DA 40 AFM

Diamond DA40 NG · Pilot's Operating Handbook

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Overview

The DA 40 Airplane Flight Manual (AFM) provides essential information for pilots and instructors regarding the safe and efficient operation of the Diamond DA40 aircraft. It includes operating limitations, emergency procedures, normal and abnormal operating procedures, performance data, mass and balance information, and a description of the airplane and its systems. The manual is designed to meet JAR-23 requirements and is applicable to all serial numbers of the DA40, with specific equipment and modification levels noted for each aircraft. Pilots are advised to familiarize themselves thoroughly with the contents of the AFM before operating the aircraft, ensuring compliance with all safety protocols and operational guidelines.

The DA40 is a single-engine aircraft with specific operating limitations that must be adhered to for safety.
Pilots should familiarize themselves with emergency procedures outlined in the AFM to handle critical situations effectively.
The maximum takeoff weight for the DA40 is specified in the operating limitations section, which is crucial for flight safety.
Performance data, including climb rates and fuel consumption, are essential for effective flight planning.
Mass and balance calculations are critical for safe operation and must be performed before flight.

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Document details

Type: Pilot's Operating Handbook
Year: 2006
Pages: 272
File size: 2.4 MB
Publisher: takeflightsandiego.com

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In this document

General

This section introduces the Airplane Flight Manual, emphasizing the importance of understanding the operational procedures and limitations of the Diamond DA40. It outlines the certification basis under JAR-23 and provides a summary of the manual's structure, including sections on operating limitations, emergency procedures, and performance data.

Operating Limitations

This chapter details the operational limits of the DA40, including maximum takeoff and landing weights, airspeeds, and environmental conditions under which the aircraft can be safely operated. It is crucial for pilots to adhere to these limitations to ensure flight safety.

Emergency Procedures

This section outlines the necessary actions to take in various emergency scenarios, including engine failure, electrical malfunctions, and other critical situations. Pilots are instructed on how to respond effectively to maintain safety during emergencies.

Normal Operating Procedures

This chapter provides step-by-step procedures for normal flight operations, including preflight checks, engine start, takeoff, and landing. It emphasizes the importance of following these procedures to ensure safe and efficient flight.

Performance

The performance section includes data on the aircraft's capabilities, such as climb rates, fuel consumption, and range. This information is vital for flight planning and operational efficiency.

Mass and Balance / Equipment List

This chapter provides guidelines for calculating the aircraft's mass and balance, which is critical for safe flight operations. It also includes an equipment list that details the specific equipment installed on the aircraft.

Description of the Airplane and Its Systems

This section describes the various systems of the DA40, including the engine, avionics, and control systems. Understanding these systems is essential for pilots to operate the aircraft effectively.

Airplane Handling, Care and Maintenance

This chapter outlines best practices for the care and maintenance of the DA40, ensuring its longevity and reliability. It includes routine checks and maintenance schedules.

Safety notes

Engine failure is a risk; avoid flying at night or in IMC without proper precautions.
Always keep the AFM on board the aircraft during flight.

Full document text

DA 40 AFM Introduction Doc. # 6.01.01-E Revision 7 15-Jul-2006 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 Introduction DA 40 AFM Page 0 - 2 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 0.1 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. 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. 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. % Introduction DA 40 AFM Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Date of Approval Date Inserted Signature Page 0 - 4 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 5 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) MÄM 40-039/a (VM 1000) MÄM 40-048 (RH emerg. window) corrections 0 0-1 thru 0-8 09 Sep 2001 [approved by Ing. Andreas Winkler for ACG] 09 Sep 2001 1 1-2, 1-5, 1-14 2 2-1, 2-16, 2-22, 2-23, 2-24 3 3-13, 3-18, 3-22, 3-23, 3-24, 3-31, 3-36 4A 4A-8, 4A-10, 4A-22, 4A-23, 4A-26 4B 4B-1, 4B-8 6 6-5, 6-8 thru 6-17 7 7-13, 7-14, 7-33, 7-35 8 8-10 9 9-3, 9-4, 9-5 Introduction DA 40 AFM Rev. No. Reason Chap- ter Page(s) Date of Revision EASA Approval No. ACG Compli- ance Date Inserted Signature Page 0 - 6 Revision 7 15-Jul-2006 Doc. # 6.01.01-E DA 40 AFM Introduction Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 0 - 7 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 0-10 0-11 0-12 0-13 % 0-14 % 15-Sep-2004 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 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 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % Ch. Page Date 1 1-13 1-14 1-15 1-16 1-17 1-18 1-19 1-20 1-21 % 1-22 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 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 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % Introduction DA 40 AFM Page 0 - 8 Revision 7 15-Jul-2006 Doc. # 6.01.01-E Ch. Page Date 2 appr. 2-18 appr. 2-19 appr. 2-20 appr. 2-21 appr. 2-22 appr. 2-23 appr. 2-24 appr. 2-25 % appr. 2-26 % appr. 2-27 % appr. 2-28 % appr. 2-29 % appr. 2-30 % appr. 2-31 % appr. 2-32 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 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 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % Ch. Page Date 3 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 3-37 % 3-38 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 %

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15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % DA 40 AFM Introduction Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 0 - 9 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 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % Ch. Page Date 4A 4A-33 4A-34 % 4A-35 % 4A-36 % 4A-37 % 4A-38 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 4B 4B-1 4B-2 4B-3 4B-4 4B-5 4B-6 4B-7 4B-8 4B-9 4B-10 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % Introduction DA 40 AFM Page 0 - 10 Revision 7 15-Jul-2006 Doc. # 6.01.01-E Ch. Page Date 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 5-21 % 5-22 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 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 6-18 % 6-19 % 6-20 % 6-21 % 6-22 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % DA 40 AFM Introduction Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 0 - 11 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 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 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 7-46 % 7-47 % 7-48 % 7-49 % 7-50 % 7-51 % 7-52 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % Introduction DA 40 AFM Page 0 - 12 Revision 7 15-Jul-2006 Doc. # 6.01.01-E Ch. Page Date 8 8-1 8-2 8-3 8-4 8-5 8-6 8-7 8-8 8-9 8-10 8-11 8-12 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 9 9-1 9-2 9-3 9-4 9-5 9-6 9-7 % 9-8 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % 15-Jul-2006 % DA 40 AFM Introduction Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 0 - 13 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 Introduction DA 40 AFM Page 0 - 14 Revision 7 15-Jul-2006 Doc. # 6.01.01-E Intentionally left blank. DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 1 CHAPTER 1 GENERAL Page 1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2 CERTIFICATION BASIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4 1.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . . 1-4 1.4 DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 1.5 DEFINITIONS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . 1-6 1.6 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-17 1.6.1 CONVERSION FACTORS . . . . . . . . . . . . . . . . . . . . . . . . . . 1-17 1.6.2 CONVERSION CHART LITERS / US GALLONS . . . . . . . . . 1-19 1.7 THREE-VIEW DRAWING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-20 1.8 SOURCE DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21 1.8.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21 1.8.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21 1.8.3 ENGINE INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-22 1.8.4 IGNITION CONTROL UNIT . . . . . . . . . . . . . . . . . . . . . . . . . 1-22 General DA 40 AFM Page 1 - 2 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 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 Operation with Winter Kit % OÄM 40-078 % 9 yes 9 no Door Locking System OÄM 40-081 9 yes 9 no DA 40 AFM General Modification Source Installed Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 3 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* % OÄM 40-163 % OÄM 40-164 % 9 yes 9 yes 9 no 9 no Winter baffle fresh air inlet % OÄM 40-183 % 9 yes 9 no Nose landing gear tie-down % OÄM 40-200 % 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 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. General DA 40 AFM Page 1 - 4 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 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 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 General DA 40 AFM Page 1 - 6 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 or % 15 x 6.0-6, 6 PR, 120 mph % CAUTION % The tire dimension 15 x 6.0-6, 6 PR, is only approved in % combination with the modified MLG strut (18 mm or 0.71 % inches thick; MÄM 40-123). % 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. DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 7 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. v NE: Never Exceed Speed in smooth air. This speed must not be exceeded in any operation. vNO 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. v x: Best Angle-of-Climb Speed. vy: Best Rate-of-Climb Speed. General DA 40 AFM Page 1 - 8 Revision 7 15-Jul-2006 Doc. # 6.01.01-E (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. DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 9 (c) Flight performance and flight planning Demonstrated Crosswind Component: The speed of the crosswind component at which adequate maneuverabil- ity 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. General DA 40 AFM Page 1 - 10 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 11 (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 % NAV/COM1 Navigation/Communication #1 % NAV/COM2 Navigation/Communication #2 % STRIKE Strike Finder % XPDR Transponder ENGINE: IGNITION Ignition INST. 1 Engine Instrument VM 1000 START Starter LIGHTING: FLOOD Flood Light INST. Instrument Lights LANDING Landing Light General DA 40 AFM Page 1 - 12 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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). DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 13 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, ACL's) % T & B Turn & Bank Indicator % TAXI/MAP Taxi Light/Map Light % General DA 40 AFM Page 1 - 14 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 % % 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 % DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 15 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 % General DA 40 AFM Page 1 - 16 Revision 7 15-Jul-2006 Doc. # 6.01.01-E (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. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 17 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] General DA 40 AFM Dimension SI-Units US Units Conversion Page 1 - 18 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 19 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 General DA 40 AFM Page 1 - 20 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 1.7 THREE-VIEW DRAWING DA 40 AFM General Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 1 - 21 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)) 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 Webpage: www.mt-propeller.de General DA 40 AFM Page 1 - 22 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 Webpage: www.unisonindustries.com Documents: L-1502 LASAR Installation, Operation, and Troubleshooting Manual DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 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 . . . . . . . . . . . . . . . . . 2-9 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 2.16.1 TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 2.16.2 BATTERY CHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 2.16.3 EMERGENCY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 2.16.4 OPERATION TIME OF ELECTRICAL EQUIPMENT . . . . . 2-31 2.16.5 DOOR LOCKING DEVICE . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 2.16.6 ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . 2-32 Operating Limitations DA 40 AFM Page 2 - 2 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. # 6.01.01-E Revision 7 15-Jul-2006 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. vNO = 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. Operating Limitations DA 40 AFM Page 2 - 4 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 - v NE. DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 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) j) Propeller manufacturer : mt-Propeller Operating Limitations DA 40 AFM Page 2 - 6 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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: 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. # 6.01.01-E Revision 7 15-Jul-2006 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 above 2700 RPM Oil temp. -- -- 149 - 230 °F 231 - 245 °F above 245 °F Cylinder head temp. -- -- 150 - 475 °F 476 - 500 °F above 500 °F Oil pressure below 25 psi 25 - 55 psi 56 - 95 psi 96 - 97 psi above 97 psi Fuel Pressure below 14 psi -- 14 - 35 psi -- above 35 psi Fuel Flow -- -- 1 - 20 US gal/hr -- above 20 US gal/hr Voltage below 24.1 V 24.1 - 25 V 25.1 - 30 V 30.1 - 32 V above 32 V Operating Limitations DA 40 AFM Page 2 - 8 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 Ammeter -- -- 2 - 75 A -- -- Fuel ' quantity, ' Standard ' Tank ' 0 US gal -- 0 - 15 US gal1 ' 0 - 17 US gal2 ' -- -- Fuel ' quantity, ' Long ' Range ' Tank ' 0 US gal ' -- ' 0 - 16 US gal ' + ' 0 - 9 US gal3 ' -- ' -- ' 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 ' DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 9 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) Operating Limitations DA 40 AFM Page 2 - 10 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 11 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 original MLG strut : 1092 kg 2407 lb modified MLG strut (MÄM 40-123/e) : 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. Operating Limitations DA 40 AFM Page 2 - 12 Revision 7 15-Jul-2006 Doc. # 6.01.01-E NOTE ' In some countries the beginning of a flight is defined by ' starting the engine. In those countries a maximum ramp mass ' of 1154 kg/2544 lb ("Normal" category), or 984 kg/2169 lb ' ("Utility" category) is approved. At the time of lift-off the ' maximum permitted take-off mass must not be exceeded. ' DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 13 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 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. Operating Limitations DA 40 AFM Page 2 - 14 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 15 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. CAUTION Aerobatics, spinning, and flight maneuvers with more than 90° of bank are not permitted in the Utility Category. 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. Operating Limitations DA 40 AFM Page 2 - 16 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 2.10 MANEUVERING LOAD FACTORS Table of maximum structural load factors: Normal Category at vA at vNE with flaps in T/O or LDG position Positive 3.8 3.8 2.0 Negative -1.52 0 Utility Category at vA at vNE with flaps in T/O 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. DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 17 2.11 OPERATING ALTITUDE The maximum demonstrated operating altitude is 16,400 ft (5,000 meters). 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 Operating Limitations DA 40 AFM Page 2 - 18 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 19 minimum operational equipment (serviceable) for daytime VFR flights in addition for night VFR flights in addition for IFR flights Flight and naviga- tion instru- ments * airspeed indicator * altimeter * magnetic compass * 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 * second VHF radio (COM) * VOR-LOC- GP receiver * marker beacon receiver engine instru- ments * fuel indicators * integrated engine instrument * annunciator panel (all lights, see 2.6) * ammeter (included in VM 1000) * voltmeter (included in VM 1000) Operating Limitations DA 40 AFM minimum operational equipment (serviceable) for daytime VFR flights in addition for night VFR flights in addition for IFR flights Page 2 - 20 Revision 7 15-Jul-2006 Doc. # 6.01.01-E lighting * position lights * strobe lights (anti collision lights) * landing light * instrument lighting * flood light * flashlight other opera- tional minimum equip- ment * stall warning system * fuel quantity measuring device (see 7.10) * safety belts for each occupied seat * airplane flight manual * Pitot heating system * alternate static valve * essential bus * emergency battery DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 21 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. Operating Limitations DA 40 AFM Page 2 - 22 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 liters) ' Unusable fuel : 2 x 0.5 US gal (app. 2 x 2 liters) ' Max. indicated fuel quantity: up to and incl. serial no. 40.054 : 15 US gal (app. 57 liters) per tank ' serial no. 40.055 & subsequent : 17 US gal (app. 64 liters) per tank ' Max. permissible difference between right and left tank : 10 US gal (app. 38 liters) DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 23 b) Long Range Tank (if installed): ' Total fuel quantity : 2 x 25.5 US gal (app. 2 x 96.5 liters) ' Unusable fuel : 2 x 0.5 US gal (app. 2 x 2 liters) ' Max. indicated fuel quantity : 16 US gal (app. 61 liters) per tank ' Indicated quantity auxiliary ' fuel tank : 0 to 9 US gal (app. 0 to 34 liters) per tank ' Max. permissible difference ' between right and left tank : 8 US gal (app. 30 liters) ' 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. ' Operating Limitations DA 40 AFM Page 2 - 24 Revision 7 15-Jul-2006 Doc. # 6.01.01-E AVGAS 100LL 76 l / 20 US gal. 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: 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 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. For further operational limitations refer to the Airplane Flight Manual. No smoking. Next to each of the two fuel filler necks: a) Standard Tank: ' DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 25 max. indicated fuel quantity: 15 US gal left and right tank max. 10 US gal difference For use of max. tank capacity see AFM AVGAS 100LL 94 l / 25 US gal. max. indicated fuel quantity: 17 US gal left and right tank max. 10 US gal difference For use of max. tank capacity see AFM 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 b) Long Range Tank (if installed): ' ' ' ' ' Next to the fuel quantity indication: a) Standard Tank: ' up to serial number 40.054: ' serial number 40.055 and subsequent: ' ' ' ' ' b) Long Range Tank (if installed): ' ' ' ' ' ' Operating Limitations DA 40 AFM Page 2 - 26 Revision 7 15-Jul-2006 Doc. # 6.01.01-E On the fuel tank selector: a) Standard Tank: ' b) Long Range Tank (if installed): ' F u e l S e l e c t o r L E F T O F F 25 US gal. 25 US gal. 94 l 94 l DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 27 max. 108 KIAS max. 91 KIAS Ess. Bus NOT for normal operation. See AFM. In the cowling, on the door for the oil filler neck: OIL 1 qt = 0.95 liters ' SAE 15W50 ashless dispersant aviation grade oil (SAE Standard J-1899) or see AFM Chapter 2 VFR Min./Max.: 4/8 qts ' IFR Min./Max.: 6/8 qts ' Next to the flap selector switch: Next to the essential bus switch (if installed): Operating Limitations DA 40 AFM Page 2 - 28 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 66 lbs 30 kg / max. In the cockpit, on the left fuselage sidewall: (if alternate static valve is installed): Next to the baggage compartment: a) Standard baggage compartment: ' DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 29 AFT BAGGAGE COMPARTMENT MAX. 18 kg [40 lb] ARM: 4.54 m [178.7"] 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 b) Extended baggage compartment (OÄM 40-163, if installed): ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' ' Operating Limitations DA 40 AFM Page 2 - 30 Revision 7 15-Jul-2006 Doc. # 6.01.01-E Beside the door locking device (OÄM 40-081, if installed): ' Above the NAV #2 CDI (OÄM 40-206, if installed): ' ' ' NAV No. 2 not approved ' for precision approaches ' EMERGENCY EXIT: The keylock must be unlocked during flight! DA 40 AFM Operating Limitations Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 2 - 31 2.16 OTHER LIMITATIONS 2.16.1 TEMPERATURE The airplane must not be operated when its temperature is less than -40 °C (-40 °F). ' CAUTION ' For cold weather starting of the engine refer to the latest ' instructions given by the engine manufacturer. ' 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 for the attitude gyro (artificial horizon) and flood light for another 1.5 hours when the emergency power pack (if installed) is used. Operating Limitations DA 40 AFM Page 2 - 32 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 1 CHAPTER 3 EMERGENCY PROCEDURES Page 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 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 . . . . . . . . . . . . . . . . . . . . . . . . 3-15 3.2.5 DEFECTIVE ENGINE CONTROLS . . . . . . . . . . . . . . . . . . . 3-16 3.2.6 RESTARTING THE ENGINE WITH STATIONARY PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . 3-18 3.3 SMOKE AND FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-20 3.3.1 SMOKE AND FIRE ON THE GROUND . . . . . . . . . . . . . . . . 3-20 3.3.2 SMOKE AND FIRE DURING TAKE-OFF . . . . . . . . . . . . . . . 3-21 3.3.3 SMOKE AND FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . 3-23 3.4 GLIDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-25 3.5 EMERGENCY LANDINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-26 3.5.1 EMERGENCY LANDING WITH ENGINE OFF . . . . . . . . . . . 3-26 3.5.2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR . . . . . . . . . . . . . . . . . . . . . 3-28 3.5.3 LANDING WITH DEFECTIVE BRAKES . . . . . . . . . . . . . . . . 3-29 Emergency Procedures DA 40 AFM Page 3 - 2 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.6 RECOVERY FROM AN UNINTENTIONAL SPIN . . . . . . . . . . . . . 3-30 3.7 OTHER EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-31 3.7.1 ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-31 3.7.2 FAILURES IN THE ELECTRICAL SYSTEM . . . . . . . . . . . . 3-32 3.7.3 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN . . . . . . . . . . . . . . . . . . . 3-36 3.7.4 'DOOR'-WARNING LIGHT ON . . . . . . . . . . . . . . . . . . . . . . 3-37 % 3.7.5 EMERGENCY EXIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-37 % NOTE Procedures for uncritical system faults are given in Chapter 4B ABNORMAL OPERATING PROCEDURES. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 3 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. Emergency Procedures DA 40 AFM Page 3 - 4 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Flight Mass % Event 850 kg 1874 lb 1000 kg 2205 lb 1150 kg 2535 lb Engine failure after take-off (Flaps T/O) 59 KIAS 66 KIAS 72 KIAS Airspeed for best glide angle (Flaps UP) 60 KIAS 68 KIAS 73 KIAS Emergency landing with engine off Flaps UP 60 KIAS 68 KIAS 73 KIAS Flaps T/O 59 KIAS 66 KIAS 72 KIAS Flaps LDG 58 KIAS 63 KIAS 71 KIAS DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 5 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 necessary; otherwise establish the cause of the problem and re-establish engine performance CAUTION If the oil pressure is below the green sector, the engine must be switched off immediately. WARNING If the problem cannot be cleared, the airplane must not be flown. Emergency Procedures DA 40 AFM Page 3 - 6 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.2.2 ENGINE PROBLEMS DURING TAKE-OFF (a) Take-off can still be abandoned (sufficient runway length available) land straight ahead: 1. Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE on the ground: 2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required CAUTION 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 . . . . . . . . . . . . . . . . . OFF DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 7 (b) Take-off can no longer be abandoned 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 abandoned and a safe height has not been reached, then a straight-ahead emergency landing should be carried out. Turning back can be fatal. 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 5000 ft) 8. Alternate Air . . . . . . . . . . . . . . . . . . . . . . . . . OPEN 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. Emergency Procedures DA 40 AFM Page 3 - 8 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. Only if there is no other alternative should an engine which is running roughly continue to be used. 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 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 DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 9 WARNING If the problem does not clear itself immediately, and the engine is no longer producing sufficient power, then an emergency landing should be carried out. Emergency Procedures DA 40 AFM Page 3 - 10 Revision 7 15-Jul-2006 Doc. # 6.01.01-E (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. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 11 (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). (d) High oil temperature Check cylinder head and exhaust gas temperature. * 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 or 317 °F 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. Emergency Procedures DA 40 AFM Page 3 - 12 Revision 7 15-Jul-2006 Doc. # 6.01.01-E (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 appropriate airfield. - Be prepared for possible emergency landing. (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. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 13 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 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. (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 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). Emergency Procedures DA 40 AFM Page 3 - 14 Revision 7 15-Jul-2006 Doc. # 6.01.01-E (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 paragraph (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. 3. Check fuel quantity. A rapid reduction in fuel quantity confirms a high fuel flow. (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. % DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 15 3.2.4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER NOTE Restarting the engine is possible at all airspeeds above 70 KIAS up to v NE 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 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 engine starts NOTE 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 Emergency Procedures DA 40 AFM Page 3 - 16 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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. (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 7. Master switch . . . . . . . . . . . . . . . . . . . . . . . . OFF DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 17 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. 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. Emergency Procedures DA 40 AFM Page 3 - 18 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.2.6 RESTARTING THE ENGINE WITH STATIONARY PROPELLER NOTE Restarting the engine is possible at all airspeeds above 80 KIAS up to v NE 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 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 meters) 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 DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 19 CAUTION Engine restart following an engine fire should only be attempted if it is unlikely that a safe emergency landing can be made. It must be expected that engine restart is impossible after an engine fire. Emergency Procedures DA 40 AFM Page 3 - 20 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 (BAT) . . . . . . . . . . . . . . . . . . OFF when the engine has stopped: 6. Ignition switch . . . . . . . . . . . . . . . . . . . . . . . OFF 7. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . open 8. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . evacuate immediately (b) Electrical fire with smoke on the ground 1. Master switch (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 DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 21 3.3.2 SMOKE AND FIRE DURING TAKE-OFF (a) If take-off can still be abandoned 1. Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . apply - bring the airplane to a stop 4. After stopping . . . . . . . . . . . . . . . . . . . . . . . proceed as in 3.3.1 - SMOKE AND FIRE ON THE GROUND (b) If take-off cannot be abandoned 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 abandoned 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . 72 KIAS (1150 kg, 2535 lb) % 66 KIAS (1000 kg, 2205 lb) % 59 KIAS (850 kg, 1874 lb) % Emergency Procedures DA 40 AFM Page 3 - 22 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 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 (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. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 23 3.3.3 SMOKE AND FIRE IN FLIGHT CAUTION % 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 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 (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. Emergency Procedures DA 40 AFM Page 3 - 24 Revision 7 15-Jul-2006 Doc. # 6.01.01-E (b) Electrical fire with smoke in flight 1. Emergency switch . . . . . . . . . . . . . . . . . . . . ON if installed 2. Master switch (BAT) . . . . . . . . . . . . . . . . . . OFF 3. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Emergency window(s) . . . . . . . . . . . . . . . . . open if required 5. Land at an appropriate airfield as soon as possible. CAUTION Switching OFF the master switch (BAT) will lead to total failure of all electronic and electric equipment. Also affected from this are - if installed - the attitude gyro (artificial horizon) and the directional gyro. However, by switching the emergency switch ON (only installed in the IFR model), the emergency battery will supply power to the attitude gyro (artificial horizon) and the flood light. 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. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 25 3.4 GLIDING 1. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 KIAS (1150 kg, 2535 lb) 68 KIAS (1000 kg, 2205 lb) 60 KIAS (850 kg, 1874 lb) NOTE The glide ratio is 8.8; i.e., for every 1000 ft (305 meters) of altitude loss the maximum horizontal distance traveled in still air is 1.45 NM (2.68 km). During this the propeller will continue to windmill. With a stationary propeller the glide ratio is 10.3; this corresponds to a maximum horizontal distance of 1.70 NM (3.14 km) for every 1000 ft altitude. In consideration of a safe airspeed however, this configuration may not be attainable. Emergency Procedures DA 40 AFM Page 3 - 26 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.5 EMERGENCY LANDINGS 3.5.1 EMERGENCY LANDING WITH ENGINE OFF 1. Select suitable landing area. If no level landing area is available, a landing on an upward slope should be sought. 2. Consider wind. 3. Approach: If possible, fly along a short-cut rectangular circuit. On the downwind leg of the circuit the landing area should be inspected for obstacles from a suitable height. The degree of offset at each part of the circuit will allow the wind speed and direction to be assessed. 4. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 KIAS (1150 kg, 2535 lb.) 68 KIAS (1000 kg, 2205 lb.) 60 KIAS (850 kg, 1874 lb.) 5. If time allows . . . . . . . . . . . . . . . . . . . . . . . . advise ATC 6. Fuel tank selector . . . . . . . . . . . . . . . . . . . . OFF when it is certain that the landing field will be reached: 7. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LDG 8. Safety harnesses . . . . . . . . . . . . . . . . . . . . . tighten DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 27 CAUTION If sufficient time is remaining, the risk of fire in the event of a collision with obstacles can be reduced as follows: Ignition switch . . . . . . . . . . . . . . . . . OFF Master switch . . . . . . . . . . . . . . . . . OFF 9. Touchdown . . . . . . . . . . . . . . . . . . . . . . . . . with the lowest possible airspeed Emergency Procedures DA 40 AFM Page 3 - 28 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.5.2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR CAUTION A defective (e.g. burst) tire is not usually easy to detect. The damage normally occurs during take-off or landing, and is hardly noticeable during fast taxiing. It is only during the roll- out after landing or at lower taxiing speeds that a tendency to swerve occurs. Rapid and determined action is then required. 1. Advise ATC. 2. Land the airplane at the edge of the runway that is located on the side of the intact tire, so that changes in direction which must be expected during roll-out due to the braking action of the defective tire can be corrected on the runway. 3. Land with one wing low. The wing on the side of the intact tire should be held low. 4. Direction should be maintained using the rudder. This should be supported by use of the brake. It is possible that the brake must be applied strongly - if necessary to the point where the wheel locks. The wide track of the landing gear will prevent the airplane from tipping over a wide speed range. There is no pronounced tendency to tip even when skidding. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 29 3.5.3 LANDING WITH DEFECTIVE BRAKES In general, a landing on grass is recommended in order to reduce the landing run by virtue of the greater rolling resistance. CAUTION 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 off engine Ignition switch . . . . . . . . . . . . . . . . . OFF Master switch . . . . . . . . . . . . . . . . . OFF Emergency Procedures DA 40 AFM Page 3 - 30 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.6 RECOVERY FROM AN UNINTENTIONAL SPIN CAUTION Steps 1 to 4 must be carried out immediately and simultaneously. 1. Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. Rudder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . full deflection against direction of spin 3. Elevator (control stick) . . . . . . . . . . . . . . . . . fully forward 4. Ailerons . . . . . . . . . . . . . . . . . . . . . . . . . . . . neutral 5. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP when rotation has stopped: 6. Rudder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . neutral 7. Elevator (control stick) . . . . . . . . . . . . . . . . . pull carefully 8. Return the airplane from a descending into a normal flight attitude. In so doing do not exceed the 'never exceed speed', vNE. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 31 3.7 OTHER EMERGENCIES 3.7.1 ICING Unintentional flight into icing conditions 1. Leave the icing area (by changing altitude or turning back, in order to reach zones with a higher ambient temperature). 2. Pitot heating . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . ON 4. Air distributor lever . . . . . . . . . . . . . . . . . . . • (up) 5. RPM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . increase, in order to prevent ice build-up on the propeller blades 6. Alternate Air . . . . . . . . . . . . . . . . . . . . . . . . . OPEN 7. Emergency window(s) . . . . . . . . . . . . . . . . . open if required CAUTION Ice build-up increases the stalling speed. If required for safety reasons, engine speeds up to 2700 RPM are admissible without time limit. 8. ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . advise if an emergency is expected CAUTION When the Pitot heating fails, and the alternate static valve is installed: Alternate static valve . . . . . . . . . . . . OPEN Emergency window(s) . . . . . . . . . . . close Emergency Procedures DA 40 AFM Page 3 - 32 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.7.2 FAILURES IN THE ELECTRICAL SYSTEM (a) Complete failure of the electrical system Due to the strong mechanical design as well as due to the required check of the system during scheduled inspections, a total failure of the electrical system is extremely unlikely. If, nevertheless, a total failure should occur, all circuit breakers should be checked, pulled and re-set. If this does not help: - Set emergency switch to ON (if installed). - When necessary, use the flood light for lighting the instruments as well as levers and switches, etc. - Set power based on lever positions and engine noise. - Prepare landing with flaps in the given position. - Land on the nearest appropriate airfield. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 33 (b) Alternator failure An alternator failure is indicated by an illuminated or flashing alternator warning light (ALT or ALTERNATOR) on the annunciator panel and a flashing ammeter on the Vision Microsystems VM 1000 engine instrument. 1. Circuit breakers . . . . . . . . . . . . . . . . . . . . . check; if all are O.K., proceed with step 2 2. Electrical equipment . . . . . . . . . . . . . . . . . . switch OFF all equipment which is not needed 3. Voltmeter . . . . . . . . . . . . . . . . . . . . . . . . . . . check regularly CAUTION Those items of equipment which are not needed for the safe operation and secure landing of the airplane can be switched off with the Essential Bus Switch (if installed). When the Essential Bus is switched ON, only the following items of equipment are supplied with power: - NAV/COM 1 - transponder (XPDR) - flood light - attitude gyro (artificial horizon) - VM 1000 engine instrument - annunciator panel - GPS (if installed) - landing light - Pitot heating system - flaps Emergency Procedures DA 40 AFM Page 3 - 34 Revision 7 15-Jul-2006 Doc. # 6.01.01-E These items of equipment can be supplied with power by the battery for at least 30 minutes. Economical use, in particular of the Pitot heating, and switching off equipment that is not needed extends the time during which the other equipment remains available. During the 30 minutes period, the airplane must be landed at a suitable airfield. For cases in which the battery capacity is not sufficient to reach a suitable airfield, an emergency battery is installed in the IFR model, serving as an additional back-up system for the attitude gyro (artificial horizon) and flood light. This battery is switched on with the Emergency Switch. It lasts for 1 hour and 30 minutes when the flood light is switched on. (c) Starter malfunction If the starter does not disengage from the engine after starting (starter warning light (START) on the annunciator panel remains illuminated or flashing after the engine has started): 1. Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. Mixture control lever . . . . . . . . . . . . . . . . . . LEAN - shut off engine 3. Ignition switch . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Master switch . . . . . . . . . . . . . . . . . . . . . . . . OFF Terminate flight preparation! DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 35 (d) Overvoltage If a voltage in the upper red sector (above 32 volts) is indicated: 1. Essential bus . . . . . . . . . . . . . . . . . . . . . . . . ON, if installed 2. Master switch (ALT) . . . . . . . . . . . . . . . . . . OFF WARNING Leave master switch (BAT) ON! 3. Equipment that is not needed, in particular Pitot heating . . . . . . . . . . . . . . . OFF 4. Land on the nearest appropriate airfield. Emergency Procedures DA 40 AFM Page 3 - 36 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 3.7.3 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN Carbon monoxide (CO) is a gas which is developed during the combustion process. It is poisonous and without smell. Since it occurs however usually together with flue gases, it can be detected. Increased concentration of carbon monoxide in closed spaces can be fatal. The occurrence of CO in the cabin is possible only due to a defect. If a smell similar to exhaust gases is noticed in the cabin, the following measures should be taken: 1. Cabin heat . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. Ventilation . . . . . . . . . . . . . . . . . . . . . . . . . . open 3. Emergency window(s) . . . . . . . . . . . . . . . . . open 4. Forward canopy . . . . . . . . . . . . . . . . . . . . . . open CAUTION In case of suspicion of carbon monoxide contamination in the cabin, 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. DA 40 AFM Emergency Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 3 - 37 3.7.4 'DOOR'-WARNING LIGHT ON % 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . reduce % 2. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . . check visually if closed % 3. Rear passenger door . . . . . . . . . . . . . . . . . . check visually if closed % % WARNING % Never unlock the rear passenger door during flight. It may % break away. % % 4. If it is not possible to lock the canopy or the rear passenger door, land on % the nearest suitable airfield. % % 3.7.5 EMERGENCY EXIT % In case of a roll-over of the airplane on ground, it can be evacuated through the rear door. % For this purpose release the front hinge of the rear door. The function is displayed on a % placard next to the hinge. % Emergency Procedures DA 40 AFM Page 3 - 38 Revision 7 15-Jul-2006 Doc. # 6.01.01-E Intentionally left blank. DA 40 AFM Normal Operating Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 4A - 1 CHAPTER 4A NORMAL OPERATING PROCEDURES Page 4A.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-2 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES . . . . 4A-2 4A.3 CHECKLISTS FOR NORMAL OPERATING PROCEDURES . . . 4A-3 4A.3.1 PRE-FLIGHT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . 4A-3 4A.3.2 BEFORE STARTING ENGINE . . . . . . . . . . . . . . . . . . . . 4A-11 4A.3.3 STARTING ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-13 4A.3.4 BEFORE TAXIING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-19 4A.3.5 TAXIING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-20 4A.3.6 BEFORE TAKE-OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-22 4A.3.7 TAKE-OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-25 4A.3.8 CLIMB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-26 4A.3.9 CRUISE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-28 4A.3.10 MIXTURE ADJUSTMENT . . . . . . . . . . . . . . . . . . . . . . 4A-30 4A.3.11 DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-32 4A.3.12 LANDING APPROACH . . . . . . . . . . . . . . . . . . . . . . . . 4A-33 4A.3.13 GO-AROUND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-35 4A.3.14 AFTER LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-35 4A.3.15 ENGINE SHUT-DOWN . . . . . . . . . . . . . . . . . . . . . . . . 4A-36 4A.3.16 POST-FLIGHT INSPECTION . . . . . . . . . . . . . . . . . . . . 4A-37 4A.3.17 FLIGHT IN RAIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-38 4A.3.18 REFUELING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A-38 4A.3.19 FLIGHT AT HIGH ALTITUDE . . . . . . . . . . . . . . . . . . . . 4A-38 Normal Operating Procedures DA 40 AFM Page 4A - 2 Revision 7 15-Jul-2006 Doc. # 6.01.01-E 4A.1 INTRODUCTION Chapter 4A contains checklists and describes extended procedures for the normal operation of the airplane. 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES Flight mass Event % 850 kg 1874 lb 1000 kg 2205 lb 1150 kg 2535 lb Airspeed for take-off climb (best rate-of-climb speed v Y) (Flaps T/O) 54 KIAS 60 KIAS 66 KIAS Airspeed for cruise climb (Flaps UP) 60 KIAS 68 KIAS 73 KIAS Approach speed for normal landing (Flaps LDG) 58 KIAS 63 KIAS 71 KIAS Minimum speed during touch & go (Flaps T/O) 54 KIAS 60 KIAS 66 KIAS DA 40 AFM Normal Operating Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 4A - 3 4A.3 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A.3.1 PRE-FLIGHT INSPECTION I. Cabin check a) MET, NAV, Mass & CG . . . . . . . . . . . . . . . . . flight planning completed b) Airplane documents . . . . . . . . . . . . . . . . . . . complete and up-to-date c) Ignition key . . . . . . . . . . . . . . . . . . . . . . . . . . pulled out d) Front canopy & rear door . . . . . . . . . . . . . . . clean, undamaged, check locking mechanism function e) All electrical equipment . . . . . . . . . . . . . . . . . OFF f) Circuit breakers . . . . . . . . . . . . . . . . . . . . . . . set in (if one has been pulled, check reason) g) Engine control levers . . . . . . . . . . . . . . . . . . . check condition, freedom of movement and full travel of throttle, RPM and mixture levers h) Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE i) Mixture control lever . . . . . . . . . . . . . . . . . . . LEAN j) RPM lever . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH RPM k) Master switch (BAT) . . . . . . . . . . . . . . . . . . . ON l) Annunciator panel . . . . . . . . . . . . . . . . . . . . . check function (see 7.11) m) Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . check % Normal Operating Procedures DA 40 AFM Page 4A - 4 Revision 7 15-Jul-2006 Doc. # 6.01.01-E NOTE Standard Tank: % Depending on the type of fuel probes installed, the indicator % can read a maximum of 15 US gal or 17 US gal (refer to % Section 7.10 for details). When the fuel quantity indicator % reads the maximum amount of fuel detectable, the correct % fuel quantity must be determined with the fuel quantity measuring device. If this measurement is not carried out, the fuel quantity available for flight planning is the indicated % amount. % Long Range Tank: % At an indication of 16 US gal the quantity of auxiliary fuel can % be determined by switching the AUX FUEL QTY switch to the % respective position (LH or RH). The auxiliary fuel quantity is % added to the 16 US gal. % An auxiliary fuel quantity of less than 3 US gal cannot be % indicated by the system. In this case the quantity must be % determined by means of the fuel quantity measuring device % (see Section 7.10 FUEL SYSTEM). % % CAUTION % Long Range Tank: % The correct indication of the fuel quantity takes 2 minutes after % actuation of the switch. % DA 40 AFM Normal Operating Procedures Doc. # 6.01.01-E Revision 7 15-Jul-2006 Page 4A - 5 n) Position lights, strobe lights (ACL's) . . . . . . . check o) Master switch (BAT) . . . . . . . . . . . . . . . . . . . OFF p) Check for loose items . . . . . . . . . . . . . . . . . . complete q) Flight controls and trim . . . . . . . . . . . . . . . . . free to move and correct r) Baggage . . . . . . . . . . . . . . . . . . . . . . . . . . . . stowed and secure % II. Walk-around check, visual inspection CAUTION A visual inspection means: examination for damage, cracks, delamination, excessive play, load transmission, correct attachment and general condition. In addition control surfaces should be checked for freedom of movement. CAUTION In low ambient temperatures the airplane must be completely % cleared of ice, snow and similar accumulations. For approved % de-icing fluids refer to Section 8.6 DE-ICING ON THE % GROUND. % CAUTION Prior to flight, remove such items as control surfaces gust lock, Pitot cover, tow bar, etc

All Diamond DA40 NG pilot's operating handbook