SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T WARTUNGSHANDBUCH Ausgabe Juni 2000

MAINTENANCE MANUAL issue June 2000

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd.Nr. 

Rev.No. 

Benennung 

Reference 

Seite 

Page 

Datum 

Date 

1 Änderungsblatt Nr. 890-2

Steuerseile Ø 3,2 mm für Schleppkupplung(en) 

ab Werk-Nr. 48 

(wahlweise Werk-Nr. 1 bis 47) 

Modification Bulletin No. 890-2

Control cable Ø 3,2 mm for tow release(s) 

S/N 48 and up 

(optional S/N 1 through 47) 

0.2.1 

3.1.1 

Februar / 

February 

2002 

2 Technische Mitteilung Nr. 890-2

Handsteuerung für Seitenruder 

(Werk-Nr. 53, 89 und wahlweise folgende 

Werknummern bei der Herstellung) 

Technical Note No. 890-2

Hand operated rudder system 

installation during constructions 

S/N 53, 89 and up optional

0.2.1 

0.2.2 

3.2.1 

5.1.1 

Diagr. 1 

Diagr. 2 

------------- 

0.2.2 

5.1.1 

Diagr. 2 

Februar / 

February 

2003 

------------- 

November 

2003 

3 Ergänzungen

Supplements

0.2.1 

0.2.2 

0.2.3 

1.1 

1.3 

3.1.1 

4.2.2 

4.2.3 

5.1.1 

5.2.1 

5.2.2 

9 

11 

Juli / July

2003 

4 FAA-Ergänzung

FAA-supplements

0.2.1 

0.2.3 

3.1.1 

3.3.1 

3.3.2 

8.8 

August 

2003 

MB: Modification Bulletin – Änderungsblatt 

 TN: Technical Note – Technische Mitteilung 

Hinweis: Nicht eingefügte Berichtigungen sind zu streichen. 

 Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren 

Note: Cross out revisions which are not included. 

 The list of effective pages must be amended by hand if necessary. 

0.1.1 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T WARTUNGSHANDBUCH Ausgabe Juni 2000

MAINTENANCE MANUAL issue June 2000

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd.Nr. 

Rev.No. 

Benennung 

Reference 

Seite 

Page 

Datum 

Date 

5 Änderungsblatt Nr. 890-3

LCD-Kraftstoffvorratsanzeiger 

ab Werk-Nr. 85 

wahlweise Werk-Nr. 1 bis 84 

Modification Bulletin No. 890-3

LCD-fuel quantity indicator 

standard on S/N 85 

optional S/N 1 through 84 

0.2.1 

0.2.3 

7.2.2 

Diagr. 9c 

Oktober / 

October

2003 

6 Ergänzung der Instrumente

Supplements of instruments

0.2.3 

7.2.3 

7.2.4 

Januar / 

January 

2004 

7 Ergänzungen

Supplements

0.2.1 

0.2.3 

0.3.1 

2.1.1 

3.2.4 

8.1 

Januar / 

January 

2005 

8 Ergänzung

Wägung, 

Leermassen-Schwerpunktbereich 

Supplement

Weighing, 

Empty mass c/g range 

0.2.2 

6.3 

6.4.3 

April 

2005 

 MB: Modification Bulletin – Änderungsblatt 

 TN: Technical Note – Technische Mitteilung 

Hinweis: Nicht eingefügte Berichtigungen sind zu streichen. 

 Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren 

Note: Cross out revisions which are not included. 

 The list of effective pages must be amended by hand if necessary. 

0.1.2 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T WARTUNGSHANDBUCH Ausgabe Juni 2000

MAINTENANCE MANUAL issue June 2000

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd.Nr. 

Rev.No. 

Benennung 

Reference 

Seite 

Page 

Datum 

Date 

9 Änderungsblatt Nr. 890-6 

Winglets, Hinterkantenklappen (Werk-Nr. 126) 

und gefedertes Fahrwerk (ab Werk-Nr. 128) 

Modification Bulletin No. 890-6 

Winglets, trailing edge flap (S/N 126) and 

landing gear with shock absorber struts 

(S/N 128 and on) 

Deckblatt / 

cover sheet 

0.2.1 

0.2.2*) 

0.2.3 

1.2.2 

1.2.3*) 

2.1.2 

2.3 

3.1.2 

3.2.1 

3.2.4 

5.4.1.1*) 

5.4.1.2*) 

5.4.2*) 

6.2.2*) 

6.4.2*) 

6.4.3*) 

6.6.2*) 

6.7*) 

8.6*) 

8.7*) 

Diagr. 1 

Diagr. 3 

Diagr. 4*) 

Diagr. 5 

Farbkennz. 

Rep. 1, 2 

*) entfällt bei 

Werk-Nr. 126 

not applicable 

for S/N 126 

September 

2005 

10 Technische Mitteilung Nr. 890-7 

Winglets wahlweise, Werk-Nr. 1 bis 125 

Technical Note 890-7 

Winglets optional, S/N 1 through 125

0.2.1 

2.1.2 

Diagr. 3 

Farbkennz. / 

Anti collision 

marking 

Rep. 1 

November 

2005 

MB: Modification Bulletin – Änderungsblatt 

 TN: Technical Note – Technische Mitteilung 

Hinweis: Nicht eingefügte Berichtigungen sind zu streichen. 

 Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren 

Note: Cross out revisions which are not included. 

 The list of effective pages must be amended by hand if necessary. 

0.1.3 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T WARTUNGSHANDBUCH Ausgabe Juni 2000

MAINTENANCE MANUAL issue June 2000

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd.Nr. 

Rev.No. 

Benennung 

Reference 

Seite 

Page 

Datum 

Date 

11 Ergänzung der Instrumente

Supplement of Instruments

0.2.1 

0.2.3 

7.2.1 

7.2.3 

7.2.4 

März / 

March 

2006 

12 Ergänzungen zum ÄB 890-6

Tragflügel in GFK/CFK, 

Werk-Nr. 147 und ab Werk-Nr. 151 

Supplement to MB 890-6

Wings in GFRP/CFRP, 

S/N 147 and S/N 151 and up 

0.2.1 

1.1 

2.2.1 

Rep. 1 

Juli / 

July 

2006 

13 Ergänzungen zum ÄB 890-6

ab Werk-Nr. 172 

Technische Mitteilung Nr. 890-9

Werk-Nr. 147, 150, 151 bis 171 optional 

Erhöhung der max. Flugmasse auf 750 kg und der 

Masse der nichttragenden Teile auf 500 kg 

Supplement to MB 890-6

S/N 172 and up 

Technical Note No. 890-9

S/N 147, 150, 151 through 171 optional 

Increase of the max. take-off mass to 750 kg and the 

mass of the non-lifting parts to 500 kg 

0.2.2 

0.2.3 

5.2.1 

5.2.2 

5.4.1.1 

6.5 

6.6.1 

6.7 

8.1 

8.2 

Juli / 

June 

2007 

14 Technische Mitteilung Nr. 890-11

Alle Werk-Nr., optional 

Ersetzen des Bugrades durch einen Schleifsporn 

Technical Note No. 890-11

All S/N, optional 

Substitution of the nose wheel by a nose skid 

0.2.2 

6.2.1 

Juni / 

June

2007 

 MB: Modification Bulletin – Änderungsblatt 

 TN: Technical Note – Technische Mitteilung 

Hinweis: Nicht eingefügte Berichtigungen sind zu streichen. 

 Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren 

Note: Cross out revisions which are not included. 

 The list of effective pages must be amended by hand if necessary. 

0.1.4 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T WARTUNGSHANDBUCH Ausgabe Juni 2000

MAINTENANCE MANUAL issue June 2000

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd.Nr. 

Rev.No. 

Benennung 

Reference 

Seite 

Page 

Datum 

Date 

15 Ergänzungen für die Zulassung in Kanada

Supplements for the Type Acceptance in Canada

0.2.1 

0.3.3 

3.1.1 

3.2.1 

3.3.1 

3.3.2 

C-1 

C-2 

C-3 

C-4 

Februar / 

February 

2011 

16 Technische Mitteilung Nr. 890-13, 2. Ausgabe

Änderung des Flughandbuchs und des Wartungshandbuchs, 

Werk-Nr. 1 bis 174 

Technical Note No. 890-13, 2nd issue

Amendment of the Flight Manual and the Maintenance Manual, 

S/N 1 through 174 

 

0.1.1 

0.1.2 

0.1.3 

0.1.4 

0.1.5 

0.2.1 

0.2.2 

0.2.3 

0.3.3 

6.4.2 

6.6.1 

8.2 

8.3 

Diag. 9d 

8.2 

November 

2011 

Januar 2013 

 

 

 MB: Modification Bulletin – Änderungsblatt 

 TN: Technical Note – Technische Mitteilung 

Hinweis: Nicht eingefügte Berichtigungen sind zu streichen. 

 Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren 

Note: Cross out revisions which are not included. 

 The list of effective pages must be amended by hand if necessary. 

0.1.5 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T MAINTENANCE MANUAL

Diagrams:

 1 Control circuits in the fuselage 

 2 Rudder control circuits 

 3 Control circuits in the wing 

 4 Undercarriage with retracting linkage and hydraulic disc brake 

 5 Inspection opening in the aileron web 

 6 Inspection opening in the fin 

 7 Aileron template 

 8 Power plant installation 

 9a Wiring diagram / cable position view single control 

 9b Wiring diagram / cable position view double control 

 9c Part list – Diagram 9a, 9b, 10a, 10b 

 9d Connector (engine to airframe) 

 10a Wiring diagram single control 

 10b Wiring diagram double control 

 11 special tool for removal and re-installation of the pylon gas strut 

 

Anti collision markings “Duo Discus T”

Check list:

 1. Engine mount (pylon) and pivoting mechanism 

 2. Fuel system 

 3. Electrical system (power plant monitoring, engine test run) 

Trouble shooting lists “Duo Discus T”

Appendix:

 1. Repair Instructions for powered sailplane model “Duo Discus T” 

 2. Repair Instructions for Schempp-Hirth Sailplanes and Powered 

Sailplanes constructed from Fiber Reinforced Plastic 

 It is recommended to insert Technical Notes (TNs) and Airworthiness 

 Directives (Ads) behind this page. 

November 2011 TN 890-13 

Revision 16 0.3.3 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T MAINTENANCE MANUAL

Diagrams:

 1 Control circuits in the fuselage 

 2 Rudder control circuits 

 3 Control circuits in the wing 

 4 Undercarriage with retracting linkage and hydraulic disc brake 

 5 Inspection opening in the aileron web 

 6 Inspection opening in the fin 

 7 Aileron template 

 8 Power plant installation 

 9a Wiring diagram / cable position view single control 

 9b Wiring diagram / cable position view double control 

 9c Part list – Diagram 9a, 9b, 10a, 10b 

 9d Connector (engine to airframe) 

 10a Wiring diagram single control 

 10b Wiring diagram double control 

 11 special tool for removal and re-installation of the pylon gas strut 

 

Anti collision markings “Duo Discus T”

Check list:

 C-1 Wing, fuselage 

 C-2 Undercarriage; rudder; horizontal tailplane 

 C-3 Equipment; control circuits and their functions 

 C-4 Checks to be made with sailplane rigged 

 1. Engine mount (pylon) and pivoting mechanism 

 2. Fuel system 

 3. Electrical system (power plant monitoring, engine test run) 

Trouble shooting lists “Duo Discus T”

Appendix:

 1. Repair Instructions for powered sailplane model “Duo Discus T” 

 2. Repair Instructions for Schempp-Hirth Sailplanes and Powered 

Sailplanes constructed from Fiber Reinforced Plastic 

 It is recommended to insert Technical Notes (TNs) and Airworthiness 

 Directives (Ads) behind this page. 

November 2011 TN 890-13 

Revision 16 supplements for type acceptance in Canada 0.3.3 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T MAINTENANCE MANUAL

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 is below the value in the table, the empty 

mass centre of gravity is in front of the rearmost allowed limit for the 

corresponding minimum cockpit load and empty mass. 

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 35.7 78.7 37.2 82,0 38,8 85,5 40,4 89,1 41,9 92,4 

420 926 36.0 79.4 37.6 82,9 39,2 86,4 40,7 89,7 42,3 93,3 

430 948 36.4 80.2 37.9 83,6 39,5 87,1 41,1 90,6 42,6 93,9 

440 970 36.7 80.9 38.3 84,4 39,9 88,0 41,4 91,3 43,0 94,8 

450 992 37.1 81.8 38.6 85,1 40,2 88,6 41,8 92,2 43,4 95,7 

460 1014 37.4 82.5 39.0 86,0 40,6 89,5 42,1 92,8 43,7 96,3 

470 1036 37.8 83.3 39.4 86,9 40,9 90,2 42,5 93,7 44,1 97,2 

480 1058 38.1 84.0 39.7 87,5 41,3 91,0 42,8 94,4 44,4 97,9 

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). 

November 2011 TN 890-13 

Revision 16 6.4.2 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T MAINTENANCE MANUAL

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 is below the value in the table, the empty 

mass centre of gravity is in front of the rearmost allowed limit for the 

corresponding minimum cockpit load and empty mass. 

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). 

November 2011 TN 890-13 

Revision 16 MB 890-6 except SN 126 6.4.2 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T MAINTENANCE MANUAL

6.6 Useful load 

Load on the seats

*) Values as an example, the actually applicable

values - see Flight Manual log chart section 6.2 -

must be entered.

**) Enter number of batteries installed at weighing

and enlisted in equipment list.

***)With removed power plant the amendment "when

fuel tank is completely filled" must be crossed out.

1 batt. engine battery (E)

2 batt.** in front of rear stick mounting frame (C1, C2)**

front

seat load

rear

seat load

LOAD ON THE SEATS

(crew incl. parachutes)

 70* kg

154* lb

The maximum load in the cockpit (load on both seats

+ baggage + trim ballast) must not be exceeded.

If the front seat load is below the minimum front seat load:

see instructions in the flight manual - section 6.2.

SEAT

LOAD

TWO PERSONS

 min. max.

at

choice

ONE PERSON

 min. max.

110 kg

243 lb

Maximum load in the cockpit when

the fuel tank is completely filled ***

222* kg / 490* lb

Maximum

fuel

kg lb Ltr. US. Gal. IMP. Gal.

12 26.5 16 4.23 3.52

valid for the following battery location(s):

110 kg

243 lb

 70* kg

154* lb

110 kg

243 lb

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

minimum front seat load and the maximum cockpit load of this particular Duo Discus 

T (to which this manual refers) may differ from the above entered values. 

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

be entered in the log chart – see flight manual, page 6.2.3 or 6.2.4. 

Determination of the values for the maximum load in the cockpit and in the seats:

The maximum front seat load and 

The maximum rear seat load 

are always 110 kg. 

The maximum load in the cockpit when the fuel tank is completely filled must 

be determined in such a way that, with considering 12kg fuel load in the fuel tank, 

the maximum weight of the non-lifting parts and the maximum weight without water 

ballast is not exceeded (see Flight Manual page 2.6). 

With removed power plant the maximum load in the cockpit must be determined 

in the same way but without considering any fuel. 

Under certain conditions the maximum load in the cockpit may be lower than 220kg. 

In this case it is not possible to use the maximum seat load in both seats at the 

same time. 

November 2011 

Revision 16 TN 890-13 6.6.1 
(if installed)

Cockpit inner skin on

the right for either seat

Above water dump valve control on

cockpit inner skin on the right

(front seat only)

Cockpit inner skin on the right

(front seat only)

Guide slot on cockpit inner skin on

the right (front seat only)

Water dump valve control

Placing:

WHEN FLOWN SOLO, THE PLACARDED

MINIMUM FRONT SEAT LOAD MAY BE

REDUCED BY UP TO:

- 05 kg (11 lb) 1

- 10 kg (22 lb) 2

- 15 kg (33 lb) 3

- 20 kg (44 lb) 4

- 25 kg (55 lb) 5

- 30 kg (66 lb) 6

NUMBER OF LEAD

PLATES REQUIRED

January 2013

Revision 16 TN 890-13 8.2

SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

*) Values as an example, the actually applicable

values - see Flight Manual log chart section 6.2 -

must be entered.

**) Enter number of batteries installed at weighing

and enlisted in equipment list.

***) With removed power plant the amendment "when

fuel tank is completely filled" must be crossed out.

1 batt. engine battery (E)

2 batt.** in front of rear stick mounting frame (C1, C2)**

front

seat load

rear

seat load

LOAD ON THE SEATS

(crew incl. parachutes)

 70* kg

154* lb

The maximum load in the cockpit (load on both seats

+ baggage + trim ballast) must not be exceeded.

If the front seat load is below the minimum front seat load:

see instructions in the flight manual - section 6.2.

SEAT

LOAD

TWO PERSONS

 min. max.

at

choice

ONE PERSON

 min. max.

110 kg

243 lb

Maximum load in the cockpit when

the fuel tank is completely filled ***

222* kg / 490* lb

Maximum

fuel

kg lb Ltr. US. Gal. IMP. Gal.

12 26.5 16 4.23 3.52

valid for the following battery location(s):

110 kg

243 lb

 70* kg

154* lb

110 kg

243 lb

Note:

The stars (*,**,***) refer to the aside mentioned comments.

In the real cockpit placard they are omitted.

Cockpit inner skin on

the right for either seat

WATER BALLAST IN THE FIN

The rear limit for the in-flight center of

gravity must not be exceeded.

Therefore for loading the fin tank strictly

follow the Flight Manual section 6.2!

(if installed)

Ballast in fin tank is dumpted

simultaneously with wing tanks

OPENED CLOSED
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

November 2011

Revision 16 TN 890-13 8.3

Cockpit inner skin on the left

- for front seat only (unless a

2nd control unit is installed)

Main switch

Front instrument panel

Placing:

Cockpit inner skin on

the right for either seat

O OPEN fuel shut-off valve

O Switch ASI to pitot head in nose cone

O EXTEND power plant at 90-100 km/h (49-54 kt, 56-62 mph)

O Ignition ON

O PULL decompression handle and HOLD

O DEPRESS fuel pump button

O Accelerate to about 100 km/h (54 kt, 62 mph)

O RELEASE decompression handle

WITH ENGINE RUNNING:

O RELEASE fuel pump button and

O Climb at 90-95 km/h (49-51 kt, 56-59 mph)

CHECK LIST

EXTENDING AND STARTING THE POWER PLANT

MAIN SW.

ON

OFF

O Reduce speed to about 90 km/h (49 kt, 56 mph)

O Ignition OFF

O CLOSE fuel shut-off valve

O RETRACT power plant for 5 seconds

O When prop has stopped, RETRACT power plant

at 90-100 km/h (49-54 kt, 56-62 mph) fully

O Switch ASI to pitot head in fin

STOPPING AND RETRACTING THE POWER PLANT

O Water ballast in fin tank correctly filled (if installed) ?

Dump all water ballast in case of doubt !

O Loading charts checked ?

O Parachute securely fastened ?

O Safety harness secured and tight ?

O Seat back, head rest and pedals in

comfortable position ?

O All controls and instruments easily accessible ?

O Airbrakes checked and locked ?

O All control surfaces checked with assistant

for full and free movement in correct sense ?

O Elevator trim correctly set ?

O ASI switched to Pitot head in fin ?

O Canopy closed and locked ?

CHECK LIST BEFORE TAKE-OFF