Technify Motors GmbH
Platanenstraße 14
D - 09356 St. Egidien
Tel. +49-(0)37204/ 696-0
Fax +49-(0)37204/ 696-2912
www.continentaldiesel.de
support@ccontinentaldiesel.de
Approved Airplane Flight Manual Supplement
for the
DA 40 D
Equipped with
TAE 125-02-114 Engine Installation
Issue 2/0
SERIAL No. _______________
REGISTER No. _______________
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.
This Airplane Flight Manual Supplement is approved with EASA
STC 10036328.
Doc.-No.: 50-0310-50022
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AFM Supplement DA 40 D
LOG OF REVISIONS
Revision Chapter Description
- All Initial Issue 1 Sept. 01,
1/1 2 New fuel,
new gearboxoil
2/0 All Change of Ownership Aug. 15,
2 New gearbox oil
New fuel,
new specs
5 splitted due to new
specs
5a New section
5b new section
6 Equipment list updated
March 16,
Approved
Date Endorsed
EASA STC
2011
2012
2015
10036328
Revision No. 1 to AFM supplement
ref. 50-0310-50021 is approved
under the authority of DOA
EASA STC
10036328,
Rev. 3
ref. EASA.21J.010.
Date: March 16, 2012
Office of Airworthiness
Note: The parts of the text which changed are
marked with a vertical line on the margin of
the page.
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AFM Supplement DA 40 D
LIST OF EFFECTIVE CHAPTERS
Chapter
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
9
Issue/Revision Date
2/0 Aug., 2015
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.
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AFM Supplement DA 40 D
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
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AFM Supplement DA 40 D
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.
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AFM Supplement DA 40 D
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
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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 Prot ec tion 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
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 mu st
be corrected by authorized personnel.
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
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AFM Supplement DA 40 D
.................................................Shell Spirax GSX 75W-80 GL-4
............................................................ Shell Spirax S6 ATF ZM
..........................................................Centurion Gearbox Oil N1
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 mu st
be corrected by authorized personnel.
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:
Indi-cation
RPM
Oil
pressure
Oil temp.
Coolant
temp.
Gearbox
temp.
Load
Fuel
temp.
Ammeter
Red
arc/bar
=
lower
prohibited
range
[RPM]
[bar]
[°C]
[°C]
[°C]
[%]
[°C]
[A]
-- -- 0-2300 --
below 1.2 1.2 to 2.2 2.3 to 5.1 5.2 to 6.5 above 6.5
below -32 -32 to 49 50 to 129 130 to 140 above 140
below -32 -32 to 59 60 to 100 101 to 105 above 105
-- -- below 115 115 to 120 above 120
-- -- 0 - 100 -- --
below -30 -30 to +4 +5 to 69 70 to 75 above 75
-- -- below 85 85 to 90 above 90
Yellow
arc/bar
=
caution
range
Green
arc/bar
=
normal
operating
range
Yellow
arc/bar
=
caution
range
Revision -, Aug. 2015
Red
arc/bar
=
upper
prohibited
range
above
2300
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AFM Supplement DA 40 D
Indi-cation
Voltmeter
Fuel qty.
Red
arc/bar
=
lower
prohibited
range
[V]
below 11 11 to 12.5
[US
below 0.45 -- 0.45 to 14 -- --
gal]
Yellow
arc/bar
=
caution
range
Green
arc/bar
=
normal
operating
range
12.6 to 14.9
Yellow
arc/bar
=
caution
range
15.0 to 15.5
Red
arc/bar
=
upper
prohibited
range
above 15.5
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.
CAUTION: Intentionally initiating negative G
maneuvers is prohibited.
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
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.
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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.
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AFM Supplement DA 40 D
CHAPTER 3
EMERGENCY PROCEDURES
The emergency procedures included in this chapter supe rsede
the procedures in the basic AFM.
For emergency procedures not included in this chapter refer to
basic AFM.
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3.2.4. RESTARTING THE ENGINE WITH WINDMILLING
PROPELLER
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.
(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) ELECT RIC MA STER.............................................. ... ....ON
(8) Airspeed .......... ............................. .................. 70-110 KIAS
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AFM Supplement DA 40 D
(9) ENGINE MASTER ............................................. OFF - ON
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.
(10)AVIONIC MASTER......................................ON, if required
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3.2.5. RESTARTING THE ENGINE WITH STATIONARY
PROPELLER
Note: Restarting the engine with sta tio na ry
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.
(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 MAS TER ........... ... ... .... ... ... ... .... ... ... ...............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) ELECT RIC MA STER.............................................. ... ....ON
(9) ENGINE MAS TER ................ .... ... ... ... .... ... ... ... ... ...........ON
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.
continued next page
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AFM Supplement DA 40 D
(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.
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AFM Supplement DA 40 D
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
Flight Mass
Airspeed for rotation
Take-off run (V
(Flaps T/O)
irspeed for take-off climb
A
(Flaps T/O)
Airspeed for cruise climb
Best rate of climb (V
(Flaps UP)
Min. speed during go-around
(Flaps T/O)
)
R
(VX)
)
Y
980 kg
(2160 lb)
54 KIAS 55 KIAS 59 KIAS
59 KIAS 60 KIAS 66 KIAS
78 KIAS 78 KIAS 78 KIAS
59 KIAS 60 KIAS 66 KIAS
1000 kg
(2205 lb)
For normal operating procedures refer to basic AFM.
1150 kg
(2535 lb)
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AFM Supplement DA 40 D
CHAPTER 4B
ABNORMAL OPERATING PROCEDURES
For abnormal operating procedures refer to basic AFM.
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AFM Supplement DA 40 D
CHAPTER 5(a)
PERFORMANCE
Note: This chapter applies to aircraft with
propeller MTV-6-A/187-129.
The correct designation can be found on
the blades.
Note: The chapter not relevant to the respective
propeller can be omitted.
5.3 PERFORMANCE TABLES AND DIAGRAMS
5.3.2 Diagram for setting engine performance
Not valid for TAE 125-02-114 engine installation.
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5.3.7 Take-off distance
Take-off distance at 1150 kg, 2535 lb
Weight:
Airspeed for initial climb:
ISA ISA + 10°C ISA + 20°C ISA + 30°C
Pressure Altitude
(ft) (m) (m) (m) (m) (m) (m) (m) (m)
SL 316 510 340 551 366 594 393 639
1000 334 539 360 582 387 628 416 675
2000 353 570 381 616 410 664 440 715
3000 374 604 403 652 434 703 466 756
4000 396 639 427 690 459 744 493 800
5000 419 677 452 731 486 788 522 848
6000 444 717 479 774 515 835 553 898
7000 480 775 518 837 557 902 598 971
8000 519 838 560 905 602 976 647 1050
9000 567 917 611 990 658 1068 706 1149
10000 620 1004 688 1084 718 1169 771 1258
Ground Roll
1150 kg / 25 35 lb
V
:
59 KIAS
R
66 KIAS Runway:
Over 15m
obstacle
Ground Roll
Over 15m
obstacle
Ground Roll
Flaps: T/O
Power:
MAX
dry , leve l, p a v ed
Over 15m
obstacle
Ground Roll
Table 5(a)-1 Take-off distance [m] at 1150 kg, 2535 lb
Over 15m
obstacle
Page 5(a)-2
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AFM Supplement DA 40 D
Take-off distance at 1150 kg, 2535 lb (continued)
Weight:
Airspeed for initial climb:
ISA ISA + 18°F ISA + 36°F ISA + 54°F
Pressure Altitude
(ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft)
SL 1037 1673 1116 1808 1201 1949 1289 2097
1000 1096 1768 1181 1910 1270 2060 1365 2215
2000 1158 1870 1250 2021 1345 2179 1444 2346
3000 1227 1982 1322 2139 1424 2307 1529 2480
4000 1299 2097 1401 2264 1506 2441 1618 2625
5000 1375 2221 1483 2398 1595 2585 1713 2782
6000 1457 2352 1572 2539 1690 2740 1814 2946
7000 1575 2543 1700 2746 1827 2959 1962 3186
8000 1703 2749 1837 2969 1975 3202 2123 3445
9000 1860 3009 2005 3248 2159 3504 2316 3770
10000 2034 3294 2257 3557 2356 3835 2530 4127
Ground Roll
1150 kg / 25 35 lb
:
V
59 KIAS
R
66 KIAS Runway:
Over 50ft
obstacle
Ground Roll
Over 50ft
obstacle
Ground Roll
Flaps: T/O
Power:
MAX
dry , leve l, p a v ed
Over 50ft
obstacle
Ground Roll
Table 5(a)-2 Take-off distance [ft] at 1150 kg, 2535 lb
Over 50ft
obstacle
Page 5(a)-3
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AFM Supplement DA 40 D
Take-off distance at 1000 kg, 2205 lb
Weight:
Airspeed for initial climb:
ISA ISA + 10°C ISA + 20°C ISA + 30°C
Pressure Altitude
(ft) (m) (m) (m) (m) (m) (m) (m) (m)
SL 220 355 237 383 255 413 274 444
1000 232 375 250 405 269 436 289 470
2000 246 397 265 428 285 462 306 497
3000 260 420 280 453 302 489 324 526
4000 275 444 297 480 319 517 343 557
5000 292 471 314 508 338 548 363 589
6000 309 499 333 538 358 580 385 625
7000 334 539 360 582 387 627 416 675
8000 361 583 389 629 419 678 450 730
9000 394 638 425 689 457 743 491 799
10000 431 698 464 754 500 813 536 875
Ground Roll
1000 kg / 2205 lb
:
V
55 KIAS
R
60 KIAS Runway:
Over 15m
obstacle
Ground Roll
Over 15m
obstacle
Ground Roll
Flaps: T/O
Power:
MAX
dry , leve l, p a v ed
Over 15m
obstacle
Ground Roll
Table 5(a)-3 Take-off distance [m] at 1000 kg, 2205 lb
Over 15m
obstacle
Page 5(a)-4
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AFM Supplement DA 40 D
Take-off distance at 1000 kg, 2205 lb (continued)
Weight:
Airspeed for initial climb:
ISA ISA + 18°F ISA + 36°F ISA + 54°F
Pressure Altitude
(ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft)
SL 722 1165 778 1257 837 1355 899 1457
1000 761 1230 820 1329 883 1430 948 1542
2000 807 1303 869 1404 935 1516 1004 1631
3000 853 1378 919 1486 991 1604 1063 1726
4000 902 1457 974 1575 1047 1696 1125 1827
5000 958 1545 1030 1667 1109 1798 1191 1932
6000 1014 1637 1093 1765 1175 1903 1263 2051
7000 1096 1768 1181 1910 1270 2057 1365 2215
8000 1184 1913 1276 2064 1375 2224 1476 2395
9000 1293 2093 1394 2261 1499 2438 1611 2621
10000 1414 2290 1522 2474 1640 2667 1759 2871
Ground Roll
1000 kg / 2205 lb
:
V
55 KIAS
R
60 KIAS Runway:
Over 50ft
obstacle
Ground Roll
Over 50ft
obstacle
Ground Roll
Flaps: T/O
Power:
MAX
dry , leve l, p a v ed
Over 50ft
obstacle
Ground Roll
Table 5(a)-4 Take-off distance [ft] at 1000 kg, 2205 lb
Over 50ft
obstacle
Page 5(a)-5
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Take-off distance at 980 kg, 21 6 1 lb
AFM Supplement DA 40 D
Weight:
Airspeed for initial climb:
ISA ISA + 10°C ISA + 20°C ISA + 30°C
Pressure Altitude
(ft) (m) (m) (m) (m) (m) (m) (m) (m)
SL 208 336 225 363 242 392 260 421
1000 220 356 237 384 256 414 274 446
2000 233 376 251 406 270 438 290 471
3000 247 398 266 430 286 464 307 499
4000 261 422 281 455 303 491 325 528
5000 277 447 298 482 321 520 344 559
6000 293 473 316 511 340 551 365 593
7000 317 511 341 552 367 595 395 641
8000 343 553 369 597 397 644 427 693
9000 374 605 403 653 434 705 466 758
10000 409 663 441 715 474 771 509 830
Ground Roll
980 kg / 2161 lb
:
V
54 KIAS
R
59 KIAS Runway:
Over 15m
obstacle
Ground Roll
Over 15m
obstacle
Ground Roll
Flaps: T/O
Power:
MAX
dry , leve l, p a v ed
Over 15m
obstacle
Ground Roll
Table 5(a)-5 Take-off distance [m] at 980 kg, 2161 lb
Over 15m
obstacle
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AFM Supplement DA 40 D
Take-off distance at 980 kg, 21 6 1 lb (con tin u e d)
Weight:
Airspeed for initial climb:
ISA ISA + 18°F ISA + 36°F ISA + 54°F
Pressure Altitude
(ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft)
SL 682 1102 738 1191 794 1286 853 1381
1000 722 1168 778 1260 840 1358 899 1463
2000 764 1234 824 1332 886 1437 951 1545
3000 810 1306 873 1411 938 1522 1007 1637
4000 856 1385 922 1493 994 1611 1066 1732
5000 909 1467 978 1581 1053 1706 1129 1834
6000 961 1552 1037 1677 1116 1808 1198 1946
7000 1040 1677 1119 1811 1204 1952 1296 2103
8000 1125 1814 1211 1959 1303 2113 1401 2274
9000 1227 1985 1322 2142 1424 2313 1529 2487
10000 1342 2175 1447 2346 1555 2530 1670 2723
Ground Roll
980 kg / 2161 lb
:
V
54 KIAS
R
59 KIAS Runway:
Over 50ft
obstacle
Ground Roll
Over 50ft
obstacle
Ground Roll
Flaps: T/O
Power:
MAX
dry , leve l, p a v ed
Over 50ft
obstacle
Ground Roll
Table 5(a)-6 Take-off distance [ft] at 980 kg, 2161 lb
Over 50ft
obstacle
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AFM Supplement DA 40 D
5.3.8 Climb Performance - Take-off climb Take-off at 1150 kg, 2535 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 646 630 614 598
1000 645 629 613 597
2000 643 627 612 596
3000 642 626 610 594
4000 641 625 609 593
5000 640 624 608 592
6000 638 622 606 590
7000 637 621 605 589
8000 636 619 603 587
9000 614 598 582 567
10000 587 572 557 541
1150 kg / 2535 lb
66 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
Flaps: T/O
Power:
ISA+20°C
ISA+36°F
MAX
ISA+30°C
ISA+54°F
Table 5(a)-7 Take-off climb performance at 1150 kg, 2535 lb
Page 5(a)-8
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
5.3.9 Climb Performance - Cruise climb Cruise climb at 1150 kg, 2535 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 815 785 754 723
1000 810 779 748 717
2000 804 773 742 711
3000 798 766 735 704
4000 792 760 729 697
5000 785 754 722 691
6000 779 747 715 684
7000 772 740 708 677
8000 765 733 701 669
9000 725 693 661 630
10000 675 644 613 583
11000 626 595 565 535
12000 576 546 517 487
13000 526 497 468 439
14000 476 448 420 391
15000 426 398 371 343
1150 kg / 2535 lb
78 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
Flaps: UP
Power:
ISA+20°C
ISA+36°F
MAX
Table 5(a)-8 Cruise climb performance at 1150 kg, 2535 lb
ISA+30°C
ISA+54°F
Page 5(a)-9
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Cruise climb at 1000 kg, 2205 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 1023 989 955 921
1000 1018 983 949 915
2000 1012 978 944 909
3000 1006 972 938 903
4000 1001 966 932 897
5000 995 960 925 891
6000 989 954 919 884
7000 983 948 913 878
8000 976 941 906 871
9000 931 896 862 827
10000 876 842 808 775
11000 821 787 754 722
12000 765 733 701 669
13000 709 678 646 615
14000 654 623 592 562
15000 597 567 538 508
1000 kg / 2205 lb
78 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
Flaps: UP
Power:
ISA+20°C
ISA+36°F
MAX
Table 5(a)-9 Cruise climb performance at 1000 kg, 2205 lb
ISA+30°C
ISA+54°F
Page 5(a)-10
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Cruise climb at 980 kg, 2161 lb
Conditions:
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 1055 1020 986 952
1000 1050 1015 980 946
2000 1044 1009 975 940
3000 1039 1004 969 934
4000 1033 998 963 928
5000 1027 992 957 922
6000 1021 986 950 915
7000 1015 979 944 909
8000 1009 973 937 902
9000 963 928 893 858
10000 907 872 838 804
11000 850 817 784 750
12000 794 761 729 696
13000 737 705 674 642
14000 681 650 619 588
15000 624 593 563 533
980 kg / 2161 lb
78 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
Flaps: UP
Power:
ISA+20°C
ISA+36°F
MAX
Table 5(a)-10 Cruise climb performance at 980 kg, 2161 lb
ISA+30°C
ISA+54°F
Page 5(a)-11
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
5.3.10 Cruise Performance Cruise performance, standard tanks
Conditions:
Weight ............................................................ 1150 kg, 2535 lb
Standard Tanks..............................106 l, 28 US gal usable fuel
Flaps.....................................................................................UP
Notes:
1. Endurance information is based on standard tanks with
106 l (28 US gal) usable fuel.
2. Endurance time of this table is reduced by the time for
startup and taxi, time, fuel and distance to climb and 45 min
reserve.
3. The range data of this table take into account the distance
to climb and are reduced by 45 min reserve.
4. Increase true airspeed (KTAS/mph)) and maximum range
(NM) by 1% per 10°C above ISA temperature.
5. Cruise Power above 75% not recomme nded. For economic
cruise set load 70% or less.
Page 5(a)-12
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Standard
Tanks: 106 l (28 US gal) usable fuel
Pres.
Alt.
2000 100 143 33.6 8.9 323 2.3
2000 90 137 29.6 7.8 365 2.7
2000 80 131 25.8 6.8 415 3.2
2000 70 124 22.1 5.8 473 3.8
2000 60 115 18.6 4.9 541 4.7
2000 50 105 15.3 4.0 617 5.8
4000 100 146 33.6 8.9 325 2.2
4000 90 140 29.6 7.8 367 2.6
4000 80 133 25.8 6.8 417 3.1
4000 70 126 22.1 5.8 474 3.7
4000 60 117 18.6 4.9 541 4.6
4000 50 107 15.3 4.0 617 5.7
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
SL 100 140 33.6 8.9 320 2.3
SL 90 135 29.6 7.8 363 2.7
SL 80 129 25.8 6.8 412 3.2
SL 70 122 22.1 5.8 470 3.9
SL 60 114 18.6 4.9 538 4.7
SL 50 104 15.3 4.0 614 5.9
6000 100 148 33.6 8.9 326 2.1
6000 90 142 29.6 7.8 369 2.5
6000 80 135 25.8 6.8 418 3.0
6000 70 128 22.1 5.8 475 3.6
6000 60 119 18.6 4.9 542 4.5
6000 50 109 15.3 4.0 616 5.6
8000 90 145 29.6 7.8 371 2.4
8000 80 138 25.8 6.8 419 2.9
8000 70 130 22.1 5.8 476 3.5
8000 60 121 18.6 4.9 542 4.3
8000 50 110 15.3 4.0 615 5.4
Page 5(a)-13
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Standard
Tanks: 106 l (28 US gal) usable fuel
Pres.
Alt.
10000 90 148 29.6 7.8 372 2.4
10000 80 140 25.8 6.8 421 2.8
10000 70 132 22.1 5.8 477 3.4
10000 60 123 18.6 4.9 541 4.2
10000 50 112 15.3 4.0 613 5.3
12000 90 150 29.6 7.8 375 2.3
12000 80 143 25.8 6.8 422 2.7
12000 70 134 22.1 5.8 477 3.3
12000 60 125 18.6 4.9 541 4.1
12000 50 113 15.3 4.0 611 5.1
14000 80 145 25.8 6.8 424 2.6
14000 70 137 22.1 5.8 478 3.2
14000 60 127 18.6 4.9 540 3.9
14000 50 115 15.3 4.0 608 4.9
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
16000 80 148 25.8 6.8 425 2.5
16000 70 139 22.1 5.8 478 3.0
16000 60 129 18.6 4.9 539 3.8
16000 50 117 15.3 4.0 605 4.7
Table 5(a)-11 Cruise performance, standard tanks
Page 5(a)-14
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Cruise performance, long range tanks
Conditions:
Weight ............................................................ 1150 kg, 2535 lb
Long Range Tanks......................147.6 l, 39 US gal usable fuel
Flaps.....................................................................................UP
Notes:
1. Endurance information is based on long-range tanks with
147.6 l (39 US gal) usable fuel.
2. Endurance time of this table is reduced by the time for
startup and taxi, time, fuel and distance to climb and 45 min
reserve.
3. The range data of this table take into account the distance
to climb and are reduced by 45 min reserve.
4. Increase true airspeed (KTAS/mph)) and maximum range
(NM) by 1% per 10°C above ISA temperature.
5. Cruise Power above 75% not recomme nded. For economic
cruise set load 70% or less.
Page 5(a)-15
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Long Range
Tanks: 147.6 l (39 US gal) usable fuel
Pres.
Alt.
2000 100 143 33.6 8.9 500 3.5
2000 90 137 29.6 7.8 558 4.1
2000 80 131 25.8 6.8 626 4.8
2000 70 124 22.1 5.8 706 5.7
2000 60 115 18.6 4.9 799 6.9
2000 50 105 15.3 4.0 903 8.6
4000 100 146 33.6 8.9 505 3.4
4000 90 140 29.6 7.8 563 4.0
4000 80 133 25.8 6.8 631 4.7
4000 70 126 22.1 5.8 711 5.6
4000 60 117 18.6 4.9 804 6.8
4000 50 107 15.3 4.0 908 8.4
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
SL 100 140 33.6 8.9 494 3.5
SL 90 135 29.6 7.8 552 4.1
SL 80 129 25.8 6.8 620 4.8
SL 70 122 22.1 5.8 699 5.7
SL 60 114 18.6 4.9 792 7.0
SL 50 104 15.3 4.0 897 8.6
6000 100 148 33.6 8.9 510 3.4
6000 90 142 29.6 7.8 568 3.9
6000 80 135 25.8 6.8 637 4.6
6000 70 128 22.1 5.8 716 5.5
6000 60 119 18.6 4.9 808 6.7
6000 50 109 15.3 4.0 911 8.3
8000 90 145 29.6 7.8 574 3.9
8000 80 138 25.8 6.8 642 4.5
8000 70 130 22.1 5.8 721 5.4
8000 60 121 18.6 4.9 812 6.6
8000 50 110 15.3 4.0 914 8.2
Page 5(a)-16
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Long Range
Tanks: 147.6 l (39 US gal) usable fuel
Pres.
Alt.
10000 90 148 29.6 7.8 580 3.8
10000 80 140 25.8 6.8 647 4.4
10000 70 132 22.1 5.8 726 5.3
10000 60 123 18.6 4.9 816 6.5
10000 50 112 15.3 4.0 916 8.0
12000 90 150 29.6 7.8 585 3.7
12000 80 143 25.8 6.8 653 4.3
12000 70 134 22.1 5.8 730 5.2
12000 60 125 18.6 4.9 820 6.3
12000 50 113 15.3 4.0 918 7.8
14000 80 145 25.8 6.8 658 4.2
14000 70 137 22.1 5.8 735 5.1
14000 60 127 18.6 4.9 823 6.2
14000 50 115 15.3 4.0 920 7.6
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
16000 80 148 25.8 6.8 664 4.1
16000 70 139 22.1 5.8 740 4.9
16000 60 129 18.6 4.9 827 6.0
16000 50 117 15.3 4.0 922 7.4
Table 5(a)-12 Cruise performance, long range tanks
Page 5(a)-17
Revision -, Aug. 2015
Issue 2
AFM Supplement DA 40 D
5.3.15 Approved Noise Data
With TAE 125-02-114 engine and Muffler LA50 Installed:
ICAO Annex 16 Chapter X........................................69.6 dB(A)
Page 5(a)-18
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
CHAPTER 5(b)
PERFORMANCE
Note: This chapter applies to aircraft with
propeller MTV-6-A/190-69.
The correct designation can be found on
the blades.
Note: The chapter not relevant to the respective
propeller can be omitted.
5.3 PERFORMANCE TABLES AND DIAGRAMS
5.3.2 Diagram for setting engine performance
Not valid for TAE 125-02-114 engine installation.
Page 5(b)-1
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
5.3.7 Take-off distance
Take-off distance at 1150 kg, 2535 lb
Weight:
Airspeed for initial climb:
ISA ISA + 10°C ISA + 20°C ISA + 30°C ISA + 35°C
Pressure Altitude
Ground Roll
Over 15m obstacle
(ft) (m) (m) (m) (m) (m) (m) (m) (m) (m) (m)
SL 275 458 294 488 314 522 343 571 362 605
1000 291 484 311 516 332 552 363 605 383 640
2000 308 512 329 547 351 584 384 641 406 678
3000 326 542 348 579 372 619 407 679 430 719
4000 345 573 369 613 394 656 432 720 456 762
5000 365 607 390 649 418 695 458 763 484 808
6000 387 643 414 688 443 737 486 810 513 858
7000 418 696 448 744 479 798 526 877 556 929
8000 452 752 484 805 519 863 569 949 602 1006
9000 494 822 529 881 567 944 623 1039 659 1101
10000 540 899 578 963 620 1034 681 1137 721 1206
1150 kg /
2535 lb
V
:
59 KIAS
R
66 KIAS Runway:
Ground Roll
Over 15m obstacle
Ground Roll
Flaps: T/O
Power:
Over 15m obstacle
MAX
dry , level, paved
Ground Roll
Over 15m obstacle
Ground Roll
Over 15m obstacle
Table 5(b)-1 Take-off distance [m] at 1150 kg, 2535 lb
Page 5(b)-2
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Take-off distance at 1150 kg, 2535 lb (continued)
Weight:
Airspeed for initial climb:
ISA ISA + 18°F ISA + 36°F ISA + 54°F ISA + 63°F
Pressure Altitude
Ground Roll
Over 50ft
obstacle
(ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft)
SL 903 1501 963 1601 1028 1711 1124 1874 1187 1984
1000 954 1587 1019 1694 1088 1810 1190 1984 1257 2101
2000 1009 1679 1078 1793 1152 1916 1261 2102 1332 2225
3000 1068 1776 1141 1898 1220 2030 1336 2227 1412 2358
4000 1131 1881 1209 2010 1293 2151 1416 2361 1496 2500
5000 1198 1992 1281 2130 1371 2280 1501 2503 1587 2652
6000 1269 2110 1358 2258 1453 2418 1593 2656 1684 2814
7000 1372 2281 1468 2442 1573 2616 1724 2875 1824 3047
8000 1483 2466 1588 2641 1702 2831 1867 3113 1975 3299
9000 1620 2696 1736 2889 1861 3098 2042 3407 2160 3612
10000 1770 2948 1897 3160 2035 3390 2234 3730 2364 3956
1150 kg /
2535 lb
V
:
59 KIAS
R
66 KIAS Runway:
Ground Roll
Over 50ft
obstacle
Ground Roll
Over 50ft
Flaps: T/O
Power:
obstacle
Ground Roll
MAX
dry , level, paved
Over 50ft
obstacle
Ground Roll
Over 50ft
Table 5(b)-2 Take-off distance [ft] at 1150 kg, 2535 lb
obstacle
Page 5(b)-3
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Take-off distance at 1050 kg, 2315 lb
Weight:
Airspeed for initial climb:
ISA ISA + 10°C ISA + 20°C ISA + 30°C ISA + 35°C
Pressure Altitude
Ground Roll
Over 15m
obstacle
(ft) (m) (m) (m) (m) (m) (m) (m) (m) (m) (m)
SL 217 361 232 385 247 412 255 425 286 477
1000 230 382 245 408 262 436 269 449 303 506
2000 243 404 259 431 277 461 285 476 321 535
3000 257 428 275 457 294 488 302 504 340 567
4000 272 453 291 484 311 518 320 534 360 602
5000 288 479 308 513 330 549 339 566 382 638
6000 305 508 327 543 350 582 360 600 405 677
7000 330 549 353 588 378 630 389 649 439 733
8000 357 594 382 636 410 681 421 703 475 794
9000 390 649 418 695 448 745 461 769 520 869
10000 426 709 457 761 490 816 504 841 569 952
1050 kg /
2315 lb
V
:
55 KIAS
R
60 KIAS Runway:
Ground Roll
Over 15m
obstacle
Ground Roll
Over 15m
Flaps: T/O
Power:
obstacle
Ground Roll
MAX
dry , level, paved
Over 15m
obstacle
Ground Roll
Table 5(b)-3 Take-off distance [m] at 1050 kg, 2315 lb
Over 15m
obstacle
Page 5(b)-4
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Take-off distance at 1050 kg, 2315 lb (continued)
Weight:
Airspeed for initial climb:
ISA ISA + 18°F ISA + 36°F ISA + 54°F ISA + 63°F
Pressure Altitude
Ground Roll
Over 50ft
obstacle
(ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft)
SL 712 1185 760 1264 812 1350 835 1393 937 1566
1000 753 1253 804 1337 859 1429 884 1474 993 1658
2000 797 1325 851 1415 909 1513 936 1560 1051 1756
3000 843 1402 901 1498 963 1602 991 1652 1114 1861
4000 893 1484 954 1587 1021 1698 1050 1751 1181 1973
5000 945 1572 1011 1681 1082 1800 1113 1856 1253 2093
6000 1002 1666 1072 1782 1147 1908 1180 1968 1329 2221
7000 1083 1801 1159 1928 1241 2065 1277 2130 1440 2405
8000 1171 1947 1254 2085 1343 2235 1382 2305 1559 2604
9000 1279 2128 1370 2280 1469 2445 1511 2522 1705 2851
10000 1397 2327 1498 2495 1606 2676 1653 2760 1866 3122
1050 kg /
2315 lb
V
:
55 KIAS
R
60 KIAS Runway:
Ground Roll
Over 50ft
obstacle
Ground Roll
Over 50ft
Flaps: T/O
Power:
obstacle
Ground Roll
MAX
dry , level, paved
Over 50ft
obstacle
Ground Roll
Over 50ft
Table 5(b)-4 Take-off distance [ft] at 1050 kg, 2315 lb
obstacle
Page 5(b)-5
Issue 2
Revision -, Aug. 2015
Take-off distance at 980 kg, 21 6 1 lb
AFM Supplement DA 40 D
Weight:
Airspeed for initial climb:
ISA ISA + 10°C ISA + 20°C ISA + 30°C ISA + 35°C
Pressure Altitude
Ground Roll
Over 15m
obstacle
(ft) (m) (m) (m) (m) (m) (m) (m) (m) (m) (m)
SL 182 302 194 322 207 344 213 355 239 399
1000 192 319 205 341 219 364 225 376 253 422
2000 203 338 217 361 232 385 238 398 268 448
3000 215 357 230 382 245 408 253 421 284 474
4000 227 378 243 404 260 433 268 446 301 503
5000 241 401 258 428 276 459 284 473 319 533
6000 255 424 273 454 292 486 301 502 339 566
7000 276 459 295 491 316 526 326 543 367 613
8000 298 496 319 531 342 569 352 587 397 664
9000 326 542 349 581 374 623 385 643 435 726
10000 356 593 382 636 409 682 421 703 475 796
980 kg / 2161 lb
:
V
54 KIAS
R
59 KIAS Runway:
Ground Roll
Over 15m
obstacle
Ground Roll
Over 15m
Flaps: T/O
Power:
obstacle
Ground Roll
MAX
dry , level, paved
Over 15m
obstacle
Ground Roll
Table 5(b)-5 Take-off distance [m] at 980 kg, 2161 lb
Over 15m
obstacle
Page 5(b)-6
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Take-off distance at 980 kg, 21 6 1 lb (con tin u e d)
Weight:
Airspeed for initial climb:
ISA ISA + 18°F ISA + 36°F ISA + 54°F ISA + 63°F
Pressure Altitude
Ground Roll
Over 50ft
obstacle
(ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft) (ft)
SL 595 990 635 1057 678 1129 698 1164 783 1309
1000 630 1047 672 1118 718 1194 739 1232 830 1386
2000 666 1108 711 1183 760 1264 782 1304 879 1468
3000 705 1172 753 1252 805 1339 828 1381 931 1556
4000 746 1241 797 1326 853 1419 878 1463 987 1649
5000 790 1314 845 1405 904 1504 930 1551 1047 1749
6000 837 1392 896 1489 959 1595 987 1645 1111 1856
7000 905 1505 969 1611 1038 1726 1068 1780 1203 2010
8000 978 1627 1048 1743 1123 1868 1155 1926 1303 2176
9000 1069 1779 1145 1906 1228 2044 1263 2108 1425 2383
10000 1168 1945 1252 2085 1342 2237 1381 2307 1560 2610
980 kg / 2161 lb
:
V
54 KIAS
R
59 KIAS Runway:
Ground Roll
Over 50ft
obstacle
Ground Roll
Over 50ft
Flaps: T/O
Power:
obstacle
Ground Roll
MAX
dry , level, paved
Over 50ft
obstacle
Ground Roll
Over 50ft
Table 5(b)-6 Take-off distance [ft] at 980 kg, 2161 lb
obstacle
Page 5(b)-7
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
5.3.8 Climb Performance - Take-off climb Take-off at 1150 kg, 2535 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 769 766 758 705 661
1000 766 764 756 702 659
2000 764 761 753 700 656
3000 762 759 751 697 654
4000 759 757 748 695 651
5000 757 754 746 692 649
6000 754 751 743 689 646
7000 752 749 740 687 643
8000 749 746 738 684 640
9000 728 725 716 664 621
10000 707 704 695 643 601
1150 kg / 2535 lb
66 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
ISA+20°C
ISA+36°F
ISA+30°C
ISA+54°F
Flaps: T/O
Power:
MAX
ISA+35°C
ISA+63°F
Table 5(b)-7 Take-off climb performance at 1150 kg, 2535 lb
Page 5(b)-8
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
5.3.9 Climb Performance - Cruise climb
Cruise climb at 1150 kg, 2535 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 918 913 901 829 918
1000 914 909 896 824 914
2000 909 904 891 819 909
3000 905 899 887 814 905
4000 900 894 882 809 900
5000 895 889 877 804 895
6000 890 884 871 798 890
7000 885 879 866 793 885
8000 880 874 861 787 880
9000 850 844 831 759 850
10000 821 814 801 730 821
11000 791 784 771 701 791
12000 761 754 740 672 761
13000 730 723 710 643 730
14000 700 693 680 614 700
15000 670 662 649 584 670
16000 639 632 618 554 639
1150 kg / 2535 lb
78 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
ISA+20°C
ISA+36°F
ISA+30°C
ISA+54°F
Flaps: UP
Power:
MAX
ISA+35°C
ISA+63°F
Table 5(b)-8 Cruise climb performance at 1150 kg, 2535 lb
Revision -, Aug. 2015
Page 5(b)-9
Issue 2
AFM Supplement DA 40 D
Cruise climb at 1050 kg, 2315 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 1048 1043 1030 952 888
1000 1044 1038 1026 947 884
2000 1039 1034 1021 942 879
3000 1035 1029 1016 938 874
4000 1030 1025 1012 933 869
5000 1026 1020 1007 928 864
6000 1021 1015 1002 923 859
7000 1016 1010 997 917 854
8000 1011 1005 991 912 848
9000 979 973 960 882 819
10000 947 941 928 851 789
11000 915 909 895 820 760
12000 883 877 863 789 730
13000 851 844 831 758 700
14000 819 812 798 727 670
15000 786 779 766 696 640
16000 753 746 733 664 609
1050 kg / 2315 lb
78 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
ISA+20°C
ISA+36°F
ISA+30°C
ISA+54°F
Flaps: UP
Power:
MAX
ISA+35°C
ISA+63°F
Table 5(b)-9 Cruise climb performance at 1050 kg, 2315 lb
Page 5(b)-10
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Cruise climb at 980 kg, 2161 lb
Notes:
1. For operation in air colder than provided, use coldest data
2. For operation in air warmer than provided, use extreme caution
Weight:
Airspeed for initial climb:
Pres. Alt.
(ft) ISA
SL 1153 1148 1135 1051 984
1000 1149 1144 1131 1047 979
2000 1144 1140 1126 1042 975
3000 1140 1135 1122 1038 970
4000 1136 1131 1117 1033 965
5000 1131 1126 1112 1028 960
6000 1127 1121 1108 1023 955
7000 1122 1117 1103 1018 950
8000 1117 1112 1098 1013 945
9000 1084 1078 1064 981 914
10000 1050 1044 1030 949 883
11000 1017 1010 996 916 852
12000 983 976 962 884 821
13000 949 942 928 851 789
14000 915 908 894 818 758
15000 880 874 860 785 726
16000 846 839 825 752 694
980 kg / 2161 lb
78 KIAS
RATE OF CLIMB (feet per minute)
Temperature (°C/ °F)
ISA+10°C
ISA+18°F
ISA+20°C
ISA+36°F
ISA+30°C
ISA+54°F
Flaps: UP
Power:
MAX
ISA+35°C
ISA+63°F
Table 5(b)-10 Cruise climb performance at 980 kg, 2161 lb
Page 5(b)-11
Revision -, Aug. 2015
Issue 2
AFM Supplement DA 40 D
5.3.10 Cruise Performance Cruise performance, standard tanks
Conditions:
Weight ............................................................ 1150 kg, 2535 lb
Standard Tanks.............................106 l (28 US gal) usable fuel
Flaps.....................................................................................UP
Notes:
1. Endurance information is based on standard tanks with
106 l (28 US gal) usable fuel.
2. Endurance time of this table is reduced by the time for
startup and taxi, time, fuel and distance to climb and 45 min
reserve.
3. The range data of this table take into account the distance
to climb and are reduced by 45 min reserve.
4. Increase true airspeed (KTAS/mph)) and maximum range
(NM) by 1% per 10°C above ISA temperature.
5. Cruise Power above 75% not recomme nded. For economic
cruise set load 70% or less.
Page 5(b)-12
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Standard
Tanks: 106 l (28 US gal) usable fuel
Pres.
Alt.
2000 100 145 33.6 8.9 330 2.2
2000 90 140 29.6 7.8 374 2.6
2000 80 133 25.8 6.8 424 3.1
2000 70 126 22.1 5.8 485 3.8
2000 60 118 18.6 4.9 556 4.6
2000 50 109 15.3 4.0 639 5.8
4000 100 148 33.6 8.9 334 2.1
4000 90 142 29.6 7.8 378 2.5
4000 80 136 25.8 6.8 428 3.0
4000 70 129 22.1 5.8 489 3.7
4000 60 120 18.6 4.9 561 4.5
4000 50 111 15.3 4.0 642 5.7
6000 100 151 33.6 8.9 337 2.1
6000 90 145 29.6 7.8 382 2.5
6000 80 138 25.8 6.8 432 2.9
6000 70 131 22.1 5.8 494 3.6
6000 60 123 18.6 4.9 565 4.4
6000 50 112 15.3 4.0 646 5.6
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
SL 100 143 33.6 8.9 326 2.3
SL 90 137 29.6 7.8 370 2.7
SL 80 131 25.8 6.8 420 3.2
SL 70 124 22.1 5.8 480 3.9
SL 60 117 18.6 4.9 552 4.7
SL 50 107 15.3 4.0 635 5.9
8000 100 154 33.6 8.9 341 2.0
8000 90 148 29.6 7.8 386 2.4
8000 80 141 25.8 6.8 437 2.9
8000 70 133 22.1 5.8 498 3.5
8000 60 125 18.6 4.9 569 4.3
8000 50 114 15.3 4.0 649 5.4
Page 5(b)-13
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Standard
Tanks: 106 l (28 US gal) usable fuel
Pres.
Alt.
10000 90 150 29.6 7.8 390 2.3
10000 80 144 25.8 6.8 441 2.8
10000 70 136 22.1 5.8 502 3.4
10000 60 127 18.6 4.9 573 4.2
10000 50 115 15.3 4.0 652 5.3
12000 90 153 29.6 7.8 394 2.2
12000 80 146 25.8 6.8 446 2.7
12000 70 138 22.1 5.8 507 3.3
12000 60 129 18.6 4.9 577 4.1
12000 50 117 15.3 4.0 654 5.2
14000 80 149 25.8 6.8 450 2.6
14000 70 141 22.1 5.8 512 3.2
14000 60 131 18.6 4.9 582 4.0
14000 50 118 15.3 4.0 656 5.1
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
16000 80 152 25.8 6.8 455 2.5
16000 70 143 22.1 5.8 516 3.1
16000 60 133 18.6 4.9 586 3.9
16000 50 120 15.3 4.0 657 4.9
Table 5(b)-11 Cruise performance, standard tanks
Page 5(b)-14
Issue 2
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AFM Supplement DA 40 D
Cruise performance, long range tanks
Conditions:
Weight ............................................................ 1150 kg, 2535 lb
Long Range Tanks.....................147.6 l (39 US gal) usable fuel
Flaps.....................................................................................UP
Notes:
1. Endurance information is based on long-range tanks with
147.6 l (39 US gal) usable fuel.
2. Endurance time of this table is reduced by the time for
startup and taxi, time, fuel and distance to climb and 45 min
reserve.
3. The range data of this table take into account the distance
to climb and are reduced by 45 min reserve.
4. Increase true airspeed (KTAS/mph)) and maximum range
(NM) by 1% per 10°C above ISA temperature.
5. Cruise Power above 75% not recomme nded. For economic
cruise set load 70% or less.
Page 5(b)-15
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Long Range
Tanks: 147.6 l (39 US gal) usable fuel
Pres.
Alt.
2000 100 145 33.6 33.6 510 3.5
2000 90 140 29.6 29.6 570 4.0
2000 80 133 25.8 25.8 639 4.7
2000 70 126 22.1 22.1 723 5.7
2000 60 118 18.6 18.6 821 6.9
2000 50 109 15.3 15.3 935 8.5
4000 100 148 33.6 33.6 517 3.4
4000 90 142 29.6 29.6 577 3.9
4000 80 136 25.8 25.8 647 4.6
4000 70 129 22.1 22.1 731 5.6
4000 60 120 18.6 18.6 830 6.8
4000 50 111 15.3 15.3 943 8.4
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
SL 100 143 33.6 8.9 503 3.5
SL 90 137 29.6 7.8 562 4.1
SL 80 131 25.8 6.8 631 4.8
SL 70 124 22.1 5.8 714 5.7
SL 60 117 18.6 4.9 812 7.0
SL 50 107 15.3 4.0 927 8.6
6000 100 151 33,6 33,6 524 3,3
6000 90 145 29.6 29.6 585 3.9
6000 80 138 25.8 25.8 655 4.6
6000 70 131 22.1 22.1 740 5.5
6000 60 123 18.6 18.6 839 6.7
6000 50 112 15.3 15.3 951 8.3
8000 100 154 33.6 33.6 532 3.2
8000 90 148 29.6 29.6 593 3.8
8000 80 141 25.8 25.8 664 4.5
8000 70 133 22.1 22.1 749 5.4
8000 60 125 18.6 18.6 848 6.6
8000 50 114 15.3 15.3 958 8.2
Page 5(b)-16
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Weight: 1150 kg / 2535 lb Flaps: UP
Long Range
Tanks: 147.6 l (39 US gal) usable fuel
Pres.
Alt.
10000 90 150 29.6 29.6 601 3.7
10000 80 144 25.8 25.8 673 4.4
10000 70 136 22.1 22.1 758 5.3
10000 60 127 18.6 18.6 857 6.4
10000 50 115 15.3 15.3 965 8.0
12000 90 153 29.6 29.6 610 3.6
12000 80 146 25.8 25.8 681 4.3
12000 70 138 22.1 22.1 767 5.2
12000 60 129 18.6 18.6 866 6.3
12000 50 117 15.3 15.3 972 7.9
14000 80 149 25.8 25.8 691 4.2
14000 70 141 22.1 22.1 777 5.1
14000 60 131 18.6 18.6 874 6.2
14000 50 118 15.3 15.3 978 7.8
Load KTAS Fuel Flow Range Endurance
(ft) (%) (kt) (l/h) (US gal/h) (NM) (hrs)
16000 80 152 25.8 25.8 700 4.1
16000 70 143 22.1 22.1 786 5.0
16000 60 133 18.6 18.6 883 6.1
16000 50 120 15.3 15.3 983 7.6
Table 5(b)-12 Cruise performance, long range tanks
Page 5(b)-17
Revision -, Aug. 2015
Issue 2
AFM Supplement DA 40 D
5.3.15 Approved Noise Data
With TAE 125-02-114 engine and Muffler LA50 Installed:
ICAO Annex 16 Chapter X........................................70.5 dB(A)
Page 5(b)-18
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
CHAPTER 6
MASS AND BALANCE / EQUIPMENT LIST
6.3 MASS AND BALANCE REPORT
After installation of the TAE 125-02-114 engine installation, the
empty mass and empty mass moment must be established.
Refer to the basic AFM and basic AMM for the DAI DA 40 D.
Record the data in the Mass and Balance Report of the basic
AFM.
Page 6-1
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY
The following equipment is approved for the TAE 125-02-114
engine installation.
Description Type Part No.
ENGINE
Engine TAE 125-02-114 Technify
Engine
Control
Unit
„xx“
refer to
Service Bulletin
TM TAE
000-0007
latest Rev.
EXHAUST SYSTEM
Muffler LA50 50-7810-H0003 01 Technify
ENGINE INDICATING
Compact
Engine
Display
PROPELLER
Propeller MTV-6-A/187-129 mt-Pro-
AIRPLANE FLIGHT MANUAL
AFM
Supplement
ECU
(D48)
ECU Firmware
TAE 125 mx.xx
Mapping
P14CxxxDA40
(Clutch)
Mapping
P14DxxxDA40
(Dual Mass Fly Wheel)
ECU
(D4)
ECU Firmware
D4-vx.xx
Mapping
G14CxxxDA40
(Clutch)
Mapping
G14DxxxDA40
(Dual Mass Fly Wheel)
TAE CED-125 02-7730-5501-(06)-
MTV-6-A/190-69
05-7610-E0001 02 Technify
02-7610-55101Rxx n/a
05-7611-E0019 04 Technify
05-7610-E0010 xx n/a
(02)
50-0310-50022 Technify
Manu-
facturer
Motors
GmbH
Motors
GmbH
Motors
GmbH
Motors
GmbH
Technify
Motors
GmbH
peller
Motors
GmbH
s/n
n/a
n/a
n/a
n/a
in-
stalled
Page 6-2
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
CHAPTER 7
DESCRIPTION OF THE AIRPLANE AND
ITS SYSTEMS
7.9.1 ENGINE, GENERAL
The TAE 125-02-114 engine has the same general characteri cs
as the TAE 125-02-99 engine, except for the continuous and
maximum power.
Max. power: 114 kW (155 DIN-HP) at 2300 RPM, ISA, SL
Max. cont. power:114 kW (155 DIN-HP) at 2300 RPM, ISA, SL
There is no difference in operation between the different TAE
125 engine variants.
Page 7-1
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
TAE 125-02-114
engine
Thermostat
Valve
Coolant Radiator
Expansion
Tank
Cabin Heat
Heat-Exchanger
Coolant
Radiator
Gear Oil
Cooler
Overflow line to
exterior
Bleed Screw
Bleed Screw
Bypass
Circuit
Main Circuit
Gearbox oil
7.9.6 COOLING SYSTEM
The cooling system of the TAE 125-02-114 installation consists
of 1 large and 1 small water-cooler. The engine oil is cooled
using an oil/water-heat exchanger as part of engine. A Cabin
Heat heat-exchanger is part of the liquid coolin g system as well
as a gearbox oil heat-exchanger. The gearbox oil heatexchanger is part of the TAE 125-02-114 engine, but connected
to the aircraft liquid cooling system. Refer to Figure 7-1 for a
schematic.
Figure 7-1 Liquid Cooling System
7.9.8 OIL SYSTEMS
Lubrication system (engine and turbocharger)
The engine oil is cooled using a oil/water heat exchange which
is part of the engine. There is no separate oil cooler as provided
in the unmodified engine installation.
Gearbox and propeller governor system
This oil system is independent of the engine lubrication system.
To cool the gearbox a heat exchanger is connected the liquid
cooling system.
Refer to Figure 7-1.
Page 7-2
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
CHAPTER 8
AIRPLANE HANDLING,
CARE AND MAINTENANCE
8.1 INTRODUCTION
For proper ground handling and servicing refer to the ba sic
AFM.
The supplement to the Airplane Maintenance Manual AMM-5002 describes the maintenance practices that apply to the TAE
125-02-114 engine installation. It supersedes or adds to the
basic DAI Airplane Maintenance Manual only as set forth
therein.
8.2 AIRPLANE INSPECTION INTERVALS
Refer to supplement to the Airplane Maintenance Manual AMM50-02 and the basic DAI Airplane Maintenance Manual.
8.3 AIRPLANE ALTERATIONS AND REPAIRS
Alterations and repairs to the STC installation may be carried
out only according to the supplement to the Airplane
Maintenance Manual AMM-50-02 or i.a.w. a repair scheme
which has been approved by Technify Motors GmbH
or by the competent Airworthiness Authority.
Page 8-1
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AFM Supplement DA 40 D
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AFM Supplement DA 40 D
CHAPTER 9
SUPPLEMENTS
9.1 INTRODUCTION
This chapter lists the supplements to the basic AFM that ar e
affected by the TAE 125-02-114 engine istallation.
For the affected supplements, a supplement has been created
which adds or supersedes the affected supplements as
described.
9.2 LIST OF SUPPLEMENTS
Sup.
No
1
2
Title Issue
Garmin G1000 Avionic System for
VFR Operation
Garmin G1000 Avionic System for
IFR Operation
applicable
yes no
1
1
Page 9-1
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AFM Supplement DA 40 D
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Page 9-2
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Supplement 1, Garmin G1000, VFR
Supplement
for the
DA 40 D
with
Garmin G1000 Avionic System for VFR Operation
equipped with
TAE 125-02-114 Engine Installation
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 and
supplement A31 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 and supplement A31.
This supplement is approved with EASA STC 10036328.
Page 9-1-1
Revision -, Aug. 2015
Issue 2
Supplement 1, Garmin G1000, VFR
Issue Pages Description
AFM Supplement DA 40 D
Approved
Date Endorsed
2/0 All
New Issue
Change of Ownership
Aug. 15,
2015
EASA STC
10036328,
Rev. 3
Remark: The parts of the text which changed are marked with
a vertical line on the margin of the page.
Page 9-1-2
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Supplement 1, Garmin G1000, VFR
1. General
This supplement contains the required information fo r operation
of the airplane with a TAE 125-02-114 engine installation and
the Garmin G1000 avionic system installed.
This supplement must be used in conjunction with the basic DAI
AFM incl. supplement A31 and the supplement for the TAE 12502-114 engine installation.
2. Limitations
No change
The engine limitations and engine instrument marking
applicable to the TAE 125-02-99 engine are valid for the TAE
125-02-114.
Refer to supplement A31 of the basic AFM.
3. Emergency Procedures
No change.
Refer to supplement A31 of the basic AFM.
4A. Normal Operating Procedures
No change.
Refer to supplement A31 of the basic AFM.
4B. Abnormal Operating Procedures
No change.
Refer to supplement A31 of the basic AFM.
5. Performance
No change.
Refer to supplement A31 of the basic AFM.
6. Mass and Balance
No change.
Refer to supplement A31 of the basic AFM.
Revision -, Aug. 2015
Page 9-1-3
Issue 2
AFM Supplement DA 40 D
Supplement 1, Garmin G1000, VFR
7. Description of the airplane and its systems
No change.
Refer to supplement A31 of the basic AFM.
8. Airplane Handling, Care and Maintenance
No change.
Refer to supplement A31 of the basic AFM.
Page 9-1-4
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Supplement 2, Garmin G1000, IFR
Supplement
for the
DA 40 D
with
Garmin G1000 Avionic System for IFR Operation
equipped with
TAE 125-02-114 Engine Installation
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 and
supplement A32 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 and supplement A32.
This supplement is approved with EASA STC 10036328.
Page 9-2-1
Revision -, Aug. 2015
Issue 2
Supplement 2, Garmin G1000, IFR
Issue Pages Description
AFM Supplement DA 40 D
Approved
Date Endorsed
2/0 All
New Issue
Change of Ownership
Aug. 15,
2015
EASA STC
10036328,
Rev. 3
Remark: The parts of the text which changed are marked with
a vertical line on the margin of the page.
Page 9-2-2
Issue 2
Revision -, Aug. 2015
AFM Supplement DA 40 D
Supplement 2, Garmin G1000, IFR
1. General
This supplement contains the required information fo r operation
of the airplane with a TAE 125-02-114 engine installation and
the Garmin G1000 avionic system installed.
This supplement must be used in conjunction with the basic DAI
AFM incl. supplement A32 and the supplement for the TAE 12502-114 engine installation.
2. Limitations
No change
The engine limitations and engine instrument marking
applicable to the TAE 125-02-99 engine are valid for the TAE
125-02-114.
Refer to supplement A32 of the basic AFM.
3. Emergency Procedures
No change.
Refer to supplement A32 of the basic AFM.
4A. Normal Operating Procedures
No change.
Refer to supplement A32 of the basic AFM.
4B. Abnormal Operating Procedures
No change.
Refer to supplement A32 of the basic AFM.
5. Performance
No change.
Refer to supplement A32 of the basic AFM.
6. Mass and Balance
No change.
Refer to supplement A32 of the basic AFM.
Revision -, Aug. 2015
Page 9-2-3
Issue 2
AFM Supplement DA 40 D
Supplement 2, Garmin G1000, IFR
7. Description of the airplane and its systems
No change.
Refer to supplement A32 of the basic AFM.
8. Airplane Handling, Care and Maintenance
No change.
Refer to supplement A32 of the basic AFM.
Page 9-2-4
Issue 2
Revision -, Aug. 2015
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