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Duo Discus T WARTUNGSHANDBUCH / MAINTENANCE MANUAL

0.2 Verzeichnis der Seiten / List of effective pages

Seite / Page Datum / Date Bezug / Reference

0.1.1

0.2.1 0.2.2 0.2.3

0.3.1 0.3.2 0.3.3

1.1 1.2.1 1.2.2 1.2.3 1.3 1.4

2.1.1 2.1.2 2.2.1 2.2.2 2.3 2.4

3.1.1 3.1.2 3.2.1 3.2.2 3.2.3 3.2.4 3.3.1 3.3.2 October 2007

October 2007 November 2011

October 2007 October 2007 October 2007 October 2007 October 2007 October 2007

October 2007 October 2007 October 2007 October 2007 October 2007 October 2007

October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 TN 890-13 or MB 890-8

0.2.1SCHEMPP-HIRTH FLUGZEUGBA U GmbH., KIRCHHEIM/TECK

Duo Discus T WARTUNGSHANDBUCH / MAINTENANCE MANUAL

0.2 Verzeichnis der Seiten / List of effective pages

Seite / Page Datum / Date Bezug / Reference

4.1 4.2.1 4.2.2 4.2.3 4.3

5.1.1 5.1.2 5.2.1 5.2.2 5.3 5.4.1.1 5.4.1.2 5.4.2 5.5 5.6 5.7.1 5.7.2 5.8.1 5.8.2 5.9 5.10 5.11

6.1 6.2.1 6.2.2 6.3 6.4.1 6.4.2 6.4.3 6.5 6.6.1 6.6.2 6.7 6.8 October 2007

October 2007 October 2007 October 2007 October 2007

October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007 October 2007

October 2007 October 2007 October 2007 October 2007 October 2007 November 2011 October 2007 October 2007 November 2011 October 2007 November 2011 October 2007 TN 890-13 or MB 890-8

TN 890-13 or MB 890-8

TN 890-13 or MB 890-8

0.2.2	

	



 	
   
   

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Duo Discus T MAINTENANCE MANUAL

Diagrams:

1 Control circuits in the fuselage Oct. 2007 2 Rudder control circuits Oct. 2007 3 Control circuits in the wing Oct. 2007 4 Undercarriage with retracting linkage and hydraulic disc brake Oct. 2007 5 Inspection opening in the aileron web Oct. 2007 6 Inspection opening in the fin Oct. 2007 7 Aileron template Oct. 2007 8 Power plant installation Oct. 2007 9 Wiring diagram avionic Nov. 2011 10a Wiring diagram / power plant - 1 control unit Oct. 2007 10b Wiring diagram / power plant - 2 control units Oct. 2007 11 Connector I-panel / airframe Nov. 2011 12 Special tool for removal and re-installation of the pylon gas strut Oct. 2007

Anti collision markings Duo Discus T Oct. 2007

Check list:

1. Engine mount (pylon) and pi voting mechanism Oct. 2007 2. Fuel system Oct. 2007 3. Electrical system (power plant mo nitoring, engine test run) Oct. 2007

Trouble shooting lists Duo Discus T Page 1 Oct. 2007 Page 2 Oct. 2007 Page 3 Oct. 2007 Page 4 Oct. 2007

Repair Instruction Duo Discus T Page 1 Oct. 2007 Page 2 Oct. 2007 Page 3 Oct. 2007 Page 4 Oct. 2007

Repair Instructions for Schempp-Hir th Sailplanes and Powered Sailplanes

constructed from Fiber Reinforced Plastic

It is recommended that Technical Notes (TNs) and Airworthiness Directives (Ads) are inserted behind this page.

November 2011 TN 890-13 / MB 890-8 Revision 3 0.3.3	

	


  


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Duo Discus T MAINTENANCE MANUAL

To facilitate the checking of the empty mass centre of gr avity, the table below shows ñ at different empty mass values ñ 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

400 882 39.9 88.0 41.5 91.5 43.1 95.0 44.7 98.6 46.3 102.1

410 904 40.4 89.1 42.0 92.6 43.6 96.1 45.1 99.4 46.7 103.0

420 926 40.8 90.0 42.4 93.5 44.0 97.0 45.6 100.6 47.2 104.1

430 948 41.3 91.1 42.9 94.6 44.5 98.1 46.1 101.7 47.6 105.0

440 970 41.7 91.9 43.3 95.5 44.9 99.0 46.5 102.6 48.1 106.1

450 992 42.2 93.1 43.8 96.6 45.4 100.1 47.0 103.6 48.6 107.2

460 1014 42.7 94.2 44.2 97.5 45.8 101.0 47.4 104.5 49.0 108.0

470 1036 43.1 95.0 44.7 98.6 46.3 102.1 47.9 105.6 49.5 109.1

480 1058 43.6 96.1 45.2 99.7 46.7 103.0 48.3 106.5 49.9 110.0

490 1080 44.0 97.0 45.6 100.5 47.2 104.1 48.8 107.6 50.4 111.1

500 1103 44.5 98.1 46.1 101.7 47.7 105.2 49.2 108.5 50.8 112.0

510 1125 44.9 99.0 46.5 102.5 48.1 106.1 49.7 109.6 51.3 113.1

520 1147 45.4 100.1 47.0 103.6 48.6 107.2 50.1 110.5 51.7 114.0

530 1169 45.8 101.0 47.4 104.5 49.0 108.0 50.6 111.6 52.2 115.1

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 TM 890-13 / MB 890-8 Revision 3 6.4.2SCHEMPP-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) **

1 batt. ** beside U/C (C3) **

1 batt. ** in fin (F1, F2) ** front seat load

rear seat load LOAD ON THE SEATS

(crew incl. parachutes)

70* kg 154* 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 ñ 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 TN 890-13 / MB 890-8 Revision 3 6.6.1

The maximum load in the cockpit (load on both seats baggage + trim ballast) must not be exceeded. the front seat load is below the minimum front sea t load: e 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

+ If

se

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 lbSCHEMPP-HIRTH FLUGZE UGBAU GmbH., KIRCHHEIM/TECK

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



### 6.7 Mass ñ C/G diagram

November 2011 A dditional permitted range with optional water ballast fin tank

MAXIMUM ALL-UP MASS

PERMITTED RANGEFOREMOST C/G POSITION

MINIMUM ALL-UP MASSREARMOST C/G POSITIONALL - UP MASS (kg / lb) 1543 700 lb kg

1433 650

1323 600

1213 550

1102 500 1654 750

1058 480

(mm / in.) aft of datum in flight mm in. X

Revision 3 TN 890-13 / MB 890-8 6.7SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

November 2011 Revision 3 TN 890-13 / MB 890-8 8.1 Placing:

Baumuster:

Werk-Nr./Bj:

Ger‰te-Nr.: Hersteller:

SCHEMPP-HIRTH Flugzeugbau GmbH Duo Discus T / EASA.A.074 

### 8. Placards and pictograms

Cockpit inner skin on the right in the rear IDENTIFICATION PLATE (fire resistant)

OPERATING LIMITS Cockpit inner skin on the left for either seat

Cockpit inner skin on the left in the rear OPERATING LIMITS 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 MAXIMUM PERMITTED SPEEDS (IAS) : km/h kt mph
Never exceed speed 262.8 142 163 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 262.8

262.8 262.8 253 241 228 215 204 192 180 170 V NE (IAS) km/h kt mph
142 142 142 137 130 123 116 110 104 97 92 163 163 163 157 150 142 134 127 119 112 106 Altitude [m] [ft]
0 3281 6562 9843 13123 16404 19685 22966 26247 29528 32808 MAX. PERMITTED A.U. WEIGHT (MASS): 1654 lb / 750 kg

Cockpit inner skin on the right for either seat

Operating Conditions: See Flight Manual (A) Inside loops (C) Lazy eight (B) Stalled turns (D) Spins A E R O B A T I C S
With max. permitted A.U.weight of 630 kg / 1389 lbs, without water ballast and power plant retracted or removed the following maneuvers are permitted:November 2011 Revision 3 TN 890-13 / MB 890-8 8.2 Placing:

Cockpit inner skin on the right for either seat

(if installed) Cockpit inner skin on the right (front seat only)

Outbd. end of main wing panels Locking device for outbd. wing panels 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

LOCKING PIN FLUSH
WITH UPPER SURFACE *) 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) **

1 batt. ** beside U/C (C3) **
1 batt. ** in fin (F1, F2) ** 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 MAINTENANCE MANUAL

Note: The stars (*,**,***) refer to the aside mentioned comments. In the real cockpit placard they are omitted.

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! Cockpit inner skin on the right for either seat (if installed)SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK

Duo Discus T MAINTENANCE MANUAL

Placing:

November 2011 Revision 3 TN 890-13 / MB 890-8 8.3 Cockpit inner skin on the right for either seat

O OPEN fuel shut-off valve O Switch ASI to pitot head in nose O Set speed to 90-100 km/h (49-54 kt, 56-62 mph) O Ignition ON O Only in manual operation: EXTEND power plant O When power plant is fully extended: PULL decompression handle and HOLD O Accelerate to about 100 km/h (54 kt, 62 mph) O RELEASE decompression handle WITH ENGINE RUNNING: O Climb at 90-100 km/h (49-54 kt, 56-62 mph) CHECK LIST EXTENDING AND STARTING THE POWER PLANT O Reduce speed to about 90-100 km/h (49-54 kt, 56-62 mph) O Ignition OFF O Only in manual operation: RETRACT power plant for 3 seconds O Only in manual operation: WHEN PROP HAS STOPPED: RETRACT power plant fully O Switch ASI to pitot head in fin O CLOSE fuel shut off valve STOPPING AND RETRACTING THE POWER PLANT

Cockpit inner skin on the left - for front seat only (unless a 2nd control unit is installed) 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