DG Flugzeugbau LS8-s Technical specifications

Flight Manual LS8-s and LS8-sb Contents
Edition: June 2016 Revision 5 TN 8024 0-1
0 M
ANUAL C ONTENTS
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
Rev.
no. Pages affected Description Date EASA Approval
1 0-1,0-2,0-3, 0-4, 0-5,
4-15, 4-27, 4-28, 4-32,
7-2, 7-3
TN8019, wheel brake
actuated by airbrake handle Feb. 2011 13.10.11
2 Title page, 0-1 ÷ 0.3, 0-
5, 4-4, 4-9, 7-2, 7-3, 7-
5, 7-13a, 7-14
ÄM LS8-1, Miscellaneous
improvements from
ser. No. 8527 on
Dezember
2011 14.02.12
3 0-1, 0-3, 0-5, 4-8, 7-6 TN8021 small tailwheel January
2015 24.02. 2015
4 0-1, 0-5, 9-5 TN DG-G-11 NOAH
Improvements May2015 7.07. 2015
5 0-1, 0-2, 0-3, 0-5, 1-4,
2-12, 4-24, 7-14 TN 8024 Manual revision June 2016 5.08. 2016

Flight Manual LS8-s and LS8-sb Contents
Edition: June 2016 Revision 5 TN 8024 0-2
0.2 List of Effective Pages
Chapter Page Edition Edition Edition Edition
0 Titel page April 2005
Warnings April 2005
0-1 See log of revisions
0-2 See log of revisions
0-3 See log of revisions
0-4 See log of revisions
0-5 See log of revisions
0-6 April 2005
1 1-1 April 2005
1-2 April 2005
1-3 April 2005
1-4 April 2005 June 2016
1-5 April 2005
2 2-1 April 2005
2-2 April 2005
2-3 April 2005
2-4 April 2005
2-5 April 2005
2-6 April 2005
2-7 April 2005
2-8 April 2005
2-9 April 2005
2-10 April 2005
2-11 April 2005
2-12 April 2005 June 2016

Flight Manual LS8-s and LS8-sb Contents
Edition: June 2016 Revision 5 TN 8024 0-3
0.2 List of Effective Pages continued
Chapter Page Edition Edition Edition Edition
3 3-1 April 2005
3-2 April 2005
3-3 April 2005
3-4 April 2005
3-5 April 2005
3-6 April 2005
3-7 April 2005
3-8 April 2005
3-9 April 2005
3-10 April 2005
3-11 April 2005
3-12 April 2005
3-13 April 2005
4-1 April 2005
4-2 April 2005
4-3 April 2005
4-4 April 2005 Dec. 2011
4-5 April 2005
4-6 April 2005
4-7 April 2005
4-8 April 2005 Jan. 2015
4-9 April 2005 Dec. 2011
4-10 April 2005
4-11 April 2005
4-12 April 2005 June 2016
4-13 April 2005
4-14 April 2005
4-15 April 2005 Feb. 2011
4-16 April 2005
4-17 April 2005
4-18 April 2005
4-19 April 2005
4-20 April 2005

Flight Manual LS8-s and LS8-sb Contents
Edition: June 2016 Revision 5 TN 8024 0-5
0.2 List of Effective Pages continued
Chapter Page Edition Edition Edition Edition
7 7-1 April 2005
7-2 April 2005 Feb. 2011 Dec. 2011
7-3 April 2005 Feb. 2011 Dec. 2011
7-4 April 2005
7-5 April 2005 Dec. 2011
7-6 April 2005 Jan. 2015
7-7 April 2005
7-8 April 2005
7-9 April 2005
7-10 April 2005
7-11 April 2005
7-12 April 2005
7-13 April 2005
7-13a Dec. 2011
7-14 April 2005 Dec. 2011 June 2016
8 8-1 April 2005
8-2 April 2005
8-3 April 2005
8-4 April 2005
8-5 April 2005
8-6 April 2005
8-7 April 2005
8-8 April 2005
8-9 April 2005
8-10 April 2005
8-11 April 2005
9 9-1 April 2005
9-2 April 2005
9-3 April 2005
9-4 April 2005
9-5 April 2005 May 2015
9-6 April 2005

Flight Manual LS8-s and LS8-sb General
Edition: June 2016 Revision 5 TN 8024 1-4
1.4 D ESCRIPTIVE AND TECHNICAL D ATA
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.
LS8-s: Rear fuselage constructed from glasfibre-reinforced plastic, no
engine compartment.
LS8-sb: Rear fuselage constructed from carbonfibre-reinforced plastic,
with engine compartment.
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 Limitations
Edition: June 2016 Revision 5 TN 8024 EASA appr. 2-12
2.12 Further Limitations
2.12.1 O PERATING P LACARDS FOR L IMITATIONS
DG Flugzeugbau GmbH
Type: LS8-xx Serial No.:_______
Data Placard
Airspeed Limits: km/h Kt MPH.
Winch launch/Auto tow 140 76 87
Aero tow 195 105 121
In rough air 195 105 121
Never exceed (VNE) 280 151 174
m ft kg lbs
Max. Take-off Mass *) 15 42 525 1157
Max. Take-off Mass *): 18 59 575 1267
*) including water ballast
Aerobatic manoeuvres not approved
Weight Limitations
Maximum Cockpit Load ....max.______kg/lbs
Minimum Cockpit Load
with tail battery, tail tank full min. ______kg/lbs
with tail battery, tail tank empty min. ______kg/lbs
without tail battery, tail tank full min _____kg/lbs
without tail battery, tail tank empty min._____kg/lbs
Lighter pilots must compensate lack of weight as
suggested in Flight Manual
near airspeed indicator, if not marked
on ASI
at baggage compartment
under instrument panel
cover
Maximum baggage weight 5kg (11 lbs)
(Soft items only)
m ft km/h mph Kt.
Up to 2000 ( 6500) - 280 174 151
Up to 3000 ( 9800) - 266 165 144
Up to 4000 (13100) - 253 157 137
Up to 6000 (19700) - 227 141 122
Up to 8000 (26200) - 202 126 109
Up to 10000 (32800) - 179 111 97
Up to 12000 (39400) - 156 97 84
xx= variant
-s or –sb
a
t
right hand cockpit wall
MINIMUM COCKPIT LOAD: kg / lbs
with tail battery, tail tank full min. ________
with tail battery, tail tank empty min. ________
without tail battery, tail tank full min. ________
without tail battery, tail tank empty min. ________

Flight Manual LS8-s and LS8-sb Normal Procedures
Edition: June 2016 Revision 5 TN 8024 EASA appr. 4-12
4.5 N ORMAL P ROCEDURES
4.5.1
C OCKPIT -C HECKLIST
LS8-s and -sb Checklist
This sailplane must be operated in
compliance with operating limitations
stated in the form of markings,
placards and EASA approved Flight
Manual.
1. Main pins secured?
2. Elevator secured?
3. Winglets secured?
4. Check controls
5. Tail fin valve operation checked?
6. When using water ballast, then
always in wing and tail!
7. Check loading conditions
8. Check tail dolly removed?
9. Fasten seat belt harness
10.Fasten parachute and connect
parachute static line
11.Lock air brakes
12.Check trim position
13.Check release system
14.Lock canopy

Flight Manual LS8-s and LS8-sb Systems
Edition: June 2016 Revision 5 TN 8024 7-14
7.10 V ARIOUS E QUIPMENT
7.10.1 E
XPENDABLE B ALLAST (T RIM W EIGHTS )
Expendable ballast to compensate pilot weight below Minimum Cockpit
Load may be fitted in front of rudder pedals and secured with knurled nut.
7.10.2 A
DDITIONAL B ATTERIES
Vertical Tail Fin Battery
Optional. The tail fin battery must be equipped with a main fuse according to
drawing 3BR-199. Measurements L 155mm * B 35mm * H 100mm (over
terminals), 6V 7.2Ah, 2 cells required.
From ser.no. 8527 on (ÄM LS8-1): If an optionally battery will be installed
in the fin the locking bow (part 10L35 made from piano wire) must be
removed. The locking bow prevents the installation of a battery and serves as
indicator if a battery is installed, as its ends are visible from the outside.
Battery in Baggage Compartment
Optional. Installation on landing gear box, see Maintenance Manual section
4.8. The battery must be equipped with an appropriate main fuse!
Measurements identical to forward seat battery with identical holder or for
instance Dittel ZT 092, 12V 6.5Ah complete with holder.
7.10.3 O XYGEN S YSTEM
Fiberglas receptacle at left main bulkhead for 3 or 4 Litre oxygen bottles of
100 mm <3.94 in> in diameter.
After permanent installation of an oxygen system according to its
manufacturers instructions by an adequately licensed repair shop, the
sailplane including oxygen system must be inspected (Weight and Balance,
Loading Instructions).
When using a removable oxygen unit, its weight must be counted as useful
load.
7.10.4 E MERGENCY L OCATOR T RANSMITTER (ELT)
Permanent installation according to Maintenance Manual chapter 11 and to
manufacturers instructions. Possible installation location in rear portion of
the baggage compartment, remote control from instrument panel necessary.
After installation, cockpit loading limit values must be checked according to
Maintenance Manual chapter 5.
Caution: When installing a 406 MHZ ELT proceed according to TN DG-G-08.