### SCHEMPP-HIRTH FLUGZEUGBA U 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 gegebenenf alls 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 FLUGZEUGBA U 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 gegebenenf alls 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 FLUGZEUGBA U 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 gegebenenf alls 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 FLUGZEUGBA U 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 gegebenenf alls 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 FLUGZEUGBA U 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, 2 nd issueAmendment 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 gegebenenf alls 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 FLUGZEUGBA U 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 bra ke 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 – Diagr am 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-i nstallation 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 pl ant 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 Tec hnical Notes (TNs) and Airworthiness Directives (Ads) behind this page.

November 2011 TN 890-13 Revision 16 0.3.3

### SCHEMPP-HIRTH FLUGZEUGBA U 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 bra ke 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 – Diagr am 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-i nstallation 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 pl ant 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 Tec hnical 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 FLUGZEUGBA U GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

To facilitate the checking of the empty mass center of gr avity, the table below shows – at different em pty mass values – the maximum permissible load on the tail wheel, wit h 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 th e 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 rearmo st allowed limit for the corresponding minimum cockpit load and empty mass.

Empty mass Load on tail wheel (or skid) wit h 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 FLUGZEUGBA U GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

To facilitate the checking of the empty mass center of gr avity, 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 re arward c/g position.

The actual load on the tail wheel is determined with th e 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 rearmo st allowed limit for the corresponding minimum cockpit load and empty mass.

Empty mass Load on tail wheel (or skid) wit h 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 FLUGZEUGBA U 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 s eat 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 installati on of fixed trim ballast, the actual minimum front seat load and the maximum cockp it 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 sh ow the actual values, which are also to be entered in the log chart – see f light 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 th e fuel tank is completely filled must be determined in such a way that, with considering 12kg fue l load in the fuel tank, the maximum weight of the non-lifting parts and the maximum weight without water ballast is not exceeded (s ee 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 l oad 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-HIR TH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

*) V alues as an example, the actually applicable values - see Flight Manual log chart section 6.2 - must be entered.

**) Enter number of batteries inst alled at weighing and enlisted in equipment list.

***) With removed power plant the amendment "when fuel t ank 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. 11 0 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):

11 0 kg 243 lb 70* kg

154* lb 11 0 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