2 - Schempp-Hirth

SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Ventus-2a WARTUNGSHANDBUCH / MAINTENANCE MANUAL 

Ventus-2b 

0.1 Erfassung der Berichtigungen / Record of Revisions 

Lfd.Nr. 

Rev.No. 

10 

11 

12 

Benennung 

Reference 

Änderungsblatt Nr. 349-41 

(Ergänzung zu ÄB-Nr. 349-42) 

Versenkte Schwerpunktkupplung 

Ventus-2a, ab Werknummer 130 

Modification Bulletin No. 349-41 

(Supplements to MB 349-42) 

C/G tow release flush with lower surface 

Ventus-2a, S/N 130 and on 

Technische Mitteilung Nr. 349-27 

Höhen- und Seitenleitwerk, Maughmer-Winglets 

- Ventus-2a: wahlweise Werk-Nr. 2 bis 120 – 

Technical Note No. 349-27 

Horizontal and vertical tail unit, 

Maughmer-winglets 

- Ventus-2a: optional S/N 2 through S/N 120 - 

Ergänzung zum Änderungsblatt Nr. 349-31 

Änderung am Stück Werk-Nr. 1 

siehe Rev. 3 

Seite 

Page 

0.2.1 

0.2.2 

5.2.4 

0.2.1 

0.2.2 

1.1 

2.1.2 

2.2.1 

2.3 

5.2.1 

5.2.3 

6.2.2 

6.4.1 

6.4.2 

6.4.3 

6.6.2 

6.7 

Diagr. 1 

Diagr. 6 

0.2.1 

0.2.2 

1.1 

2.1.2 

2.2.1 

2.3 

5.2.1 

5.2.3 

6.2.2 

6.4.1 

6.4.2 

6.4.3 

6.6.2 

6.7 

Diagr. 1 

Diagr. 6 

Datum 

Date 

Dezember 

2002 

Januar 

2003 

Januar 

2003 

MB: Modification Bulletin – Änderungsblatt 

TN: Technical Note – Technische Mitteilung 

0.1.4



Ventus-2b 

0.2 Verzeichnis der Seiten / List of effective pages 

Seite / Page 

0.1.1 

0.1.2 

0.1.3 

0.1.4 

0.2.1 

0.2.2 

0.2.3 

0.3.1 

0.3.2 

0.3.3 

1.1 

1.2.1 

1.2.2 

1.2.3 

1.3 

1.4 

2.1.1 

2.1.2 

2.2.1 

2.2.2 

2.3 

2.4 

3.1.1 

3.1.2 

3.2.1 

3.2.2 

3.2.3 

3.2.4 

3.3.1 

3.3.2 

Datum / Date Bezug / Reference 

August 1995 

August 1995 

August 1995 

Januar 2003 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

Januar 2003 

Januar 2003 

August 1995 

Januar 2003 

Dezember 2002 

August 1995 

August 1995 

August 1995 

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August 1995 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

Rev. 8 

0.2.1



Ventus-2b 


Seite / Page 

4.1 

4.2 

4.3 

5.1.1 

5.1.2 

5.2.1 

5.2.2 

5.2.3 

5.2.4 

5.3 

5.4.1 

5.4.2 

5.4.3 

6.1 

6.2.1 

6.2.2 

6.3 

6.4.1 

6.4.2 

6.4.3 

6.5 

6.6.1 

6.6.2 

6.7 


August 1995 

August 1995 

August 1995 

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August 1995 

Januar 2003 

August 1995 

Januar 2003 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

Januar 2003 

August 1995 

Januar 2003 

Januar 2003 

Januar 2003 

August 1995 

August 1995 

Januar 2003 

Januar 2003 

Rev. 8 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

0.2.2



Ventus-2b 


Seite / Page 

4.1 

4.2 

4.3 

5.1.1 

5.1.2 

5.2.1 

5.2.2 

5.2.3 

5.2.4 

5.3 

5.4.1 

5.4.2 

5.4.3 

6.1 

6.2.1 

6.2.2 

6.3 

6.4.1 

6.4.2 

6.4.3 

6.5 

6.6.1 

6.6.2 

6.7 


August 1995 

August 1995 

August 1995 

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August 1995 

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August 1995 

Januar 2003 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

August 1995 

Januar 2003 

August 1995 

Januar 2003 

Januar 2003 

Januar 2003 

August 1995 

August 1995 

Januar 2003 

Januar 2003 

Rev. 8 

TN 349-27 

MB 349-38, TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

TN 349-27 

0.2.2


Ventus-2a MAINTENANCE MANUAL 

Ventus-2b 

1. Description of components and systems 

NOTE: 

Further descriptions and assembly are provided on sections 1.4, 1.5, and 7 

of the Flight Manual. 

1.1 Airframe 

The model Ventus-2a and Ventus-2b are single-seat high performance sailplanes, 

constructed from fiber reinforced plastic (FRP), featuring wingflaps 

and a T-tail (with fixed horizontal stabilizer and elevator). 

Wing 

The wing shells are a CFRP/foam-sandwich with spar flanges made from 

carbon fiber rovings and shear webs constructed as a CFRP/foam-sandwich. 

Fuselage 

This is a pure carbon fiber lay-up with a Kevlar and glass fiber reinforcement 

in the cockpit area for high energy absorbtion. 

Horizontal tailplane 

The horizontal tailplane consists of a fixed stabilizer with elevator. 

The stabilizer is a GFRP/foam-sandwich, the elevator halves are a pure 

carbon fiber lay-up. 

Vertical tail 

Both fin and rudder are constructed as a glass fiber/foam-sandwich. 

January 2003 

Revision 11 TN-No. 349-27 1.1



Ventus-2b 

15.0 m [ 49.21 ft ] 

3° 

TAILPLANE INCIDENCE 

-2.5° 

2.3 m [ 7.55 ft ] 

ELEVATOR 

+3 mm 

2 mm 

+0.12 in. ] 

0.08 in. ] 

44 

0.23° 

Up or down 

[ 1.73 

323 mm [ 12.72 in. ] 

138 mm 

[ 5.43 in. ] 

Ventus-2a - 6.41 m [ 21.03 ft ] 

RUDDER 

To either side: 155 ± 15 mm [ 6.10 ± 0.59 in. ] 

AILERONS (flaps set at "0") 

33 ± 3 mm 

Up 

[ 1.30 ± 0.12 in. ] 

25 ± 3 mm 

Down 

[ 0.98 ± 0.12 in. ] 

126 mm 

[ 4.96 in. ] 

325 ± 25 mm 

[ 12.80 ± 0.98 in. ] 

30 ± 2 mm 

[ 1.18 ± 0.08 in. ] 

0 ± 2 mm 

[ 0 ± 0.08 in. ] 

22 ± 2 mm 

[ 0.87 ± 0.08 in. ] 

FLAPS 

set at "S1" (up) 

set at "0" (neutral) 

Sailplane attitude for all measurements: 

Tail jacked up such that a wedge-shaped block, 

100 : 3.125, placed on the rear top fuselage, is 

horizontal along its upper edge. 

set at "L" (down) 

RIGGING DATA AND CONTROL SURFACE DEFLECTIONS 

January 2003 

Revision 11 TN-No. 349-27 2.1.2



Ventus-2b 

2.3 Play in the control circuits 

With the cockpit controls fixed, the play at the control surfaces must not exceed 

the following values: 

Inboard +/- 2.0 mm measured 126 mm behind hinge axis 

aileron: (+/- 0.08 in.) (4.96 in.) 

Between inbd. 

and mid +/- 2.0 mm measured 106 mm behind hinge axis 

aileron: (+/- 0.08 in.) (4.17 in.) 

Between mid 

and outbd. +/- 1.0 mm measured 88 mm behind hinge axis 

aileron: (+/- 0.04 in.) (3.46 in.) 

Elevator: +/- 3.0 mm measured 138 mm behind hinge axis 

(+/- 0.12 in.) (5.43 in.) 

If there is excessive play in the hinge bearings and/or linkages, they must be 

replaced or the manufacturer should be contacted regarding possible measures 

to reduce the play. 

The rudder control circuit is an open circuit, operated directly by control cables, 

and is therefore not subject to play. 

January 2003 

Revision 11 TN-No. 349-27 2.3



Ventus-2b 

5.2 Tow release(s) – removal and reinstallation 

Nose tow release mechanism (option) 

The nose tow release is located in the fuselage nose cone. 

It must be checked regularly for damage and also be cleaned and greased. 

Model "Ventus-2a": To remove the nose tow release proceed as follows: 

- Disconnect gas strut from panel mounting frame and withdraw 

frame axle so that the frame/panel assembly can be moved aside. 

- Remove nose access panel (by undoing the six mounting bolts), the tow 

release is now accessible. 

- It is removed by disconnecting the release cable from the actuating 

segment, undoing the four (4) mounting bolts and pulling it clear to the 

rear. 

Be sure that the electrical bonding strap is reattached when reinstalling the 

nose tow release mechanism (see sketch below). 

Torque: M4 2Nm (1.4 lbft) 

M5 5 Nm (3.6 lbft) 

EXTRACTED FROM DRAWING 

NO. HS08-10.108 

4 mounting bolts 

nose tow 

release type E 85 

actuating segment 

ground strap 

nose release access panel 

(attached by 6 bolts) 

January 2003 

Revision 11 TN-No. 349-27 5.2.1



Ventus-2b 


NO. HS11-10.201 

tow release 

EUROPA G 88 

1 

3 

2 

4 

January 2003 (S/N 2 through 109) 

Revision 11 TN-No. 349-27 5.2.3 

5 

to be attached by bolts No. 2 and 5



Ventus-2b 


NO. S08 RB 851 

tow release 

EUROPA G 88 

1 

2 

4 

3 

(S/N 110 through 120) 

January 2003 MB-No. 349-38 

Revision 11 TN-No. 349-27 5.2.3 

5 

to be attached by bolts No. 2 and 5



Ventus-2b 

Datum plane: Wing leading edge at root rib 

Aircraft attitude: Tail jacked up such that a wedge-shaped 

block, 100 : 3.125 for model “Ventus-2a” 

placed on the rear top fuselage, is horizontal 

along its upper edge. 

Distance main wheel 

model “Ventus-2a”: a = 106 mm (4.17 in.) 

Distance tail wheel/skid 

model “Ventus-2a”: b = 3927 mm (154,61 in.) 

Empty mass c/g position: 

C/G position in flight: 

x = W2 x b 

W 

(just given for the case that the “c/g position in flight” is to be determined by 

weighing rather than by computing it on the basis of the empty mass c/g position) 

The aircraft is to be weighed fully equipped (pilot with parachute and complete 

outfit incl. barograph, cushions, cameras etc.) Seat back and rudder pedals 

should be correctly adjusted for this purpose. 

January 2003 

Revision 11 TN-No. 349-27 6.2.2 

x = 

+ a 

W 2 loaded x b 

W empty + W disposable 

+ a



Ventus-2b 

6.4 Empty mass and empty mass c/g position 

a) Empty mass 

The basic empty mass of a “Ventus-2a” or “Ventus-2b” is the sailplane 

• without pilot 

• without parachute and 

• without water ballast 

but including all its fixed equipment. 

b) Empty mass center of gravity 

It must always be ensured that the empty mass center of gravity remains 

within the permitted range. 

If necessary, compensating ballast weights must be installed. 

If the empty mass c/g limits (see diagram on page 6.4.3) and the load 

limits on the seat (see load chart) are complied with, the center of gravity 

in flight will remain within the permitted range. 

The empty mass c/g ranges shown in the diagram on page 6.4.3 are 

derived from the following seat loads: 

Forward c/g limits: With a maximum seat load of 110 kg (242.5 lb) 

and with maximum permitted water ballast 

Rearward c/g limits: With various minimum seat loads, and a baggage 

load of 2.0 kg (4.4 lb) 

To facilitate the checking of the empty mass center of gravity, the table 

on page 6.4.2 shows – at different empty mass values – the maximum 

permissible load on the tail wheel (or skid), with various seat loads and 

in relation to the most rearward c/g position. 

The actual load on the tail wheel (or skid) is determined with the aircraft 

in weighing attitude, i.e. main wheel on the ground and tail jacked up as 

described on page 6.2.1. 

If the load on the tail wheel (or skid) does not exceed the corresponding 

value in the table, the center of gravity is within the permitted range. 

January 2003 

Revision 11 TN-No. 349-27 6.4.1



Ventus-2b 

Ventus-2a: 

Empty mass 

Load on tail wheel (or skid) with a minimum seat load of: 

70 154 75 165 80 176 85 187 90 198 

kg lb kg lb kg lb kg lb kg lb kg lb 

230 507 29.4 64.8 30.4 67.0 31.4 69.2 32.5 71.7 33.5 73.9 

235 518 29.7 65.5 30.7 67.7 31.7 69.9 32.8 72.3 33.8 74.5 

240 529 30.0 66.1 31.0 68.3 32.1 70.8 33.1 73.0 34.1 75.2 

245 540 30.3 66.8 31.4 69.2 32.4 71.4 33.4 73.6 34.5 76.1 

250 551 30.6 67.5 31.7 69.9 32.7 72.1 33.8 74.5 34.8 76.7 

255 562 31.0 68.3 32.0 70.5 33.0 72.8 34.1 75.2 35.1 77.4 

260 573 31.3 69.0 32.3 71.2 33.4 73.6 34.4 75.8 35.4 78.0 

265 584 31.6 69.7 32.7 72.1 33.7 74.3 34.7 76.5 35.8 78.9 

270 595 31.9 70.3 33.0 72.8 34.0 75.0 35.1 77.4 36.1 79.6 

January 2003 

Revision 11 TN-No. 349-27 6.4.2



Ventus-2b 

Empty mass c/g range 

EMPTY MASS C/G POSITION (mm / in.) AFT OF DATUM 

in. mm 

27.56 700 

27.17 690 

26.77 680 

26.38 670 

25.98 660 

25.59 650 

25.20 640 

24.80 630 

24.41 620 

24.02 610 

23.62 600 

23.23 590 

22.83 580 

22.44 570 

22.05 560 

21.65 550 

21.26 540 

20.87 530 

20.47 520 

20.08 510 

230 

507 

V e n t u s - 2 a 

V e n t u s - 2 a 

240 

529 

250 

551 

EMPTY MASS (kg / lb) 

January 2003 

Revision 11 TN-No. 349-27 6.4.3 

260 

573 

permissible rearmost empty mass 

c/g position with a minimum 

seat load of : 

90 kg 

198 lb 

85 kg 

187 lb 

80 kg 

176 lb 

75 kg 

165 lb 

70 kg 

154 lb 

FOREMOST EMPTY 

MASS C/G POS. 

270 kg 

595 lb



Ventus-2b 

For establishing a „Weight & Balance Report“ the following lever arms 

are to be used: 

C/G position of pilot 

(with parachute or back cushion) 

Ventus-2a: 455 mm (17.91 in.) forward of datum 

C/G position of wing water ballast 

179 mm (7.05 in.) aft of datum 

C/G position of water ballast or battery in fin 

Ventus-2a: 4092 mm (161,11 in.) aft of datum 

C/G position of battery in fin 

Ventus-2a: 3995 mm (157,28 in.) aft of datum 

C/G position of trim ballast mount 

Ventus-2a: 1635 mm (64.37 in.) forward of datum 

C/G position of battery tray at base of instrument panel 

Ventus-2a: 1120 mm (44,09 in.) forward of datum 

January 2003 

Revision 11 TN-No. 349-27 6.6.2



Ventus-2b 

6.7 Mass – C/G diagram 

ALL - UP MASS (kg / lb) 

lb kg 

1157 525 

1102 500 

992 450 

882 400 

772 350 

761 345 

750 340 

661 300 

654 296.6 

551 250 

FOREMOST C/G POSITION 

220 

8.66 

MAXIMUM ALL-UP MASS 

250 

9.84 

PERMITTED 

RANGE 

264.9 

10.43 296.2 

11.66 300 

11.81 

340.9 

13.42 

X in flight (mm / in.) aft of datum 

with optional water 

ballast fin tank 

January 2003 

Revision 11 TN-No. 349-27 6.7 

REARMOST C/G POSITION 

350 mm 

13.78 in. 

360 

14.17



Ventus-2b 

FUSELAGE CONTROLS 

1. Flaps and ailerons 

2. Airbrakes 

3. Elevator 

4. Elevator trim 

January 2003 

Revision 11 TN-No. 349-27 DIAGRAM 1



Ventus-2b 

1075 mm 

42.32 in. 

INSPECTION OPENING IN FIN 

(to be cut if required) 

∅20 mm 

∅0.79 in. 

parallel to 

shroud on fin 

to be measured 

at outer edge 

of tube 

390 mm 

15.35 in. 

shroud on fin 

Should it become necessary to replace the vertical elevator 

actuating rod, an additional opening may be cut into the fin 

on the far side. 

January 2003 

Revision 11 TN-No. 349-27 DIAGRAM 6



Ventus-2b 

70 

880 

Colour to be orange (RAL-Code No. 2004) 

or red (RAL-Code No. 3000 or 3024) 

120 

ANTI-COLLISION MARKINGS (optional) 

25 

80 

130 130 130 130 

130 130 130 

80 

80 

20° 

80 

80 

80 

80 

PROPOSAL 1 PROPOSAL 2 PROPOSAL 3 PROPOSAL 4 

January 2003 

Revision 1 TN-No. 349-27


Ventus-2a REPAIR INSTRUCTIONS 

Ventus-2b 

REPAIR INSTRUCTIONS FOR „Ventus-2a“ AND „Ventus-2b“ 

The components of these sailplanes are constructed as follows: 

1. Wing 

CFRP/foam-sandwich, with HEREX C 70.55, 

thickness 6 mm and 8 mm (0.24 and 0.31 in.) 

2. Ailerons 

Inboard: 

Mid and 

CFRP/foam-sandwich, with HEREX C 70.55, 

thickness 4 mm (0.16 in.) 

outboard: Pure CFRP-shell 

3. Winglet 

Pure GFRP/CFRP-shell 

4. Fuselage 

Forward section: Pure CFRP/Kevlar/GFRP-shell 

Aft section: Pure CFRP-shell 

5. Fin 

GFRP/foam-sandwich, with HEREX C 70.55, 


6. Rudder 



7. Horizontal stabilizer 



8. Elevator halves 

Pure CFRP-shell 

January 2003 

Revision 1 TN-No. 349-27 - 1 -

2 - Schempp-Hirth

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