Grob G 103 TWIN II, G 103A TWIN II ACRO Flight Manual

GROB-WERKE GMBH

N228BG

33995-

K-228

Utah Soaring Association

Unternehmensbereich

Burkhart Grob Flugzeugbau

8939 Mattsies

Am Flugplatz

.

Telefon Telex 539 623'

08268/411

&

CO.

KG

FLIGHT

This manual must be carried on board of the sailplane at all times.

This Flight manual is FAA approved for stered gliders in accordance with the provisions of

14

CFR Section 21.29. and is required by FAA Type

Certificate Data Sheet No. G 39 EU.

--

Registration:

Owner:

German edition of operating instructions are approved

§

under Published September 1981.

Approval of translation has been done by best knowledge and judgement

lancruane is authoritative.

12 (1) 2. of LuftGerPO.

MANUAL

U.

S, regi-

. .

. . . . .

-

in any case the original text in German

.

. . . .

.

Factory Serial No.

LBA

Date 17th march 1981

approved

:

.

FLIGHT HANDBOOK GROB G

1.1. Updates

Page

8,

1, la,

10,12,14

17,19

I, la, 12,

21,

5a

No.

3730 and June 1982

subsequent

Automatic connection

of

elevator and sorina

trim

system os

33879

ario

s-bseq~ent

103

.

SIN

I

I I

I

"

1

26,

Sept,

84

1, la, 5a

MSB 315-65 16.10.2003

OSB

315-66 16.10.2003

Rev.

4, 16.10.2003

'

FLIGHT HANDBOOK GROB

List of

effective

Daaes

G

103

I

a

(*)

only

for

GROB G 103A TWIN

I1

ACRO

FAA

Issue

:LIGHT

I.

MANUAL

2

Contents

I.

I. I.

I, 3 Photograph

I. I.

GROB G 103

General

1 Log of revisions

2

Contents (LBA approved pages:

1,

la and 6 through 31, except

9

and

4

Drawing

5 Description

Operating limitations

Airworthiness Group

Permitted operating conditions Minimum equipment Maximum Speeds Flight envelope

Weight limits

Centre of gravity position

Load scheme, weighing report

Tow hooks and cable length Weak link strength 10 Tire pressure 10

Crosswinds

Placards, control markings and 11,12,

instrument markings 13,

22)

.

page

1,

la

2,3

2

6

k.

6

7

8

8,

9

10

12a

14,

15

111. Emergency procedures

111.

1 Recovery from the spin 16

111.

2

Emergency canopy jettison and exit.

111.

3

Miscellaneona (Rain, ice, 16

groundloops)

September 1981.

16

FLIGHT MANUAL

GROB

G

103

3

IV. Nonnal IV. 1 Godxplt and controb (Plcture)

IV.

2

Dally prefllghl Inspection

3

iV. IV. 1V.

IV.

IV. IV.

IV.10

Control &edw before

4

Take off

5

Free

6

Slow flylng and stalla

7

Hlgh speed fllght

8

Simple Aerobatics

9

Approach and landing

Storage

procedures

flight

toke

ofl

V.

App.ndI-8

1

Fllght performance

2

Determination of the center of

gravity

September

1981

FLIGHT

MANUAL

GROB

GI03

4

September

1981

FLIGHT

MANUAL

-

GROB

G

-.

103

6

September

198

1

FLIGHT HANDBOOK GROB

G

103

5a

If the fuselage reinforcement according to

following is applicable:

I1

The glider GROB G 103A "WIN to structural reinforcements the 'TWIN According to MSB 315-65 only "simple aerobatics" (Loop. Turn, Lazy Eight, Chandelle, Spin) is approved (refer to 11.2 and IV.9)

The

Flight Handbook for Aerobatics

-

GROB G 103A "WIN

Edition February 1984

f

LBA approved

is unvaiid according to MSB 315-65 and must be removed from the Flight Handbook.

If the fuselage reinforcement according to following is applicable:

The aiider GROB G 103 A 'TWIN to stnctural re.nforcements the "WIN conlunction with [he following valld operating instructions:

FI ght handbook for acrooatics, GROB G 103 A edition February 1964, LBA approved.

"

Wih

ACRO is derived from the GROB G 103 "WIN

II

ACRO"

II

ACR0 is derived from the GROB G 103 "TWIN

II

ACRO.

OSB

315-66

had not been Dertormed the

II

ACRO is approved in the category "Acrobatic".

OSB

315-66

had been performed the

II

ACRO' is approved and certtfied for

acrobatics

II".

11".

Due

1

in

These operating instructions must be added to the flight manual and contain special instructions valid for acrobatic operations. Main modifications to the "normal" Right manual are contained in the following sections:

-

Airworthiness group (11. 1)

"?

-

Permitted operating conditions (11.

-

Minimum equipment (11.

-

Maximum speeds (11. 4)

-

Flight envelope (1 1.5)

-

Load scheme (11.6)

The following items were modified in the maintenance handbook with respect to the acrobatic version:

-

Weights and moments of control surfaces (VI)

References to the flight handbook for acrobatics are shown on the affected pages of the "standard" flight manual.

Rev.

4,

16.10.2003

3)

2)

FAA

I

Issue

FLIGHT

1.

6

LbmIpmn

ThellTWIN

T-tall,

and upper surface airbrakea. Thlr sallplanr Glass flbre wnrtruotlon.

It Is designed for training, hlgh performance end slmple eerobstlc

flylng.

MANUAL

1111

ib

nnsd

wlth r nonretractable tandem undercarriage

ir

monulaotured using the latest techniques In industrial

GROB

a hlgh performance two seater

G

103

sailplane

wlth a

8

T.durlul

&M

Len(lth

Helght

A.pect Ratlo 17.1 Maxfmurn Wlng Loading

t

N.

Operating

II.1-9

DN:

17.6 m

8,1810

1

,55m

Certification.

21.29

worthiness Requirements

(57.4lt.)

(26,8ft)

(5,

1

ft)

limitations

Wlng Arm 17.8 rn'

Maxlmum Flying Welght

:

,

asis: 14 CFR Sections 21.23 and

effective 1 February 1965; and Joint Air-

for

Powered Sailplanes (JAR-22),dated

The

plane

I8

lbmwd

1

VFR

2.

Glmplr

11.

3

1.

2

2.

2

3.

Full Hamem Strap* In front

4.

6.

8.

~llght Limlta

7. Fllght

Day

AomWlca

Uinhuaa~

Alr apwd lndlcaton rerdlng to

Attimeten.

Parachute or Loadlng llmlt plaque In front and back cockpit.

IManual

(ar:

(Lwpa,

bad

cwhlon at leut 7 cm

plaque.

Wl

~d

turns,

3W

badc

Lazy

kmlhr

codcplt.

(3

Qlgl

5

0

kg

(1279

32,

(6,

6

68

ibs)

kg/mg

IbsIfi.')

k

Sailplanes and

1

April 1980.

elght, Cbdelle and

(182

kts,

187 mph)

inch) thldc

n

f

or

each

occupant.

f'.''

.

17

th

march

L

1982

FLl

GHT

777170 km/h=42-92 kts.48- 105 170-250 km/h=92-135 kts:105- 155 at 250 km/h=135 kts: 155

at

95 km/h= 51 kts=' 59

Installation Errors

-1

MANUAL

Ii.

4

#nmdmm

Maximum speed Maximum permitted speed in rough alr

Maximum winch iaund? speed Maxlmum ~emthw speed

Conditions in rough air are similar to those encountered in rotors,

clouds, whirlwinds and when overfiylng mountain ranges. Manoeuvring speed is the maximum speed at whlch full control deflec-

tions may be used. At maximum speed (VNE) the control deflections

-.should be True airspeed

altitude.

Altitude (ft) 0-6500 10000 13000 16500 19001

VNE

Air

in

calm air

(indicated knote) 135 128 121 115 109 (indicated

speed indicator markings

GR08

~.

sp..d.

permitted

. . . .

Manoeuvring

restricted

VNE

to

ie

decreases according to following table.

km/h)

G

103

,

.

speed

.

113

of the lull range.

higher

mph

m

fecommended minimum aPv. speed)

~h~

pitot head in the tail tin, statlo vents side of the fuselage between the two seats. Uslng a calibrated ASi the position error la not ~reater than

1

kt or

or

11.

5

FlIW

The saiipiane daelQn limit load fsctore ere 8s lollow8: At manoeuvring speed

At

VNE

(Brakes closed and calm sir)

indicator must

1.2

mph. A calibration ouwe is therefore not necessary.

wwbw.

+ +

5.3

4.0

'be

-

-1.5

.

VNE

-

250

kmlh

(135

kts,

155

mph)

Vg

-

170km/h(92k

V

-

170

kmlh

VW

-

120

VT

-

170

than

indicated airapeed at

250 237 225

mph

mph-

h

connected to the following sources:

2.85

(

kmlh

(

kmlh

(

-'Grern

YUl0w

-

Red line(max. Speed)

-

yellow triangle

ts,

105mph)

92

kls,

105

66

kts.

92

kts,

arcfiormal range arc(caution range

74

105

213

f

2

rnph) mph)

mph)

kmlh

-

202

17

th march 1982

FLIGHT

MANUAL

GROB

G

103

tl

Empty

Maxlmwn qewltted wight of non iiftln~ parts

/

The approved range of cenlre of gravity posliona during lllght is

1

li

A?;

ths

I

The

.

payload dMrkwtion rpscltied in the loadlng

,

Th. exact posltlon of c@lcuiated eocordlng to41

weight

Maximum flying weight .

260

mm

(10.24

P.

e uivalent to

a(ltitude: incidence. board of

datum line

spprovd

Mkimum load In Mulmum Maximum load In

lo&

.

e

lnohes) to

24.7%

I8

centre

ot grsvity rango

ih.

hont

In

ihr

the

..

.,

.

about

480

mm

(15.11

to

43.5%

of the

Uudront adge ot

the

centre

5.

rul

lront

brdc

wnl

wat

for

of

all

.

380

kg(837,7

.

580 kc(1278,67

400 kg(881 ,a4

indzes) behind the

M.A.c.'~~

the wing.

600:Z

tho

wlng

st

the

dng

does

not gel exceeded by the

plan

11.8.

gravlty

lllght

.

. .

at

flying WiQht can be

.

70

kg

.

110

kg

110

kg

lbs)

datum anele.

root.

(154

ibs)

(242

ibs)

(242

ibs)

ibs

Maximum 1o.d In

The

maximum flying weight of

must

Trim

not

be

weights must be ueed at

in front

~u'

baggog.

exceeded.

of

stick

the front seat load

(

154

lbs

).

See page

comp~~t

580

bulkhead

18

lower

to compensate

14.

10

.

kg

(1278,67

the

than

suspensions

70

kg

(

22

kg

lbs)

if

-

Grob G 103 TWIN II, G 103A TWIN II ACRO Flight Manual

Specifications and Main Features

Frequently Asked Questions

User Manual