SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T FLUGHANDBUCH Ausgabe Mai 2000 

FLIGHT MANUAL issue May 2000 

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd. Nr. 

der 

Berichtigung 

Abschnitt Seiten Datum 

der 

Berichtigung 

Bezug 

Datum der 

Anerkennung 

durch 

LBA/EASA

Datum 

der Einarbeitung

Zeichen 

/Unter- 

 schrift 

Revision

No. 

Affected 

section 

Affected 

page 

Date of 

issue 

Reference Date of 

Approval 

by 

LBA/EASA

Date of 

Insertion 

Signature 

1 

0 

9 

0.2.6 

9.1.1 

9.2 

9.3 

Februar/ 

February.

2003 

TN 890-2

(Handst. für Seitenr. Werk-Nr. 53, und ab 

89 wahlw. bei der Herstlg.) 

(hand operated rudder system, S/N 53, 89 

and up optional installation during constr.)

10.03.2003

 

2 

0 

2 

4 

7 

0.2.2 

0.2.3 

0.2.5 

2.5 

4.2.2 

7.3.1 

7.3.5 

Oktober/ 

October 

2003 

MB 890-3 

LCD-Tankanzeige Werk-Nr. 1 bis 84 wahlweise, Serie ab 85 

LCD fuel quantity indicator 

optional S/N 1 – 84, standard S/N 85 and 

up

09.12.2003

 

3 

0 

7 

0.2.5 

7.2.1 

7.2.7 

7.3.1 

Februar/ 

February.

2004 

MB 890-5 

(Haubenscharnier Hebel vorn ab S/N 97 

(canopy hinge, lever Front S/N 97 and up)

11.06.2004

 

4 4 

7 

4.4 

7.2.4 

August 

2004 

TN 890-4

(herausnehmbarer hinterer Steuerknüppel 

wahlweise alle Werk-Nr.) 

(removable aft stick, optional all S/N)

10.12.2004

 

5 

0 

1 

2 

3 

4 

5 

8 

0.2.1 

0.2.2 

0.2.3 

0.2.4 

0.2.6 

1.2 

2.15 

3.8 

4.1.1 

4.2.3.1 

4.3.1 

5.3.2.1 

8.3 

Januar/ 

January 

2005 

Allgemeine Berichtigung 

General revisions 

 

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 FLUGHANDBUCH Ausgabe Mai 2000 

FLIGHT MANUAL issue May 2000 

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd. Nr. 

der 

Berichtigung 

Abschnitt Seiten Datum 

der 

Berichtigung

Bezug 

Datum der 

Anerkennung durch 

LBA/EASA 

Datum 

der Einarbeitung

Unter- 

 schrift 

Revision

No. 

Affected 

section 

Affected 

page 

Date of 

issue 

Reference Date of 

Approval by 

LBA/EASA 

Date of 

Insertion 

Signature 

6 0 

4 

0.2.1 

0.2.3 

4.5.1.2 

Juli 

July 

2005 

TN 890-6 

F-Schlepp mit Motorsegler, wahlweise 

Werk-Nr. 1 bis 125 

Aerotow with powered 

sailplane, optional 

S/N 1 through 125

20.12.2005 

 

7 

0 

1 

2 

4 

5 

6 

7 

Deckblatt cover sheet

0.2.2 

0.2.3 

0.2.4 

0.2.5 

1.2 

1.4.1 

1.4.3 

1.5 

2.3 

4.3.1 

4.3.2 

4.5.1.2 

4.5.3.1 

4.5.3.3 

4.5.3.4 

4.5.4.1 

4.5.5 

5.2.2 

5.3.2.1 

5.3.2.2 

6.2.3 

6.2.4 

6.2.7 

7.2.1*)

7.2.4 

7.2.7*)

7.7 

September 

2005 

*) entfällt bei 

Werk-Nr. 126 

not applicable 

for S/N 126

MB 890-6 

Winglets, Hinterkantenklappen (Werk-Nr. 126) 

und gefedertes Fahrwerk ab Werk-Nr. 128 

Winglets, trailing edge 

flap (S/N 126) and 

landing gear with shock 

absorber struts 

S/N 128 and on. 

10.02.2006 

 

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 FLUGHANDBUCH Ausgabe Mai 2000 

FLIGHT MANUAL issue May 2000 

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd. 

Nr. der

Berichtigung 

Abschnitt Seiten 

Datum 

der 

Berichtigung 

Bezug 

Datum der 

Anerkennung durch 

LBA/EASA 

Datum 

der Einarbeitung

Unter- 

 schrift 

Revision 

No. 

Affected 

section 

Affected 

page 

Date of 

issue 

Reference Date of 

Approval by 

LBA 

Date of 

Insertion 

Signature 

8 

0 

1 

4 

5 

0.2.1 

0.2.2 

0.2.3 

0.2.4 

1.4.1 

1.5 

4.3.1 

4.5.3.1 

4.5.3.3 

4.5.3.4 

4.5.4.1 

5.3.2.1 

5.3.2.2 

November 

2005 

TN 890-7 

Winglets wahlweise 

Werk-Nr. 1 bis 125 

winglets, optional 

S/N 1 through 125 

17.03.2006 

 

9 0 

1 

0.2.2 

1.4.1 

Juli / 

July 

2006 

Ergänzungen zum ÄB 890-6

Flügel in CFK-Bauweise 

Werk-Nr. 147, 150 und ab Werk-Nr.151 

Supplement to MB 890-6 

Wing construction in CFRP shell, 

S/N 147,150 and 151 and up

24.10.2006 

(Werk-Nr. 

150: 

07.09.2007) 

 

10 

0 

1 

2 

3 

4 

5 

6 

0.2.2 

0.2.3 

0.2.4 

1.4.3 

2.6 

2.10 

2.13 

2.15 

3.5 

4.5.1.2 

4.5.1.4 

4.5.3.2 

4.5.4.1 

5.2.2 

5.3.2.1 

6.2.1 

6.2.5 

6.2.6 

Juni / 

June 

2007 

Ergänzungen zum ÄB 890-6 

ab Werk-Nr. 172 

oder 

TM 890-9 

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

optional 

Erhöhung der max. Flugmasse auf 750 

kg und der nichttragenden Teile 

auf 500 kg 

Supplement to MB 890-6 

S/N 172 and up 

or 

TN 890-9 

SN 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

07.09.2007 

 

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 FLUGHANDBUCH Ausgabe Mai 2000 

FLIGHT MANUAL issue May 2000 

0.1 Erfassung der Berichtigungen / Record of Revisions

Lfd. 

Nr. der

Berichtigung 

Abschnitt Seiten 

Datum 

der 

Berichtigung 

Bezug 

Datum der 

Anerkennung durch 

LBA/EASA 

Datum 

der Einarbeitung

Unter- 

 schrift 

Revision 

No. 

Affected 

section 

Affected 

page 

Date of 

issue 

Reference Date of 

Approval by 

LBA 

Date of 

Insertion 

Signature 

11 0 

9 

0.2.6 

9.2 

9.4 

Juni / 

June 

2007 

TN 890-11 

Nasenschleifsporn wahlweise 

Alle Werk-Nr. 

Nose skid optional 

All S/N

29.06.2007 

 

12 0 

2 

4 

0.1.2 

0.1.3 

0.1.4 

0.1.5 

0.2.2 

0.2.3 

2.10 

4.3.3 

4.3.4 

4.5.3.7 

4.5.8 

November

2011 

TN 890-13 

Änderung des Flughandbuchs und des 

Wartungshandbuchs, 

Werk-Nr. 1 bis 174 

MASSNAHME 1 

Amendment of the Flight Manual and 

the Maintenance Manual, 

S/N 1 through 174 

ACTION 1 

 

0 

1 

2 

4 

6 

0.1.5 

0.2.2 

0.2.4 

1.2 

2.15 

4.4 

6.2.1 

6.2.3 

6.2.4 

6.2.7 

November

2011 

TN 890-13 

Änderung des Flughandbuchs und des 

Wartungshandbuchs, 

Werk-Nr. 1 bis 174 

MASSNAHME 2 

Amendment of the Flight Manual and 

the Maintenance Manual, 

S/N 1 through 174 

ACTION 2 

 

 

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 FLIGHT MANUAL

1.2 Certification basis

This non-self-launching powered sailplane, model designation 

Duo Discus T 

has been approved originally by the Luftfahrt-Bundesamt (LBA) in compliance 

with the airworthiness requirements 

JAR- 22 effective on October 28, 1995 

(Change 5 of the English original issue). 

The LBA Type Certificate is No. 890 and was issued originally on 21.12.2001 

Category of Airworthiness: UTILITY 

The Noise Certification was based on the 

„Aircraft Noise Protection Requirements „ (LSL), Revision of January 1, 1991,

and includes the supplement dated April 6, 2000. 

By the European Aviation Safety Agency a new Type Certificate was issued. 

This EASA-Type Certificate EASA.A.074 was issued on 10.02.2006. 

November 2011 TM 890-13 

Revision 12 1.2 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

2.10 Flight crew

 When flown solo, the “Duo Discus T” is controlled from the front seat. 

 Observe the minimum load on the front seat – if necessary, ballast must be 

 installed to bring the load up to a permissible figure. See also section 6.2: 

 “Weight and Balance Record / Permitted Payload Range”. 

 When flown with two pilots, the “Duo Discus T” can be operated from the rear 

 seat in compliance with the following requirements: 

„ All necessary control elements and instruments, including engine 

control unit, must be installed for the rear seat. The priority selector 

switch must be switched with the key up (engine control unit in the rear 

panel active). 

„ The responsible pilot needs sufficient experience and practice in flying 

from the rear seat 

„ No water ballast in the wings 

November 2011 TN 890-13 approved 

Revision 12 MB 890-6 except SN 126 2.10 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T FLIGHT MANUAL

November 2011

Revision 12 TN 890-13 appr. 2.15

Note: Further placards are shown in the Maintenance Manual.

2.15 Limitations placards

MAXIMUM PERMITTED SPEEDS (IAS) : km/h kt mph

Never exceed speed 250 135 155

Rough air speed 180 97 112

Maneuvering speed 180 97 112

Aerotowing speed 180 97 112

Winch launching speed 150 81 93

Landing gear operating speed 180 97 112

For power plant extension/retraction 110 59 68

With ignition ON 125 67 78

Power plant extended speed 160 86 99

PERMISSIBLE MINIMUM SPEED (IAS):

For power plant extension/retraction 90 49 56

Max. permitted speed

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

250

250

250

241

229

217

205

194

183

172

162

VNE(IAS)

km/h kt mph

135

135

135

130

124

117

111

105

 99

 93

 87

155

155

155

150

142

135

127

121

114

107

101

Altitude

[m] [ft]

0

3281

6562

9843

13123

16404

19685

22966

26247

29528

32808

MAX. PERMITTED A.U.WEIGHT (MASS): 1543 lb / 700 kg

WEAK LINK FOR TOWING

Nose wheel : 3.0 bar (43 psi)

Main wheel : 4.0 bar (57 psi)

Tail wheel :

(if installed) 3.0 bar (43 psi)

for Aerotow: max. 850 daN (1910 lb)

for Winch launch: max. 950 daN (2135 lb)

TIRE PRESSURE

*) Values as an example, the actually applicable

values - see 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
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T FLIGHT MANUAL

November 2011 TN 890-13

Revision 12 TN 890-9 or S/N 172-174 (MB 890-6) appr. 2.15

Note: Further placards are shown in the Maintenance Manual.

2.15 Limitations placards

MAXIMUM PERMITTED SPEEDS (IAS) : km/h kt mph

Never exceed speed 250 135 155

Rough air speed 180 97 112

Maneuvering speed 180 97 112

Aerotowing speed 180 97 112

Winch launching speed 150 81 93

Landing gear operating speed 180 97 112

For power plant extension/retraction 110 59 68

With ignition ON 125 67 78

Power plant extended speed 160 86 99

PERMISSIBLE MINIMUM SPEED (IAS):

For power plant extension/retraction 90 49 56

Max. permitted speed

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

250

250

250

241

229

217

205

194

183

172

162

VNE(IAS)

km/h kt mph

135

135

135

130

124

117

111

105

 99

 93

 87

155

155

155

150

142

135

127

121

114

107

101

Altitude

[m] [ft]

0

3281

6562

9843

13123

16404

19685

22966

26247

29528

32808

MAX. PERMITTED A.U.WEIGHT (MASS): 1654 lb / 750 kg

WEAK LINK FOR TOWING

Nose wheel : 3.0 bar (43 psi)

Main wheel : 4.0 bar (57 psi)

Tail wheel :

(if installed) 3.0 bar (43 psi)

for Aerotow: max. 850 daN (1910 lb)

for Winch launch: max. 950 daN (2135 lb)

TIRE PRESSURE

*) Values as an example, the actually applicable

values - see 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
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

 (4) a) Check fuselage for damage, especially on its lower side 

b) Check that the static pressure ports for the ASI on the tail boom 

(1.02 m / 3.35 ft forward of the base of the fin) and below the spar 

stub cut-out are clear 

Visual inspection of the power plant:

CAUTION: IGNITION MUST BE SWITCHED OFF ! 

c) Check propeller hub and propeller blades for cracks or other 

damage, in particular also the area near the blade bearing marked 

in the following picture. 

 

 Check propeller blades for ease of movement. Each blade should

unfold automatically when it is in the bottom position, otherwise the 

bearing at the blade root should be lubricated with thin oil. 

d) Check power plant for loose bolts and nuts, check all locks and 

stops 

e) Check exhaust system and engine pylon for cracks, especially at 

the welding joints 

November 2011 TN 890-13 appr. 

Revision 12 4.3.3
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

f) Check cooling baffles for cracks and correct attachment 

g) Check rubber elements of the engine mounting and exhaust 

h) Check components, lines, hoses, pipes and wires etc. for chafing marks 

i) Check condition, function and tension of engine arresting wires, engine 

door operating cables and door actuating mechanism 

j) Check condition of the retaining elastic band and that it is hooked up to 

the engine arresting wires 

k) Pull back the decompression handle and hold - prop must rotate freely. 

Release the handle and check that the actuating lever on the pylon 

returns to its stop. 

The gap between the decompression valve interconnecting link and the 

actuating lever on the pylon must be at least 2.0 mm (0.08 in.) 

(5) a) Check condition of tail skid or wheel. 

 If the latter is installed, check the tire pressure: 

 3.0 bar (44 psi) 

b) Should a total energy compensation probe be used, mount it and check 

the line (when blowing gently from the front to the probe, the 

variometer(s) connected should read "climb”) 

c) Check that the fin-mounted PITOT tube is clear. 

 When blowing gently into this probe, the ASI must register 

 (with pneumatic valve set at “Power off”) 

d) Check that the opening for the fuel tank vent line 

 (at the upper end of the fin) is clear 

When equipped with a water ballast fin tank (option):

e) Check that the fin tank spill holes are clear 

f) Check water ballast level in fin tank (in case of doubt, discharge ballast) 

g) Check that the dump hole for the fin tank in the tail wheel fairing (if 

installed) is clear 

November 2011 TN 890-13 appr. 

Revision 12 4.3.4 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL 

4.4 Pre-flight inspection 

November 2011 TN 890-13 appr. 

Revision 12 4.4 

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 ? 

CHECKLIST BEFORE TAKE-OFF
SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

Automatic control of engine speed (RPM)

In order to reduce the increase of the engine speed as flying speed 

increases, the number of ignition impulses is electronically lowered on 

exceeding the speed for best climb VY so that the engine is throttled down. 

Automatic ignition cutt-off device

As a safety device the ignition of both cylinders is cut off just prior to reaching 

the maximum permitted propeller speed. 

Normally the ignition is cut off after reaching the maximum permitted speed 

Vmax1 (i.e. at about 125 km/h, 67 kt, 78 mph). The ignition nevertheless may 

also be cut off at lower speeds due to gusts, causing an increase of the RPM. 

Once the ignition has been cut off, reduce the flying speed quickly to 95 km/h 

(51 kt, 59 mph) through 105 km/h (57 kt, 65 mph) so that the ignition is 

activated automatically. 

Then the engine will run within its normal operating range. 

Or switch the ignition off when the engine will not be further used. 

WARNING:

The ignition cut-off device is a safety measure. 

Operating the “Duo Discus T” with the ignition cut-off device constantly in 

action is not permitted. 

Leave this speed range immediately by reducing the flying speed or switch 

off the ignition. 

IMPORTANT NOTE:

The use of the engine in rain must be avoided, as this may damage the 

propeller. 

November 2011 TN 890-13 approved 

Revision 12 4.5.3.7 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

4.5.8 Flight in rain

When flying the “Duo Discus T” with a wet surface or in rain, the water 

drops adhering to the wings cause a deterioration of its flight 

performance which cannot be expressed in numerical values due to 

the difficulties involved with such measurements. Often the air mass 

containing the moisture is also descending so that - compared with a 

wet powered sailplane in calm air - the sink rates encountered are 

higher. 

Flight tests in rain, conducted by the manufacturer, did not reveal any 

significant differences in the stalling behaviour or stalling speeds. 

It cannot be excluded, however, that excessive alterations of the airfoil 

(as caused by snow, ice or heavy rain) may result in higher minimum 

speeds. 

Do not fly into rain areas with the power plant extended and running 

because there is a danger that the propeller blades could be damaged. 

Approach in rain: See page 4.5.4 

November 2011 TN 890-13 appr. 

Revision 12 4.5.8 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

6.2 Weight and balance record / Permitted seat load range

The following loading chart, page 6.2.3 (power plant installed) or 6.2.4 

(power plant removed) shows beneath others the empty mass, the 

maximum and minimum Ioad on the seats and the maximum load in the 

fuselage. 

These charts are established with the aid of the last valid weighing 

report - the required data and diagrams are found in the Maintenance 

Manual. 

Both loading charts (weight & balance log sheets) are only applicable 

for this particular “Duo Discus T”, the serial number of which is shown 

on the title page. 

A front seat Ioad of less than the required minimum 

is to be compensated by ballast - there are three (3) methods: 

1. By attaching ballast (lead or sand cushion) 

 firmly to the lap belt mounting brackets. 

Optional trim ballast mounting provision(s)

2. a) By installing ballast (by means of lead plates) 

 at the base of the front instrument panel 

 (for further information refer to page 6.2.2) 

b) By attaching, ballast (in addition to method 2 a) 

 by means of lead plates to the front control stick mounting frame 

on the starboard side near the base of the instrument panel 

(for further details refer to page 6.2.2). 

3. When flown with two occupants, the minimum load on the front seat can 

be reduced by 25% of the load on the rear seat. This reduction of the 

minimum load on the front seat is allowed only if the nose heavy 

moment of the load in the rear seat is not compensated by water 

ballast in the fin. 

November 2011 TN 890-13 

Revision 12 6.2.1
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL 

WEIGHT AND BALANCE LOG SHEET (loading chart) FOR S/N ........... 

 POWER PLANT INSTALLED 

Date of weighing: 

Empty mass [kg] 

Equipment list dated 

Installed batteries 2)

count count count count 

1 E 1 E 1 E 1 E 

 C1/C2 C1/C2 C1/C2 C1/C2 

Empty mass c/g position aft of 

datum 

 

Max. load [kg] in fuselage 

Load [kg] on the seats (crew including parachute): 

Front seat load 

when flown solo:

with two occupants:

max. 110 110 110 110 

max. 110 110 110 110 

Rear seat load 

with two occupants: max. 110 110 110 110 

Water ballast fin tank 

installed (YES / NO) 

 

Front seat load regardless of load on rear seat min.1)

 

Inspector 

Signature / Stamp 

 

1)

 

2) Installed batteries (see page 7.12.2): 

 (E) engine battery 

 (C1/C2) batteries in front of rear stick mounting frame 

For the determination of the water ballast quantity permitted in the wing tanks refer 

to page 6.2.5. 

For the determination of the water ballast quantity permitted in the fin tank refer to 

page 6.2.6 through 6.2.8. 

November 2011 TN 890-13 

Revision 12 6.2.3 

Warning: 

 If a fin tank is installed, the pilot must either dump all water ballast prior of take-off, or ensure that 

the ballast quantity in the fin tank is compensated by an appropriate load in the wing tanks and/or 

on the rear seat. 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL 

WEIGHT AND BALANCE LOG SHEET (loading chart) FOR S/N ........... 

 POWER PLANT REMOVED 

Date of weighing: 

Empty mass [kg] 

Equipment list dated 

Installed batteries 2)

count count count count 

E E E E 

 C1/C2 C1/C2 C1/C2 C1/C2 

Empty mass c/g position aft of 

datum 

 

Max. load [kg] in fuselage 

Load [kg] on the seats (crew including parachute): 

Front seat load 

when flown solo:

with two occupants:

max. 110 110 110 110 

max. 110 110 110 110 

Rear seat load 

with two occupants: max. 110 110 110 110 

Water ballast fin tank 

installed (YES / NO) 

 

Front seat load regardless of load on rear seat min.1)

 

Inspector 

Signature / Stamp 

 

1)

 

2) Installed batteries (see page 7.12.2): 

 (E) engine battery 

 (C1/C2) batteries in front of rear stick mounting frame 

For the determination of the water ballast quantity permitted in the wing tanks refer 

to page 6.2.5. 

For the determination of the water ballast quantity permitted in the fin tank refer to 

page 6.2.6 through 6.2.8. 

November 2011 TN 890-13 

Revision 12 6.2.4 

Warning: 

 If a fin tank is installed, the pilot must either dump all water ballast prior of take-off, or ensure that 

the ballast quantity in the fin tank is compensated by an appropriate load in the wing tanks and/or 

on the rear seat. 
SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK 

Duo Discus T FLIGHT MANUAL

Waterballast in (optional) fin tank

Note: When determining the useful load in the fuselage, it is not

necessary to take the water ballast in the fin into account because 

of flight mechanic reasons. 

In order to avoid that the maximum permitted all-up weight (mass) is exceeded, 

the ballast in the fin tank must also be taken into account when determining the 

maximum allowable ballast quantity for the wing tanks. 

 

Example: 

Assumed ballast load in wing tanks: 40 kg/Liters 

 (88 lb/10.6 US Gal) 

Assumed load on aft seat: 75 kg (165 lb) 

According to the diagrams on page 6.2.8 the following loads in the fin tank are 

permissible (fill only full Liters): 

For ballast in wing tank : m FT = 1 kg/Liter 

 (2.2 lb/0.26 US Gal) 

For load on aft seat : Fm FT = 6 kg/Liters 

 (13.2 lb/1.58 US Gal) 

Total ballast in fin tank : m FT + Fm FT = 7 kg/Liters 

 (15.5 lb/1.85 US Gal) 

November 2011 TN 890-13 

Revision 12 6.2.7