### 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. derBerichtigung Abschnitt Seiten Datum

derBerichtigung Bezug Datum derAnerkennung 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 T N 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 T N 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 st reichen. Das Verzeichnis der Seiten ist gegebenenfalls hand schriftlich zu aktualisieren Note: Cross out revisions which are not included. The list of effective pages must be amended by han d 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. derBerichtigung Abschnitt Seiten Datum der Berichtigung Bezug Datum derAnerkennung 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 st reichen. Das Verzeichnis der Seiten ist gegebenenfalls hand schriftlich zu aktualisieren Note: Cross out revisions which are not included. The list of effective pages must be amended by han d 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. derBerichtigung Abschnitt Seiten Datum derBerichtigung Bezug Datum derAnerkennung 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 Ä B 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 st reichen. Das Verzeichnis der Seiten ist gegebenenfalls hand schriftlich zu aktualisieren Note: Cross out revisions which are not included. The list of effective pages must be amended by han d 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. derBerichtigung Abschnitt Seiten Datum derBerichtigung Bezug Datum derAnerkennung 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 st reichen. Das Verzeichnis der Seiten ist gegebenenfalls hand schriftlich zu aktualisieren Note: Cross out revisions which are not included. The list of effective pages must be amended by han d if necessary

. 

### 0.1.5

### SCHEMPP-HIRTH FLUGZEUGBA U GmbH., KIRCHHEIM/TECK

D u o D i s c u s T FLIGHT MANUAL



## 1.2 Certification basis

This non-self-launching powered sailplane, model designation

Duo Discus T

has been approved originally by the Lu ftfahrt-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 Certificatio n 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 wa s 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 FLUGZEUGBA U GmbH., KIRCHHEIM/TECK

D u o D i s c u s T F L I G H T M A N U A L



## 2.10 Flight crew

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

Observe the minimum load on the front s eat – if necessary, ballast must be installed to bring the load up to a pe rmissible figure. See also section 6.2:

“Weight and Balance Record / Permitted Payload Range”.

When flown with two pilots, the “Duo Discu s 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 Limit ations 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 V NE (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 Limit ations 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 V NE (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 FLUGZEUGBA U GmbH, KIRCHHEIM/TECK

D u o D i s c u s 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 fi n) 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 propel ler 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 py lon for cracks, especially at the welding joints

November 2011 TN 890-13 appr. R e v i s i o n 1 2 4

. 3

. 3

### SCHEMPP-HIRTH FLUGZEUGBA U 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 tens ion 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 compensati on 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 balla st fin tank (option):

e) Check that the fin tank spill holes are clear

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

g) Check that the dump hole for the fi n 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 in stalled) ? 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 po sition ?
O All controls and instruments easily accessible ?
O Airbrakes checked and locked ?
O All control surfaces checked with assistant for ful l and free movement in correct sense ?
O Elevator trim correctly set ?
O ASI switched to Pitot head in fin ?
O Canopy closed and locked ?

CHECKLIS T BEFORE TAKE

- OFF

### SCHEMPP-HIRTH FLUGZEUGBA U GmbH., KIRCHHEIM/TECK

D u o D i s c u s 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 im pulses is electronically lowered on exceeding the speed for best climb V Y 

### so that the engine is throttled down.

Automatic ignition cutt-off device

As a safety device the ignition of both cyli nders is cut off just prior to reaching the maximum permitted propeller speed.

Normally the ignition is cut off afte r reaching the maximum permitted speed V max1 

### (i.e. at about 125 km/h, 67 kt, 78 m ph). The ignition nevertheless may also be cut off at lower speeds due to gus ts, causing an increase of the RPM.

Once the ignition has been cut off, r educe 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 rang e. 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 i gnition cut-off device constantly in action is not permitted. Leave this speed range immediately by r educing the flying speed or switch off the ignition.

IMPORTANT NOTE: The use of the engine in rain must be avoided, as this may d amage the propeller.

November 2011 TN 890-13 approved Revision 12 4.5.3.7

### SCHEMPP-HIRTH FLUGZEUGBA U GmbH, KIRCHHEIM/TECK

D u o D i s c u s 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 express ed in numerical values due to the difficulties involved with such measurements. Often the air mass containing the moisture is also de scending so that - compared with a wet powered sailplane in calm ai r - 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 stallin g speeds.

It cannot be excluded, however, that ex cessive 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 FLUGZEUGBA U GmbH, KIRCHHEIM/TECK

D u o D i s c u s T FLIGHT MANUAL



## 6.2 Weight and balance record / P ermitted 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 em pty mass, the maximum and minimum Ioad on the seats and the maximum load in t he fuselage.

These charts are established with t he aid of the last valid weighing report - the required data and diagra ms are found in the Maintenance Manual.

Both loading charts (weight & balanc e 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 bel t 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 informati on 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 bas e 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 R e v i s i o n 1 2 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 REMO VED



### 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 FLUGZEUGBA U GmbH, KIRCHHEIM/TECK

D u o D i s c u s T FLIGHT MANUAL

Waterballast in (optional) fin tank

Note: When determining the useful l oad 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 t he maximum permitted all-up we ight (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 th e 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 : F m FT 

### = 6 kg/Liters (13.2 lb/1.58 US Gal)

Total ballast in fin tank : m FT 

### + F m FT 

### = 7 kg/Liters (15.5 lb/1.85 US Gal)

November 2011 TN 890-13 Revision 12 6.2.7