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DA 40
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Diamond DA 40 Flight Manual

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Page 1
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Introduction DA 40 AFM
FOREWORD
We congratulate you on the acquisition of your new DIAMOND STAR. Skillful operation of an airplane increases both safety and the enjoyment of flying. Please
take the time therefore, to familiarize yourself with your new DIAMOND STAR. This airplane may only be operated in accordance with the procedures and operating
the complete contents of this Airplane Flight Manual. In the event that you have obtained your DIAMOND STAR second-hand, please let us
know your address, so that we can supply you with the publications necessary for the safe operation of your airplane.
This document is protected by copyright. All associated rights, in particular those of translation, reprinting, radio transmission, reproduction by photo-mechanical or similar means and storing in data processing facilities, in whole or part, are reserved.
Copyright © by: DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. Otto-Strasse 5 A-2700 Wiener Neustadt, Austria Phone. : +43-2622-26700 Fax : +43-2622-26780 E-Mail : [email protected]
Page 0 - 0 Revision 6 15-Sep-2004 Doc. # 6.01.01-E
Page 3
DA 40 AFM Introduction

0.1 APPROVAL%

The content of approved chapters is approved by EASA. All other content is approved% by DAI under the authority of EASA DOA No. EASA.21J.052 in accordance with Part 21.%

0.2 RECORD OF REVISIONS

All revisions of this manual, with the exception of -
C Temporary Revisions, C updates of the modification level (Section 1.1), C updated mass and balance information (Section 6.3), C updates of the Equipment Inventory (Section 6.5), and C updates of the List of Supplements (Section 9.2)
must be recorded in the following table. % The new or amended text is indicated by a vertical black line at the left hand side of the
revised page, with the revision number and date appearing at the bottom of the page.
NOTE
If pages are revised which contain information valid for your particular serial number (modification level of the airplane, weighing data, Equipment Inventory, List of Supplements), then this information must be transferred to the new pages in hand-writing.
Temporary Revisions, if applicable, are inserted into this manual. Temporary Revisions are used to provide information on systems or equipment until the next 'permanent' Revision of the Airplane Flight Manual. When a 'permanent' Revision covers a Mandatory or Optional Design Change Advisory (MÄM or OÄM), then the corresponding Temporary Revision is superseded. For example: Revision 5 covers OÄM-40-061, therefore the Temporary Revision TR-OÄM-40-061 is superseded by the 'permanent' Revision 5.
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 1
Page 4
Introduction DA 40 AFM
Rev.
No.
Reason
1 corrections all all 26-Sep-2000
OÄM 40-060
(White Wire
optional)
OÄM 40-068
(Essential Bus)
2
OÄM 40-073
(LASAR
optional)
corrections
Chapte
r
0 0-2, 0-4 thru 0-7 11-16
2
3
4A
4B 4B-4 thru 4B-6
6
7
0 0-2 thru 0-7
Page(s)
2-1, 2-7 thru 2-9,
2-13 thru 2-19 3-7, 3-8, 3-19,
3-20, 3-25, 3-26
4A-3 thru 4A-8,
4A-14, 4A-15
6-1, 6-2,
6-12 thru 6-14 7-1, 7-8, 7-14,
7-28 thru 7-38
Date of
Revision
19-Dec-2000
Approval
[approved by Ing. Andreas
Winkler for
ACG]
approved by
Ing. Andreas
Winkler for
ACG]
Date of
Approval
09-Oct-2000
25-Jan-2001
Date Inserted Signature
11-2
2-1, 2-8, 2-9, 2-12,
2
2-15 thru 2-20
3 3-1, 3-25 thru 3-27
4A
5 5-7, 5-14, 5-16
6
7 7-32, 7-35, 7-36 8 8-1 thru 8-9
4A-1,
4A-8 thru 4A-31
6-7, 6-9,
6-12 thru 6-14
05-Feb-2001
[approved by Ing. Andreas
Winkler for
ACG]
02 Jul 2001
3
OÄM 40-064
(Night VFR)
OÄM 40-069 (control surf.
gust lock)
OÄM 40-070
(tow bar)
corrections
Page 0 - 2 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 5
DA 40 AFM Introduction
Rev.
No.
4
5
Reason
OÄM 40-067
(IFR)
corrections
OÄM 40-061
(KAP 140 autopilot)
OÄM 40-073
(SlickSTART)
OÄM 40-081
(door lock)
OÄM 40-085
(KX 155A
as COM 1)
OÄM's 40-092
thru 40-094
(Mikrotechna
ASI, altimeter,
VSI)
Chapte
r
all all 09 Apr 2001
0 0-1 thru 0-8
1 1-2, 1-5, 1-14
2
3
4A
4B 4B-1, 4B-8
6 6-5, 6-8 thru 6-17
Page(s)
2-1, 2-16, 2-22,
2-23, 2-24
3-13, 3-18, 3-22, 3-23, 3-24, 3-31,
3-36
4A-8, 4A-10, 4A-22,
4A-23, 4A-26
Date of
Revision
09 Sep 2001
Approval
[approved by Ing. Andreas
Winkler for
ACG]
[approved by Ing. Andreas
Winkler for
ACG]
Date of
Approval
02 Jul 2001
09 Sep 2001
Date Inserted Signature
MÄM 40-039/a
(VM 1000)
MÄM 40-048
(RH emerg.
window)
corrections
7-13, 7-14, 7-33,
7
88-10
9 9-3, 9-4, 9-5
7-35
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 3
Page 6
Introduction DA 40 AFM
Rev.
No.
%
Reason Chapter Page(s)
type certifi-
6
cation in China
MÄM-40-
-047, -069,
-075, -078,
-096, -099,
-123e, -133,
-141, -174,
OÄM-40-
-063/b, -071/c,
-077, -078,
-080, -083/a,
-090, -091,
-097, -098,
-103, -104,
-105, -106,
-111, -112,
-114, -115,
-117, -117/a,
7
-119, -120,
-121, -122,
-124, -127,
-128, -138,
-140, -154,
-165, -167,
-168, -179,
-181, -183,
-185, -186,
-190, -198,
-200, -206,
-237, 250/a;
-175;
0 0-0, 0-5, 0-6 15 Sep 2004 2004-12326
all
all except cover
page
Date of
Revision
15 Jul 2006
EASA Approv-
al No.
Revision No. 7
of the AFM %
Doc. No.%
6.01.01-E is% approved% under the%
authority of%
DOA No.%
EASA.21J.052 %
ACG
Compliance
[Ing. Andreas
Winkler for
ACG]
[11 Aug 2006
Dipl.-Ing.
(FH)
Manfred
Reichel for DAI]
Date
Inserted
Signature
RÄM-40-
-014;
corrections;
double-sided
layout
Page 0 - 4 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 7
DA 40 AFM Introduction
Rev.
No.
Reason Chapter Page(s)
MÄM-40-%
-176, -227/a,%
-313, -344,%
-360/a, -378,%
-401, -415,%
-428, -446;%
%
OÄM-40-%
-217, -251,%
8%
%%%
-253/b, 258,%
-267, -277/a,%
-279, 283/a,%
-284, -289,%
-326, -327;%
all except cover%
all%
page%
Date of
Revision
01 Dec 2010%
EASA Approv-
al No.
Revision No. 8%
of the AFM%
Doc. No.%
6.01.01-E is% approved% under the%
authority of%
DOA No.%
EASA.21J.052%
ACG
Compliance
Date
Inserted
Signature
%
corrections%
%
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 5
Page 8
Introduction DA 40 AFM

0.3 LIST OF EFFECTIVE PAGES

Ch. Page Date
0 0-0 15-Sep-2004
0-0a 15-Sep-2004
0-1 01-Dec-2010 0-2 01-Dec-2010
0-3 01-Dec-2010 0-4 01-Dec-2010 0-5 01-Dec-2010 0-6 01-Dec-2010 0-7 01-Dec-2010 0-8 01-Dec-2010
0-9 01-Dec-2010 0-10 01-Dec-2010 0-11 01-Dec-2010 0-12 01-Dec-2010
Ch. Page Date
1 1-1 01-Dec-2010
1-2 01-Dec-2010 1-3 01-Dec-2010 1-4 01-Dec-2010 1-5 01-Dec-2010 1-6 01-Dec-2010 1-7 01-Dec-2010 1-8 01-Dec-2010
1-9 01-Dec-2010 1-10 01-Dec-2010 1-11 01-Dec-2010 1-12 01-Dec-2010 1-13 01-Dec-2010 1-14 01-Dec-2010
0-13 01-Dec-2010 0-14 01-Dec-2010
1-15 01-Dec-2010 1-16 01-Dec-2010 1-17 01-Dec-2010 1-18 01-Dec-2010 1-19 01-Dec-2010 1-20 01-Dec-2010 1-21 01-Dec-2010 1-22 01-Dec-2010 1-23 01-Dec-2010 1-24 01-Dec-2010
Page 0 - 6 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
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DA 40 AFM Introduction
Ch. Page Date
2 appr. 2-1 01-Dec-2010
appr. 2-2 01-Dec-2010 appr. 2-3 01-Dec-2010 appr. 2-4 01-Dec-2010 appr. 2-5 01-Dec-2010 appr. 2-6 01-Dec-2010 appr. 2-7 01-Dec-2010 appr. 2-8 01-Dec-2010
appr. 2-9 01-Dec-2010 appr. 2-10 01-Dec-2010 appr. 2-11 01-Dec-2010 appr. 2-12 01-Dec-2010 appr. 2-13 01-Dec-2010 appr. 2-14 01-Dec-2010
Ch. Page Date
2 appr. 2-28 01-Dec-2010
appr. 2-29 01-Dec-2010 appr. 2-30 01-Dec-2010 appr. 2-31 01-Dec-2010 appr. 2-32 01-Dec-2010 appr. 2-33 01-Dec-2010 appr. 2-34 01-Dec-2010
appr. 2-15 01-Dec-2010 appr. 2-16 01-Dec-2010 appr. 2-17 01-Dec-2010 appr. 2-18 01-Dec-2010 appr. 2-19 01-Dec-2010 appr. 2-20 01-Dec-2010 appr. 2-21 01-Dec-2010 appr. 2-22 01-Dec-2010 appr. 2-23 01-Dec-2010 appr. 2-24 01-Dec-2010 appr. 2-25 01-Dec-2010 appr. 2-26 01-Dec-2010 appr. 2-27 01-Dec-2010
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 7
Page 10
Introduction DA 40 AFM
Ch. Page Date
3 3-1 01-Dec-2010
3-2 01-Dec-2010 3-3 01-Dec-2010 3-4 01-Dec-2010 3-5 01-Dec-2010 3-6 01-Dec-2010 3-7 01-Dec-2010 3-8 01-Dec-2010
3-9 01-Dec-2010 3-10 01-Dec-2010 3-11 01-Dec-2010 3-12 01-Dec-2010 3-13 01-Dec-2010 3-14 01-Dec-2010
Ch. Page Date
3 3-29 01-Dec-2010
3-30 01-Dec-2010 3-31 01-Dec-2010 3-32 01-Dec-2010 3-33 01-Dec-2010 3-34 01-Dec-2010 3-35 01-Dec-2010 3-36 01-Dec-2010 3-37 01-Dec-2010 3-38 01-Dec-2010 3-39 01-Dec-2010 3-40 01-Dec-2010 3-41 01-Dec-2010 3-42 01-Dec-2010
3-15 01-Dec-2010 3-16 01-Dec-2010 3-17 01-Dec-2010 3-18 01-Dec-2010 3-19 01-Dec-2010 3-20 01-Dec-2010 3-21 01-Dec-2010 3-22 01-Dec-2010 3-23 01-Dec-2010 3-24 01-Dec-2010 3-25 01-Dec-2010 3-26 01-Dec-2010 3-27 01-Dec-2010 3-28 01-Dec-2010
Page 0 - 8 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 11
DA 40 AFM Introduction
Ch. Page Date
4A 4A-1 01-Dec-2010
4A-2 01-Dec-2010 4A-3 01-Dec-2010 4A-4 01-Dec-2010 4A-5 01-Dec-2010 4A-6 01-Dec-2010 4A-7 01-Dec-2010 4A-8 01-Dec-2010
4A-9 01-Dec-2010 4A-10 01-Dec-2010 4A-11 01-Dec-2010 4A-12 01-Dec-2010 4A-13 01-Dec-2010 4A-14 01-Dec-2010
Ch. Page Date
4A 4A-28 01-Dec-2010
4A-29 01-Dec-2010 4A-30 01-Dec-2010 4A-31 01-Dec-2010 4A-32 01-Dec-2010 4A-33 01-Dec-2010 4A-34 01-Dec-2010 4A-35 01-Dec-2010 4A-36 01-Dec-2010 4A-37 01-Dec-2010 4A-38 01-Dec-2010 4A-39 01-Dec-2010 4A-40 01-Dec-2010
4A-15 01-Dec-2010 4A-16 01-Dec-2010 4A-17 01-Dec-2010 4A-18 01-Dec-2010 4A-19 01-Dec-2010 4A-20 01-Dec-2010 4A-21 01-Dec-2010
4A-22 01-Dec-2010 4A-23 01-Dec-2010 4A-24 01-Dec-2010 4A-25 01-Dec-2010 4A-26 01-Dec-2010 4A-27 01-Dec-2010
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 9
Page 12
Introduction DA 40 AFM
Ch. Page Date
4B 4B-1 01-Dec-2010
4B-2 01-Dec-2010 4B-3 01-Dec-2010 4B-4 01-Dec-2010 4B-5 01-Dec-2010 4B-6 01-Dec-2010 4B-7 01-Dec-2010 4B-8 01-Dec-2010
4B-9 01-Dec-2010 4B-10 01-Dec-2010 4B-11 01-Dec-2010 4B-12 01-Dec-2010
Ch. Page Date
5 5-1 01-Dec-2010
5-2 01-Dec-2010 5-3 01-Dec-2010 5-4 01-Dec-2010 5-5 01-Dec-2010 5-6 01-Dec-2010 5-7 01-Dec-2010 5-8 01-Dec-2010
5-9 01-Dec-2010 5-10 01-Dec-2010 5-11 01-Dec-2010 5-12 01-Dec-2010 5-13 01-Dec-2010 5-14 01-Dec-2010 5-15 01-Dec-2010 5-16 01-Dec-2010 5-17 01-Dec-2010 5-18 01-Dec-2010 5-19 01-Dec-2010 5-20 01-Dec-2010 5-21 01-Dec-2010 5-22 01-Dec-2010 5-23 01-Dec-2010 5-24 01-Dec-2010
Page 0 - 10 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 13
DA 40 AFM Introduction
Ch. Page Date
6 6-1 01-Dec-2010
6-2 01-Dec-2010 6-3 01-Dec-2010 6-4 01-Dec-2010 6-5 01-Dec-2010 6-6 01-Dec-2010 6-7 01-Dec-2010 6-8 01-Dec-2010
6-9 01-Dec-2010 6-10 01-Dec-2010 6-11 01-Dec-2010 6-12 01-Dec-2010 6-13 01-Dec-2010 6-14 01-Dec-2010
Ch. Page Date
6 6-28 01-Dec-2010
6-29 01-Dec-2010 6-30 01-Dec-2010 6-31 01-Dec-2010 6-32 01-Dec-2010
6-15 01-Dec-2010 6-16 01-Dec-2010 6-17 01-Dec-2010 6-18 01-Dec-2010 6-19 01-Dec-2010 6-20 01-Dec-2010 6-21 01-Dec-2010 6-22 01-Dec-2010 6-23 01-Dec-2010 6-24 01-Dec-2010 6-25 01-Dec-2010 6-26 01-Dec-2010 6-27 01-Dec-2010
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 11
Page 14
Introduction DA 40 AFM
Ch. Page Date
7 7-1 01-Dec-2010
7-2 01-Dec-2010 7-3 01-Dec-2010 7-4 01-Dec-2010 7-5 01-Dec-2010 7-6 01-Dec-2010 7-7 01-Dec-2010 7-8 01-Dec-2010
7-9 01-Dec-2010 7-10 01-Dec-2010 7-11 01-Dec-2010 7-12 01-Dec-2010 7-13 01-Dec-2010 7-14 01-Dec-2010
Ch. Page Date
7 7-28 01-Dec-2010
7-29 01-Dec-2010 7-30 01-Dec-2010 7-31 01-Dec-2010 7-32 01-Dec-2010 7-33 01-Dec-2010 7-34 01-Dec-2010 7-35 01-Dec-2010 7-36 01-Dec-2010 7-37 01-Dec-2010 7-38 01-Dec-2010 7-39 01-Dec-2010 7-40 01-Dec-2010 7-41 01-Dec-2010
7-15 01-Dec-2010 7-16 01-Dec-2010 7-17 01-Dec-2010 7-18 01-Dec-2010 7-19 01-Dec-2010 7-20 01-Dec-2010 7-21 01-Dec-2010 7-22 01-Dec-2010 7-23 01-Dec-2010 7-24 01-Dec-2010 7-25 01-Dec-2010 7-26 01-Dec-2010 7-27 01-Dec-2010
7-42 01-Dec-2010 7-43 01-Dec-2010 7-44 01-Dec-2010 7-45 01-Dec-2010 7-46 01-Dec-2010 7-47 01-Dec-2010 7-48 01-Dec-2010 7-49 01-Dec-2010 7-50 01-Dec-2010 7-51 01-Dec-2010 7-52 01-Dec-2010 7-53 01-Dec-2010 7-54 01-Dec-2010
Page 0 - 12 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 15
DA 40 AFM Introduction
Ch. Page Date
7 7-55 01-Dec-2010
7-56 01-Dec-2010 7-57 01-Dec-2010 7-58 01-Dec-2010
Ch. Page Date
8 8-1 01-Dec-2010
8-2 01-Dec-2010 8-3 01-Dec-2010 8-4 01-Dec-2010 8-5 01-Dec-2010 8-6 01-Dec-2010 8-7 01-Dec-2010 8-8 01-Dec-2010
Ch. Page Date
9 9-1 01-Dec-2010
9-2 01-Dec-2010 9-3 01-Dec-2010 9-4 01-Dec-2010 9-5 01-Dec-2010 9-6 01-Dec-2010
8-9 01-Dec-2010 8-10 01-Dec-2010 8-11 01-Dec-2010 8-12 01-Dec-2010
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 0 - 13
Page 16
Introduction DA 40 AFM

0.4 TABLE OF CONTENTS

Chapter
GENERAL
(a non-approved chapter) ....................................... 1
OPERATING LIMITATIONS
(an approved chapter) .......................................... 2
EMERGENCY PROCEDURES
(a non-approved chapter) ....................................... 3
NORMAL OPERATING PROCEDURES
(a non-approved chapter) ......................................4A
ABNORMAL OPERATING PROCEDURES
(a non-approved chapter) ......................................4B
PERFORMANCE
(a non-approved chapter) ....................................... 5
MASS AND BALANCE / EQUIPMENT LIST
(a non-approved chapter) ....................................... 6
DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS
(a non-approved chapter) ....................................... 7
AIRPLANE HANDLING, CARE AND MAINTENANCE
(a non-approved chapter) ....................................... 8
SUPPLEMENTS .................................................... 9
Page 0 - 14 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 17
DA 40 AFM General
CHAPTER 1

GENERAL

Page
1.1 INTRODUCTION .......................................1-2
1.2 CERTIFICATION BASIS ..................................1-5
1.3 WARNINGS, CAUTIONS AND NOTES ......................1-5
1.4 DIMENSIONS..........................................1-6
1.5 DEFINITIONS AND ABBREVIATIONS .......................1-8
1.6 UNITS OF MEASUREMENT .............................1-18
1.6.1 CONVERSION FACTORS ..........................1-18
1.6.2 CONVERSION CHART LITERS / US GALLONS.........1-20
1.7 THREE-VIEW DRAWING................................1-21
1.8 SOURCE DOCUMENTATION ............................1-22
1.8.1 ENGINE ........................................1-22
1.8.2 PROPELLER ....................................1-23
1.8.3 ENGINE INSTRUMENTS ...........................1-23
1.8.4 IGNITION CONTROL UNIT .........................1-24
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 - 1
Page 18
General DA 40 AFM

1.1 INTRODUCTION

This Airplane Flight Manual has been prepared in order to provide pilots and instructors with all the information required for the safe and efficient operation of the airplane.
The Airplane Flight Manual includes all the data which must be made available to the pilot according to the JAR-23 requirement. Beyond this, it contains further data and operating instructions which, in the manufacturer’s opinion, could be of value to the pilot.
This Airplane Flight Manual is valid for all serial numbers. Equipment and modification level (design details) of the airplane may vary from serial number to serial number. Therefore, some of the information contained in this manual is applicable depending on the respective equipment and modification level. The exact equipment of your serial number is recorded in the Equipment Inventory in Section 6.5. The modification level is recorded in the following table (as far as necessary for this manual).
Modification Source Installed
RH Emergency Window MÄM 40-048 9 yes 9 no Modified MLG Strut MÄM 40-123/e 9 yes 9 no
1200 kg Maximum Take-Off Mass% MÄM 40-227% 9 yes% 9 no% Autopilot OÄM 40-061 9 yes 9 no Tow-Plane Operation OÄM 40-063/b 9 yes 9 no Emergency Switch OÄM 40-067 9 yes 9 no
Essential Bus OÄM 40-068 9 yes 9 no Long Range Tank OÄM 40-071/b 9 yes 9 no
Alternate Static Valve OÄM 40-072 9 yes 9 no SlickSTART Ignition System OÄM 40-073 9 yes 9 no
MT P-420-10 Governor
% OÄM 40-077% 9 yes% 9 no%
Operation with Winter Kit OÄM 40-078 9 yes 9 no
Page 1 - 2 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 19
DA 40 AFM General
Modification Source Installed
Door Locking System OÄM 40-081 9 yes 9 no NLG Speedkit OÄM 40-105 9 yes 9 no MLG Speedkit OÄM 40-106 9 yes 9 no Essential Tie Relay Bypass OÄM 40-126 9 yes 9 no Baggage Extension
Baggage Tray* Winter Baffle Fresh Air Inlet OÄM 40-183 9 yes 9 no Nose Landing Gear Tie-Down OÄM 40-200 9 yes 9 no Electrical Rudder Pedal Adjustment% OÄM 40-251% 9 yes% 9 no% CO Monitor% OÄM 40-253% 9 yes% 9 no% Autopilot Static Source% OÄM 40-267% 9 yes% 9 no% Tall Main Landing Gear% OÄM 40-283% 9 yes% 9 no% ELT Artex ME 406 ‘ACE’% OÄM 40-284% 9 yes% 9 no% MT P-860-23 Governor% OÄM 40-289% 9 yes% 9 no% Emergency Axe% OÄM 40-326% 9 yes% 9 no%
*For installation of the Baggage Tray the Baggage Extension must be installed. This Airplane Flight Manual must be kept on board the airplane at all times. Its designated
OÄM 40-163 OÄM 40-164
9 yes 9 yes
9 no 9 no
place is the side bag of the forward left seat. This Airplane Flight Manual constitutes an FAA Approved Airplane Flight Manual for
US registered airplanes in accordance with FAA regulation 14 CFR, Part 21.29.
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 - 3
Page 20
General DA 40 AFM
CAUTION
The DA 40 is a single engine airplane. When the operating limitations and maintenance requirements are complied with, it has the high degree of reliability which is required by the certification basis. Nevertheless, an engine failure is not completely impossible. For this reason, flights during the night, on top, under instrument meteorological conditions (IMC), or above terrain which is unsuitable for a landing, constitute a risk. It is therefore highly recommended to select flight times and flight routes such that this risk is minimized.
Page 1 - 4 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 21
DA 40 AFM General

1.2 CERTIFICATION BASIS

This airplane has been type certified in accordance with the JAA JC/VP procedure. The certification basis is JAR-23, published on 11-Mar-1994.

1.3 WARNINGS, CAUTIONS AND NOTES

Special statements in the Airplane Flight Manual concerning the safety or operation of the airplane are highlighted by being prefixed by one of the following terms:
WARNING
means that the non-observation of the corresponding procedure leads to an immediate or important degradation in 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 in flight safety.
NOTE
draws the attention to any special item not directly related to safety but which is important or unusual.
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 - 5
Page 22
General DA 40 AFM

1.4 DIMENSIONS

Overall Dimensions
Span : appr. 11.94 m appr. 39 ft 2 in Length : appr. 8.01 m appr. 26 ft 3 in Height : appr. 1.97 m appr. 6 ft 6 in
Wing
Airfoil : Wortmann FX 63-137/20 - W4 Wing Area : appr. 13.54 m² appr. 145.7 sq.ft. Mean aerodynamic
chord (MAC) : appr. 1.121 m appr. 3 ft 8.1 in Aspect ratio : appr. 10.53 Dihedral : appr. 5° Leading edge sweep : appr. 1°
Aileron
Area (total, left + right) : appr. 0.654 m² appr. 7.0 sq.ft.
Wing Flaps
Area (total, left + right) : appr. 1.56 m² appr. 16.8 sq.ft.
Horizontal Tail
Area : appr. 2.34 m
2
appr. 25.2 sq.ft. Elevator area : appr. 0.665 m² appr. 7.2 sq.ft. Angle of incidence : appr. -3.0° relative to longitudinal axis of airplane
Page 1 - 6 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 23
DA 40 AFM General
Vertical Tail
Area : appr. 1.60 m² appr. 17.2 sq.ft. Rudder area : appr. 0.47 m² appr. 5.1 sq.ft.
Landing Gear
Track : appr. 2.97 m appr. 9 ft 9 in Wheelbase : appr. 1.68 m appr. 5 ft 6 in
Nose wheel : 5.00-5; 6 PR, 120 mph
Main wheel : (a) 6.00-6; 6 PR, 120 mph%
in combination with any MLG strut%
(b) 15 x 6.0-6; 6 PR, 160 mph%
only in combination with the "thin"% (MÄM 40-123/e) or the "tall" (OÄM 40-283)% MLG strut%
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 - 7
Page 24
General DA 40 AFM

1.5 DEFINITIONS AND ABBREVIATIONS

(a) Airspeeds
CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and
instrument errors. CAS equals TAS at standard atmospheric conditions at MSL. IAS: Indicated Airspeed as shown on an airspeed indicator. KCAS: CAS in knots. KIAS: IAS in knots. TAS: True Airspeed. The speed of the airpl ane relative to the air. TAS is CAS
corrected for errors due to altitude and temperature. vA: Maneuvering Speed. Full or abrupt control surface movement is not permissible
above this speed. vFE: Max. Flaps Extended Speed. This speed must not be exceeded with the given
flap setting. vNE: Never Exceed Speed in smooth air. This speed must not be exceeded in any
operation. v
NO
Maximum Structural Cruising Speed. This speed may be exceeded only in
smooth air, and then only with caution. vS: Stalling Speed, or the minimum continuous speed at which the airplane is still
controllable in the given configuration. v
: Stalling Speed, or the minimum continuous speed at which the airplane is still
S0
controllable in the landing configuration. vx: Best Angle-of-Climb Speed. vy: Best Rate-of-Climb Speed.
Page 1 - 8 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
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DA 40 AFM General
(b) Meteorological Terms
ISA: International Standard Atmosphere. Conditions at which air is
identified as an ideal dry gas. The temperature at mean sea level is 15 EC (59 °F), air pressure at MSL is 1013.25 hPa (29.92 inHg); the temperature gradient up to the altitude at which the temperature reaches -56.5 EC (-69.7 °F) is -0.0065 EC/m (-0.00357 °F/ft), and
above this 0 EC/m (0 °F/ft). MSL: Mean Sea Level. OAT: Outside Air Temperature. QNH: Theoretical atmospheric pressure at MSL, calculated from the
elevation of the measuring point above MSL and the actual
atmospheric pressure at the measuring point. Indicated Pressure Altitude:
Altitude reading with altimeter set to 1013.25 hPa (29.92 inHg). Pressure Altitude: Altitude above MSL, indicated by a barometric altimeter which is set
to 1013.25 hPa (29.92 inHg). The Pressure Altitude is the Indicated
Pressure Altitude corrected for installation and instrument errors.
In this Airplane Flight Manual altimeter instrument errors are regarded
as zero. Density Altitude: Altitude in ISA conditions at which the air density is equal to the
current air density. Wind: The wind speeds which are shown as variables in the diagrams in
this manual should be regarded as headwind or downwind
components of the measured wind.
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General DA 40 AFM
(c) Flight Performance and Flight Planning
Demonstrated Crosswind Component:
The speed of the crosswind component at which adequate maneuverability for take-off and landing has been demonstrated during
type certification. MET: Weather, weather advice. NAV: Navigation, route planning.
(d) Mass and Balance (M&B, W&B)
DP: Datum Plane; an imaginary vertical plane from which all horizontal
distances for center of gravity calculations are measured. Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravity
of a component. Moment: The mass of a component multiplied by its moment arm. CG: Center of Gravity, also called 'center of mass'. Imaginary point in which
the airplane mass is assumed to be concentrated for mass and balance
calculations. Its distance from the Datum Plane is equal to the Center
of Gravity Moment Arm. Center of Gravity Moment Arm:
The Moment Arm which is obtained if one divides the sum of the individual
moments of the airplane by its total mass. Center of Gravity Limits:
The Center of Gravity range within which the airplane, at a given mass,
must be operated.
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DA 40 AFM General
Usable Fuel: The quantity of fuel available for flight planning. Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight. Empty Mass: The mass of the airplane including unusable fuel, all operating
consumables and the maximum quantity of oil. Useful Load: The difference between take-off mass and empty mass. Maximum Take-off Mass:
The maximum permissible mass for take-off. Maximum Landing Mass:
The highest mass for landing conditions at the maximum descent velocity.
This velocity was used in the strength calculations to determine the
landing gear loads during a particularly hard landing.
(e) Engine
Take-off Power:
Maximum permissible engine output power for take-off. Maximum Continuous Power:
Maximum permissible engine output power used continuously during
flight. CHT: Cylinder Head Temperature. EGT: Exhaust Gas Temperature.
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General DA 40 AFM
(f) Designation of the Circuit Breakers on the Instrument Panel
Asymmetric Instrument Panel (Circuit Breakers Right Hand)
AVIONICS:
ADF Automatic Direction Finder AUDIO Audio Panel / Intercom AUTOPILOT Autopilot AVIONIC BUS Avionic Bus DME Distance Measuring Equipment ESSENTIAL AVIONIC Essential Avionic Bus GPS Global Positioning System GPS2 Global Positioning System #2
ENGINE:
NAV/COM1 Navigation/Communication #1 NAV/COM2 Navigation/Communication #2 STRIKE Strike Finder XPDR Transponder
IGNITION Ignition INST. 1 Engine Instrument VM 1000 START Starter
Page 1 - 12 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
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DA 40 AFM General
LIGHTING:
FLOOD Flood Light INST. Instrument Lights LANDING Landing Light POSITION Position Lights STROBE Strobe Light (=Anti Collision Light = ACL) TAXI/MAP Taxi Light/Map Light
SYSTEMS:
ANNUN. Annunciator Panel DG Directional Gyro FAN/OAT Fan/Outside Air Temperature Indicator FLAPS Flaps FUEL PUMP Fuel Pump HORIZON Artificial Horizon (Attitude Gyro) PITOT HEAT Pitot Heating System T&B Turn & Bank Indicator
ELECTRICAL:
ALT. Alternator ALT. CONT. Alternator Control ALT. PROT. Alternator Protection BATT. Battery ESSENTIAL TIE Bus Interconnection MAIN TIE Bus Interconnection MASTER CONTROL Master Control (avionic master switch, essential bus
switch, essential avionics relay, bus interconnection relay, avionics master relay)
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General DA 40 AFM
Symmetric Instrument Panel (Circuit Breakers Bottom Side)
MAIN BUS:
ALT. Alternator ALT. CONT. Alternator Control ALT. PROT. Alternator Protection AV. BUS Avionic Bus DG Directional Gyro FAN/OAT Fan/Outside Air Temperature Indicator FUEL PUMP Fuel Pump IGNITION Ignition INST. Instrument Lights MAIN TIE Bus Interconnection POSITION Position Lights START Starter STROBE Strobe Lights (Anti Collision Lights, ACLs) T & B Turn & Bank Indicator TAXI/MAP Taxi Light/Map Light
Page 1 - 14 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
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DA 40 AFM General
MAIN AV. BUS (Main Avionic Bus):
ADF Automatic Direction Finder AUDIO Audio Panel / Intercom AUTO PILOT Autopilot COM2 Communication #2 COM/NAV2 Communication / Navigation #2 DME Distance Measuring Equipment GPS2 Global Positioning System #2 GPS/NAV2 Global Positioning System/Navigation #2 STRIKE Strike Finder Wx 500 Stormscope TAS Traffic Advisory System%
ESS. AV. BUS (Essential Avionic-Bus):
COM1 Communication #1 COM/NAV1 Communication/Navigation #1 GPS1 Global Positioning System #1 GPS/NAV1 Global Positioning System/Navigation #1 XPDR Transponder
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General DA 40 AFM
ESSENTIAL BUS:
ANNUN. Annunciator Panel BATT. Battery ESS. AV. Essential Avionic-Bus ESS TIE Bus Interconnection FLAPS Flaps FLOOD Flood Light HORIZON Artificial Horizon (Attitude Gyro) INST. 1 Engine Instrument VM 1000 LANDING Landing Light MASTER CONTROL Master Control (avionic master switch, essential bus
switch, essential avionics relay, bus interconnection relay, avionics master relay)
PITOT Pitot Heating System
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DA 40 AFM General
(g) Equipment
ELT: Emergency Locator Transmitter.
(h) Design Change Advisories
MÄM: Mandatory Design Change Advisory. OÄM: Optional Design Change Advisory.
(i) Miscellaneous
ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation). ATC: Air Traffic Control. CFRP: Carbon Fiber Reinforced Plastic. GFRP: Glass Fiber Reinforced Plastic. JAR: Joint Aviation Requirements. JC/VP: Joint Certification/Validation Procedure. PCA: Primary Certification Authority.
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General DA 40 AFM

1.6 UNITS OF MEASUREMENT

1.6.1 CONVERSION FACTORS

Dimension SI-Units US Units Conversion
Length [mm] millimeters
[m] meters [km] kilometers
Volume [l] liters [US gal] US gallons
Speed [km/h] kilometers
per hour
[m/s] meters per
second
Speed of rotation
Mass [kg] kilograms [lb] pounds [kg] x 2.2046 = [lb] Force,
weight
[RPM] revolutions per minute
[N] newtons [lbf] pounds force [N] x 0.2248 = [lbf]
[in] inches [ft] feet [NM] nautical
miles
[qts] US quarts [kts] knots
[mph] miles per
hour
[fpm] feet per
minute
[mm] / 25.4 = [in] [m] / 0.3048 = [ft] [km] / 1.852 = [NM]
[l] / 3.7854 = [US gal] [l] / 0.9464 = [qts]
[km/h] / 1.852 = [kts] [km/h] / 1.609 = [mph] [m/s] x 196.85 = [fpm]
--
Pressure [hPa] hecto-
pascals [mbar]millibars [bar] bars
Temperature [°C] degrees
Celsius
Page 1 - 18 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
[inHg] inches of
mercury
[psi] pounds per
square inch
[°F] degrees
Fahrenheit
[hPa] = [mbar] [hPa] / 33.86 = [inHg] [bar] x 14.504 = [psi]
[°C]x1.8 + 32 = [°F] ([°F] - 32)/1.8 = [°C]
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DA 40 AFM General
Dimension SI-Units US Units Conversion
Intensity of electric current
Electric charge (battery capacity)
Electric potential
Time [sec] seconds --
[A] ampères
[Ah] ampère-hours
[V] volts
--
--
--
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General DA 40 AFM

1.6.2 CONVERSION CHART LITERS / US GALLONS

Liters US Gallons US Gallons Liters
5 1.3 1 3.8 10 2.6 2 7.6 15 4.0 4 15.1 20 5.3 6 22.7 25 6.6 8 30.3 30 7.9 10 37.9 35 9.2 12 45.4 40 10.6 14 53.0 45 11.9 16 60.6 50 13.2 18 68.1 60 15.9 20 75.7 70 18.5 22 83.3 80 21.1 24 90.9 90 23.8 26 98.4
100 26.4 28 106.0 110 29.1 30 113.6 120 31.7 32 121.1 130 34.3 34 128.7 140 37.0 36 136.3 150 39.6 38 143.8 160 42.3 40 151.4 170 44.9 45 170.3 180 47.6 50 189.3
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DA 40 AFM General

1.7 THREE-VIEW DRAWING

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General DA 40 AFM

1.8 SOURCE DOCUMENTATION

This Section lists documents, manuals and other literature that were used as sources for the Airplane Flight Manual, and indicates the respective publisher. However, only the information given in the Airplane Flight Manual is valid.

1.8.1 ENGINE

Address: Textron Lycoming
652 Oliver Street WILLIAMSPORT, PA 17701
USA Phone: +1-570-323-6181 Webpage: www.lycoming.textron.com
Documents: a) Textron Lycoming Operator’s Manual, Aircraft Engines
60297-12 (Part No.)
b) Service Bulletins (SB)
Service Instructions (SI); (e.g. SI 1014, SI 1070) Service Letters (SL); (e.g. SL114 (subscriptions))
Page 1 - 22 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
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DA 40 AFM General

1.8.2 PROPELLER

Address: mt-Propeller
Airport Straubing Wallmühle D-94348 ATTING GERMANY
Phone: +49-9429-9409-0 E-mail: [email protected] Webpage: www.mt-propeller.de
Documents: E-124, Operation and Installation Manual
Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25

1.8.3 ENGINE INSTRUMENTS

Address: VISION MICROSYSTEMS, INC.
ADVANCED ELECTRONIC INSTRUMENTATION 4071 Hannegan Road, Suite T BELLINGHAM, WA 98226
USA Phone: +1-360-714-8203 Documents: 5010002 REV F, VM 1000 Owner’s Manual
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 - 23
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General DA 40 AFM

1.8.4 IGNITION CONTROL UNIT

The electronic ignition control unit LASAR is optional equipment. Address: UNISON Industries
7575 Baymeadows Way JACKSONVILLE, FL 32256 USA
Phone: +1-904-739-4066 Webpage: www.unisonindustries.com
Documents: L-1502
LASAR Installation, Operation, and Troubleshooting Manual
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DA 40 AFM
Limitations
CHAPTER 2

OPERATING LIMITATIONS

2.1 INTRODUCTION .......................................2-2
2.2 AIRSPEED ............................................2-3
2.3 AIRSPEED INDICATOR MARKINGS ........................2-4
2.4 POWER-PLANT LIMITATIONS ............................2-5
2.5 ENGINE INSTRUMENT MARKINGS ........................2-7
Operating
Page
2.6 WARNING, CAUTION AND STATUS LIGHTS.................2-9
2.7 MASS (WEIGHT) ......................................2-11
2.8 CENTER OF GRAVITY .................................2-13
2.9 APPROVED MANEUVERS ..............................2-14
2.10 MANEUVERING LOAD FACTORS ........................2-16
2.11 OPERATING ALTITUDE ................................2-17
2.12 FLIGHT CREW........................................2-17
2.13 KINDS OF OPERATION.................................2-18
2.14 FUEL................................................2-22
2.15 LIMITATION PLACARDS ................................2-24
2.16 OTHER LIMITATIONS ..................................2-32
2.16.1 TEMPERATURE.................................2-32
2.16.2 BATTERY CHARGE..............................2-32
2.16.3 EMERGENCY SWITCH ...........................2-32
2.16.4 OPERATION TIME OF ELECTRICAL EQUIPMENT .....2-32
2.16.5 DOOR LOCKING DEVICE .........................2-33
2.16.6 ELECTRONIC EQUIPMENT........................2-33
2.16.7 USE OF THE SUN VISORS ........................2-33'
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approved
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Operating
DA 40 AFM
Limitations

2.1 INTRODUCTION

Chapter 2 of this Airplane Flight Manual includes operating limitations, instrument markings, and placards necessary for safe operation of the airplane, its power-plant, standard systems and standard equipment.
The limitations included in this Chapter are approved.
WARNING
Operation of the airplane outside of the approved operating limitations is not permissible.
Page 2 - 2 Rev. 8 01-Dec-2010
EASA
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Doc. # 6.01.01-E
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DA 40 AFM

2.2 AIRSPEED

Airspeed IAS Remarks
v
Maneuvering
A
speed
108 KIAS
(above 980 kg / 2161 lb up to 1150 kg / 2535 lb)
94 KIAS
(780 kg / 1720 lb
up to 980 kg / 2161 lb)
If MÄM 40-227 is carried'
out: '
Operating
Limitations
Do not make full or abrupt control surface movement above this speed.
111 KIAS'
(above 1036 kg /2284 lb'
up to 1200 kg / 2646 lb)'
'
94 KIAS'
(780 kg / 1720 lb'
up to 1036 kg / 2284 lb)'
v
Max. flaps ex-
FE
tended speed
v
Max. structural
NO
=
cruising speed
v
C
v
Never exceed
NE
speed in smooth
LDG: 91 KIAS
T/O: 108 KIAS
Do not exceed these speeds with the given flap setting.
129 KIAS Do not exceed this speed
except in smooth air, and then only with caution.
178 KIAS Do not exceed this speed in
any operation.
air
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Operating
DA 40 AFM
Limitations

2.3 AIRSPEED INDICATOR MARKINGS

Marking IAS Significance
White arc 49 KIAS - 91 KIAS Operating range with flaps fully extended.
Green arc 52 KIAS - 129 KIAS Normal operating range.
Yellow arc 129 KIAS - 178 KIAS ‘Caution’ range - “Only in smooth air”.
Red line 178 KIAS Maximum speed for all operations - vNE.
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Doc. # 6.01.01-E
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DA 40 AFM

2.4 POWER-PLANT LIMITATIONS

a) Engine manufacturer : Textron Lycoming b) Engine designation : IO-360 M1-A c) RPM limitations
Max. take-off RPM : 2700 RPM Max. continuous RPM : 2400 RPM
d) Manifold pressure limitations
Maximum : FULL throttle
e) Oil pressure
Minimum (IDLE) : 25 PSI / 1.72 bar
Operating
Limitations
Maximum : 98 PSI / 6.76 bar Normal operating range : 55 to 95 PSI / 3.8 to 6.55 bar
f) Oil quantity
Minimum : 4 qts Maximum : 8 qts
g) Oil temperature
Maximum : 245 °F (118 °C)
h) Fuel pressure
Minimum : 14 PSI / 0.97 bar Maximum : 35 PSI / 2.4 bar
i) Cylinder head temperature
Maximum : 500 °F (260 °C)
j) Propeller manufacturer : mt-Propeller
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Operating
DA 40 AFM
Limitations
k) Propeller designation : MTV-12-B/180-17 or
MTV-12-B/180-17f
l) Propeller diameter : 1.80 m (+ 0 mm, - 50 mm)
5 ft 10.9 in (+ 0.0 in, - 2.0 in) m) Propeller pitch angle (0.75 R) : 10.5° to 30° n) Oil specification: Airplane engine oil should be used which meets SAEJ1899 (MIL-L-22851) Standard
(ashless dispersant type). During the first 50 hours of operation of a new or newly overhauled engine, or after replacement of a cylinder, airplane engine oil should be used which meets SAEJ1966 (MIL-L-6082) Standard (straight mineral type). The viscosity should be selected according to the recommendation given in the following table:
During the first 50 hours:
OAT at Ground Level
All temperatures --- SAE 15-W50, SAE 20-W50 above 80 °F
(above 27 °C) above 60 °F
(above 16 °C) 30 °F to 90 °F
(-1 °C to 32 °C) 0 °F to 90 °F
(-18 °C to 32 °C) 0 °F to 70 °F
(-18 °C to 21 °C)
SAEJ1966 / MIL-L-6082 Mineral Oil
SAE 60 SAE 60
SAE 50 SAE 40 or SAE 50
SAE 40 SAE 40
SAE 20-W50 SAE 20-W50 or SAE 15-W50
SAE 30
After 50 hours:
SAEJ1899 / MIL-L-22851 Ashless Dispersant Oil
SAE 30, SAE 40, or SAE 20-W40
below 10 °F (below -12 °C)
Page 2 - 6 Rev. 8 01-Dec-2010
SAE 20 SAE 30 or SAE 20-W30
EASA
approved
Doc. # 6.01.01-E
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Operating
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Limitations

2.5 ENGINE INSTRUMENT MARKINGS

Engine instrument markings and their color code significance are shown in the table below:
NOTE
When an indication lies in the upper or lower prohibited range, the numerical indication will begin flashing as well.
Red
arc/bar
Indi-
cation
Manifold pressure
RPM -- -­Oil
temp. Cylinder
head temp.
Oil pressure
Fuel pressure
=
lower
prohibited
range
-- -- 13 - 30 inHg -- --
-- -- 149 - 230 °F 231 - 245 °F above 245 °F
-- -- 150 - 475 °F 476 - 500 °F above 500 °F
below
25 PSI
below
14 PSI
Yellow
arc/bar
caution
range
25 - 55 PSI 56 - 95 PSI 96 - 97 PSI above 97 PSI
Green
arc/bar
=
-- 14 - 35 PSI -- above 35 PSI
=
normal
operating
range
500 - 2400
RPM
Yellow
arc/bar
=
caution
range
2400 - 2700
RPM
Red
arc/bar
=
upper
prohibited
range
above 2700
RPM
Fuel flow
Voltage Ammeter -- -- 2 - 75 A -- --
Doc. # 6.01.01-E Rev. 8 01-Dec-2010
-- --
below
24.1 V
24.1 - 25 V 25.1 - 30 V 30.1 - 32 V above 32 V
1 - 20
US gal/hr
--
EASA
approved
above 20 US gal/hr
Page 2 - 7
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Operating Limitations
DA 40 AFM
Indi-
cation
Fuel quantity, Standard
Red
arc/bar
=
lower
prohibited
range
Yellow
arc/bar
caution
range
0 US gal --
=
Green
arc/bar
=
normal
operating
range
0 - 15 US gal 0 - 17 US gal
1
2
Yellow arc/bar
=
caution
range
-- --
Red
arc/bar
=
upper
prohibited
range
Tank Fuel
quantity, Long Range
0 US gal --
0 - 16 US gal
+
0 - 9 US gal
3
-- --
Tank
1
up to and including serial number 40.054
2
serial number 40.055 and subsequent
3
numerical indication of the additional (auxiliary) fuel quantity, for a total fuel quantity on one side in the range between 16 and 25 US gal
Page 2 - 8 Rev. 8 01-Dec-2010
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EASA
Doc. # 6.01.01-E
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Operating
DA 40 AFM
Limitations

2.6 WARNING, CAUTION AND STATUS LIGHTS

The following tables show the color and significance of the warning, caution and status lights on the annunciator panel. There are two variants of the annunciator panel, 'DAI' and 'White Wire' (see Section 7.11).
NOTE
Section 7.11 includes a detailed description of the lights on the annunciator panel.
Color and Significance of the Warning Lights (Red)
Warning Lights (Red)
Variant
'DAI'
OIL PR OIL PRESS Oil pressure Oil pressure below 25 PSI FUEL PR FUEL PRESS Fuel pressure Fuel pressure below 14 PSI
ALT ALTERNATOR
START START Starter
DOOR DOORS Doors
Variant
'White Wire'
TRIM FAIL Trim failure
Meaning
Alternator (Generator)
Alternator failure
Operation of starter, or failure of the starter motor to disengage from the engine after starting
Front canopy and/or rear door not completely closed and locked
Failure in the automatic trim system of the autopilot (if installed)
Cause
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Operating Limitations
Color and Significance of the Caution Lights (Amber)
Caution Lights (Amber)
DA 40 AFM
Variant
'DAI'
L FUEL
R FUEL
VOLT LOW VOLTS Voltage On-board voltage below 24 V
PITOT PITOT Pitot heating
Variant
'White Wire'
LOW FUEL Fuel quantity
Meaning
Fuel quantity left tank
Fuel quantity right tank
Fuel quantity in the left tank less than 3 US gal (±1 US gal)
Fuel quantity in the right tank less than 3 US gal (±1 US gal)
1st caution: fuel quantity in one tank less
than 3 US gal (±1 US gal) 2nd caution: fuel quantity in second tank
less than 3 US gal (±1 US gal)
Pitot heating not switched ON, or fault in the Pitot heating system
Cause
Color and Significance of the Status Light (White)
Status Light (White)
Variant
'DAI'
IGN IGNITION Ignition
Page 2 - 10 Rev. 8 01-Dec-2010
Variant
'White Wire'
Meaning
Cause
Electronic ignition control unit (if installed) not in operation
EASA
approved
Doc. # 6.01.01-E
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Operating
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Limitations

2.7 MASS (WEIGHT)

Maximum take-off mass (Normal Category) : 1150 kg 2535 lb
if MÄM 40-227 is carried out : 1200 kg 2646 lb' Maximum take-off mass (Utility Category) : 980 kg 2161 lb Maximum landing mass
Original MLG strut : 1092 kg 2407 lb
Modified MLG strut
(MÄM 40-123/e or OÄM 40-283) : 1150 kg 2535 lb' Maximum zero fuel mass : 1150 kg 2535 lb' Max. load in standard baggage compartment : 30 kg 66 lb
Max. load in baggage tube : 5 kg 11 lb Max. load in extended baggage compartment (OÄM 40-163)
Max. load in forward part : 45 kg 100 lb
Max. load in aft part : 18 kg 40 lb
Max. total load forward + aft : 45 kg 100 lb Max. surface load for baggage compartments : 75 kg/m² 15.3 lb/ft²
WARNING
Exceeding the mass limits will lead to an overstressing of the airplane as well as to a degradation of flight characteristics and flight performance.
NOTE
The maximum landing mass is the highest mass for landing conditions at the maximum descent velocity. This velocity was used in the strength calculations to determine the landing gear loads during a particularly hard landing.
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Operating Limitations
DA 40 AFM
NOTE
In some countries the beginning of a flight is defined by starting the engine. In those countries a maximum ramp mass 4 kg (9 lb) above the maximum take-off mass is approved.' At the time of lift-off the maximum permitted take-off mass must not be exceeded.
Page 2 - 12 Rev. 8 01-Dec-2010
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Operating
DA 40 AFM
Limitations

2.8 CENTER OF GRAVITY

Datum Plane
The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight. The airplane’s longitudinal axis is parallel with the upper surface of a 600:31 wedge which is placed on top of the rear fuselage in front of the vertical stabilizer. When the upper surface of the wedge is aligned horizontally, the Datum Plane is vertical. The Datum Plane is located 2.194 meters (86.38 in) forward of the most forward point of the root rib on the stub wing.
Center of Gravity Limitations
The center of gravity (CG) for flight conditions must lie between the following limits: Most forward CG:
2.40 m (94.5 in) aft of DP from 780 kg to 980 kg (1720 lb to 2161 lb)
2.46 m (96.9 in) aft of DP at 1150 kg (2535 lb)
linear variation between these values If MÄM 40-227 is carried out:'
2.40 m (94.5 in) aft of DP from 780 kg to 980 kg (1720 lb to 2161 lb)'
2.48 m (97.6 in) aft of DP at 1200 kg (2646 lb)'
linear variation between these values' Most rearward CG:
a) Standard Tank : 2.59 m (102.0 in) aft of DP
b) Long Range Tank : 2.55 m (100.4 in) aft of DP
WARNING
Exceeding the center of gravity limitations reduces the controllability and stability of the airplane.
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Limitations

2.9 APPROVED MANEUVERS

The airplane is certified in the Normal Category and in the Utility Category in accordance with JAR-23.
Approved Maneuvers
a) Normal Category:
1) All normal flight maneuvers;
2) Stalling (with the exception of dynamic stalling); and
3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 60° is attained.
CAUTION
Aerobatics, spinning, and flight maneuvers with more than 60° of bank are not permitted in the Normal Category.
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DA 40 AFM
b) Utility Category:
1) All normal flight maneuvers;
2) Stalling (with the exception of dynamic stalling); and
3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 90° is attained.
Aerobatics, spinning, and flight maneuvers with more than 90° of bank are not permitted in the Utility Category.
Operating
Limitations
CAUTION
CAUTION
The accuracy of the attitude gyro (artificial horizon) and the directional gyro is affected by the maneuvers approved under item 3 if the bank angle exceeds 60°. Such maneuvers may therefore only be flown when the above mentioned instruments are not required for the present kind of operation.
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Operating Limitations

2.10 MANEUVERING LOAD FACTORS

Table of maximum structural load factors:
Normal Category
DA 40 AFM
at v
A
at v
NE
or LDG Position
Positive 3.8 3.8 2.0 Negative -1.52 0
Utility Category
With Flaps in T/O
With Flaps in T/O
at v
A
at v
NE
or LDG Position
Positive 4.4 4.4 2.0 Negative -1.76 -1
WARNING
Exceeding the maximum load factors will lead to an overstressing of the airplane.
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Operating
DA 40 AFM
Limitations

2.11 OPERATING ALTITUDE

The maximum demonstrated operating altitude is 16,400 ft (5,000 m). The maximum approved operating altitude for US registered airplanes is 14,000 ft MSL
unless an approved supplemental oxygen system is installed.

2.12 FLIGHT CREW

Minimum crew number : 1 (one person) Maximum number of occupants:
Normal Category : 4 (four persons) Utility Category : 2 (two persons), both of whom must sit in front
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Operating
DA 40 AFM
Limitations

2.13 KINDS OF OPERATION

Provided that national operational requirements are met, the following kinds of operation are approved:
* Daytime flights according to Visual Flight Rules (VFR). * With the appropriate equipment: night flights according to Visual Flight Rules
(NVFR).
* With the appropriate equipment: flights according to Instrument Flight Rules
(IFR).
Flights into known or forecast icing conditions are prohibited. Flights into known thunderstorms are prohibited.
Minimum Operational Equipment (Serviceable)
The following table lists the minimum serviceable equipment required by JAR-23. Additional minimum equipment for the intended operation may be required by national operating rules and also depends on the route to be flown.
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DA 40 AFM
Operating
Limitations
Minimum Operational Equipment (Serviceable)
Flight and Naviga­tion Instru­ments
Engine Instru­ments
For Daytime
VFR Flights
* Airspeed
indicator * Altimeter * Magnetic
compass
* Fuel indicators * Integrated
engine
instrument
In Addition
for Night VFR Flights
* Vertical speed indicator (VSI) * Attitude gyro (artificial horizon) * Turn & bank indicator * Directional gyro * OAT indicator * Chronometer with indication of
hours, minutes, and seconds
* VHF radio (COM) with speaker
and microphone * VOR receiver * Transponder (XPDR),
Mode A and Mode C * 1 headset
* Ammeter (included in VM 1000) * Voltmeter (included in
VM 1000)
In addition
for IFR Flights
* Second VHF
radio (COM)
* VOR-LOC-
GP receiver
* Marker
beacon receiver
* Annunciator
panel (all lights, see 2.6)
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Operating Limitations
DA 40 AFM
Minimum Operational Equipment (Serviceable)
For Daytime
VFR Flights
Lighting * Position lights
* Strobe lights (anti collision
lights) * Landing light * Instrument lighting * Flood light * Flashlight
Other Opera­tional Minimum Equip­ment
* Stall warning
system
* Fuel quantity
measuring device (see
7.10)
* Safety belts for
each occupied seat
* Pitot heating system * Alternate static valve * Essential bus
In Addition
for Night VFR Flights
In addition
for IFR Flights
* Emergency
battery
* Airplane flight
manual
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DA 40 AFM
Operating
Limitations
NOTE
A list of approved equipment can be found in Chapter 6.
NOTE
For the upgrade of an airplane for Night VFR or IFR operation it is not sufficient to install the required equipment. The retrofit must be carried out in accordance with the requirements of the manufacturer (see Service Bulletins) and the national Airworthiness Authority. Any additional equipment (equipment which is not listed in the Equipment List in Section 6.5) must also be approved for the intended kind of operation by the national Airworthiness Authority.
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Operating Limitations

2.14 FUEL

Fuel Grade AVGAS 100LL
Fuel Quantity
a) Standard Tank:
Total fuel quantity : 2 x 20.6 US gal (app. 2 x 78 liter) Unusable fuel : 2 x 0.5 US gal (app. 2 x 2 liter) Max. indicated fuel quantity:
DA 40 AFM
up to and incl. serial no. 40.054 : 15 US gal (app. 57 liter) per tank serial no. 40.055 & subsequent : 17 US gal (app. 64 liter) per tank
Max. permissible difference between right and left tank : 10 US gal (app. 38 liter)
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DA 40 AFM
b) Long Range Tank (if installed):
Total fuel quantity : 2 x 25.5 US gal (app. 2 x 96.5 liter) Unusable fuel : 2 x 0.5 US gal (app. 2 x 2 liter) Max. indicated fuel quantity : 16 US gal (app. 61 liter) per tank Indicated quantity auxiliary
fuel tank : 0 to 9 US gal (app. 0 to 34 liter) per tank Max. permissible difference
between right and left tank : 8 US gal (app. 30 liter)
Operating
Limitations
CAUTION
If a fuel indicator shows 16 US gal and the aux. fuel indicator reads 0 US gal on the same side, then 19 US gal must be assumed for the calculation of the difference between right and left tank.
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Operating
DA 40 AFM
Limitations

2.15 LIMITATION PLACARDS

All limitation placards are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 6.02.01), Chapter 11.
On the Instrument Panel:
If MÄM 40-227 is not carried out:'
Maneuvering speed:
vA = 108 KIAS (above 980 up to 1150 kg / above 2161 up to 2535 lb) vA = 94 KIAS (780 to 980 kg / 1720 to 2161 lb)
This airplane may only be operated in accordance with the Airplane Flight Manual. It can be operated in the “Normal” and “Utility” categories in non­icing conditions. Provided that national operational requirements are met and the appropriate equipment is installed, this airplane is approved for the following kinds of operation: day VFR, night VFR and IFR. All aerobatic maneuvers including spinning are prohibited.
For further operational limitations refer to the Airplane Flight Manual. No smoking.
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DA 40 AFM
If MÄM 40-227 is carried out:'
Maneuvering Speed: vA = 111 KIAS (above 1036 up to 1200 kg, above 2284 up to 2646 lb)' vA = 94 KIAS (780 to 1036 kg, 1720 to 2284 lb)' The airplane may only be operated in accordance with the Airplane Flight Manual. It can be operated in the „Normal“ and the „Utility“ categories in non-icing conditions. Provided that national operational requirements are met and the appropriate equipment is installed, this airplane is approved for the following kinds of operation: day VFR, night VFR and IFR. All aerobatic maneuvers including spinning are prohibited.
Operating
Limitations
For further operational limitations refer to the Airplane Flight Manual. No smoking.'
Next to Each of the Two Fuel Filler Necks:
a) Standard Tank:
AVGAS 100LL
76 l / 20 US gal.
b) Long Range Tank (if installed):
AVGAS 100LL
94 l / 25 US gal.
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Operating Limitations
Next to the Fuel Quantity Indication:
a) Standard Tank:
Up to serial number 40.054:
max. indicated fuel quantity: 15 US gal
left and right tank max. 10 US gal difference
For use of max. tank capacity see AFM
Serial number 40.055 and subsequent:
max. indicated fuel quantity: 17 US gal
left and right tank max. 10 US gal difference
For use of max. tank capacity see AFM
DA 40 AFM
b) Long Range Tank (if installed):
Fuel qty. indication: 16 + 9 US gal
max. difference LH/RH tank: 8 US gal
AUX FUEL QTY switch for LH/RH auxiliary fuel quantity
NOTE: See AFM for more information on AUX FUEL
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DA 40 AFM
On the Fuel Tank Selector:
a) Standard Tank:
Operating
Limitations
b) Long Range Tank (if installed):
F
L
25 US gal. 25 US gal. 94 l 94 l
e
l
S
l
e
u
T
F
E
e
c
t
o
r
F
F
O
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Operating Limitations
In the Cowling, on the Door for the Oil Filler Neck:
DA 40 AFM
OIL
ashless dispersant aviation
grade oil (SAE Standard J-1899)
Next to the Flap Selector Switch:
max.
108 KIAS
1 qt = 0.95 liters
SAE 15W50
or see AFM Chapter 2
VFR Min./Max.: 4/8 qts
IFR Min./Max.: 6/8 qts
max.
91 KIAS
Next to the Essential Bus Switch (if installed):
Ess. Bus NOT for normal operation. See AFM.
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DA 40 AFM
In the Cockpit, on the Left Fuselage Sidewall: (if alternate static valve is installed):
Operating
Limitations
Next to the Baggage Compartment:
a) Standard Baggage Compartment:
max.
30 kg /
66 lbs
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Operating Limitations
b) Extended Baggage Compartment (OÄM 40-163, if installed):
DA 40 AFM
FORWARD BAGGAGE
COMPARTMENT
MAX. 45 kg [100 lb]
ARM: 3.89 m [153.1"]
MAX. BAGGAGE TOTAL 45 kg [100 lb] MAX. SURFACE LOAD: 75 kg/m² [15 lb/sq.ft.]
CAUTION: OBSERVE WEIGHT AND BALANCE LIMITATIONS
SEE AIRPLANE FLIGHT MANUAL CHAPTER 6
AFT BAGGAGE COMPARTMENT MAX. 18 kg [40 lb] ARM: 4.54 m [178.7"]
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DA 40 AFM
Beside the Door Locking Device (OÄM 40-081, if installed):
EMERGENCY EXIT:
The keylock must be
unlocked during flight!
Above the NAV #2 CDI (OÄM 40-206, if installed):
NAV No. 2 not approved
for precision approaches
Operating
Limitations
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Operating Limitations

2.16 OTHER LIMITATIONS

2.16.1 TEMPERATURE

The airplane may only be operated when its temperature prior to operation is not less' than -40 °C (-40 °F) and not higher than 54 °C (129 °F).'
For cold weather starting of the engine refer to the latest instructions given by the engine manufacturer.
DA 40 AFM
CAUTION

2.16.2 BATTERY CHARGE

Taking off for a Night VFR or IFR flight with an empty battery is not permitted. The use of an external power supply for engine starting with an empty airplane battery
is not permitted if the subsequent flight is intended to be an IFR flight. In this case the airplane battery must first be charged.

2.16.3 EMERGENCY SWITCH

IFR flights are not permitted when the seal on the emergency switch is broken.

2.16.4 OPERATION TIME OF ELECTRICAL EQUIPMENT

Following an alternator failure and with the essential bus (if installed) switched ON, it can be expected that the systems listed under 3.7.2 - FAILURES IN THE ELECTRICAL SYSTEM are supplied with power for half an hour. After this, electrical power is available
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Operating
DA 40 AFM
Limitations
for the attitude gyro (artificial horizon) and flood light for another 1.5 hours when the emergency power pack (if installed) is used.

2.16.5 DOOR LOCKING DEVICE

The canopy and the passenger door must not be blocked by the door locking device during operation of the airplane.

2.16.6 ELECTRONIC EQUIPMENT

The use and switching on of electronic equipment other than that which is part of the equipment of the airplane is not permitted, as it could lead to interference with the airplane’s avionics.
Examples of undesirable items of equipment are:
- Mobile telephones.
- Remote radio controls.
- Video screens employing CRTs.
- MiniDisc recorders when in the record mode. This list is not exhaustive. The use of laptop computers, including those with CD-ROM drives, CD and minidisc
players in the replay mode, cassette players and video cameras is permitted. All this equipment however should be switched off for take-off and landing.

2.16.7 USE OF THE SUN VISORS'

The sun visors (if installed, OÄM 40-327) may only be used during cruise. During all other' phases of flight the sun visors must be locked in the fully upward position.'
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Operating Limitations
DA 40 AFM
Intentionally left blank.
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Emergency
DA 40 AFM
Procedures
CHAPTER 3

EMERGENCY PROCEDURES

3.1 INTRODUCTION .......................................3-3
3.1.1 GENERAL........................................3-3
3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES ..............3-4
3.2 ENGINE PROBLEMS....................................3-5
Page
3.2.1 ENGINE PROBLEMS ON THE GROUND ...............3-5
3.2.2 ENGINE PROBLEMS DURING TAKE-OFF ..............3-6
3.2.3 ENGINE PROBLEMS IN FLIGHT......................3-8
3.2.4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER
...............................................3-17
3.2.5 DEFECTIVE ENGINE CONTROLS ...................3-18
3.2.6 RESTARTING THE ENGINE WITH STATIONARY PROPELLER
...............................................3-20
3.3 SMOKE AND FIRE.....................................3-22
3.3.1 SMOKE AND FIRE ON THE GROUND ................3-22
3.3.2 SMOKE AND FIRE DURING TAKE-OFF ...............3-24
3.3.3 SMOKE AND FIRE IN FLIGHT.......................3-26
3.4 GLIDING.............................................3-28
3.5 EMERGENCY LANDINGS ...............................3-29
3.5.1 EMERGENCY LANDING WITH ENGINE OFF...........3-29
3.5.2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING
GEAR..........................................3-31
3.5.3 LANDING WITH DEFECTIVE BRAKES ................3-32
3.6 RECOVERY FROM AN UNINTENTIONAL SPIN..............3-33
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Emergency Procedures
3.7 OTHER EMERGENCIES ............................... 3-34
DA 40 AFM
3.7.1 ICING ......................................... 3-34
3.7.2 FAILURES IN THE ELECTRICAL SYSTEM ............ 3-35
3.7.3 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE
CABIN ........................................ 3-39
3.7.4 'DOOR'-WARNING LIGHT ON ...................... 3-40
3.7.5 EMERGENCY EXIT .............................. 3-41
NOTE
Procedures for uncritical system faults are given in Chapter 4B - ABNORMAL OPERATING PROCEDURES.
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Emergency
DA 40 AFM
Procedures

3.1 INTRODUCTION

3.1.1 GENERAL

This Chapter contains checklists as well as the description of recommended procedures to be followed in the event of an emergency. Engine failure or other airplane-related emergencies are most unlikely to occur if the prescribed procedures for pre-flight checks and airplane maintenance are followed.
If, nonetheless, an emergency does arise, the guidelines given here should be followed and applied in order to clear the problem.
As it is impossible to foresee all kinds of emergencies and cover them in this Airplane Flight Manual, a thorough understanding of the airplane by the pilot is, in addition to his knowledge and experience, an essential factor in the solution of any problems which may arise.
WARNING
In each emergency, control over the flight attitude and the preparation of a possible emergency landing have priority over attempts to solve the current problem ("first fly the aircraft"). Prior to the flight the pilot must consider the suitability of the terrain for an emergency landing for each phase of the flight. For a safe flight the pilot must constantly keep a safe minimum flight altitude. Solutions for various adverse scenarios should be thought over in advance. Thus it should be guaranteed that the pilot is at no time shocked by an engine failure and that he can act calmly and with determination.
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Emergency Procedures

3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES

DA 40 AFM
Flight Mass
Event
Engine failure after take-off (Flaps T/O)
Airspeed for best glide angle (Flaps UP)
Emergency landing with engine off
Flaps UP 60 KIAS 68 KIAS 73 KIAS 76 KIAS% Flaps T/O 59 KIAS 66 KIAS 72 KIAS 74 KIAS% Flaps LDG 58 KIAS 63 KIAS 71 KIAS 73 KIAS%
850 kg
1874 lb
59 KIAS 66 KIAS 72 KIAS 74 KIAS%
60 KIAS 68 KIAS 73 KIAS 76 KIAS%
1000 kg
2205 lb
1150 kg
2535 lb
1200 kg%
2646 lb%
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DA 40 AFM

3.2 ENGINE PROBLEMS

3.2.1 ENGINE PROBLEMS ON THE GROUND

1. Throttle ............................ IDLE
2. Brakes ............................. as required
3. Engine............................. switch off, if considered
CAUTION
Emergency
Procedures
necessary; otherwise establish the cause of the problem and re-establish engine performance
If the oil pressure is below the green sector, the engine must be switched off immediately.
If the problem cannot be cleared, the airplane must not be flown.
END OF CHECKLIST
WARNING
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Emergency Procedures

3.2.2 ENGINE PROBLEMS DURING TAKE-OFF

(a) Take-Off Can Still Be Aborted (Sufficient Runway Length Available)%
Land Straight Ahead:
1. Throttle............................. IDLE
On the Ground:
2. Brakes ............................. as required
CAUTION
DA 40 AFM
If sufficient time is remaining, the risk of fire in the event of a collision can be reduced as follows:
- Fuel tank selector ............ OFF
- Mixture control lever........... LEAN - shut engine off
- Ignition switch ............... OFF
- Master switch (ALT/BAT) ...... OFF%
CONTINUED
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DA 40 AFM
(b) Take-Off Can No Longer Be Aborted%
1. Airspeed ........................... 74 KIAS (1200 kg, 2646 lb)%
Emergency
Procedures
72 KIAS (1150 kg, 2535 lb) 66 KIAS (1000 kg, 2205 lb) 59 KIAS (850 kg, 1874 lb)
WARNING
If, in the event of an engine problem occurring during take-off, the take-off can no longer be aborted and a safe height has% not been reached, then a straight-ahead emergency landing
If Time Allows:
2. Fuel tank selector .................... check selected tank
3. Electrical fuel pump................... check ON
4. Ignition switch ....................... check BOTH
5. Throttle ............................ check MAX PWR
6. RPM lever .......................... check HIGH RPM
7. Mixture control lever .................. check RICH (leaner above
8. Alternate Air......................... OPEN
should be carried out. Turning back can be fatal.
5000 ft)
WARNING
If the problem does not clear itself immediately, and the engine is no longer producing sufficient power, then an emergency landing must be carried out.
END OF CHECKLIST
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Emergency Procedures

3.2.3 ENGINE PROBLEMS IN FLIGHT

(a) Engine Running Roughly
WARNING
An engine which is running very roughly can lead to the loss of the propeller. If the engine is running roughly operation% should only be continued if there is no other alternative.%
1. Airspeed ............................ 76 KIAS (1200 kg, 2646 lb)%
DA 40 AFM
73 KIAS (1150 kg, 2535 lb) 68 KIAS (1000 kg, 2205 lb) 60 KIAS (850 kg, 1874 lb)
2. Electrical fuel pump ................... check ON
3. Fuel tank selector .................... check selected tank
4. Engine instruments ................... check
5. Throttle............................. check
6. RPM lever .......................... check
7. Mixture control lever .................. set for smooth running
8. Alternate Air......................... OPEN
9. Ignition status light.................... check (only if the electronic
ignition control unit is installed)
10. Ignition switch ....................... check BOTH
CONTINUED
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DA 40 AFM
Procedures
11. Ignition circuit breaker (IGN) ............ pull (only if the electronic
ignition control unit is installed); if rough running is cleared by doing this, the circuit breaker should remain open
12. Throttle/RPM/Mixture ................. try various settings
WARNING
If the problem does not clear itself immediately, and the engine is no longer producing sufficient power, then an
Emergency
emergency landing should be carried out.
END OF CHECKLIST
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Emergency
DA 40 AFM
Procedures
(b) Loss of Oil Pressure
1. Check oil pressure warning light and oil pressure indicator.
2. Check oil temperature. 2a. If the oil pressure indication drops below the green sector and the oil temperature
is normal (oil pressure warning light does not illuminate or flash): * Monitor the oil pressure warning light: it is probable that the oil pressure
indication is defective.
* Monitor the oil and cylinder head temperatures.
2b. If the oil pressure indication drops below the green sector while the oil or cylinder
head temperature is rising, or If the oil pressure warning light illuminates or flashes, or If both of these occur together: * Reduce engine power to the minimum required. * Land as soon as possible. * Be prepared for engine failure and emergency landing.
2c. Oil pressure tending to zero combined with:
Vibration, loss of oil, possibly unusual metallic noise and smoke: * A mechanical failure in the engine is apparent. * Shut off engine immediately and * Carry out emergency landing in accordance with 3.5.1 - EMERGENCY
LANDING WITH ENGINE OFF.
END OF CHECKLIST
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DA 40 AFM
(c) High Oil Pressure
Check oil temperature.
* If the oil temperature is normal, it is probable that the fault lies in the oil
pressure indication, which should thus be ignored (the airplane should be serviced).
END OF CHECKLIST
(d) High Oil Temperature
Check cylinder head and exhaust gas temperature.
Emergency
Procedures
* If neither of these is high, it is probable that the fault lies in the oil temperature
indication. The airplane should be serviced. A stable oil temperature indication of 26 °F (-3 °C) or 317 °F (158 °C) suggests a failure of the oil% temperature sensor.
* If the cylinder head temperature or exhaust gas temperature is also high:
- Check oil pressure. If the oil pressure is low, proceed as in 3.2.3 (b ) ­LOSS OF OIL PRESSURE.
- If the oil pressure is in the green sector:
- Check mixture setting, enrich mixture if necessary.
- Reduce power; if this produces no improvement, land at the nearest
appropriate airfield.
END OF CHECKLIST
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Emergency Procedures
(e) High Cylinder Head Temperature
Cylinder head temperature in yellow sector or above:
1. Check mixture setting, enrich mixture if necessary.
2. Check oil temperature.
* If the oil temperature is also high:
- Check oil pressure. If the oil pressure is low, proceed as in 3.2.3 (b) ­LOSS OF OIL PRESSURE.
- If the oil pressure is in the green sector:
- Reduce power; if this produces no improvement, land at the nearest
DA 40 AFM
appropriate airfield.
- Be prepared for possible emergency landing.
END OF CHECKLIST
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DA 40 AFM
(f) High RPM
RPM moves on its own into the yellow sector, or is in the red sector:
1. Check friction adjuster for throttle quadrant.
2. Check oil pressure: Following a loss of oil or oil pressure, the propeller governor sets a high RPM. In this case the RPM should be regulated using the throttle. Proceed as in 3.2.3 (b) - LOSS OF OIL PRESSURE.
3. If oil pressure is normal:
* Pull RPM lever back and listen for an associated drop in RPM:
- If the indication does not change in spite of an audible drop in RPM, it is probable that the RPM indication is defective, which should thus be
Emergency
Procedures
ignored (the airplane should be serviced).
- If there is no audible drop in RPM, it is probable that the governor system is defective. In this case the RPM should be regulated using the throttle.
END OF CHECKLIST
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Emergency Procedures
(g) Loss of RPM
1. Electrical fuel pump ................... check ON
2. Fuel tank selector .................... check
3. Friction adjuster for throttle quadrant ...... check sufficiently tight
4. RPM lever .......................... HIGH RPM
* Listen for rise in RPM.
- If there is no audible rise in RPM, it is probable that the governor system
DA 40 AFM
is defective. In this case the RPM can be regulated within certain limits using the throttle.
- Land at the nearest appropriate airfield.
- Be prepared for possible emergency landing.
- If the indication does not change in spite of an audible rise in RPM, it is probable that the RPM indication is defective, which should thus be ignored (the airplane should be serviced).
END OF CHECKLIST
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DA 40 AFM
(h) High Fuel Flow
Fuel flow in the red sector:
1. Electrical fuel pump................... ON
2. Fuel pressure ....................... check after 10 - 15 sec:
* If the fuel pressure is low, refer to 3.2.3 (i) - LOW FUEL PRESSURE WITH
THE ELECTRICAL FUEL PUMP SET TO ON.
* If the fuel pressure is in the green sector, or the fuel pressure warning light
is not illuminated, the likely cause is a defective fuel flow indication, which should thus be ignored (the airplane should be serviced). Fuel flow data should be taken from the engine performance table in Chapter 5.
Emergency
Procedures
3. Check fuel quantity. A rapid reduction in fuel quantity confirms a high fuel
flow.
END OF CHECKLIST
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Emergency
DA 40 AFM
Procedures
(i) Low Fuel Pressure with the Electrical Fuel Pump Set to ON
Fuel pressure warning light illuminates, or fuel pressure indication below the green sector:
1. Fuel flow ........................... check:
* If the fuel flow is high, there is possibly a leak (between the injection system
and the injectors). Land on the nearest suitable airfield.
* If the fuel flow is in the green sector and the engine is running smoothly, the
likely cause is a defective fuel pressure indication, which should thus be ignored (the airplane should be serviced).
Monitor engine for power loss and rough operation that could indicate fuel starvation. If the engine is no longer producing sufficient power, then an emergency landing should be carried out.
END OF CHECKLIST
Page 3 - 16 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 91
DA 40 AFM

3.2.4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER

NOTE
Restarting the engine is possible at all airspeeds above 70 KIAS up to vNE and up to the maximum demonstrated operating altitude.
NOTE
As long as an airspeed of at least 65 KIAS is maintained, and there is no major engine failure, the propeller will continue to windmill.
1. Airspeed ........................... 80 KIAS
Emergency
Procedures
2. Fuel tank selector .................... fullest tank
3. Ignition switch ....................... check BOTH
4. Mixture control lever .................. check appropriate position
5. Electrical fuel pump................... check ON
6. Alternate air......................... OPEN
If Engine Does Not Start:
7. Mixture control lever .................. LEAN
8. Mixture control lever .................. push forward slowly until
If it is not possible to start the engine:
- Adopt glide configuration as in 3.4 - GLIDING.
- Carry out emergency landing as in 3.5.1 - EMERGENCY LANDING WITH ENGINE OFF.
engine starts
NOTE
END OF CHECKLIST
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 3 - 17
Page 92
Emergency Procedures

3.2.5 DEFECTIVE ENGINE CONTROLS

Defective Mixture Control Cable
(a) Flight and Landing:
1. Maintain altitude to the nearest airfield.
2. During descent, test the reaction of the engine to a higher power setting. A lean mixture can lead to engine roughness and a loss of power. The landing approach must be planned accordingly.
WARNING
Go-around may become impossible with the remaining power.
DA 40 AFM
(b) Engine Shut-Down:
1. Parking brake........................ set
2. Engine instruments ................... check
3. Avionics master switch................. OFF
4. All electrical equipment ................ OFF
5. Throttle............................. IDLE
6. Ignition switch ....................... OFF
%
END OF CHECKLIST
7. Master switch (ALT/BAT) .............. OFF
Page 3 - 18 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 93
DA 40 AFM
Defective Throttle Control Cable
(a) Sufficient Engine Power Available to Continue Flight:
1. Approach nearest airfield, control engine power with RPM lever.
2. Perform landing with shut-down engine.
(b) No Sufficient Engine Power Available to Continue Flight:
1. Carry out emergency landing as in 3.5.1 - EMERGENCY LANDING WITH ENGINE OFF.
END OF CHECKLIST
Emergency
Procedures
Defective RPM Lever Control Cable
(a) Sufficient Engine Power Available to Continue Flight:
1. Approach nearest airfield, control engine power with throttle.
2. Perform normal landing.
WARNING
Go-around may become impossible with the remaining power.
(b) No Sufficient Engine Power Available to Continue Flight:
1. Carry out emergency landing as in 3.5.1 - EMERGENCY LANDING WITH ENGINE OFF.
END OF CHECKLIST
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 3 - 19
Page 94
Emergency Procedures

3.2.6 RESTARTING THE ENGINE WITH STATIONARY PROPELLER

NOTE
Restarting the engine is possible at all airspeeds above 80 KIAS up to vNE and up to the maximum demonstrated operating altitude.
1. Airspeed ............................ 80 KIAS
2. Electrical equipment................... OFF
3. Avionics master switch................. OFF
4. Master switch (BAT) .................. check ON
5. Mixture control lever .................. check
6. Fuel tank selector .................... check
DA 40 AFM
7. Electrical fuel pump ................... check ON
8. Alternate air ......................... OPEN
9. Ignition switch ....................... START
NOTE
By increasing the airspeed above approximately 130 KIAS, the propeller will begin to rotate and the engine can thus be started. For this, the Ignition switch should be set at BOTH (see 3.2.4 - RESTARTING THE ENGINE WITH WINDMILLING PROPELLER). An altitude loss of at least 1000 ft (300 meter) must be allowed for.
if it is not possible to start the engine:
- Adopt glide configuration as in 3.4 - GLIDING
- Carry out emergency landing as in 3.5.1 - EMERGENCY LANDING WITH ENGINE OFF.
CONTINUED
Page 3 - 20 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 95
DA 40 AFM
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.
END OF CHECKLIST
Emergency
Procedures
CAUTION
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 3 - 21
Page 96
Emergency Procedures

3.3 SMOKE AND FIRE

3.3.1 SMOKE AND FIRE ON THE GROUND

(a) Engine Fire When Starting on the Ground
1. Fuel tank selector .................... OFF
2. Cabin heat .......................... OFF
3. Brakes ............................. apply
After Standstill:
4. Throttle............................. MAX PWR
5. Master switch (ALT/BAT)............... OFF%
DA 40 AFM
When the Engine Has Stopped:
6. Ignition switch ....................... OFF
7. Canopy ............................ open
8. Airplane ............................ evacuate immediately
END OF CHECKLIST
Page 3 - 22 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 97
DA 40 AFM
(b) Electrical Fire with Smoke on the Ground
1. Master switch (ALT/BAT)............... OFF%
If the Engine is Running:
2. Throttle ............................ IDLE
3. Mixture control lever .................. LEAN - shut off engine
When the Engine Has Stopped:
4. Ignition switch ....................... OFF
5. Canopy ............................ open
6. Airplane ............................ evacuate immediately
Emergency
Procedures
END OF CHECKLIST
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 3 - 23
Page 98
Emergency Procedures

3.3.2 SMOKE AND FIRE DURING TAKE-OFF

(a) If Take-Off Can Still Be Aborted%
1. Throttle............................. IDLE
2. Cabin heat .......................... OFF
3. Brakes ............................. apply - bring the airplane to
4. After stopping ........................ proceed as in 3.3.1 -
END OF CHECKLIST
DA 40 AFM
a stop
SMOKE AND FIRE ON THE GROUND
(b) If Take-Off Cannot Be Aborted%
1. Cabin heat .......................... OFF
2. If possible, fly along a short-cut traffic circuit and land on the airfield.
WARNING
If, in the event of an engine problem occurring during take-off, the take-off can no longer be aborted and a safe height has% not been reached, then a straight-ahead emergency landing should be carried out. Turning back can be fatal.
%
3. Airspeed ............................ 74 KIAS (1200 kg, 2646 lb)
72 KIAS (1150 kg, 2235 lb) 66 KIAS (1000 kg, 2205 lb) 59 KIAS (850 kg, 1874 lb)
CONTINUED
Page 3 - 24 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
Page 99
Emergency
DA 40 AFM
Procedures
After Climbing to a Height From Which the Selected Landing Area Can Be Reached Safely:
4. Fuel tank selector .................... OFF
5. Electrical fuel pump................... OFF
6. Cabin heat .......................... OFF
7. Master switch (ALT/BAT)............... OFF%
8. Emergency window(s) ................. open if required
9. Carry out emergency landing with engine off. Allow for increased landing distance due to the flap position.
CAUTION
In case of extreme smoke development, the front canopy may be unlatched during flight. This allows it to partially open, in order to improve ventilation. The canopy will remain open in this position. Flight characteristics will not be affected significantly.
END OF CHECKLIST
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 3 - 25
Page 100
Emergency Procedures

3.3.3 SMOKE AND FIRE IN FLIGHT

In the event of smoke or fire, prepare to land the airplane without delay while completing fire suppression and/or smoke evacuation procedures. If it cannot be visually verified that the fire has been completely extinguished, whether the smoke has cleared or not, land immediately at the nearest suitable airfield or landing site.
(a) Engine Fire in Flight
1. Cabin heat .......................... OFF
DA 40 AFM
CAUTION
2. Select appropriate emergency landing field.
When it Seems Certain that the Landing Field Will Be Reached:
3. Fuel tank selector .................... OFF
4. Throttle............................. MAX PWR
5. Electrical fuel pump ................... OFF
6. Master switch (ALT/BAT)............... ON%
7. Emergency window(s) ................. open if required
8. Carry out emergency landing with engine off.
CAUTION
In case of extreme smoke development, the front canopy may be unlatched during flight. This allows it to partially open, in order to improve ventilation. The canopy will remain open in this position. Flight characteristics will not be affected significantly.
END OF CHECKLIST
Page 3 - 26 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E
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