DG Flugzeugbau LS8-s Especificaciones técnicas

Flight Manual LS8-s and LS8-sb

Contents

Edition: June 2016 Revision 5 TN 8024 0-1

0 M

ANUAL

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

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

PERATING

LACARDS FOR

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

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

ROCEDURES

4.5.1

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

QUIPMENT

7.10.1 E

XPENDABLE

ALLAST

RIM

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

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

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

OCATOR

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.

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