DA 40 AFM Introduction

DIAMOND DA40 · Parts Catalog

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Overview

The document is the Airplane Flight Manual (AFM) for the Diamond DA40 aircraft, providing essential information for safe operation. It includes operating limitations, emergency procedures, and performance data, among other critical sections.

The manual must be reviewed before the first flight.
It is essential to follow the operating limitations outlined in the AFM.
Revisions to the manual must be recorded appropriately.
Temporary revisions provide interim information until permanent updates are issued.
The document is protected by copyright.
The manual includes a list of effective pages and a table of contents.

Document

Source

Originally published by seagle.aero. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

View original at seagle.aero

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Document details

Type: Parts Catalog
Year: 2001
File size: 2.0 MB
Publisher: seagle.aero
Language: en

About this document

What is the DA 40 AFM Introduction?

The DA 40 AFM Introduction is a parts catalog for the DIAMOND DA40, dated 2001.

Where does the DA 40 AFM Introduction come from?

This copy of the DA 40 AFM Introduction was originally published by seagle.aero and is hosted on Sprinkle as a free, searchable reference copy.

What year was the DA 40 AFM Introduction published?

The DA 40 AFM Introduction — the DIAMOND DA40 parts catalog on file — is dated 2001.

Documentation completeness

4/7

Most owners only have the POH. Here's the essential set for the DIAMOND DA40.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins on file
Type Certificate (TCDS)

More DIAMOND DA40manuals & documents

In this document

General

This section introduces the aircraft and outlines the certification basis, warnings, cautions, and notes relevant to the operation of the DA40.

Operating Limitations

Details the approved operating limitations that must be adhered to for safe flight operations.

Emergency Procedures

Outlines the procedures to follow in case of an emergency during flight.

Normal Operating Procedures

Describes the standard procedures for operating the aircraft under normal conditions.

Performance

Provides performance data for the aircraft, including speeds and operational capabilities.

Mass and Balance / Equipment List

Includes information on the aircraft's mass and balance requirements and a list of equipment.

Safety notes

The aircraft must be operated in accordance with the procedures and limitations specified in the AFM.
Pilots must familiarize themselves with the entire manual before flight.
Revisions must be recorded and approved by Austro Control GmbH.

Full document text

DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 1 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 limitations of this Airplane Flight Manual. Before this airplane is operated for the first time, the pilot must familiarize himself with 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 : office@diamond-air.at DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 2 0.1 RECORD OF REVISIONS All revisions of this manual, with the exception of - ' • Temporary Revisions, ' • updates of the modification level (Section 1.1), ' • updated mass and balance information (Section 6.3), ' • updates of the Equipment Inventory (Section 6.5), and ' • updates of the List of Supplements (Section 9.2) ' must be recorded in the following table. Revisions of approved Chapters require the countersignature of Austro Control GmbH. 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. 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 behind the cover page of 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 ' 40-039, therefore the Temporary Revision TR-OÄM-40-039 is superseded by the ' 'permanent' Revision 5. ' Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Date of Approval Date Inserted Signature 1 corrections all all 26-Sep-2000 [approved by Ing. Andreas Winkler for ACG] 09-Oct-2000 DA 40 AFM Introduction Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Date of Approval Date Inserted Signature Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 3 2 OÄM 40-060 (White Wire optional) OÄM 40-068 (Essential Bus) OÄM 40-073 (LASAR optional) corrections 0 0-2, 0-4 thru 0-7 19-Dec-2000 [approved by Ing. Andreas Winkler for ACG] 25-Jan-2001 '' 1 1-16 ''''' '' 2 2-1, 2-7 thru 2-9, 2-13 thru 2-19 ''''' ' 3 3-7, 3-8, 3-19, 3-20, 3-25, 3-26 ''''' '' 4A 4A-3 thru 4A-8, 4A-14, 4A-15 ''''' '' 4B 4B-4 thru 4B-6 ''''' ' 6 6-1, 6-2, 6-12 thru 6-14 ''''' ' 7 7-1, 7-8, 7-14, 7-28 thru 7-38 ' ' ''' 3 OÄM 40-064 (Night VFR) OÄM 40-069 (control surf. gust lock) OÄM 40-070 (tow bar) corrections 0 0-2 thru 0-7 05-Feb-2001 [approved by Ing. Andreas Winkler for ACG] 02 Jul 2001 '' 1 1-2 ''''' '' 2 2-1, 2-8, 2-9, 2-12, 2-15 thru 2-20 ''''' '' 3 3-1, 3-25 thru 3-27 ''''' '' 4A 4A-1, 4A-8 thru 4A-31 ''''' '' 5 5-7, 5-14, 5-16 ''''' '' 6 6-7, 6-9, 6-12 thru 6-14 ''''' 7 7-32, 7-35, 7-36 ' ' 8 8-1 thru 8-9 ' ' ' '' 4 OÄM 40-067 (IFR) corrections all all 09 Apr 2001 [approved by Ing. Andreas Winkler for ACG] 02 Jul 2001 DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 5 0.2 LIST OF EFFECTIVE PAGES Ch. Page Date 0 0-0 0-1 0-2 0-3 0-4 0-5 0-6 0-7 0-8 0-9 09-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Apr-2001 1 1-1 1-2 1-3 1-4 1-5 1-6 1-7 1-8 1-9 1-10 1-11 1-12 1-13 1-14 1-15 1-16 1-17 1-18 1-19 1-20 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 Ch. Page Date 2 2-1 appr. 2-2 appr. 2-3 appr. 2-4 appr. 2-5 appr. 2-6 appr. 2-7 appr. 2-8 appr. 2-9 appr. 2-10 appr. 2-11 appr. 2-12 appr. 2-13 appr. 2-14 appr. 2-15 appr. 2-16 appr. 2-17 appr. 2-18 appr. 2-19 appr. 2-20 appr. 2-21 appr. 2-22 appr. 2-23 appr. 2-24 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 6 Ch. Page Date 3 3-1 3-2 3-3 3-4 3-5 3-6 3-7 3-8 3-9 3-10 3-11 3-12 3-13 3-14 3-15 3-16 3-17 3-18 3-19 3-20 3-21 3-22 3-23 3-24 3-25 3-26 3-27 3-28 3-29 3-30 3-31 3-32 3-33 3-34 3-35 3-36 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001

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09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' Ch. Page Date 4A 4A-1 4A-2 4A-3 4A-4 4A-5 4A-6 4A-7 4A-8 4A-9 4A-10 4A-11 4A-12 4A-13 4A-14 4A-15 4A-16 4A-17 4A-18 4A-19 4A-20 4A-21 4A-22 4A-23 4A-24 4A-25 4A-26 4A-27 4A-28 4A-29 4A-30 4A-31 4A-32 4A-33 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 7 Ch. Page Date 4B 4B-1 4B-2 4B-3 4B-4 4B-5 4B-6 4B-7 4B-8 4B-9 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 5 5-1 5-2 5-3 5-4 5-5 5-6 5-7 5-8 5-9 5-10 5-11 5-12 5-13 5-14 5-15 5-16 5-17 5-18 5-19 5-20 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 Ch. Page Date 6 6-1 6-2 6-3 6-4 6-5 6-6 6-7 6-8 6-9 6-10 6-11 6-12 6-13 6-14 6-15 6-16 6-17 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 8 Ch. Page Date 7 7-1 7-2 7-3 7-4 7-5 7-6 7-7 7-8 7-9 7-10 7-11 7-12 7-13 7-14 7-15 7-16 7-17 7-18 7-19 7-20 7-21 7-22 7-23 7-24 7-25 7-26 7-27 7-28 7-29 7-30 7-31 7-32 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 Ch. Page Date 7 7-33 7-34 7-35 7-36 7-37 7-38 7-39 7-40 7-41 7-42 7-43 7-44 7-45 09-Sep-2001 ' 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 8 8-1 8-2 8-3 8-4 8-5 8-6 8-7 8-8 8-9 8-10 8-11 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Apr-2001 09-Sep-2001 ' 09-Apr-2001 9 9-1 ' 9-2 ' 9-3 ' 9-4 ' 9-5 ' 9-6 ' 20-Apr-2001 20-Apr-2001 09-Sep-2001 ' 09-Sep-2001 ' 09-Sep-2001 ' 20-Apr-2001 DA 40 AFM Introduction Doc. No. 6.01.01-E Revision 5 09-Sep-2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 0 - 9 0.3 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 DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 1 CHAPTER 1 GENERAL Page 1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2 CERTIFICATION BASIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 1.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . 1-4 1.4 DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 1.5 DEFINITIONS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . 1-7 1.6 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-15 1.6.1 CONVERSION FACTORS . . . . . . . . . . . . . . . . . . . . . . . . . 1-15 1.6.2 CONVERSION CHART LITERS / US GALLONS . . . . . . . . 1-17 1.7 THREE-VIEW DRAWING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-18 1.8 SOURCE DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19 1.8.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19 1.8.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19 1.8.3 ENGINE INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . 1-20 1.8.4 IGNITION CONTROL UNIT . . . . . . . . . . . . . . . . . . . . . . . . 1-20 DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 2 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 Autopilot % OÄM 40-061 % 9 yes % 9 no % Emergency switch OÄM 40-067 9 yes 9 no Essential Bus OÄM 40-068 9 yes 9 no Alternate Static Valve OÄM 40-072 9 yes 9 no SlickSTART Ignition System % OÄM 40-073 % 9 yes % 9 no % Door Locking System % OÄM 40-081 % 9 yes % 9 no % RH Emergency Window % MÄM 40-048 % 9 yes % 9 no % DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 3 This Airplane Flight Manual must be kept on board the airplane at all times. Its designated 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. 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. 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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 4 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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 5 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 m2 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 DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 6 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 : 6.00-6; 6 PR, 120 mph DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 7 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. KCAS: CAS in knots. IAS: Indicated Airspeed as shown on an airspeed indicator. KIAS: IAS in knots. TAS: True Airspeed. The speed of the airplane 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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 8 vC: 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. vS0: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration. vx: Best Angle-of-Climb Speed. vy: Best Rate-of-Climb Speed. (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 °C (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 °C (-69.7 °F) is -0.0065 °C/m (-0.00357 °F/ft), and above this 0 °C/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). DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 9 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. (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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 10 (d) Mass and balance 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. 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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 11 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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 12 (f) Designation of the circuit breakers on the instrument panel 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 NAV/COM Navigation/Communication Equipment XPDR Transponder ENGINE: IGNITION Ignition INST. 1 Engine Instrument VM 1000 START Starter 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 DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 13 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. PROT. Alternator Protection ALT. CONT. Alternator Control 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). DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 14 (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. DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 15 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeters [m] meters [km] kilometers [in] inches [ft] feet [NM] nautical miles [mm] / 25.4 = [in] [m] / 0.3048 = [ft] [km] / 1.852 = [NM] Volume [l] liters [US gal] US gallons [qts] US quarts [l] / 3.7854 = [US gal] [l] / 0.9464 = [qts] Speed [km/h] kilometers per hour [m/s] meters per second [kts] knots [mph] miles per hour [fpm] feet per minute [km/h] / 1.852 = [kts] [km/h] / 1.609 = [mph] [m/s] x 196.85 = [fpm] Speed of rotation [RPM] revolutions per minute -- Mass [kg] kilograms [lb] pounds [kg] x 2.2046 = [lb] Force, weight [N] newtons [lbf] pounds force [N] x 0.2248 = [lbf] Pressure [hPa] hecto- pascals [mbar] millibars [bar] bars [inHg] inches of mercury [psi] pounds per square inch [hPa] = [mbar] [hPa] / 33.86 = [inHg] [bar] x 14.504 = [psi] Temperature [°C] degrees Celsius [°F] degrees Fahrenheit [°C]x1.8 + 32 = [°F] ([°F] - 32)/1.8 = [°C] DA 40 AFM General Dimension SI-Units US Units Conversion Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 16 Intensity of electric current [A] ampères -- Electric charge (battery capacity) [Ah] ampère-hours -- Electric potential [V] volts -- Time [sec] seconds -- DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 17 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 DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 18 11940 mm (39 ft 2 in) 8007 mm (26 ft 3 in) 1.7 THREE-VIEW DRAWING DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 19 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 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)) 1.8.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 ATTING GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Internet: www.mt-propeller.de DA 40 AFM General Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 1 - 20 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 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 Internet: www.unisonindustries.com Documents: L-1502 LASAR Installation, Operation, and Troubleshooting Manual DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 1 CHAPTER 2 OPERATING LIMITATIONS Page 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 2.6 WARNING, CAUTION AND STATUS LIGHTS . . . . . . . . . . . . . . . . 2-8 2.7 MASS (WEIGHT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 2.8 CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 2.9 APPROVED MANEUVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 2.10 MANEUVERING LOAD FACTORS . . . . . . . . . . . . . . . . . . . . . . . . 2-14 2.11 OPERATING ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 2.12 FLIGHT CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 2.13 KINDS OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16 2.14 FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 2.15 LIMITATION PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 2.16 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 2.16.1 TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 2.16.2 BATTERY CHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 2.16.3 EMERGENCY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 2.16.4 OPERATION TIME OF ELECTRICAL EQUIPMENT . . . . 2-23 ' 2.16.5 DOOR LOCKING DEVICE . . . . . . . . . . . . . . . . . . . . . . . . 2-23 ' 2.16.6 ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . 2-24 ' DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 2 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. DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 3 2.2 AIRSPEED Airspeed IAS Remarks vA Maneuvering 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) Do not make full or abrupt control surface movement above this speed. vFE Max. flaps ex- tended speed LDG: 91 KIAS T/O: 108 KIAS Do not exceed these speeds with the given flap setting. vc Max. structural cruising speed 129 KIAS Do not exceed this speed except in smooth air, and then only with caution. vNE Never exceed speed in smooth air 178 KIAS Do not exceed this speed in any operation. DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 4 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. DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 5 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 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) DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 6 j) Propeller manufacturer : mt-Propeller k) Propeller designation : MTV-12-B/180-17 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: OAT at ground level During the first 50 hours: SAEJ1966 / MIL-L-6082 Mineral Oil After 50 hours: SAEJ1899 / MIL-L-22851 Ashless Dispersant Oil All temperatures --- SAE 15-W50, SAE 20-W50 above 80 °F (above 27 °C) SAE 60 SAE 60 above 60 °F (above 16 °C) SAE 50 SAE 40 or SAE 50 30 °F to 90 °F (-1 °C to 32 °C) SAE 40 SAE 40 0 °F to 90 °F (-18 °C to 32 °C) SAE 20-W50 SAE 20-W50 or SAE 15-W50 0 °F to 70 °F (-18 °C to 21 °C) SAE 30 SAE 30, SAE 40, or SAE 20-W40 below 10 °F (below -12 °C) SAE 20 SAE 30 or SAE 20-W30 DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 7 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. Indi- cation Red arc/bar = lower prohibited range Yellow arc/bar = caution range Green arc/bar = normal operating range Yellow arc/bar = caution range Red arc/bar = upper prohibited range Manifold Pressure -- -- 13 - 30 inHg -- -- RPM -- -- 500 - 2400 RPM 2400 - 2700 RPM > 2700 RPM Oil temp. -- -- 149 - 230 °F 231 - 245 °F > 245 °F Cylinder head temp. -- -- 150 - 475 °F 476 - 500 °F > 500 °F Oil pressure < 25 psi 25 - 55 psi 56 - 95 psi 96 - 97 psi > 97 psi Fuel Pressure < 14 psi -- 14 - 35 psi -- > 35 psi Fuel Flow -- -- 1 - 20 US gal/hr -- > 20 US gal/hr Voltage < 24.1 V 24.1 - 25 V 25.1 - 30 V 30.1 - 32 V > 32 V Ammeter -- -- 2 - 75 A -- -- Fuel quantity 0 US gal -- 0 - 15 US gal -- -- DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 8 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) CauseVariant 'DAI' Variant 'White Wire' Meaning OIL PR OIL PRESS oil pressure Oil pressure below 25 psi FUEL PR FUEL PRESS fuel pressure Fuel pressure below 14 psi ALT ALTERNATOR alternator (generator) Alternator failure START START starter Operation of starter, or failure of the starter motor to disengage from the engine after starting DOOR DOORS doors Front canopy and/or rear door not completely closed and locked TRIM FAIL trim failure Failure in the automatic trim system of the autopilot (if installed) DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 9 Color and significance of the caution lights (amber) Caution lights (amber) CauseVariant 'DAI' Variant 'White Wire' Meaning L FUEL fuel quantity left tank Fuel quantity in the left tank less than 3 US gal (±1 US gal) R FUEL fuel quantity right tank Fuel quantity in the right tank less than 3 US gal (±1 US gal) LOW FUEL fuel quantity 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) VOLT LOW VOLTS voltage On-board voltage below 24 V PITOT PITOT Pitot heating Pitot heating not switched ON, or fault in the Pitot heating system Color and significance of the status light (white) Status light (white) CauseVariant 'DAI' Variant 'White Wire' Meaning IGN IGNITION ignition Electronic ignition control unit (if installed) not in operation DA 40 AFM Operating Limitations Doc. No. 6.01.01-E Rev. 5 09 Sep 2001 OÄM 40-061, -073, -081, -085, -092, -093, -094 MÄM 40-039/a, -048 Page 2 - 10 2.7 MASS (WEIGHT) Maximum take-off mass (Normal Category) : 1150 kg 2535 lb Maximum take-off mass (Utility Category) : 980 kg 2161 lb Maximum landing mass : 1092 kg 2407 lb Max. load in baggage compartment : 30 kg 66 lb 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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