Rolladen-Schneider LS8-s Technical specifications

DG Flugzeugbau GmbH
Otto-Lilienthal-Weg 2 / Am Flugplatz •• D-76646 Bruchsal •• Germany
Postfach 1480, D-76604 Bruchsal •• Germany
Tel. [phone] •• Fax [phone] •• eMail: [email protected]
Spareparts and Materials: Tel. [phone] •• eMail: [email protected]
http://www.dg-flugzeugbau.de
FLIGHT MANUAL
FOR THE
SAILPLANES
LS8-s AND LS8-sb
Type: LS8-a
Versions: LS8-s
LS8-sb
TCDS No.: EASA TCDS No. A.047
Serial-No.: __________________________
Registration Signs: __________________________
Edition: April 2005
Pages marked “EASA-approved“ are approved by:
(Signature)
(Authority)
(Stamp)
(Date of Approval) 19.August 2005
This sailplane is to be operated in compliance with information and
limitations contained herein.
Warnings
•Each sailplane is a highly complex unit. It may threaten your health or
endanger your life, when being used improperly or outside its approved
operating range or being maintained improperly.
•Before using the plane, study all manuals thoroughly. Especially take note of
warnings, cautions and notes provided.
•Never fly without a thorough pre-flight check according to the Flight
Manual!
•Always stay within safety altitudes.
•Always make sure to be able to perform a safe out landing.
•Respect stall speeds. Always use a safety margin above the stall speed
related to the flight condition, especially at low altitudes and in the
mountains.
•Only use battery chargers specified in the Manual.
•Do not work on control systems apart from lubrication.
•Maintenance and repairs should only be accomplished by the manufacturer
or at certified repair stations rated for these types of work. A list of stations
with experience at LS aircraft may be obtained from DG Flugzeugbau.
•Even if no annual inspections are required in your country, have your aircraft
checked annually, see Maintenance Manual chapter 2
.
•Please pay attention to our web-site www.dg-flugzeugbau.de. There you will
find the latest technical notes and service information for your glider:
www.dg-flugzeugbau.de/tech-mitteilungen-e. The „DG Pilot Info“ informs
you immediately by e-mail about the publication of new technical notes and
service information. If you don’t receive this info service, please send a mail
to [email protected] with subject "DG Newsletter please" to
receive this service free of charge.

Flight Manual LS8-s and LS8-sb Contents
Edition: April 2005 0.1
0 MANUAL CONTENTS
0.1 Log of Revisions
Any revision of the present manual, except actual weighing data, must be
recorded in the following table and in case of approved Sections endorsed by the
responsible airworthiness authority.
The new or amended text in the revised page will be indicated by a black vertical
line on the right margin, and the revision No. and the date will be shown on the
bottom left hand of the page
Revision No. Chapter Pages Date of Issue Approval
Signature
Date of EASA
Approval
Flight Manual LS8-s and LS8-sb Contents
Edition: April 2005 0.2
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0 Titel page April 2005
Warnings April 2005
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Edition: April 2005 0.4
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Edition: April 2005 0.5
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Flight Manual LS8-s and LS8-sb Contents
Edition: April 2005 0.6
0.3 TABLE OF CONTENTS
Section Chapter Approval Status
1 General........................................................................... not approved
2 Limitations ............................................................................ approved
3 Emergency Procedures ........................................................ approved
4 Normal Procedures .............................................................. approved
5 Performance ................................................................partly approved
6 Weight and Balance ....................................................... not approved
7Description of Systems ................................................... not approved
8 Handling, Servicing and Maintenance ........................... not approved
9 Supplements.................................................................... not approved

Flight Manual LS8-s and LS8-sb General
Edition: April 2005 1-1
1 General
Contents of Chapter 1: Page
1 General....................................................................... 1-1
1.1 Introduction ............................................................. 1-2
1.2 Certification Basis..................................................... 1-2
1.3 Warnings, Caution and Notes (Definitions) ............... 1-3
1.4 Descriptive and Technic al Data ................................. 1-4
1.5 Three View Drawing ................................................. 1-5
Flight Manual LS8-s and LS8-sb General
Edition: April 2005 1-2
1.1 INTRODUCTION
This sailplane Flight Manual has been prepared to provide pilots and
instructors with information for the safe and efficient operation of the
LS 8-s and LS8-sb sailplanes.
This manual includes the material required to be furnished to the pilot by
JAR Part 22. It also contains supplementary data supplied by the sailplane
manufacturer.
The LS8-s or LS8-sb is a high performance sailplane, not a basic trainer.
However excellent its design, construction, performance and handling
qualities, flying it requires a skilled pilot, who observes the limitations and
recommendations set out in this manual.
1.2 CERTIFICATION BASIS
These sailplanes with the type designation LS8-s or LS8-sb have been
approved by EASA in accordance with JAR-22 dated 28. October 1985,
(Change 5).
The EASA-Type Certificate No. A.047 for LS 8-s and LS8-sb has been
issued on 19.August 2005.
Category of Airworthiness: "Utility".

Flight Manual LS8-s and LS8-sb General
Edition: April 2005 1-3
1.3 WARNINGS,CAUTIONS AND NOTES (Definitions)
The following definitions apply to warnings, cautions and notes used in the
Flight Manual
Warning: Means that the non-observation of the corresponding
procedure leads to an immediate or important
degradation of the flight safety.
Caution: Means that the non-observation of the corresponding
procedure leads to a minor or to a more or less long
term degradation of the flight safety.
Note: Draws the attention to any special item not directly related to
safety, but which is important or unusual.
Flight Manual LS8-s and LS8-sb General
Edition: April 2005 1-4
1.4 DESCRIPTIVE AND TECHNICAL DATA
The LS 8-s and LS8-sb are single-seater sailplanes with carbon fibre wing
shell, winglets, T-tail, wing and vertical tail fin water ballast systems,
retractable and sprung landing gear, and upper wing surface air brakes.
They may be operated in 15m or 18m span and winglets in both versions.
The fuselage structure of LS8-s and LS8-sb is different, because the
LS8-sb is prepared for later engine installation. Otherwise both planes are
structurally identical.
These sailplanes have been produced using the latest technology of
industrial fibre design (Glass-, Aramid- and Carbon fibres).
Models LS8-s and LS8-sb are designed for competition flights – high
performance combined with excellent handling characteristics.
Wing span 15 m 49,2 ft 18 m 59,6 ft
Length 6,74 m 22,11 ft 6,74 m 22,11 ft
Height 1,33 m 4,36 ft 1,33 m 4,36 ft
MAC 0,700 m 2,30 ft 0,634 m 2,08 ft
Wing Area 10,5 m² 113,0 sq. ft 11,40 m² 122,9 sq. ft
Wing aspect ratio 21,43 21,43 28,38 28,38
Maximum gross weight 525 kg 1157 lbs 575 kg 1267 lbs
Max. wing loading 50 kg/m² 10,2 lbs/sq. ft 50,4 kg/m² 10,3 lb/sq. ft

Flight Manual LS8-s and LS8-sb General
Edition: April 2005 1-5
1.5 THREE VIEW DRAWING
Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-1
2 LIMITATIONS
Contents of Chapter 2:
2 Limitations ................................................................. 2-1
2.1 Introduction ............................................................ 2-2
2.2 Airspeeds (IAS) ...................................................... 2-3
2.3 Airspeed Indicator colour markings .......................... 2-4
2.4 Mass (Weight) ......................................................... 2-5
2.5 Centre of gravity limits ............................................. 2-6
2.6 Approved manoeuvres ............................................. 2-7
2.7 Manoeuvring load factors ........................................ 2-7
2.8 Kinds of operation ................................................... 2-8
2.9 Flight crew .............................................................. 2-9
2.10 Minimum equipment .............................................. 2-10
2.11 Aero tow, winch- and auto tow launching ............... 2-11
2.12 Other limitations .................................................... 2-12
2.12.1 Operating placards for limitations ........................ 2-12

Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-2
2.1 INTRODUCTION
Section 2 includes operating limitations, instrument markings and basic
placards necessary for safe operation of the LS8-s and LS8-sb sailplanes,
their standard systems and standard equipment.
The limitations included in this section have been approved by EASA.
The LS 8-s and LS8-sb sailplanes have been designed and approved
according to JAR 22 requirements. Factors of safety (relation of ultimate
loads to permissible maximum loads occurring during operation) are 1.5
only. Thus, ultimate loads will be reached, when exceeding permissible load
factors by 50%. When exceeding permissible speeds, the safety reserve is
much lower.
Maximum loads should never be caused by the pilots control surface
deflections – they result from severe turbulence and the necessary control
surface deflections to retain the desired flight attitude. Severe turbulence
according to airworthiness requirements includes wave rotors,
cumulonimbus clouds, dust devils and turbulence when crossing mountain
ridges in strong winds.
Warning: Therefore, operational limits, - speeds and load factors - must be
adhered to !
Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-3
2.2 AIRSPEEDS (IAS)
Maximum permissible
speed
IAS
km/h Kt MPH
Remarks
VNE
Never exceed speed in
calm air and up to an
altitude above MSL of:
2000 m (6500 ft) 280 151 174
Do not exceed this speed in any
operation and do not use more than 1/3
of control deflection.
3000 m (9800 ft) 266 144 165
4000 m (13100 ft) 253 137 157
6000 m (19700 ft) 227 122 141
8000 m (26200 ft) 202 109 126
10000 m (32800 ft) 179 97 111
12000 m (39400 ft) 156 84 97
VRA Rough air speed 195 105 121
Do not exceed this speed except in calm
air and then only with caution.
Examples of rough air are lee wave
rotor, thunderclouds, dust devils and
turbulence when crossing mountain
ridges in strong winds.
VA Manoeuvring speed 195 105 121
Do not make full or abrupt control
movement above this speed, because
under certain conditions the sailplane
may be overstressed by full control
movement.
VW Maximum winch- launching
speed
140 76 87 Do not exceed this speed during winch-
or auto-tow launching.
VT Maximum aero towing
speed
195 105 121 Do not exceed this speed during aero
towing.
VL0 280 151 174
Maximum landing gear
operating speed
Do not extend or retract the landing gear
above this speed.
Maximum air brake
extension speed
280 151 174

Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-4
2.3 AIR SPEED INDICATOR COLOUR MARKINGS
Airspeed indicator markings and their colour-code significance are shown
below.
Marking (IAS) range or
value
Significance
Green arc 97-195 km/h
52-105 Kt
60-121 MPH
Normal operating range
(Air brakes retracted)
Yellow arc 195-280 km/h
105-151 Kt
121-174 MPH
Manoeuvres must be conducted with caution
and only in smooth air.
Red line 280 km/h
151 Kt
174 MPH
Maximum speed for all not restricted operations
Yellow
triangle
95 km/h
51 Kt
59 MPH
Recommended minimum approach speed at
maximum weight without water ballast
For an example of airspeed indicator colour marking see Maintenance Manual
chapter 8.
Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-5
2.4 MASS (WEIGHT)
Maximum take-off masses
Maximum take-off mass (15m wing span) .................... 525 kg <1157 lbs>
Maximum take-off mass (18m wing span) .................... 575 kg <1267 lbs>
Important Note:When landing on airfields, water ballast should
preferably be dumped. Before outlandings, water
ballast must always be dumped. Pilots are advised
against landing with maximum all-up mass.
LS8-s: Maximum weight of non-lifting parts ......... 255 - 263 kg <562 – 580 lbs>
LS8-sb: Maximum weight of non-lifting parts ......... 280 - 288 kg <617 – 635 lbs>
Value must be determined according to table in Maintenance Manual, chapter 5,
related to empty mass and empty mass C.G. position. The term “non-lifting”
parts includes the following:
•Fuselage (with permanently installed equipment, canopy, and main pins)
•Cockpit load (Pilot + parachute + equipment <for instance tail fin battery
in baggage compartment instead of in tail fin>)
•Horizontal tail
Tail fin water ballast and tail fin battery in tail fin do not count for “non-lifting”
parts, but for maximum all-up weight.
continued next page

Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-6
2.6 MASS (WEIGHT)(continued)
Water ballast in wings
(depending on loading conditions)..........................max. 190 kg <419 lbs>
Warning: Wing water ballast must always be compensated by tail fin
water ballast according to table 4.7.10.5 .
Tail fin water ballast (depending on wing water ballast)
LS8-s with integral tail fin tank ........................... max. 12 kg <26,5 lbs>
LS8-sb with integral tail fin tank ............................. max. 7,5 kg <16,5 lbs>
Note: Due to production tolerances, the tail fin tank can take
some more water. Therefore the actually filled amount
of water must be positively checked!
Maximum mass in Baggage Compartment: ............ max. 5.0 kg <11 lbs>
Maximum mass of all instrument panel installations
..... max. 6.7 kg <14.8 lbs>
Warning: The vertical tail fin battery may be removed from the tail fin to
reduce Minimum Cockpit Load (See entries section 6.2 for
possible combinations !)
Flight Manual LS8-s and LS8-sb Limitations
Edition: April 2005 EASA appr. 2-7
LS8-s / LS8-sb Inflight C.G. position
300
350
400
450
500
550
600
260 280 300 320 340 360 380 400 420
Inflight C.G. position [mm aft of Datum]
All-up Weight [kg]
15m
18m
1
3
2
4
567
2.5 CENTRE OF GRAVITY LIMITS
Datum Point: Leading edge of wing at root, when under side of fuselage boom
is placed horizontal.
Maximum allowable forward C.G.
at maximum mass: 280 mm <11.024 in> aft of Datum
Maximum allowable rearward
C.G. position: 400 mm <15.748 in> aft of Datum
Warnung: Vertical tail fin water ballast MUST be used to compensate
C.G. displacement due to wing water ballast, surplus may be
used to compensate pilot weight above Minimum Cockpit Load
!
Maximum amounts see “Normal procedures” sections 4.7.10.4
and 4.7.10.5/6.