

Entry speed

At 140 km/h

Shortly before the top apply opposite aileron.

Note: The stall turn is difficult of

the high moment

dently Initiated during the climb lock all controls in

the centre position.

3.

Spin (possible in aft

Preparation. Decrease speed slowly 50

mph) pull stick back and give full rudder. Glider

spins slowly. Rotation rate is one turn every 3 seconds

with a height loss

Exit Rudder fully opposite against direction

neutr~lise

stopped.

• 180 km/h

(76

kts,

87

mph) slowly apply rudder.

to

carry out because

of

inertia. If

e.G.

positions only}

of

about

stick then pull out slowly after rotation has

100

a.

tallslide

to

80

m (300ft.)

km/h

per

turn.

Is

(43

of

(97

acci-

kts,

turn,

kts,

111

mph}

FLIGHT

4.

ChandeiJe

HANDBOOK

TWIN

ASTIR

24

Entry speed *

170 km/h

(92

kts,

105

mph)

Pull up to fly 90° turn. During turn decrease speed

and exit from turn with rudder and aileron.

Chandelle

should be completed heading in opposite direction.

• NB: For twoseater configuration increase entry speed by

(12

mph,

11

kts).

IV.

10

Approach

Normal flying practice

and

landing

Is to approach at 100 km/h =

54

20

km/h

kts. The airbrakes are sufficiently powerful for steep approaches. The use of brakes causes the glider to be holds the required speed

by

Avoid changing the alrbrake setting

slightly nose heavy, so that the glider

itself.

during the roundout to avoid

heavy landing.

IV.

11

.·

Flight

The water tanks are

(11

gal.)

of the

Wings.

noticeable water movement when the tanks are

of

baffles installed within the

amounts of water in each tank

with

waterballast

In

the front of the wings and can hold about

per

wing. The tanks are filled through the openings on the top

The cap can be removed with a pin. There is no

partially filled because

t~nks.

to

avoid affecting the stability in roll.

There must always

be

50

equal

I

The white lever on the right hand side of the cockpit should be

pulled back

behind the wheel. strongly recommended that the tanks are emptied before landing

of

field.

to

empty the tanks. The outlet

lt

takes about 4 minutes to empty the tanks.

Is

underneath the fuselage

it

out

Is

FLIGHT

V.

Rigging and derlgglng

V.

1 Rigging

HANDBOOK TWIN ASTIR

25

The fuselage

lt

is recommended

must"

be

held firmly In a horizontal position when rigging.

to

use a fuselage stand

or

the trailer fittings are

used.

The glider can be rigged by

4 people.

1. Wings

Unlock the

brakes

safety catches on gently moving the wing to and. fro will be heard place. Next tips

up

lined up

4 main wing fittings

on

the

wings. Guide the right wing into the fuselage. The

on

the fuselage fittings should now be released,

or

with

guide

down

the left wing

so that the pin on the end of the spar stub

the

appropriate hole in the opposite wing root and

in

the fuselage. Unlock the air-

to

snap into

l"nto

the fuselage. Move the wing

slide into place. Next release the safety catches on the left hand

fuselage fittings and by gently moving the wing too

can

be made to snap into place.

to

and fro they

Original wing-fuselage connection:

To secure the so that the

Moving the to be

sufficiently turned (4). They should be hand tight and should

not reach the end

wing

fittings the safety catches (1) have to be turned

pins (2} are pressed to the angled slots.

wing

tip

strongly

of

the angled slot.

to

and fro enables the safety catches

and

Is

Wing-fuselage connection according to

To

secure

nut { 1) must be turned into the threaded socket (2) so that the socket

drawn against the red rings which are held

By

means

tight

end

of

04.11.96

Rev.

7

the

wing-fuselage

of

moving

(4)

while

the

milled selector of the shaft guide.

the

securing

wing

the

connection

tips

guide

for

pins

SB

in

by

and

aft,

however,

315-58:

the

closes

the guide pins (3).

the

must

knurled

not

position, the

nut can

strike

knurled

be

secured

against

is

the

FLIGHT HANDBOOK

TWIN

ASTIR

25a

Original wing-fuselage connection:

a opened

r--mv;m...---.

2

b closed

c sured

Wing-fuselage connection

to

SB 315-58:

a

geoffnet

r-~~~~~~~opened

according

max. position

Check: threaded

tightened

In from. the

2. The aileron and

The .short

the

The

red

rings at

the

sockets. the socket (or

hand

tight.

closed,

locking

but not

.

secured

brake

connecting

fuselage

connection

the

knurled

position

{b),

connections lie behind the spar.

rods in the fuselage are fitted

lock fasteners which must be coupled onto

the

that move inside

After rigging

the

wings.

connections should be examined to check that

the sprung catches are properly inserted

mm out of

Also after

not be extracted with rods and locks in

the

locks. · ·

coupling

the

quick-lock fasteners, check that the

by

twisting the lock back and forth. Do this·

not more than 10 lbs pull. Check all the control connecting

a methodical order.

nut

the

rods

must

be

covered

ace.

to

SB

315-58}

wing

bolt

cannot

be

removed

with

the

balls on the linkages

$0

that they project some

ball

by

must

quick

can

gently

the

be

04.11.96

Rev.

7

FLIGHT

3.

Tailplane

Before assembly is commenced the front cover must be opened and the rotating wing bolt pulled out to the limit. The be positioned by standing behind the rudder. The tailplane can be

rested on top of the fin with the elevator angled upwards so that the snap lock fastener on the elevator push rod can be attached

the ball on the elevator horn. The front

be necessary to tighten the wing bolt clockwise to secure the tail-

plane. The assembly is complete when the wing bolt is sufficiently

tight that there is

safety measure

zontal. suit. Derigging is carried out in the opposite order and the wing bolt is turned anticlockwise and

HANDBOOK

lowered and pushed back onto the three pins.

as

If necessary the wing bolt has to be turned a

TWIN

no

play in any direction. The cover provides a

it

can only

ASTIR

tailplane can

of

the tailplane can then

be

attached with the wing bolt hori-

pulled fully out.

lt

1/4

26

to

Is then

turn

to

Checks

1. Check that the 4 main wing fittings are locked.

2.

3.

4.

5.

6.

to

be

made

Check that aileron and brake quick-actions locks are properly

located on the knobs.

Ensure that the tow hook is functioning correctly.

Test the operation

in the tire.

Check that the tailplane is securely seated

push-rod is connected.

Rudder movement.

after

of

assembly

the wheelbrake and ·the pressure

· and

that the elevator

of

the air

Oerlgglng

Derigglng is carried out in the opposi

not matter which wing is removed first. Excessive fore and aft rocking

of

the wing tips should be avoided.

V.

2

Storage

te

order and this case

it

does

When the glider Is stored the canopy should be locked. To tie down

wi11g,

the

For ground handling the rotating tall wheel should be used.

a rope can be pulled through the wing tip

skidso'

FLJG.HT

V.

3 Transport

HANDBOOK

TWIN

ASTIR

27

We recommend the use The parts must

be

of

a closed trailer

carefully supported and secured so they cannot

slide.

1.

Fuselage

A fuselage positioned in front trolley should be

if

required. The tail skid should be secured so that

trolley moulded to the shape of the fuselage and

of

the main wheeL The mlnimum length

400

mrn

and

it

can

sideways.

2.

Wings

for

The minimum length should start at the face padded well with foam rubber

the spar support should be 200

of

the root rib. The mounting must be ·

or

The mounting under the aileron

mounting block with a minimum length

400

mm.

The mounting must be padded with felt.

3.

Tailplane

for

transporting the glider.

of

the

be

attached

to

the wing fittings

it

cannot slide

mm

and

felt.

Inboard end should be a shaped

of

300

mm

and height of

Either horizontal on padded supports with the upper surface

or

downwards and secured with straps

vertical supported on the

leading edge in shaped mounting blocks. Profile drawings are

and tailplane fittings.

V. 4 Maintenance of the glider

avaitable

for

the manufacture

·

of

f-uselage, wing

The entire surface of the glider is coated with weather resistant white polyester gelcoat.

The greatest care should

of

surface

the glider. Luke warm water should be used to wash off dust, grease, dead flies and other dirty marks. More resistant shquld

be

removed by using a mild cleaning agent. Only special sili-

be

taken

in

maintainln·g the fibre glass

dirt

con-tree preparations should be used in maintaining· the painted surfaces.

or

0 Z-Spezialreiniger

Reinigungspolish

Fa.

Lesonal).

....., D 2,

Fa.

W.

Sauer and Co., 5060

Bensb~rg

F L I'G

HT

HA

N D B 0 0 K T W I N

AS

T I R

28

Although very resistant

the

glider

should possible against rain and dampness. Water be

dealt

with

by storing

the

glider

in a dry

over the dismantled parts. The

most

cleaner

cloth

down. Never rub perspex The

general wear. checked

Because very

damage, cleaned and greased. hook lever and take

hook

turer, Tost. For

effective

but

if

or

chamois-Jeather should

way

to

necessary

clean the

iuke

with

Safety harness should

The

for

of

grimy

can should

metal

corrosion.

its position,

and muddy.

easily

be

taken out. Remove

out

the retaining screws. For reconditioning, the

sent

further

parts

the

winch launch

lt

must therefore

with

the

details

canopy

warm

water

be

employed

anything dry.

be

regularly checked

of

the

harness should

hook

When

the

record

the

card

manufacturers manuals should be

consulted.

be

protected as much as

that

has seeped

in

should

place, frequently turning

is

to

use a special perspex

can

be

used. A soft, clean

to

wipe

for

is susceptible

be

frequently inspected

the

canopy

damage and

be

frequently

to

getting

seat-well Is removed connecting

to

the

tow

wire

hook

from

manufac-

tor

the the

tow

.

The cables .and pulley

tor

wear

kept at 2.5

The disc

Drum by

moving

Disc

under During the

Bowden

brake

onto

Remove out

assembly smear

during

to

2.8 atmospheres

wheelbrake

brake).

brake:

the

The

the

The

rear

Bowden

seat.

removing

cable

cylinder must

one

side

the

by

pulling

the yearly inspection.

Is

of a

bowden

main

Use

the

must

be

of

screws

it

all

Before assembling the

for

the

nose and belly hooks should

The

main

wheel

tire

pressure

"(

36-40

psi).

dru~

type

(tor

SIN's

3000

...

3139

cab)e

can

be

adjusted.

cable

at

the

drum

b(&ke

only

main

wheel

be

disconnected

removed

cylinder

brake

and

fluid

for

cleaning,

(disc

·

th~

according

from

brake).

Screw

the axle and take

that

hold

the

brake-lever

end.

brake

optional

The

adjustment

fluid

reservoir

to

specification

greasing

the

Do

out

or

brake

lever

not

open

the

M 6 threaded special

the screws and

in

as a hydraulic

Is

canied out

are

OOT3/

changing

(drum

the

brake

place. Take

downwards. Clean all the parts and before re-

of

them

glider

with

the

grease.

pins

and

sockets

at

the

wings and fuselage, and tailplane and fuselage , should and greased.

28.09.92

TM 315-50

be

located

the

tire

brake}

fluid

the

joints

be

checked

should

OOT4.

or

the

hose.

tool

spindle.

the

wheel

between

cleaned

be

.

FLIGHT

VI.

Appendices

VI.

1

Flight

HANDBOOK

Performance

TWIN

ASTIR

29

Flying weight 470 (1036) 560 (1234} 650 (1435) Wing loading 26.4 (5.4)

Best glide Angle 37.0

at

a speed

Minimum sink

at

a speed

Vl

E o

.......

r-

~

.£

E

-

=1/XJ

0

UJ

~000

·

m

~

(.!)

a

z

~

(.)

ill

~

z

(./)

1

2

3

4

5

of

0

10

95

0.62 (2.03) 0.68 (2.23) 0.73 (2.3)

75 (40)

~

~ ~

FLUGGESCHWINDIGKEIT

50

GESCHWINDIGKEI1SPOLARE

FLIGHT

(51)

VELOciTY

""

If

31.5 (6.5) 36.5 {7.5)

37.5 38.0

105

(57)

80

(43)

J kts)

~

w

~

oo

100

~

-

150

~

TWIN -ASTIR

POLAR

110

(60)

90 (49)

oo

~

.....

~~

..........

[ km/hJ

'

kg {lbs)

kg/m1 (I

km/hr

m/sec {ft./sec)

km/hr

m m m m

200

f-..

.

'

-..>·

...

-

~'

-~Bso~

,

~''Vi>

v1b

"

bs/ft.

(kts)

250

2

)

FLIGHT

VI. 2

Service

Regular service.

HANDBOOK

and

TWIN

Maintenance

ASTIR

instructions

30

The following schedule of service should be carried out every

or

at the annual inspection, which occurs first.

1.

The entire glider should be checked for cracks, holes and bumps.

2.

All fittings should be inspected for satisfactory condition (play, scores

3.

All metal parts should be examined for corrosion, cracks, defor-

mation

4. Check that there is no play in the wing and tailplane to fuselage fittings.

5.

The

cables) should be inspected and replaced

bending

6. The controls tional test and the control deflections checked.

7.

If the controls do not move free throughout their range, search

for the cause and correct.

8.

The undercarriage should be Inspected and the wheel and brake checked to be

and

corrosion).

and

If necessary reconditioned and freshly protected.

control linkages (Bearings, stops, fittings, hinges and control

if

there Is evidence of

or

corrosion.

Including the brakes should be submitted to a func-

in

good condition.

100

hours

9.

The tow hooks should be treated in accordance with their appropriate maintenance manual.

10

. Check the pitot for the

instruments is in good condition and free of leaks

11

. The condition and calibration of all instruments should be checked

and any other equipment inspected.

12.

Equ

ipment

equipment list.

13.

Check markings and placards.

14.

After repair or change

updated

weighing

and

Instruments should be checked against the

with· the new empty weight and Center

or

calculation.

ASI

is clear and that the tubing to

or

kinks.

of

equipment, the weight ·table should be

of

Gravity

an

py

FLIGHT

HANDBOOK

TWIN

ASTIR

31

After extended storage check accordingly to regular service pos. 1 to

11

and inspect for evidence of rodents and birdness.

VI.

3 Reference to Repairs

The attached repair instructions give information for the execution

of

minor repairs. Major repairs, in accordance with the glider information sheet are only

permitted to be carried out by

an

authorised aircraft works. Grob will name a company with the appropriate qualifications in any individual case.

VI. 4 Installation, maintenance and examination

One

Is bound by the Maintenance Manuals for the nose hooks 'E

and

'E

75' published

belly hooks 'Europa G 12: and 'Europa G

VI. 5 Determination

The determination riage lowered and the that

an

Incidence board of

In

May 1975 and the Maintenance Manual for the

73'

of

the Center

of

the center

glider supported

of

600 : 24

Gravity

gravity Is made with the undercar-

on

angle is set horizontal on the back

of

the release hooks

72'

published In May 1975.

two scales at heights such

of the fuselage. The . reference plane

lies at the front

of

the wing at the root. The

distances a and b are measured with the help

G1

empty weight is the sum of the two weights

and

of

a plumb line. The

G2.

..

-··

··

..... .

·-

- -- -·-----

F L 1 G H T H A N D 8 0 0 K T W I N

-·-

·

--

---- -

------

-·

--·-----

.A.

S T I R 32

-·

--

__

..

___

_

Procedure

tor

determlnlg C.

~.G.,__,

Datum Lme: Front edge

:_evei

Means. With a 600:24 Incidence Board set

the top

of

G. empty

GL = G1 + G2

__

of

the

wing

of

the rear fuselage.

b

at the

600

root

.2[,

up

horizontal on

Weigt-~t

Weight on tail-skid

Empty

Dtstance · Distance -

Empty Weight C.

on main-wheel

Weight

to

Gl

main-wheel

tail-sl<id

of

X -

'he

;1ea3urements

G

•JI

G.

and

the

;:Ji,(1er

Con11ertio;·,

A:

nply

of

waterballast

-

Gt

~..:.

G2

-~

""

Gt

G2

=

a=

--

b

G.

j-

to

determine

loading limitations must always be taken with the

frnrn

Kg

the

to

lbs

inches

empty weight,

multiply with

kg I lbs

/lbs

kg

kg I lbs

mm 1 inches mm/

mm.'inches

Datum

inches

Line

the

2.2

0.

0394

behind

empty weight

FLJGHT

HANDBOOK

TWIN

ASTIR

33

If the limits of the empty weight limitations

be within the permitted range.

Empty Weight

chart are adhered to the

Range

kg

390 395 400 405 893 708

410

415

420

lbs

860

871

882

904 702

915

926

mm

725 28.54 747 29.41 719

713

697 27.44 730

692 27.24 727

C.

of

G.

C.

of

C.

Forward

inches

28.31

28.07 740 29.13

27.87 737

27.64

positions and the loading

G.

of the loaded glider will

of

G.

behind Datum

Aft

mm

744

733 28.86

inches

29.29

29.02

28.74

28.62

425 937 430

lt

should

admissable load for non-lifting parts must not The weight of the

and maximum load (1036 lbs)

respondingly decreased.

The Centre of Gravity should

installation

the

he

.s elapsed after the last weighing.

The empty weight, empty weight should be recorded after

book.

948

be

noted that to make use

non-liftlng parts Is the

In

the fuselage and must not exceed 470

or

the maximum load permitted in the fuselage must

of

additional equipment

each

687

682 26.85

be

C.

weighing on page 9 of the. Flight

27.05 724

of

the maximum load the maximum

sum

recalculated after repair, repainting,

or

when a period of 4 years

of

G.

posiUon

28.50

720

be

exceeded.

of the fuselage, tailplane

·

anct

28.35

be

cor-

maximum load,

Han.d-

kgs