DG DG-500M Technical specifications

DG Flugzeugbau GmbH
Im Schollengarten 20 •
••
•D-76646 Bruchsal - Untergrombach •
••
•Germany
Postbox 4120, D-76625 Bruchsal •
••
•Germany
Phone [phone] aircraft sales and service
Phone [phone] spare part and material sales
Phone [phone] repairservice
Phone [phone] switch board and management
Telefax 07257/8922 •
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•eMail: [email protected] •
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•Internet: www.dgflugzeugbau.de
F L I G H T M A N U A L
for the
M O T O R G L I D E R
DG-500M
Model: DG-500M
German Data Sheet No.: 843
Factory Serial No.: _____________________
Registration No.: _____________________
Date of Issue: November 1998
Pages as indicated by "App." are approved by:
(Signature) _____________________
(Authority) _____________________
(Stamp) _____________________
(Original date of approval) _____________________
This motorglider is to be operated in compliance with information and
limitations contained herein. The original German Language edition of this
manual has been approved as operating instruction according to "Paragraph
12(1) 2. of Luft-Ger Po". Approval of translation has been done by best
knowledge and judgement.
0.0

DG Flugzeugbau GmbH Flight manual DG500 M
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 Revision No. and the date
will be shown on the bottom left hand of the page.
Rev.
No.
Affected pages /
section
D
escription Issue
Date
LBA
Approval
Date
Inserted
Date
Signature
1 0.3-0.5, 2.6,4.10,
4.15,4.17
TN 843/2 Febr.92 March
04, 92
2 0.1,0.3, 0.4,0.5,
3.4, 6.6, 6.7, 7.2,
7.7, 7.8, 8.7
TN 843/5 Sept.92 Dec.08,
92
3 0.1,0.3, 0.4,0.5,
2.6, 2.8, 2.10,
TN 843/7 Febr.96 April 08,
96
4.12, 4.13, 5.9, 6.5, 6.9, 7.17, 7.18, 8.2, 8.6
4 0.1,0.3,2.6 TN 843/8 March
97
05.06.97
5 0.1, 0.5, 7.11 TN 843/11 Dec. 98 Dec. 17,
98
6 0.1, 0.3, 0.5, 4.8,
7.14, 8.2
TN 843/16 Jan. 01 07.02.01
Rev.
No.
Affected pages /
section
D
escription Issue
Date
EASA
Approval
Date
Inserted
Date
Signature
7 0.3-0.5, 2.8, 3.1,
3.2, 3.4-3.7, 4.1,
4.8, 4.25, 7.1,
7.16
TN 843/28
m
anual revision
May
2008
August 1.
2008
8 0.
, 9.1, 9.2
Special
equipment for
v
ery small
p
ilots
TN500/02
May
2010
20.07.
2010
Issued: May 2010 TN500/02 0.1

DG Flugzeugbau GmbH Flight manual DG500 M
Issued: November 1998 0.2

DG Flugzeugbau GmbH Flight manual DG500 M
0.2 List of effective pages
Section page issued Replaced/ replaced/ replaced
replaced
0 0.0 April 89
0.1 -See record of revisions
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1 1.1 April 89
1.2 Febr. 91
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2 App. 2.1 "
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3 " 3.1 " May 08
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4 " 4.1 April 89 May 08
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App. 4.9 "
Issued: May 2008 TN843/28 0.3

DG Flugzeugbau GmbH Flight manual DG500 M
0.2 List of effective pages (cont.)
Section Page issued replaced replaced replaced replaced
4 App. 4.10 " Febr.92
" 4.11 April 89
" 4.12 April 89 Febr. 96
" 4.13 " " "
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6.6 " Sept. 92
6.7 " Sept. 92
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Issued: May 2008 TN843/28 0.4

DG Flugzeugbau GmbH Flight manual DG500 M
0.2 List of effective pages (cont.)
Section page issued replaced replaced replaced replaced
7 7.1 April 89 May 08
7.2 " Sept. 92
7.3 "
7.4 "
7.5 "
7.6 "
7.7 " Sept. 92
7.8 " " "
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8 8.1 "
8.2 " Febr. 96 Jan. 01
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8.4 "
8.5 "
8.6 " Febr. 96
8.7 " Sept. 92
9 9.1 April 89 May 10
9.2 May 10
Issued: May 2010 TN500/02 0.5

DG Flugzeugbau GmbH Flight manual DG500 M
0.3 Table of contents
Section
General (a non-approved section) 1
Limitations (an approved section) 2
Emergency procedures (an approved section) 3
Normal procedures (an approved section) 4
Performance (a partly approved section) 5
Mass (weight) and balance
(a non-approved section) 6
Sailplane and systems description
(a non-approved section) 7
Sailplane handling, care and maintenance 8
(a non-approved section)
Supplements 9
Issued: November 1998 0.6

DG Flugzeugbau GmbH Flight manual DG-500M
Section 1
1. General
1.1 Introduction
1.2 Certification basis
1.3 Warnings, cautions and notes
1.4 Descriptive data
1.5 Three view drawing
Issued: April 1997 1.1

DG Flugzeugbau GmbH Flight manual DG-500 M
1.1 Introduction
The sailplane flight manual has been prepared to provide pilots and in-
structors with information for the safe and efficient operation of the DG-
500M motorglider.
This manual includes the material required to be furnished to the pilot by
JAR Part 22. It also contains supplemental data supplied by the motorgli-
der manufacturer.
1.2 Certification basis
This type of motorglider has been approved by the Luftfahrt-Bundesamt
(LBA) in accordance with:
Airworthiness requirements:
JAR Part 22 sailplanes and powered sailplanes Change 4, issued 7th May,
1987.
Noise requirements: Chapter VI LSL (BAZ announcement issued Jan. 1st,
1989)
The Type Certificate No. 843 has been issued on February 28th, 1991.
Category of Airworthiness: Utility
Issued: April 1997 1.2

DG Flugzeugbau GmbH Flight manual DG-500 M
1.3 Warnings, cautions and notes
The following definitions apply to warnings, cautions and notes used in the
flight manual.
Warning: means that the non observation of the corresponding procedure
leads to an immediate or important degradation of the flight safety.
Caution: means that the non observation of the corresponding procedure
leads to a minor or to a more or less long term degradation of the
flight safety.
Note: draws the attention on any special item not directly related to safe-
ty but which is important or unusual.
Issued: April 1997 1.3

DG Flugzeugbau GmbH Flight manual DG-500 M
1.4 Descriptive data
The DG-500M is a twoplace high performance sailplane with wing flaps
and retractable powerplant.
4-piece wing constructed from carbonfibre with wing flaps. The wing
joint is designed with the sparend at the inner wing panel for easy rigging
and that the ailerons hook up automatically.
Automatic hook ups for all controls.
Comfortable seating and modern cockpit design similar to the DG-single-
seaters - safety cockpit.
Large 2 piece canopy for very good inflight vision.
Draught free canopy demist and 1 adjustable swivel air vent for each pilot.
Sealed airbrake- and landing gear box.
Retractable main wheel with large spring travel due to steel springs, nose
wheel (steerable as option), tailwheel, wing tip wheels.
Controls in each cockpit - including the engine controls.
All controls including the engine are operated with the left hand, which
enables the right hand to remain on the control stick.
Powerplant
Electrical engine extension-retraction, operated automatically with the
ignition switch, electronical safety devices to avoid misoperation.
Engine control instruments with digital LCD indication (Microprocessor
technology) in both cockpits.
Liquid cooled Rotax 535 two stroke engine with electronic dual ignition,
60 hp (44 kw) take off power.
1 handle control of the motor due to electric fuel injection instead of a
choke valve.
Issued: April 1997 1.4

DG Flugzeugbau GmbH Flight manual DG-500 M
1.4 ff
Belt reduction 3 : 1 and a large propeller (dia. 1.58 m, 5.18 feet)
results in a low noise emission
Excellent power on performance
Further details: Waterballast and fuel tanks in the wings as options.
Technical data
wing span 22 m 72.2 ft
wing surface 18.29 m< 196.9 ft²
aspect ratio 26.5 26.5
length 8.66 m 28.4 ft
fuselage width 0.73 m 2.4 ft
fuselage height 1.00 m 3.3 ft
horizontal tailplane
span 3.17 m 10.4 ft
mean aerodynamic
chord MAC 0.91 m 3.0 ft
empty weight* with
batteries and min.
instruments appr. 550 kg Appr. 1210 lbs
fuselage tank 38 l 10 USgal
waterballast (option) 100 kg 220 lbs
wing fuel tanks (option) 40 l 10.6 USgal
max. TOW 825 kg 1819 lbs
wing loading (with pilot
+ fuel = 85 kg, 187 lbs) ca.34.7 kg/m< ca.7.10 lbs/ft²
max. wing loading 45.1 kg/m< 9.24 lbs/ft2
*options increase the empty weight accordingly
Issued: April 1997 1.5

DG Flugzeugbau GmbH Flight manual DG-500 M
1.5 3 view drawing
Issued: April 1997 1.6

DG Flugzeugbau GmbH Flight manual DG-500M
Section 2
2. Limitations
2.1 Introduction
2.2 Airspeed
2.3 Airspeed Indicator Markings
2.4 Power Plant
2.5 Power Plant Instrument Markings
2.6 Fuel
2.7 Weight
2.8 Center of Gravity
2.9 Approved manoeuvres
2.10 Manoeuvring load factors
2.11 Flight crew
2.12. Kinds of operation
2.13 Minimum equipment
2.14 Aerotow and Winch- and Autotow - launching
2.14.1 Weak links
2.14.2 Towing cable
2.14.3 Max. towing speeds
2.14.4 Tow Release
2.15 Cross wind
2.16 Tyre pressure
2.17 Water ballast (Option)
2.18 Wing fuel tanks (Option)
2.19 Limitations Placards
Issued: April 1997 2.1

DG Flugzeugbau GmbH Flight manual DG-500M
2.1 Introduction
Section 2 includes operating limitations, instrument markings and basic
placards necessary for safe operation of the motorglider, its engine,
standard systems and standard equipment.
The limitations included in this section have been approved by the LBA.
Issued: April 1997 2.2

DG Flugzeugbau GmbH Flight manual DG-500M
2.2 Airspeed
Airspeed limitations and their operational significance are shown below:
Speed (IAS) Remarks
km/h(kts)
VNE Never exceed 270
speed (146)
flaps 0° up to
-10°
Do not exceed this speed in any
operation and do not use more
than 1/3 of control deflection.
with the 197 Do not exceed this speed
engine extended (106) with the engine extended (engine idling)
VRA Rough air speed 197
(106)
Do not exceed this speed except
in smooth air and then only with
caution Rough air is in lee-wave
rotor, thunderclouds etc.
VA Manoeuvring 197 Do not make full or abrupt
speed (106) control movement above this
speed, because under certain
condition the sailplane may be
overstressed by full control
movement.
VFE Maximum flap Do not exceed these speeds
extended speed with the given flap setting
L = + 15° 150
( 81)
+10°, +5° 197
(106)
VW Maximum
winch-
140
launching speed ( 76)
Do not exceed this speed during
winch- or auto-tow-launching
VT Maximum aero- 197 Do not exceed this speed
towing speed (106) during aerotowing
VLO Maximum
landing
197
gear operating (106)
Do not extend or retract
the landing gear above this speed
speed
VPO Max. speed to 110 Do not extend or retract
extend and re- ( 59) the powerplant above this
tract the power- speed
plant
Warning: At higher altitudes the true airspeed is higher than the indicated
airspeed, so VNE is reduced with altitude see sect. 4.5.9.
Issued: April 1997 2.3

DG Flugzeugbau GmbH Flight manual DG-500M
2.3 Airspeed Indicator Markings
Airspeed indicator markings and their color code significance are shown
below:
Marking (IAS) value or Significance
range
km/h (kts)
White Arc 79 - 197 Positive Flap Operating Range
(43 - 106) (lower limit is maximum weight
1.1 VSO in landing configuration.
Upper limit is maximum speed
permissible with flaps extended
positive + 10°, + 5°)
Green Arc 88 - 197 Normal Operating Range
(48 - 106)
(Lower limit is maximum weight
1.1 VS1 at most forward c.g. with
flaps neutral. Upper limit is rough
air speed.)
Yellow Arc 197 - 270 Manoeuvres must be conducted
with caution and only in smooth air.
(106 - 146)
Red Line 270 Maximum speed for all
(146) operations.
L 150 Max. speed for landing
( 81) configuration L + 15°
Blue line 90 Speed of best climb Vy
(49)
Yellow 105 Approach speed at maximum
Triangle ( 57) weight without water ballast
Issued: April 1997 2.4

DG Flugzeugbau GmbH Flight manual DG-500M
2.4 Power plant
Engine manufacturer: Bombardier Rotax,
Gunskirchen Austria
Engine model: Rotax 535 C
Maximum power: Take off: 44 kw (60 PS)
continuous: 44 kw (60 PS)
Max. engine RPM at MSL: Take off
(max. 5 minutes): 7200 RPM
continuous: 6900 RPM
Max. cylinder head temperature 95°C
(cooling water): (203°F)
Cooling liquid: Water with anti-freeze for -20°C
(-4°F) for altitude flights increase anti freeze to -40°C (-40°F)
Oil for rotary valve drive: Super quality 2-stroke-oil
Propeller: Diameter 1.58 m (5.2 ft), Reduction 3:1
Manufacturer: mt-propeller Straubing W. Germany
Model: MT 158 R 125 - 1 A
2.5 Power plant instrument markings
Power plant instrument markings and their significance are shown below:
Engine speed indicator:
Centre LCD display, indication digital with 3 digits, limitation data printed
above display:
Green 6900 max. continuous RPM
Yellow 6900 – 7200 caution range
Red 7200 max. take off RPM
Max. continuous RPM:
When exceeding this RPM a blinking double point appears between the
second and the third digit in the display.
Max. take off RPM:
When exceeding this RPM the engine speed display starts blinking.
Issued: April 1997 2.5

DG Flugzeugbau GmbH Flight manual DG-500M
2.5 ff
Cylinderhead temperature indicator:
Right LCD display, indication digital with 3 digits, limitation data printed
above display:
red 95 °C
When this temperature is exceeded the CHT display starts blinking.
Fuel quantity indicator (only for the fuselage tank):
Limitation data for the non usable amount of fuel printed above the display:
red 1 l
When this quantity is reached LL is displayed and this display starts
blinking.
2.6 Fuel
Total fuel capacity:
Fuselage: 40 l (10.6 US gal.)
Wings (option) 20 l (5.3 US gal.) each
Usable amount of fuel: 39 l (10.3 US gal.)
or 78 l (20.7 US gal.)with wing tanks
Non usable amount of fuel:
Fuselage tank: 1 l (0.3 US gal.)
Wing tanks (option)0.5 l (0.15 US gal.) each
Approved fuel grades: Car super gasoline leaded or unleaded,
min.95 octane (RON)(ROZ)
or: AVGAS 100 LL (only if car super
gasoline is not available)
or: mix 50% AVGAS 100 LL and 50% Car
super gasoline unleaded min. 92 octane
(RON)(ROZ)
mixed with self mixing Super quality two stroke oil - specifiation TSC 3
respective API TC or higher quality. Mixing ratio 1:50.
Caution: Empty the fuel tank for extended storage periods (more than 3
months). Don´t use this fuel in the glider again.
Issued: April 1997 2.6

DG Flugzeugbau GmbH Flight manual DG-500M
2.7 Mass (weight)
Maximum Take-Off mass:
with waterballast: 825 kg, 1819 lbs
without waterballast: W=WNLP + Wwings
WNLP = max. mass of all non lifting parts
see below
Wwings = actual mass of the wings
Maximum landing mass: 825 kg, 1819 lbs
Caution: It is recommended to dump the waterballast before landing on
airfields. Dump the ballast before an outlanding in any case.
Maximum mass of all
non lifting parts = 560 kg(1235 lbs)
Maximum mass in baggage
Compartment = 15 kg( 33 lbs)
Caution: Heavy pieces of baggage must be secured to the baggage
compartment floor (screwing to the floor or with belts). The max.
mass secured on one half of the floor (left and right of fuselage
centre line) should not exceed 7,5 kg (16.5 lbs).
Maximum waterballast
in the wings = 100 kg(221 lbs)
The max. take off mass is not to be exceeded.
Warning: Follow the loading procedures see sect. 6.
2.8 Center of gravity
Center of gravity range in flight is
255 mm (10.04 in.) up to 480 mm (18.9 in.) behind datum.
Datum = wing leading edge at the rootrib
reference line = aft fuselage centre line horizontal
C.G. diagrams and loading chart see sect.6.
Issued: April 1997 2.7