Grob G 103 TWIN II Technical specifications

GROB-WERKE GMBH & CO. KG
Unternehmensbereich
Burkhart Grob Flugzeugbau
8939 Mattsies
Am Flugplatz
Telefon
. 08268/411
Telex 539 623'
FLIGHT MANUAL
This manual must be carried on board of the sail-
plane at all times.
This Flight manual is FAA approved for
U. S, regi-
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:
.. .. . .. . . . .. . Factory Serial No. : . .
--
Owner:
German edition of operating instructions are approved
under
§ 12 (1) 2. of LuftGerPO.
Published September 1981.
LBA approved
Date 17th march 1981
Approval of translation has been done by best knowledge
and judgement
- in any case the original text in German
lancruane is authoritative.
N228BG
33995-
K-228
Utah Soaring Association

FLIGHTHANDBOOKGROB G 103
I
1.1. Updates
Page
1,la,
8,
10,12,14
17,19
I,la,12,
21,
5a
1, la,5a
1,la,5a
No. 3730 and June 1982
subsequent I
Automatic connection I
of elevatorand sorina I
. "
trim system os SIN
1 26, Sept, 84
33879 ario s-bseq~ent
MSB 315-65 16.10.2003
OSB 315-66 16.10.2003
Rev. 4, 16.10.2003

' FLIGHT HANDBOOK GROB G 103 I a
List of effective Daaes
(*) only for GROB G 103A TWIN I1 ACRO
FAA Issue

:LIGHT MANUAL GROB G 103 . . 2
I. 2 Contents
page
I. General
I. 1 Log of revisions 1, la
I. 2 Contents (LBA approved pages: 2,3
1, la and 6 through 31, except
9 and 22)
I, 3 Photograph
I. 4 Drawing
I. 5 Description
Operating limitations
Airworthiness Group
6
Permitted operating conditions k. 6
Minimum equipment 6
Maximum Speeds 7
Flight envelope 7
Weight limits 8
Centre of gravity position 8
Load scheme, weighing report 8, 9
Tow hooks and cable length 10
Weak link strength 10
Tire pressure 10
Crosswinds
10
Placards, control markings and 11,12, 12a
instrument markings 13, 14, 15
111. Emergency procedures
111. 1 Recovery from the spin 16
111. 2 Emergency canopy jettison and 16
exit.
111. 3 Miscellaneona (Rain, ice, 16
groundloops)
September 1981.

FLIGHT MANUAL GROB G 103 3
IV. Nonnal procedures
IV. 1 Godxplt and controb (Plcture)
IV.
2 Dally prefllghl Inspection
iV.
3 Control &edw before toke ofl
IV.
4 Take off
1V.
5 Free flight
IV.
6 Slow flylng and stalla
IV.
7 Hlgh speed fllght
IV. 8 Simple Aerobatics
IV. 9 Approach and landing
IV.10 Storage
V. App.ndI-8
V. 1 Fllght performance
V. 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

1
FLIGHT HANDBOOKGROB G 103
5a
If the fuselage reinforcement according to OSB 315-66 hadnotbeen Dertormedthe
following isapplicable:
Theglider GROB G 103A"WIN
I1 ACROis derivedfrom theGROB G 103"WIN II". Due
to structuralreinforcementsthe'TWIN
II ACRO is approved inthe category"Acrobatic".
According to MSB 315-65 only "simpleaerobatics" (Loop. Turn, Lazy Eight, Chandelle, Spin)
is approved (referto 11.2 and IV.9)
The Flight Handbookfor Aerobatics
-
GROBG 103A "WIN II ACRO"
Edition February 1984
f LBAapproved
is unvaiid accordingto MSB 315-65and must be removedfromthe Flight Handbook.
Ifthe fuselage reinforcement according to
OSB 315-66 hadbeen performed the
following isapplicable:
The aiider GROB G 103A 'TWIN
II ACR0is derived from the GROB G 103"TWIN 11". Due 1
to stnctural re.nforcements the "WIN II ACRO' is approved and certtfied for acrobatics in
conlunction with [hefollowingvalld operating instructions:
FIght handbookfor acrooatics,
GROBG 103A
" Wih II ACRO.
edition February 1964,
LBAapproved.
These operating instructions must be added to the flight manual and contain special
instructions valid for acrobatic operations. Main modificationsto the "normal" Right manual
are contained inthe followingsections:
- Airworthinessgroup (11. 1)
"? - Permittedoperatingconditions (11. 2)
- Minimumequipment (11. 3)
- Maximumspeeds (11. 4)
- Flightenvelope (11.5)
- Load scheme (11.6)
The following items were modifiedinthe maintenance handbookwith respectto the acrobatic
version:
I
- Weightsand momentsof controlsurfaces(VI)
I
Referencesto theflight handbookfor acrobatics are shown on the affected pages ofthe
"standard"flight manual.
I
Rev. 4, 16.10.2003
FAA Issue

FLIGHT MANUAL GROB G 103
8
1. 6 LbmIpmn
ThellTWIN 1111 ib a hlgh performance two seater sailplane wlth a
T-tall,
nnsd wlth r nonretractable tandem undercarriage
and upper surface airbrakea.
Thlr sallplanr
ir monulaotured using the latest techniques In industrial
Glass flbre wnrtruotlon.
It Is designed for training, hlgh performance end slmple eerobstlc
flylng.
T.durlul
DN:
&M 17.6 m (57.4lt.) Wlng Arm 17.8 rn'
Len(lth
8,1810 (26,8ft)
A.pect
Qlgl f'.''
Helght 1 ,55m (5, 1 ft) Maxlmum FlyingWelght
5 0 kg
(1279 ibs)
Ratlo 17.1 MaxfmurnWlng Loading
32, 6 kg/mg
t (6, 68 IbsIfi.')
N. Operating limitations : k
II.1-9 ,
Certification. asis: 14 CFR Sections 21.23 and
21.29 effective 1 February 1965; and Joint Air-
worthiness Requirements
for Sailplanes and
Powered Sailplanes (JAR-22),dated
1 April 1980.
The plane I8 lbmwd (ar:
1 VFR Day
2. Glmplr AomWlca (Lwpa, Wl turns, Lazy elght, Cbdelle and
11. 3 Uinhuaa~
1. 2 Alr apwdlndlcatonrerdlng to 3W kmlhr (182 kts, 187 mph)
2. 2 Attimeten.
3. Full HamemStrap* Infront ~d badc codcplt.
4. Parachuteor bad cwhlon at leut 7 cm (3 inch)thldc f or each .
6. Loadlng llmlt plaque Infront and back cockpit. occupant.
8. ~llghtLimlta plaque.
7. Fllght IManual
n
17 th march 1982
L

FLl GHT MANUAL GR08 G 103 -
~.
. .
Ii. 4 #nmdmm sp..d.
Maximum permitted
speed in calm air . . . . VNE - 250 kmlh (135 kts, 155 mph)
Maximum permitted
speed in rough alr
, . . Vg - 170km/h(92k ts, 105mph)
Manoeuvring speed
V - 170 kmlh ( 92 kls, 105 rnph)
Maximum winch iaund?speed
VW - 120 kmlh ( 66 kts. 74 mph)
Maxlmum ~emthwspeed
. VT - 170 kmlh ( 92 kts, 105 mph)
Conditions in rough air are similar to those encountered in rotors,
clouds, whirlwinds and when overfiylng mountainranges.
Manoeuvringspeed is the maximum speed at whlch full control deflec-
tions may be used. At maximum speed (VNE) the control deflections
-.should be
restricted to 113 of the lull range.
True airspeed
ie higher than indicated airapeedat
altitude.
VNE decreases according to following table.
Altitude (ft) 0-6500 10000 13000 16500 19001
VNE (indicated knote) 135 128 121 115 109
(indicated
km/h) 250 237 225 213 202
Air speed indicator markings
777170 km/h=42-92 kts.48- 105
mph
-'Grern arcfiormal range
170-250 km/h=92-135 kts:105- 155
mph- YUl0w arc(caution range
at 250 km/h=135 kts: 155
mph
- Red line(max. Speed)
at 95 km/h= 51kts=' 59 m h - yellow triangle
fecommended minimum aPv. speed)
Installation Errors
-1
~h~ indicator must
'be connected to the following sources:
pitot head inthe tail tin, statlo vents side of the fuselage between the
two seats.
Uslng a calibrated ASi the position error la not ~reaterthan
f 2 kmlh
or
1 kt or 1.2 mph. A calibration ouwe is therefore not necessary.
11. 5 FlIW wwbw.
The saiipiane daelQnlimit loadfsctore ere 8s lollow8:
At manoeuvring speed
+ 5.3 - 2.85
At VNE + 4.0 -1.5
(Brakes closed and calm sir)
17 th march 1982

FLIGHT MANUAL GROB G 103 tl
Empty weight . e .. ., . about 380 kg(837,7 lbs)
Maximum flying weight . . 580 kc(1278,67 lbs)
Maxlmwn qewltted wight of non iiftln~parts 400 kg(881 ,a4 ibs
/
The approved range of cenlre of gravity posliona during lllght is
1
260 mm (10.24 lnohes) to 480 mm (15.11 indzes) behind the datum
li P. e uivalentto 24.7% to 43.5% of the M.A.c.'~~ the wing.
A?; a(ltitude: incidence.board of 600:Z
anele.
I
ths datum line I8 Uudront adge ot tho wlng st the dng root.
.
The spprovd centre ot grsvity rango does not gel exceeded by the
payload dMrkwtionrpscltied in the loadlng
plan 11.8.
, Th. exact posltlon of the centre of gravlty at flying WiQht can be
c@lcuiatedeocordlngto41
5.
Mkimum loadIn ih. hont rul for all lllght .
. 70 kg (154 ibs)
Mulmum
lo& In ihr lront wnl . . . . 110 kg (242 ibs)
Maximum load In
the brdc wat . . . 110 kg (242 ibs)
Maximum 1o.d In
~u' baggog. comp~~t .
10 kg ( 22 lbs)
The maximum flying weight of 580 kg (1278,67 lbs)
must not be exceeded.
Trim weights must be ueed at the suspensions
in front
of stick bulkhead to compensate if
the front seat load 18 lower than 70 kg
( 154 lbs ). See page 14.
-

FLIGHT MANUAL GROB G 103
0
September 198 1

. .
II. 8 Tow hoot. and cable length
For Aerotow: Nose hook 'E 75' with mod1fication 1-79.
For Wina launch: Safety bad release hook "G
72" or "G 73".
.Minimum herotow cahlc length
40 ~n 1 130 it)
14inimum launch cable length 600 m (1 970 it)
-I)
I I
W~nalaunch and serotow max;1S1: dm , nax lbr
- - .-
11. 11 Tire Praasure
mainwheel
6.00-6 2,5-2,8 bar
norewbeel
260x85 2, 5 bar
, tailwheel 210~6% 2,5 bar
L
11. 12 Cn#rrhcD
The maximum noswindcomponent approvedfoitake ofl and lending.
la 20 kmlh (11 kb. 12 mph).
16th june 1982

-.
FLIGHT MANUAL GROB G 103 11
"' ,. ./ . , i ../ ..: _,*:; . ...., l...,.. , . *I I . ... -
, .,, . . .
,< ... .
11. 13. Placards, control markirigs and instrument
-
markings
(~aximumflying weight 680kg lll~~lbr 1
kmlhr WS mpA
Never exceed VME 250 138 155
VB 170 92 105
-
-
VT 170 Q2 105
1
..
Payload(Pfiot and Parachute)
Minimum in Front cockpit 70kg
154 ib
for all flight
Less must be compensated with
ballast secured in the seat
Maximum load front IlOkg
2421b
The maximum yeight must not be exceeded
both cockpits
r
8impf.-Jrrpcrdr
RoC0mnwnd.d
entry * krn/hr knob mph -
LW 180 W 111
SWI turn 180
87 Ill
Spin
80 43 W
1.
Chdailo 170 91: 106
Required la cards (front and back cockpit)
&
17 th march 1982

I FLIGHT MANUAL FROB G103
12
#
Altitude ift) 10-6500110 000 )1301~0116 500 ( 19 000
VNE (KIAS)
1 I35 I 128 1 121 ( 115 1 109
near aBeed ind.
both cockpits
Front cockpit
Crrpl--lelwmoY-
1
By Canopy release front and back
16th june 1982
mainwheel
noaewheel
tailwheel

FLIGHT MANUAL GROB G 103 1 Za
Rudder
fin
.---. - .
Baggage compartment
lift here
Rudder
near magnetic direction
indicator
17 th march 1982
~~ . ~~ --
Tolal wrgy
compensation tube

FLIGHT MANU4L GROB G 103
13
Cable
release
Pedaladju8tment Alr-vont
Top right of front Top
lefl of front
Instrument panel Instrument panel
17 th march 1982

FLIGHT MANUAL GROB GI03 14
I TRIM WEIGHTS
1 Number 12 11 0 I
Pilotaweight
including
parachute
L
1 Trim weight: 5,6kg (12,31bs)
'3
front cockpit
Ldrhrpdm outside of the fuselage
-
-
--
--
kg
lba
1. Marking wntmlling VH correct tlgglng of UM -Ms.
*
2. Label for tho tow energy tuba.
3. Label for tailplane security
4. Label for tyre pressure
Label for tyre preaaure
6. Red ring round the etatic prdasure port
7. Marking to find the belly boo*
16th june 1982
55-62,4
121-137
62,5-69,g
138-153
70-1
1 o
154-242

FLIGHT MANUAL GROB G103 15
- -
Speed
rnph knob krnih Mark
Significance
~- -- ~
~~ -- - -- ~~
48-105 42-$2 77 -170 Green Arc Norrnai range of
-1
flylng speed
105-155 82-135 170-250 Yeiiow Arc Range of flylng
speeds to be
used with care
at
155 1 35 250 Radial Red Line Maxlrnurn Speed
95 Yellow Triangle Minimum recorn-
men& landing
~eed
I load
17 th march 1982
L+

FLl GHT MANUAL GROB G 103 16
111. Emergency procedures
111. 1. Recovery from the spin
Recovery spin can be accomplished by the standard
recovery procedure:
- Full opposite rudder
- Neutralize stick
- Ailerons should be neutral
- When rotation stops neutralize rudder an pull out gently,
1
! 111. 2. Emergency canopy jettison and exit
- Pull red handles on right and left of canopy full back
simultaneously.
- Push canopy up and away with the left hand.
- Release safety harness.
- Stand up and get out over left or right side depending
on the attitude.
- When using a manual parachute grip release and pull
firmly to full extend after 1-3 seconds.
111. 3. Miscellaneous
Flying in rain, iced wings
There is a noticeable deterioration of flying characte-
ristics by wet,or lightly iced wings, which raises the
stall speed by about
6 knots:
Increase take off and approach speed by
6 knots.
1
Wing dropping
If a wing drops in
a turn or straight flight, leave the
stick neutral and apply rudder against the direction of
rotation.
Groundloops
The aircraft is not prone to ground loop in take off,
If one wing touches the ground or the aircraft changef
direction by more than release cable im-
mediately.
17 th march 1982