DG Flugzeugbau DG-1000M Technical specifications

Flight Manual DG-1000M
Issued: July 2014 TN1000/23
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited 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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited 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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited 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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited 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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited
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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited
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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited
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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited
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
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited
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.