DG Flugzeugbau DG-1000M Technische Daten

Flight Manual DG-1000M

Issued: July 2014 TN1000/23

0.2

0Revisions

0.1

Record of revisions

Any revision of the present manual, except actual weighing data, must be

recorded in the following table and in case of approved sections endorsed

by the responsible airworthiness authority.

The new or amended text in the revised page will be indicated by a black

vertical line in the right hand margin, and the under lying document for the

revision and the date will be shown on the bottom of the page.

Rev.

No.

Affected

Pages/section

Description Issue

Date

EASA

Approval

Date

Inserted

Date

Signature

1 Title, 0.1, 0.2,

0.4÷0.7, 1.5, 2.5, 2.7,

2.10, 2.11, 2.13,

2.14, 3.2, 4.7, 4.9

÷4.11, 4.14, 4.15,

4.21, 4.24, 4.29,

4.33, 5.1, 5.4 ÷ 5.12,

6.1 ÷ 6.3, 6.5, 6.7,

6.9 ÷ 6.15, 7.2, 7.6,

7.9, 7.12, 7.25 ÷

7.28, 7.30, 8.3

Manual revision

TN1000/22

October

2012

10. Dec.

2012

2 0.2, 0.4 ÷ 0.6, 2.5,

2.6, 4.33, 7.19, 7.30

Manual revision

TN1000/23

July

2014

7 August

2014

Flight Manual DG-1000M

Issued: July 2014 TN1000/23

0.4

0.2 List of effective pages

Section page issued replaced replaced

0 Title October 2010 October 2012

0.1 see manual amendments

0.2 "

0.3 "

0.4 "

0.5 "

0.6 "

0.7

0.8

1 1.1 October 2010

1.2 March 2011

1.3 October 2010

1.4 October 2010

1.5 October 2010 October 2012

1.6 October 2010

2 EASA-app. 2.1 October 2010

" 2.2 October 2010

" 2.3 October 2010

" 2.4 October 2010

" 2.5 October 2010 October 2012 July 2014

" 2.6 October 2010 July 2014

" 2.7 October 2010 October 2012

" 2.8 October 2010

" 2.9 October 2010

" 2.10 October 2010 October 2012

" 2.11 October 2010 October 2012

" 2.12 October 2010

" 2.13 October 2010 October 2012

" 2.14 October 2010 October 2012

3 " 3.1 October 2010

" 3.2 October 2010 October 2012

" 3.3 October 2010

" 3.4 October 2010

" 3.5 October 2010

" 3.6 October 2010

" 3.7 October 2010

" 3.8 October 2010

Flight Manual DG-1000M

Issued: July 2014 TN1000/23

0.5

0.2 List of effective pages (cont.)

Section page issued replaced

4 EASA-app. 4.1 October 2010

" 4.2 October 2010

" 4.3 October 2010

" 4.4 October 2010

" 4.5 October 2010

4 4.6 October 2010

4.7 October 2010 October 2012

" 4.8 October 2010

" 4.9 October 2010 October 2012

" 4.10 October 2010 October 2012

" 4.11 October 2010 October 2012

" 4.12 October 2010

" 4.13 October 2010

" 4.14 October 2010 October 2012

" 4.15 October 2010 October 2012

" 4.16 October 2010

" 4.17 October 2010

" 4.18 October 2010

" 4.19 October 2010

" 4.20 October 2010

" 4.21 October 2010 October 2012

" 4.22 October 2010

" 4.23 October 2010

" 4.24 October 2010 October 2012

" 4.25 October 2010

" 4.26 October 2010

" 4.27 October 2010

" 4.28 October 2010

" 4.29 October 2010 October 2012

" 4.30 October 2010

" 4.31 October 2010

" 4.32 October 2010

" 4.33 October 2010 October 2012 July 2014

5 " 5.1 October 2010 October 2012

" 5.2 October 2010

" 5.3 October 2010

" 5.4 October 2010 October 2012

5.5 October 2010 October 2012

5.6 October 2010 October 2012

EASA-app. 5.7 October 2010 October 2012

5.8 October 2010 October 2012

5.9 October 2010 October 2012

5.10 October 2010 October 2012

5.11 October 2012

5.12 October 2012

Flight Manual DG-1000M

Issued: July 2014 TN1000/23

0.6

0.2 List of effective pages (cont.)

Section page issued replaced Section

6 6.1 October 2010 October 2012

6.2 October 2010 October 2012

6.3 October 2010 October 2012

6.4 October 2010

6.5 October 2010 October 2012

6.6 October 2010

6.7 October 2010 October 2012

6.8 October 2010

6.9 October 2010 October 2012

6.10 October 2010 October 2012

6.11 October 2010 October 2012

6.12 October 2010 October 2012

6.13 October 2012

6.14 October 2012

6.15 October 2012

7 7.1 October 2010

7.2 October 2010 October 2012

7.3 October 2010

7.4 October 2010

7.5 October 2010

7.6 October 2010 October 2012

7.7 October 2010

7.8 October 2010

7.9 October 2010 October 2012

7.10 October 2010

7.11 October 2010

7.12 October 2010 October 2012

7.13 October 2010

7.14 October 2010

7.15 October 2010

7.16 October 2010

7.17 October 2010

7.18 October 2010

7.19 October 2010 July 2014

7.20 October 2010

7.21 October 2010

7.22 October 2010

7.23 October 2010

7.24 October 2010

7.25 October 2010 October 2012

7.26 October 2010

7.27 October 2010 October 2012

7.28 October 2010 October 2012

7.29 October 2010

7.30 October 2010 October 2012 July 2014

Flight Manual DG-1000M

Issued: July 2014 TN1000/23 EASA app. 2.5

2.4 Power plant Solo Kleinmotoren

Sindelfingen/Maichingen

Engine

manufacturer: Germany

Engine Solo 2 625 02 i, liquid cooled

two cylinder two stroke engine

Start: 50 KW / 68 PS (horse power)Maximum

power: Continuous: 50 KW / 68 PS

Max. Engine RPM: 6600 1/min

" Continuous RPM: 6600 1/min

Max. cylinderhead (coolant) temperature: 105°C

Reduction gear (with 5 V-belts) approx. 1:2,8

Caution: The engine is equipped with an emergency system which may be

activated via a switch in the front (and optionally in the rear) instrument panel in

case of a failure of the engine control unit (ECU). This system ensures

uninterrupted engine operation.

Note: The engine control (ECU) prevents exceeding an engine RPM of 6700 by

switching off the ignition. If you reduce the engine speed the ignition will be

activated again.

Note: The max. engine RPM given by the engine manufacturer is 6700 RPM.

This max. RPM is reduced for operation in the DG-1000M for not exceeding the

max. permissible RPM of the propeller.

Propeller: Diameter 1.6 m (5.25 ft)

Manufacturer: Binder Flugzeug und Motorenbau GmbH

Type /Variant: BM-G1-160-R-120-1

2.5 Power plant instrument markings

(on DEI-NT, DEI=digital engine indicator)

Power plant instrument markings and their significance are shown below:

Engine speed indicator:

At the centre of the DEI-NT display, digital indication with 4 digits,

limitation data printed above display:

green 0-6600 normal operation range RPM

red 6600 max. RPM

Max. continuous RPM:

No indication as identical with max. RPM.

Max. RPM:

When exceeding this RPM a full screen warning message “Engine

Speed” appears, when this warning has been confirmed (by pushing the

selector knob at the right hand side of the display) the engine speed display

is blinkingwhilst the engine speed is above max. RPM.

Flight Manual DG-1000M

Issued: July 2014 TN1000/23 EASA app. 2.6

Cylinderhead (coolant) temperature indicator (CHT):

On right hand upper side of the DEI-NT display, digital indication with 3

digits, limitation data printed above display:

red 95°C up to ser. No. 10-204M22,

105°C from ser. No. 10-205M23 on and earlier ser. No.s if

instruction 3 from TN1000/23 has been executed.

When exceeding this temperature a full screen warning “CHT overTemp”

appears, when this warning has been confirmed (by pushing the selector

knob at the right hand side of the display) the CHT display will keep

blinking as long as the CHT is above the max. CHT.

Fuel quantity indicator:

On left hand upper side of the DEI-NT display, indication digital with 2

digits. Limitation data for the non useable amount of fuel printed above the

display:

red 1 L

When a fuel quantity of approx. 4 Litres is reached a full screen warning

“Low Fuel” appears, when this warning has been confirmed (by pushing

the selector knob at the right hand side of the display) “R” is displayed and

blinking.

2.6 Fuel

Fuel capacity:

Fuselage tank:

total: 41 L (10.83 US gal.)

Non useable amount of fuel: 1 L (0.26 US gal.)

Useable amount of fuel: 40 L (10.57 US gal)

Approved fuel grades:

Car super gasoline min. 95 octane (ROZ) (RON) leaded or unleaded

or: AVGAS 100 LL (only if super gasoline is not available)

or: mix 50% AVGAS 100 LL and 50% Car super gasoline unleaded min

92 octane (ROZ) (RON)

Caution: Fuel with more than 10% Ethanol is not acceptable to be used for the

DG-1000M engine.

mixed with self mixing Super quality two stroke oil - specification JASO

FC or FD or higher quality. Mixing ratio 1:50.

Note: The SOLO company recommends the following oil types: CASTROL

Actevo 2T or CASTROL Super TwoStroke..

Flight Manual DG-1000M

Issued: July 2014 TN1000/23 EASA app. 4.33

4.6 Flight with the engine removed from the aircraft

The DG-1000M can be flown without the engine when the engine is sent

for a major overhaul, or removed to decrease the aircraft empty weight for

competition flying or for aerobatics.

The following items must be executed: (see sect. 4.10.9 in the maintenance

manual).

1. Remove the powerplant. Spindle drive, gas struts and exhaust system

remain in the fuselage.

Insulate the terminal of the starter motor positive wire (in the engine

compartment).

2. In addition to the on-board battery install a battery in the fin see section.

7.17.6.

3. Carry out a C.G. calculation according to section 6.9. The in-flight C.G.

will be moved forward by approx. 75 mm (3 in.) depending on the

flight mass and empty mass C.G.

This C.G. shift is acceptable, as the forward limit of the in-flight C.G.

for operation with engine removed is 120 mm in front of the C.G. with

engine installed.

Item mass C.G. behind

datum moment

kg lbs. m ft. kg×m ft.×lbs.

Mass reduction

engine with propeller -58 -127.9 1.261 4.14 -73.14 -529.0

Additional mass

fin battery 5.5 12.1 5.34 17.52 29.37 212.4

Difference -52.5 -115.7 0.834 2.735 -43.77 -316.6

4. Fix the limit switch “engine retracted” with a Ty-rap in the actuated

position. Otherwise the DEI-NT will remain in the powered flight

mode.

5. Tape the engine doors carefully with fabric tape.

Note: After switching on the main switch some failure messages will be

displayed. Confirm each message by pressing the selector switch to eliminate

the message.

Flight Manual DG-1000M

Issued: July 2014 TN1000/23 7.19

13."Raise Gear" = Landing gear should be retracted, appears 8 minutes after

take-off in case the landing gear is still extended.

14."Starter Run" = Starter motor didn’t disengage and is producing electric

power, stop the engine immediately to prevent damage of the control unit.

This message can't be erased by pushing the selector knob.

15."CBox OvrTemp" = Starter motor control in control unit above temperature

limit. If this warning appears don’t operate the starter motor any more. If

possible switch off the main switch.

16."Battery Overch." = Battery voltage constantly above 14,9V.

17."Low Battery" = Battery voltage below 11V for more than 30 seconds.

Caution: The starter motor control in the control unit will supply no electric

power to the starter motor if the battery voltage is below 11 V prior to the

starting attempt, starting is not possible!

18."Main Switch" = Reminder to switch off the main switch.

With landing gear retracted (e.g.on the trailer after derigging) after 60

seconds.

With landing gear extended (e.g. in the hangar) after 5 minutes.

In both cases time counts after the last operation of any item of the

electrical system.

19.Only with TNDG-G-09 executed: "Open Fuel! " = Fuel cock not fully

opened. Warning appears when ignition will be switched on.

7.4.5.3 Explanation for failure messages

Spindle Fuse:

The re-settable fuse for the spindle drive may be blown in the following

cases:

a) The propeller hub hooks during extension at the engine doors.

b) The limit switch in position engine extended or retracted is not operated.

As soon as the fuse is blown the Control Unit changes to manual extension-

retraction mode and thus cuts off power to the spindle drive and reports the

failure to the DEI-NT.

After the cool-down time (approx. 10sec.) the message disappears and the

symbol for manual operation (hand) will be displayed on the screen.

You may reactivate the automatic operation by operating the ignition

switch, even during the cool-down time.

Case a) Retract the powerplant again manually, then try to extend the

engine again.

Case b) Partially retract the engine manually and then try to extend the

powerplant manually up to its operating position.

Flight Manual DG-1000M

Issued: July 2014 TN1000/23 7.30

7.17.5 Battery in the baggage compartment with battery selector switch

An additional battery Z73 12V/7Ah with holder Z72 or Z01 12V/10Ah

with holder Z200 may be installed in the baggage compartment.

In this case a battery selector switch must be installed in the front

instrument panel.

Selector positions:

up = internal battery centre position = off down = additional batteries

Preferably the gliding computers and loggers shall be connected to this

switch.

The battery fuse is installed at the battery, type: G fuse G 250 V 5 x 20 / 4

A fast.

7.17.6 Battery in the fin

A battery may be installed in the fin.

Section 4.2.5 and the loading chart see section 6.8.4 must be regarded.

Only the use of the factory supplied battery Z110 (12 V, min. 12 Ah, mass

5.5 kg (12.1 lbs.) is permitted.

The battery fuse is installed at the battery, type: G fuse G 250 V 5 x 20 / 4

A fast.

The wiring for this battery is in parallel to the battery in the baggage

compartment.

7.17.7 Radio installation with automatic commutation

If the factory approved radio installation set is installed, the radio will be

switched automatically from "normal" mode to "engine on" mode with the

engine extended. With "normal mode" only the goose neck microphones

are working.

With "engine on" mode the intercom system is working. Only the

microphones of the headsets are working.

The loudspeaker and the speakers of the headsets are working together in

both modes.

Note: Some modern radios (e.g. Becker AR 6201) enable operation of headsets

with standard microphones together with the gooseneck-microphones which are

equipped with dynamic microphones.

To use headsets with standard microphones one V-adapter 10E109 must be

installed per headset. In gliding mode the standard microphones of the headsets

will not be switched off.

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