canopy - Schempp-Hirth Flugzeugbau GmbH

SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus 

WARTUNGSHANDBUCH / MAINTENANCE MANUAL 

0.1 Erfassung der Berichtigungen / Record of Revisions 

Lfd.Nr. 

Rev.No. 

Benennung 

Reference 

Seite 

Page 

Datum 

Date 

20 Technische Mitteilung Nr. 396-16 

Optionale Verwendung der Segelflugzeug- 

Rümpfe nach dem 

ÄB-Nr. 396-15 (Duo x) oder 

ÄB-Nr. 396-16 (Duo xL) 

Werk-Nr. 1 bis 533 und 535 bis 541 

Technical Note No. 396-16 

Optional use of fuselages according to 

MB-No. 396-15 (Duo x) or 

MB-No. 396-16 (Duo xL) 

SN 1 through 533 and 535 through 541 

0.2.1 

0.2.2 

0.2.3 

1.1 

1.2.3 

2.1.2 

3.1.2 

3.2.2 

5.4.1.1 

5.4.1.2 

6.2.2 

6.4.2 

6.4.3 

6.6.1 

6.6.2 

6.7 

7.1*) 

7.2.1*) 

7.2.2*) 

7.2.3*) 

7.2.4*) 

7.2.5*) 

8.2 

8.3*) 

8.5 

Diagramm 3*) 

Diagramm 4 

Rep.1 

Rep. 2 

Rep. 3 

Rep. 4 

*) nur bei Verwendung 

des „xL“- 

Rumpfes nach dem 

(ÄB-Nr. 396-16) 

only use for „xL“ 

fuselage 

(MB-No. 396-16) 

Februar 

2008 

MB: Modification Bulletin – Änderungsblatt 

TN: Technical Note – Technische Mitteilung 

0.1.5


Duo Discus 

MAINTENANCE MANUAL 

1. Description of components and systems 

Further descriptions and assembly are provided on sections 1.4, 1.5, 4.2 and 

7 of the Flight Manual. 

1.1 Airframe 

The “Duo Discus ” is a two-seat sailplane for advanced training and crosscountry 

flying, constructed from fiber reinforced plastic (FRP), featuring a 

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

Wing 

The wing shells are a glass and carbon fiber/foam-sandwich with spar 

flanges made from carbon fiber rovings and shear webs constructed as a 

glass fiber/foam-sandwich. 

Fuselage 

This is a pure carbon fiber (CFRP) lay-up with a aramid 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/CFRP/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. 

February 2008 MB-No. 396-15 resp. MB-No. 396-16 

Revision 20 TN-No. 396-15 (x / xL) 1.1


Duo Discus 


Undercarriage with wheel brake 

Steel push-pull tubes connect the u/c operating handles in the cockpit (which 

are guided in a gate) to the actuating arm on the rear pivot shaft of the u/c 

assembly. A gas strut on the u/c assists in retracting the wheel. 

For “wheel up”, the travel of the u/c operating tube in the cockpit is restricted 

by the actuating arm resting against the steel tube center frame; for “wheel 

down”, the extension stop is the overcentering of the rear u/c struts. 

Additionally the travel of the u/c operating tube in the cockpit is restricted by 

the gate guiding the front operating handle. 

The hydraulic main wheel disc brake is actuated by steel cables (running in a 

bowden conduit), connecting the stick mounted brake handles to the wheel 

brake master cylinder. 

A view of the undercarriage is provided in diagram 4. 

Water ballast system(s) 

For a description of the water ballast system(s) refer to section 7.9 of the 

Flight Manual. 


Revision 20 TN-No. 396-15 (x / xL) 1.2.3


Duo Discus MAINTENANCE MANUAL 

170 mm 

[6.69 in.] 

TAILPLANE INCIDENCE: 

-2.65° 

WING INCIDENCE: 

1.5° 

410 mm [16.14 in.] 

176 mm 

[6.93 in.] 

AILERONS: 

Up: 

71 ± 5 mm 

[2.80 ± 0.20 in.] 

Down: 

36 ± 5 mm 

[1.42 ± 0.20 in.] 

WING SWEEPBACK: 

Negative sweepback of leading edge 

on trapezoidal inboard wing section 

228 ± 20 mm 

[8.98 ± 0.79 in.] 

RIGGING DATA AND 

CONTROL SURFACE DEFLECTIONS 

February 2008 MB 396-15 

Revision 20 TN 396-16 (x) 2.1.2



170 mm 

[6.69 in.] 

TAILPLANE INCIDENCE: 

-2.65° 

WING INCIDENCE: 

1.5° 

410 mm [16.14 in.] 

176 mm 

[6.93 in.] 

AILERONS: 

Up: 

71 ± 5 mm 

[2.80 ± 0.20 in.] 

Down: 

36 ± 5 mm 

[1.42 ± 0.20 in.] 

WING SWEEPBACK: 

Negative sweepback of leading edge 

on trapezoidal inboard wing section 

228 ± 20 mm 

[8.98 ± 0.79 in.] 

RIGGING DATA AND 

CONTROL SURFACE DEFLECTIONS 

February 2008 TN 396-12 / MB 396-15 

Revision 20 TN 396-16 (x) 2.1.2


Duo Discus 


• Tow release mechanism(s) 

Checks should be carried out in accordance with the 

“Operating & Maintenance Instructions for the TOST tow Release Mechanism(s)” 

- see also section 9 “Service Instructions”. 

• Instruments 

In the case of all installed instruments and equipment, the instructions of 

the relevant manufacturer should be followed. 

• Safety harness 

At present the service time of the webbing on the restraint systems 

available is limited to twelve (12) years including the time of storage. 

See also the service instructions provided by the relevant manufacturer. 

• Gas strut 

A tension gas strut is attached to the U/C. 

The rod of the gas strut must always be perfectly clean and must not be 

damaged in any way whatsoever. 

If oil has escaped through the seal, the gas strut must be replaced. 

February 2008 



Duo Discus 


After cleaning the entire aircraft, the following checks should be made: 

• Check the aircraft externally for damage such as cracks, holes, scratches, 

buckling and delamination. 

If the outer layer(s) of a component, constructed as a sandwich, has been 

damaged, then the inner skin must be checked as well. 

It is recommended to call upon expert assistance. 

• All fittings which are mounted on GFRP (CFRP) structures must be 

checked to confirm there has been no movement. 

Check also the CFRP (GFRP) structure at the fittings for cracks, white 

spots and delamination. 

• Check all accessible metal parts for damage. 

It is generally found, however, that if the aircraft is operated correctly, no 

damage will have occured. 

If repairs are necessary, then the manufacturer’s recommendations 

should be followed. 

• Check all accessible metal parts such as fittings, control rods (push/pull 

tubes) and actuating levers for corrosion. 

If necessary, remove the rust, clean thoroughly and apply a fresh corrosion 

protection. 

The special primer and paint for this surface protection may be obtained 

from Schempp-Hirth Flugzeugbau GmbH. 

• Linkage for attaching and locking the canopy 

Check linkage attaching/detaching and locking/opening the canopy for 

any damage. 

Check guides for locking rod on canopy frame, locating pins on fuselage 

and front GFRP hinge for delamination/cracks. Check rear metal hinge for 

deformation. 

February 2008 



Duo Discus 


5.4 Main wheel with hydraulic disc brake 

Main wheel TOST: 

When removing the main wheel to clean and grease it, first remove the two 

bolts attaching the brake back plate to the brake cylinder, then remove brake 

calliper (hydraulic pressure hose remains attached). 

Disassemble the attachment bolt of the brake shield on the inner side of the 

swinging arm. 

Next remove cotter pin and castle nut from one side of the wheel axle and 

withdraw the latter. Take out spacer on the ride side of the wheel and remove 

the wheel (take care that no washers, spacers or bushings get lost). 

Prior to re-assembly, clean all parts and lubricate bearings, bushings and the 

axle. 

Observe the instructions provided by the supplier of the wheel, 

TOST company, Munich, Germany 

Main wheel BERINGER 

Observe the instructions provided by the supplier of the wheel, 

BERINGER company, Chǎtelneuf, France. 

NOTE: Do not disconnect the hydraulic pressure hose from the brake 

cylinder and do not actuate the wheel brake while brake calliper is 

removed from the brake disc. 

The hydraulic wheel brake may be actuated by the handle provided at the 

control sticks. 

Front wheel-brake: 

The Bowden cable is directly connected with the actuating segment of the 

brake master cylinder. 

Rear wheel-brake: 

The Bowden cable is connected to the attachment of the brake master 

cylinder. The tube of the Bowden cable fits to the actuating segment of the 

brake master cylinder and actuates the actuating segment when the rear 

wheel brake is applied. 

Whenever a reduced effectiveness of the wheel brake is observed, 

see page 5.4.1.2. 


Revision 20 TN-No. 396-16 (x / xL) 5.4.1.1


Duo Discus 


In case of reduced effectiveness of the wheel brake 

1. Check brake pads: 

If the thickness of the brake pads is less then 1.5 to 2mm replace brake pads. 

Therefore both parts of the brake calliper have to be removed. 

2. Check leak tightness of the hydraulic-system. 

3. Check brake fluid: 

a) Remove front seat pan 

b) Remove cover of brake fluid-container 

c) If necessary refill missing brake fluid and bleed the braking system as 

described on page 5.4.2 

d) Check effectiveness of the wheel brake. Afterwards reassemble the 

disassembled parts 

4. Readjustment of the Bowden cables: 

Note: 

a) The Bowden cables may be readjusted at the adjustment 

point at the control stick until the gap between the 

actuating segment on the brake master cylinder and the 

cylinder case is about 1.0 mm (0.04 in). To do this the 

wheel brake has to be relieved. 

To check the readjustment pull the brake handle several 

times. With relieved wheel brake: 

i) the wheel can still be rotated by hand 

ii) 

it has still to be possible to push the brake 

calliper back in direction to the wheel by hand 

b) Check the function of the wheel brake after assembling 

the seat pan 

Normally the brake system has to be bleeded, if the fuselage is stored inverted! 

If the brake handle is fixed in pulled position during the inverted storage of the 

fuselage, the bleeding of the brake system usually is not necessary 


Revision 20 TN-No. 396-16 (x / xL) 5.4.1.2


Duo Discus 


Datum plane: 

Aircraft attitude: 

Wing leading edge at root rib 

Tail jacked up such that a wedge-shaped 

block, 100 : 4.5, placed on the rear top 

fuselage, is horizontal along its upper 

edge. 

Distance main wheel: a = 8 mm (0.31 in.) 

Distance tail wheel: 

Distance skid: 

b = 5322 mm (209.53 in.) 

b = 5357 mm (210.91 in.) 

Empty mass c/g position: 

x = 

W 2 

x b 

W 

+ a 

C/G position in flight: 

(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 (crew with parachutes and 

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

pedals should be correctly adjusted for this purpose. 

x = 

W 2 loaded 

x b 

W empty 

+ W disposable 

+ a 




Duo Discus 


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

on either seat and with maximum permitted water 

ballast 

Rearward c/g limits: With various minimum loads on the front seat 

(allowance for 5.0 kg / 11.02 lb baggage already 

made) 

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

below shows – at different empty mass values – the maximum permissible 

load on the tail wheel, with various loads on the front seat and in 

relation to the most rearward c/g position. 

The actual load on the tail wheel 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 does not exceed the corresponding value in 

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

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 

410 904 39.7 87.5 41.2 90.8 42.8 94.4 44.3 97.7 45.9 101.2 

420 926 40.1 88.4 41.7 91.9 43.2 95.3 44.8 98.8 46.3 102.1 

430 948 40.6 89.5 42.1 92.8 43.7 96.4 45.2 99.7 46.8 103.2 

440 970 41.1 90.6 42.6 93.9 44.2 97.5 45.7 100.8 47.3 104.3 

450 992 41.5 91.5 43.1 95.0 44.6 98.3 46.2 101.9 47.7 105.2 

460 1014 42.0 92.6 43.5 95.9 45.1 99.4 46.6 102.8 48.2 106.3 

470 1036 42.4 93.5 44.0 97.0 45.5 100.3 47.1 103.9 48.6 107.2 

480 1058 42.9 94.6 44.4 97.9 46.0 101.4 47.5 104.7 49.1 108.3 

490 1080 43.3 95.5 44.9 99.0 46.4 102.3 48.0 105.8 49.5 109.1 

500 1103 43.8 96.6 45.3 99.9 46.9 103.4 48.4 106.7 50.0 110.3 

Note: 

Should a tail skid be fitted (instead of a tail wheel), the above values are 

to be multiplied by a factor of 0.993). 

February 2008 MB-No. 396-15 

Revision 20 TN-No. 396-16 (x) 6.4.2


Duo Discus 


Empty mass c/g range 

in. mm 

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 

90kg 

198lb 

85kg 

187lb 

20.08 510 

19.69 500 

19.29 490 

18.90 480 

18.50 470 

80kg 

176lb 

75kg 

165lb 

70kg 

154lb 

18.11 460 

17.72 450 

17.32 440 

FOREMOST EMPTY 

MASS C/G POS. 

16.93 430 

EMPTY MASS (kg / lb) 

500 

1103 

kg 

lb 


Revision 20 TN-No. 396-16 (x) 6.4.3


Duo Discus 


6.6 Useful load 

Load on the seats 

a) Water ballast fin tank not installed 

Note: 

(*) Depending on its equipment and the installation of fixed trim ballast, the actual 

minimum and/or maximum seat loads of this “Duo Discus” (to which this manual 

refers) may differ from the above typical weights. 

The placards in the cockpit must always show the actual weights, which are also 

to be entered in the log chart – see flight manual, page 6.2.3. 

Neither the maximum permitted all-up mass nor the maximum mass of the non-lifting 

parts must be exceeded. 

Determination of the maximum permitted load on the seats: 

Flown solo: 

Two occupants: 

SEAT 

LOAD 

front 

seat load 

rear 

seat load 

LOAD ON THE SEATS 

(crew incl. parachutes) 

TWO PERSONS 

min. max. 

70* kg 

154* lb 

at choice 

Maximum cockpit seatload 

110* kg 

243* lb 

110* kg 

243* lb 

Always 110 kg (242.5 lb) 

ONE PERSON 

min. max. 

70* kg 

154* lb 

110* kg 

243* lb 

Maximum cockpit load (load on both seats) may not be 

exceeded. For seat loads below the placarded minimum 

refer to Flight manual - section 6.2 

The total of the loads on front and rear seat has to be lower 

than the maximum cockpit seatload. 

At the same time pay attention, that the load on each seat 

stays below 110 kg (242.5 lb) 

Maximum seat load: This is the difference between the maximum permitted mass of 

the non-lifting parts (440 kg / 970 lb) and their actual mass 

(refer to last weighing report). 

b) Water ballast fin tank installed 

Note: 

SEAT 

LOAD 

front 

seat load 

rear 

seat load 



TWO PERSONS 

min. max. 

100 ** 

220 kg 100 ** 

* 

** lb 110* 

243* kg 220 * 

kg 

** lb 

( 70* kg) 

lb ( 70* kg) 

(154* lb) 

(154* lb) 

110* 

at choice 

243* kg 

lb 

Maximum cockpit seatload 

ONE PERSON 

min. max. 

110* 

243* kg 

lb 

Maximum cockpit load (load on both seats) may not be 

exceeded. For seat loads below the placarded minimum refer 

to Flight manual - section 6.2. The value shown in parenthesis 

may be used after having thoroughly checked the ballast 

quantity in the fin tank and the appropriate loading chart. 

(*) Depending on its equipment and the installation of fixed trim ballast, the actual 

minimum and/or maximum seat loads of this “Duo Discus” (to which this manual 

refers) may differ from the above typical weights. 

If so, the log charts and the placards must be altered accordingly. 

(**) 1. For safety reasons the minimum seat load for flights with empty fin tank must 

be increased by 30 kg (66 lb) so as to allow for an unnoticed filled fin tank. 

2. Adding the mass of 30 kg (66 lb) is not required, however, if the pilot either 

- dumps all water ballast (prior to take off) 

or 

- determines the ballast quantity in the fin tank and ensures that it is 

compensated by an appropriate load in the wing tanks and/or on the 

aft seat. 

The placards in the cockpit must always show the actual weights (including those 

allowing for a filled fin tank **), which are also to be entered in the log chart – see 

flight manual, page 6.2.3. 

Neither the maximum permitted all-up mass nor the maximum mass of the non-lifting 

parts must be exceeded. 

February 2008 MB-No. 396-15 / TN-No. 396-13 

Revision 20 TN-No. 396-16 (x) 

6.6.1

Duo Discus 



For establishing a "Weight & Balance Report" the following lever arms 

are to be used: 

Trim ballast under front instrument 

panel 

Trim ballast on right hand side of 

front control stick mounting frame 

Pilot, front seat (with parachute or 

back cushion) 

Pilot, rear seat (with parachute or 

back cushion) 

Battery at rear control stick 

mounting frame 

Center of gravity of: 

2055 mm forward of datum 

80.91 in. 


73.03 in. 


55.12 in. 


11.42 in. 


26.77 in. 

Main wheel 8 mm aft of datum 

0.31 in 

Waterballast, wings 65 mm aft of datum 

2.56 in. 

Tail wheel 5330 mm aft of datum 

209.84 in. 

Tail skid 5365 mm aft of datum 

211.22 in. 

Water ballast, fin 5320 mm aft of datum 

209.45 in. 

Baggage 1000 mm aft of datum 

39.37 in. 


Revision 20 TN-No. 396-16 

6.6.2


Duo Discus 


6.7 Mass – C/G diagram 

lb 

kg 

1543 700 

MAXIMUM ALL-UP MASS 

1433 650 

ALL - UP MASS (kg / lb) 

1378 625 

1323 600 

1257 570 

1213 550 

1135 515 

FORE MOST C/G POSITION 

PERMITTED 

RANGE 

REARMOST C/G POSITION 

1102 500 

1038 471 

mm 

in. 

X (mm / in.) aft of datum 

in flight 


Revision 20 TN 396-16 (x) 6.7


Duo Discus 


without fin tank 



SEAT LOAD TWO PERSONS ONE PERSON 

min. max. min. max. 

front 

seat load 

rear 

seat load 

70* kg 

154* lb 

at 

choice 

110* kg 

243* lb 

110* kg 

243* lb 

70* kg 

154* lb 

110* kg 

243* lb 

Maximum cockpit seat load 220* kg / 485* lb 

Maximum cockpit load (load on both seats) may not 

be exceeded. For seat loads below the placarded 

minimum refer to Flight manual - section 6.2. 

(if installed) 

fin tank installed 



SEAT LOAD TWO PERSONS ONE PERSON 

min. max. min. max. 

100* kg 

100* kg 

front 220* lb 110* kg 220* lb 110* kg 

seat load ( 70* kg) 243* lb ( 70* kg) 243* lb 

(154* lb) 

(154* lb) 

rear 

seat load 

at 

choice 

110* kg 

243* lb 

Maximum cockpit seat load 220* kg / 485* lb 

Maximum cockpit load (load on both seats) may not 

be exceeded. For seat loads below the placarded 

minimum refer to Flight manual - section 6.2. 

The value shown in parenthesis may be used after 

having thoroughly checked the ballast quantity in the 

fin tank and the appropriate loading chart. 

Placing: 

Cockpit inner skin on 

the right for either seat 

WHEN FLOWN SOLO, THE PLACARDED 

MINIMUM FRONT SEAT LOAD MAY BE 

REDUCED BY UP TO: 

NUMBER OF LEAD 

PLATES REQUIRED 

- 05 kg (11 lb) 1 

- 10 kg (22 lb) 2 

- 15 kg (33 lb) 3 

Cockpit inner skin on the right 

(front seat only) 

- 20 kg (44 lb) 4 

- 25 kg (55 lb) 5 

- 30 kg (66 lb) 6 

LOCKING PIN FLUSH 

WITH UPPER SURFACE 

Locking device for outbd. wing panels 

Outbd. end of main wing panels 

February 2008 MB-No. 396-15 / TN-No. 396-13 

Revision 20 TN-No. 396-16 (x) 8.2



Placing: 

Locking of canopy 

On red locking lever on the left, 

provided for either seat 

(if installed) 

Ballast in fin tank is dumped 

simultaneously with wing tanks 

Operating knob for dumping 

ballast from wing tanks 

Front seat above guide slot for operating 

knob on cockpit inner skin on the right 

Air quantity 

Next to operating knob protruding 

from front instrument panel 

push 

pull 

Airstream direction 

Next to operating knob protruding 

from front instrument panel 

C A N O P Y 

attachment / detachment 

Canopy 

attachment/detachment 

Above operating handle on 

cockpit inner skin on the right 

for either seat 


Revision 20 TN 396-16 (x) 8.5


Duo Discus T MAINTENANCE MANUAL 

UNDERCARRIAGE WITH RETRACTING LINKAGE 

AND HYDRAULIC DISC BRAKE 

1. Front retracting linkage 

2. Rear retracting linkage 

3. Brake handle on front control stick 

4. Brake handle on rear control stick 

5. Brake master cylinder with reservoir 


Revision 20 TN 396-16 (x) DIAGRAM 4


Duo Discus 

REPAIR INSTRUCTIONS 

REPAIR INSTRUCTIONS FOR „Duo Discus “ 

The components of this aircraft are constructed as follows: 

1. Inboard wing panels 

GFRP/foam-sandwich, with HEREX C 70.55, 

thickness 8 mm (0.31 in.) 

Wing tip extension 

GFRP/foam-sandwich, 

with HEREX C 70.55, 


2. Ailerons 

Inboard: GFRP/foam-sandwich, with HEREX C 70.55, 


Outboard: 

Pure GFRP/CFRP-shell 

3. Fuselage 

Forward section: Pure CFRP/Kevlar/GFRP-shell 

Aft section: 

Pure CFRP-shell 

4. Fin 



5. Rudder 



6. Horizontal stabilizer 



7. Elevator halves 


February 2008 

Revision 20 TN-No. 396-16 (x + xL) - 1 -


Duo Discus 











with winglets 


2. Ailerons 



Outboard: 


3. Fuselage 


Aft section: 


4. Fin 



5. Rudder 








February 2008 TN-No. 396-12 

Revision 20 TN-No. 396-16 (x + xL) - 1 -


Duo Discus 











with winglets 


2.a Ailerons 



Outboard: 


2.b Trailing edge flap 




3. Fuselage 


Aft section: 


4. Fin 



5. Rudder 









Revision 20 TN-No. 396-16 (x / xL) - 1 -


Duo Discus 


The first stage in carrying out repairs on components constructed from fiber reinforced 

plastic (FRP) is to examine the construction of the component at the location 

in question and to proceed in accordance with the latest applicable issue of 

the 

„REPAIR INSTRUCTIONS FOR SCHEMPP-HIRTH SAILPLANES 

AND POWERED SAILPLANES CONSTRUCTED FROM FIBER 

REINFORCED PLASTIC“ 

General considerations 

For repairs only the following resin systems must be used: 

1. For GFRP-components 

Resin Hardener Mixing proportion 

by weight 

L 285 286 or 287 100 : 38 

LY 5052 HY 5052 100 : 38 

L 335 335 or 340 100 : 38 

Curing : 15 hours at 50° C (122° F) 

2. For CFRP/AFRP components 

Resin Hardener Mixing proportion 

by weight 

L 285 286 or 287 100 : 38 

LY 5052 HY 5052 100 : 38 

L 335 335 or 340 100 : 38 

Curing : 15 hours at 55° C (131° F) 




Duo Discus 


MATERIALS (AND SUPPLIERS) FOR THE REPAIR OF CFRP-COMPONENTS 

Resin system: See page 2 

Carbon fiber cloth: 

(Yarn DIN 65184 CC 200 f 3000-F) 

Cloth 1/1 (warp equal weft) 

a) Weight 200 g/m²: e.g. Quality 98140 or 98141 from CS-Interglas AG, Ulm 

Sigratex KDL 8003 from SGL Carbon Group, Meitingen 

Style 450 from C. Cramer & Co., Heek-Nienborg 

b) Weight 285 g/m²: e.g. Quality 98160 from CS-Interglas AG, Ulm 

Style 475T from C. Cramer & Co., Heek-Nienborg 

Unidirectional 

carbon fiber cloth: 

Weight 140 g/m² 

(carbon fiber 120 g/m², glass fiber 20 g/m²), quality 

e.g. Style 763 from C. Cramer & Co., Heek-Nienborg or 

MDL 9001 from SGL Carbon Group, Meitingen 

Carbon fiber tape: (Yarn DIN 65184) 

e.g. Quality Sigratex KDU/NF6, 39-7.5 

Sigratex KDU -1001, width: 75 mm (2.95 in.) 

from SGL Carbon Group, Meitingen 

Carbon fiber / Aramid 

fiber (Kevlar) cloth: CF: Yarn DIN 65184 CC 200 f 3000-F 

AF: Yarn DIN 65427 

Linen cloth 1/1 (warp equals weft), weight 205 g/m² 

e.g. Quality 98355 from CS-Interglas AG, Ulm 

Carbon fiber rovings: 

(Yarn DIN 65184 CC 800 f 12000-F) 

e.g. Quality Tenax HTA 5131 800tex f 12000to 

from Tenax-Fibers, Wuppertal 




Duo Discus 


Surface coating: ● UP-Vorgelat, white, No. T 35 

● UP-Hardener No. SF 10 

● UP-Thinner No. SF 

from Scheufler, Stuttgart 

Mixing proportion by weight: 

100 parts UP-Vorgelat T 35 to 10 parts hardener SF 10

canopy - Schempp-Hirth Flugzeugbau GmbH

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