Technify Motors TAE 125-02-114 Configuration guide

Technify Motors GmbH
Platanenstraße 14
D - 09356 St. Egidien
Tel. [phone]
Fax [phone]
www.continentaldiesel.de
[e-mail]
Doc.-No.: 50-0310-50022
Approved Airplane Flight Manual Supplement
for the
DA 40 D
Equipped with
TAE 125-02-114 Engine Installation
Issue 2/0
This supplement must be attached to the EASA approved
Airplane Flight Manual when the TAE 125-02-114 engine has
been installed in accordance with EASA STC 10036328.
The information contained in this supplement supersedes or
adds to the EASA approved Airplane Flight Manual only as set
forth herein.
For limitations, procedures, performance and loading
information not contained in this supplement, consult the basic
EASA approved Airplane Flight Manual.
ThisAirplaneFlightManualSupplementisapprovedwithEASA
STC 10036328.
SERIAL No. _______________
REGISTER No. _______________

This page intentionally left blank

AFM Supplement DA 40 D
Page iii
Issue 2
Revision -, Aug. 2015
LOG OF REVISIONS
Revision Chapter Description Approved
Date Endorsed
- All Initial Issue 1 Sept. 01,
2011 EASA STC
10036328
1/1 2 New fuel,
new gearboxoil March 16, 2012
Revision No. 1 to AFM supplement ref. 50-0310-50021 is approved under the authority of DOA ref. EASA.21J.010. Date: March 16, 2012 Office of Airworthiness
2/0 All Change of Ownership Aug. 15,
2015 EASA STC
10036328,
Rev. 3
2 New gearbox oil
New fuel,
new specs
5 splitted due to new
specs
5a New section
5b new section
6 Equipment list updated
Note: The parts of the text which changed are
marked with a vertical line on the margin of
the page.

AFM Supplement DA 40 D
Page iv
Issue 2
Revision -, Aug. 2015
LIST OF EFFECTIVE CHAPTERS
APPROVAL
The content of approved chapters is approved by EASA. All
other content is approved by TAE under the authority of EASA
DOA No. EASA.21J.010 in accordance with Part 21.
GENERAL REMARK
The content of this AFM supplement is developed on basis of
the EASA-approved AFM, DAI Document No. 6.01.05-E.
Chapter Issue/Revision Date
1 2/0 Aug., 2015
2 2/0 Aug., 2015
3 2/0 Aug., 2015
4A 2/0 Aug., 2015
4B 2/0 Aug., 2015
5a 2/0 Aug., 2015
5b 2/0 Aug., 2015
6 2/0 Aug., 2015
7 2/0 Aug., 2015
8 2/0 Aug., 2015
92/0 Aug., 2015

AFM Supplement DA 40 D
Page v
Issue 2
Revision -, Aug. 2015
TABLE OF CONTENTS
CHAPTER 1..........GENERAL
(a non-approved chapter)
CHAPTER 2..........OPERATING LIMITATIONS
(an approved chapter))
CHAPTER 3..........EMERGENCY PROCEDURES
(a non-approved chapter))
CHAPTER 4a........NORMAL OPERATING PROCEDURES
(a non-approved chapter)
CHAPTER 4b........ABNORMAL OPERATING PROCEDURES
(a non-approved chapter))
CHAPTER 5..........PERFORMANCE
(a non-approved chapter))
CHAPTER 6..........WEIGHT AND BALANCE /
EQUIPMENT LIST
(a non-approved chapter))
CHAPTER 7..........DESCRIPTION OF THE AIRPLANE AND
ITS SYSTEMS
(a non-approved chapter))
CHAPTER 8..........AIRPLANE HANDLING, CARE AND
MAINTENANCE
(a non-approved chapter))
CHAPTER 9..........SUPPLEMENTS

AFM Supplement DA 40 D
Page vi
Issue 2
Revision -, Aug. 2015
This page is intentionally left blank

AFM Supplement DA 40 D
Page 1-1
Issue 2
Revision -, Aug. 2015
CHAPTER 1
GENERAL
1.1 INTRODUCTION
This supplement must be attached to the EASA approved
Airplane Flight Manual when the TAE 125-02-114 engine has
been installed in accordance with EASA STC 10036328.
The information contained in this supplement supersedes or
adds to the EASA approved Airplane Flight Manual only as set
forth herein.
For limitations, procedures, performance and loading
information not contained in this supplement, consult the basic
EASA approved Airplane Flight Manual.
1.2 CERTIFICATION BASIS
The certification basis for the TAE 125-02-114 engine
installation is CS-23, dated November 14, 2003.
1.5 DEFINITIONS AND ABBREVIATIONS
(i) Miscellaneous
EASA: European Aviation Safety Agency
1.8 SOURCE DOCUMENTATION
UPDATE AND REVISION OF THE MANUAL
WARNING: A safe operation is only assured with an up
to date AFM supplement. Information about
actual AFM, supplement issues and
revisions are published in the Service
Bulletin TM TAE 000-0004.
Note: The Doc.-No of this AFM supplement is
published on the cover sheet of this
supplement.

AFM Supplement DA 40 D
Page 1-2
Issue 2
Revision -, Aug. 2015
This page intentionally left blank

AFM Supplement DA 40 D
Page 2-1
Issue 2
Revision -, Aug. 2015
CHAPTER 2
OPERATING LIMITATIONS
2.4 POWERPLANT LIMITATIONS
a) Engine manufacturer: .......................Technify Motors GmbH
b) Engine designation:.....................................TAE 125-02-114
c) RPM limitations (shown as propeller PRM)
Maximum: .................................................................2300 RPM
Maximum overspeed:..........................2500 RPM (max 20 sec)
d) Engine Power
Max. take-off power: ................ 114 kW (155 HP) at 2300 RPM
Max. continuous power:........... 114 kW (155 HP) at 2300 RPM
Max. recommended cruise power:......................................85%
e) Oil Pressure
Min. oil pressure:.............................................................1.2 bar
Min. oil pressure (at Take-off power): .............................2.3 bar
Min. oil pressure (in flight):..............................................2.3 bar
Max. oil pressure:............................................................6.0 bar
Max. oil pressure (cold start < 20 sec.):..........................6.5 bar
g) Oil Temperature
Min. oil temperature (engine starting temp.): ....................-32°C
Min. oil temperature (min. operating limit temp.):...............50°C
Max. oil temperature:.......................................................140°C
h) Coolant Temperature
Min. coolant temp. (engine starting temp.):.......................-32°C
Min. coolant temp. (min. operating limit temp.):.................60°C
Max. coolant temperature:...............................................105°C

AFM Supplement DA 40 D
Page 2-2
Issue 2
Revision -, Aug. 2015
j) Manufacturer:......................MT Propeller Entwicklung GmbH
k) Model: ....................................................... MTV-6-A/187-129
........................................................................ MTV-6-A/190-69
l) Propellerdiameter:........................1.87 m (MTV-6-A/187-129)
..........................................................1.90 m (MTV-6-A/190-69)
m) Propeller pitch angle (0.75R):............................13.5° to 28°
n) Oil Specification:............AERO SHELL OIL DIESEL ULTRA
....................................................SHELL HELIX ULTRA 5W-30
....................................................SHELL HELIX ULTRA 5W-40
..........................................AERO SHELL OIL DIESEL 10W-40
o) Coolant: ...........Water/Radiator Protection at a ratio of 50:50
Radiator Protection:............. BASF Glysantin Protect Plus/G48
........................................................Mobil Antifreeze Extra/G48
.......................................................ESSO Antifreeze Extra/G48
.............................. Comma Xstream Green - Concentrate/G48
..................................................................Zerex Glysantin G48
p) Gearbox Oil:..........................Shell Spirax S6 GXME75W-80
.........................................................Shell Spirax S4 G 75W-90
......................................Shell Getriebeöl EP 75W-90 API GL-4
............................................................ Shell Spirax EP 75W-90
CAUTION: The use of water which does not meet the
specifications according to the applicable
OM-02-02 may cause engine damage.
CAUTION: If the coolant level is too low the reason
must be determined and the problem must
be corrected by authorized personnel.

AFM Supplement DA 40 D
Page 2-3
Issue 2
Revision -, Aug. 2015
.................................................Shell Spirax GSX 75W-80 GL-4
............................................................ Shell Spirax S6 ATF ZM
..........................................................Centurion Gearbox Oil N1
q) Maximum restart altitude: .........................................14000 ft
2.5 ENGINE INSTRUMENT MARKINGS
Engine instrument markings and their color code significance
are shown in the tables below:
CAUTION: Use approved oil with exact designation
only!
CAUTION: If the gearbox oil level is too low the reason
must be determined and the problem must
be corrected by authorized personnel.
Indi-cation
Red
arc/bar
=
lower
prohibited
range
Yellow
arc/bar
=
caution
range
Green
arc/bar
=
normal
operating
range
Yellow
arc/bar
=
caution
range
Red
arc/bar
=
upper
prohibited
range
RPM [RPM] -- -- 0-2300 -- above
2300
Oil
pressure [bar] below 1.2 1.2 to 2.2 2.3 to 5.1 5.2 to 6.5 above 6.5
Oil temp. [°C] below -32 -32 to 49 50 to 129 130 to 140 above 140
Coolant
temp. [°C] below -32 -32 to 59 60 to 100 101 to 105 above 105
Gearbox
temp. [°C] -- -- below 115 115 to 120 above 120
Load [%] -- -- 0 - 100 -- --
Fuel
temp. [°C] below -30 -30 to +4 +5 to 69 70 to 75 above 75
Ammeter [A] -- -- below 85 85 to 90 above 90

AFM Supplement DA 40 D
Page 2-4
Issue 2
Revision -, Aug. 2015
From -30 °C to -6 °C the lower yellow bar of the fuel temp bar
flashes, from -5 °C to +4 °C the lower yellow bar of the fuel temp
is continuously on. This applies only to conventional instrument
panel versions.
2.9 APPROVED MANEUVRES
Refer to basic AFM.
2.14 FUEL
Approved fuel grades:.........................JET A-1 (ASTM D 1655)
............................................................... JET A (ASTM D 1655)
.....................................................JET Fuel No. 3 (GB6537-94)
.............................................................JP-8 (MIL-DTL-83133E)
.....................................................JP-8+100 (MIL-DTL-83133E)
........................................................... Diesel Fuel (DIN EN590)
............................................................. TS-1 (GOST 10227-86)
..........................................TS-1 (GSTU 320.00149943.011-99)
....................................................................SASOL GTL Diesel
Volt-
meter [V] below 11 11 to 12.5
12.6 to 14.9 15.0to 15.5 above 15.5
Fuel qty. [US
gal] below 0.45 -- 0.45 to 14 -- --
CAUTION: Intentionally initiating negative G
maneuvers is prohibited.
CAUTION: Additional temperature must be observed if
the airplane is operated with Diesel Fuel or
blends of Diesel Fuel with JET Fuel. If there
is uncertainty about which fuel is in the
tank, it must be assumed that it is Diesel.
Indi-cation
Red
arc/bar
=
lower
prohibited
range
Yellow
arc/bar
=
caution
range
Green
arc/bar
=
normal
operating
range
Yellow
arc/bar
=
caution
range
Red
arc/bar
=
upper
prohibited
range

AFM Supplement DA 40 D
Page 2-5
Issue 2
Revision -, Aug. 2015
2.16 OTHER LIMITATIONS
Fuel Temperature
The fuel temperature limitations applicable for the
TAE 125-02-99 engine are valid for the TAE 125-02-114.
Refer to basic AFM.

AFM Supplement DA 40 D
Page 3-1
Issue 2
Revision -, Aug. 2015
CHAPTER 3
EMERGENCY PROCEDURES
The emergency procedures included in this chapter supersede
the procedures in the basic AFM.
For emergency procedures not included in this chapter refer to
basic AFM.

AFM Supplement DA 40 D
Page 3-2
Issue 2
Revision -, Aug. 2015
3.2.4. RESTARTING THE ENGINE WITH WINDMILLING
PROPELLER
(1) Airspeed for best glide angle...73 KIAS (1150 kg, 2535 lb)
........................................................68 KIAS (1000 kg, 2205 lb)
..........................................................60 KIAS (850 kg, 1874 lb)
(2) Power lever.................................................................IDLE
(3) Emergency fuel valve ...............................check NORMAL
(4) Alternate air ..............................................................OPEN
(5) Fuel transfer pump.........................................................ON
(6) AVIONIC MASTER......................................................OFF
(7) ELECTRIC MASTER.....................................................ON
(8) Airspeed .........................................................70-110 KIAS
continued next page
Note: As long as an airspeed of at least 70 KIAS
is maintained, and there is no major
mechanical engine defect, the propeller will
continue to windmill. After a complete stop
the propeller starts to windmill at airspeeds
above 115 KIAS.
CAUTION: The maximum airspeed for windmilling is
120 KIAS. Higher airspeeds may result in
propeller overspeed.
Note: Restarting the engine with windmilling
propeller is possible at airspeeds between
70 and 110 KIAS and altitudes below
14000 ft pressure altitude.

AFM Supplement DA 40 D
Page 3-3
Issue 2
Revision -, Aug. 2015
(9) ENGINE MASTER .............................................OFF - ON
(10)AVIONIC MASTER......................................ON, if required
Note: If it is not possible to start the engine:
- adopt glide configuration
- carry out emergency landing
Refer to basic AFM
CAUTION: Engine restart following an engine fire
should only be attempted if it is unlikely that
a safe emergency landing can be made. It
must be expected that engine restart is
impossible after an engine fire.

AFM Supplement DA 40 D
Page 3-4
Issue 2
Revision -, Aug. 2015
3.2.5. RESTARTING THE ENGINE WITH STATIONARY
PROPELLER
(1) Airspeed for best glide angle...73 KIAS (1150 kg, 2535 lb)
........................................................68 KIAS (1000 kg, 2205 lb)
..........................................................60 KIAS (850 kg, 1874 lb)
(2) ENGINE MASTER.......................................................OFF
(3) Power lever.................................................................IDLE
(4) Emergency fuel valve ...............................check NORMAL
(5) Alternate air ..............................................................OPEN
(6) Fuel transfer pump.........................................................ON
(7) AVIONIC MASTER......................................................OFF
(8) ELECTRIC MASTER.....................................................ON
(9) ENGINE MASTER ........................................................ON
continued next page
Note: Restarting the engine with stationary
propeller is possible at altitudes below
14000 ft pressure altitude.
Note: Restarting the engine with windmilling
propeller is possible at airspeeds between
70 and 110 KIAS and altitudes below
14000 ft.
Note: Only if the ENGINE MASTER is switched
OFF and ON again, glowing will be initiated.
Glowing must be initiated shortly before the
restart attempt.

AFM Supplement DA 40 D
Page 3-5
Issue 2
Revision -, Aug. 2015
(10)ELECTRIC MASTER..............................................START
(release when engine running)
Note: By increasing the airspeed above
approximately 115KIAS, the propeller will
begin to rotate due to windmilling and the
engine can thus be started. For this, the
ELECTRIC MASTER should be set to ON
(see 3.2.4 - RESTARTING THE ENGINE
WITH WINDMILLING PROPELLER of this
supplement). A loss of altitude of at least
1000 ft (300 meters) must be expected.
If it is not possible to start the engine:
- adopt glide configuration
- carry out emergency landing
Refer to basic AFM
CAUTION: Engine restart following an engine fire
should only be attempted if it is unlikely that
a safe emergency landing can be made. It
must be expected that engine restart is
impossible after an engine fire.

AFM Supplement DA 40 D
Page 3-6
Issue 2
Revision -, Aug. 2015
This page intentionally left blank

AFM Supplement DA 40 D
Page 4A-1
Issue 2
Revision -, Aug. 2015
CHAPTER 4A
NORMAL OPERATING PROCEDURES
4A.2 AIRSPEEDS FOR NORMAL OPERATING
PROCEDURES
For take-off, climb, cruise climb and go-around the following
airspeeds apply for the TAE 125-02-114 engine installation
For normal operating procedures refer to basic AFM.
Flight Mass 980 kg
(2160 lb) 1000 kg (2205 lb) 1150 kg (2535 lb)
Airspeed for rotation
Take-off run (VR)
(Flaps T/O) 54 KIAS 55 KIAS 59 KIAS
A
irspeed for take-off climb (VX)
(Flaps T/O) 59 KIAS 60 KIAS 66 KIAS
Airspeed for cruise climb
Best rate of climb (VY)
(Flaps UP) 78 KIAS 78 KIAS 78 KIAS
Min. speed during go-around
(Flaps T/O) 59 KIAS 60 KIAS 66 KIAS