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