DA 42 NG AFM
Diamond DA42 VI · Pilot's Operating Handbook
Overview
The DA 42 NG Airplane Flight Manual (AFM) is designed to provide pilots and instructors with essential information for the safe and efficient operation of the Diamond DA 42 NG aircraft. This manual includes operational limitations, emergency procedures, normal and abnormal operating procedures, performance data, mass and balance information, and a description of the airplane and its systems. It is crucial for pilots to familiarize themselves with the contents of this manual before operating the aircraft, as it contains vital safety and operational guidelines. The manual is applicable to DA 42 NG airplanes with specific design changes and modifications, which may vary between individual aircraft. The AFM is a comprehensive resource that ensures pilots have the necessary information to operate the aircraft safely under various conditions.
- Maximum Take-Off Weight: 1999 kg (4409 lbs)
- Maximum Landing Mass: 1999 kg (4409 lbs)
- Engine Type: Diesel engine with specific software versions
- Wing Span: 13.42 m (44 ft)
- Stalling Speed (V_S): Specific values vary based on configuration
Document
Source
Originally published by dieflugschule.at. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Pilot's Operating Handbook
- Year
- 2017
- Pages
- 464
- File size
- 2.7 MB
- Publisher
- dieflugschule.at
Common. Rarer than 1% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Diamond DA42 VI.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
General
This section introduces the DA 42 NG AFM, emphasizing the importance of familiarization with the manual for safe operation. It outlines the certification basis under JAR-23 and provides details on the modifications applicable to specific aircraft serial numbers. The section also highlights the necessity of keeping the AFM on board the aircraft at all times.
Operating Limitations
This chapter details the operational limits of the DA 42 NG, including maximum take-off and landing weights, and other critical performance parameters. It is essential for pilots to adhere to these limitations to ensure safe flight operations.
Emergency Procedures
This section outlines the procedures to follow in various emergency situations, ensuring pilots are prepared to handle unexpected events during flight. It includes checklists and guidelines for effective emergency response.
Normal Operating Procedures
This chapter provides the standard operating procedures for the DA 42 NG, including pre-flight checks, take-off, cruising, and landing protocols. Following these procedures is vital for safe and efficient flight operations.
Performance
This section includes performance data for the DA 42 NG, such as climb rates, fuel consumption, and other critical performance metrics that pilots need to consider during flight planning.
Mass and Balance / Equipment List
This chapter provides information on the mass and balance calculations necessary for safe flight operations, along with 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 DA 42 NG, including avionics, propulsion, and control systems, providing pilots with a comprehensive understanding of the aircraft's capabilities.
Safety notes
- An engine failure is possible; select flight routes to mitigate risks during single-engine operation.
- Always keep the AFM on board the aircraft.
Full document text
DA 42 NG AFM Introduction Page 0 - 0a Rev. 4 02-Oct-2017 Doc. # 7.01.16-E Intentionally left blank. DA 42 NG AFM Introduction Doc. # 7.01.16-E Rev. 4 02-Oct-2017 Page 0 - 1 FOREWORD We congratulate you on the acquisition of your new DIAMOND DA 42 NG. 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 DA 42 NG. 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 DA 42 NG 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 42 NG AFM Page 0 - 2 Rev. 4 02-Oct-2017 Doc. # 7.01.16-E 0.1 APPROVAL The content of approved chapters is approved by EASA. All other content is approved by DAI under the authority of EASA DOA No. EASA.21J.052 in accordance with Part 21. 0.2 RECORD OF REVISIONS All revisions of this manual, with the exception of - • Temporary Revisions, • updates of the modification level (Section 1.1), • updated mass and balance information (Section 6.3), • updates of the Equipment Inventory (Section 6.5), and • updates of the List of Supplements (Section 9.2) must be recorded in the following table. The new or amended text is indicated by a vertical black line at the left hand side of the revised page, with the revision number and date appearing at the bottom of the page. If pages are revised which contain information valid for your particular serial number (modification level of the airplane, weighing data, Equipment Inventory, List of Supplements), then this information must be transferred to the new pages in hand-writing. The cover pages of Temporary Revisions, if applicable, are inserted behind the cover page of this manual. Temporary Revisions are used to provide information on systems or equipment until the next 'permanent' Revision of the Airplane Flight Manual. When a 'permanent' Revision covers a Mandatory or Optional Design Change Advisory (MÄM or OÄM), then the corresponding Temporary Revision is superseded. For example: If Revision 5 covers OÄM 42-039, then the Temporary Revision TR OÄM-42-039 is superseded by the 'permanent' Revision 5. DA 42 NG AFM Introduction Doc. # 7.01.16-E Rev. 4 02-Oct-2017 Page 0 - 3 Rev. No. Reason Chap- ter Page(s) Date of Revision EASA Approval No. Approval Date Date Inserted Signature 1 FAA- Approval 0 0-0, 0-0a, 0-3, 0-4 19-Jun-2012 Revision 1 of the AFM Doc. No. 7.01.16-E is approved by EASA under Project No. 0010016964. 27-Jul-2012 2 MÄM 42-654, 42-685, 42-696, 42-701, 42-757, 42-778, 42-785 OÄM 42-055, 42-056, 42-094, 42-119, 42-160/a, 42-179, 42-199, 42-203, 42-204/a & 42- 193/a, 42-213, 42-222, 42-224, 42-226, 42-251 Corrections All All except Cover Page 28-Feb-2014 Revision 2 of the AFM Doc. No. 7.01.16-E is approved under the authority of DOA No. EASA.21J.052 18-Mar-2014 3 MÄM 42-659, 42-678, 42-759 OÄM 42-253, 42-260 Corrections All All except Cover Page 01-Apr-2014 Revision 3 of the AFM Doc. No. 7.01.16-E is approved by EASA with Approval No.10048945. 05-May-2014 ' Introduction DA 42 NG AFM Rev. No. Reason Chap- ter Page(s) Date of Revision EASA Approval No. Approval Date Date Inserted Signature Page 0 - 4 Rev. 4 02-Oct-2017 Doc. # 7.01.16-E 4 ' MÄM 42- ' -600, -744, -756, ' -828 & -760, ' -855, -868, -885, ' -938/b, -942, -973, ' -976, -978, -995, ' -1005, .-1030, ' ' OÄM 42- ' -111/a & -158/a & ' -246, -160/b ' -168, -169, -170, ' -173, -178, -194, ' -208, -209, -213/a, ' -218, -228, -240, ' -241, -247, -250, ' -255, - 257, -259, ' -267, -270, -273, ' -277, -279, -281, ' -283, -287, -288, ' -298, -301, -304, ' ' Corrections ' All ' All except Cover ' Page ' 02-Oct-2017 ' Revision 4 of ' the AFM ' Doc. No. ' 7.01.16-E is ' approved ' under the ' authority of ' DOA No. ' EASA.21J.052 ' 27-Oct-2017 ' '' DA 42 NG AFM Introduction Doc. # 7.01.16-E Rev. 4 02-Oct-2017 Page 0 - 5 0.3 LIST OF EFFECTIVE PAGES Ch. Page Date 0 0-0 19-Jun-2012 0-0a 02-Oct-2017 ' 0-1 02-Oct-2017 ' 0-2 02-Oct-2017 ' 0-3 02-Oct-2017 ' 0-4 02-Oct-2017 ' 0-5 02-Oct-2017 ' 0-6 02-Oct-2017 ' 0-7 02-Oct-2017 ' 0-8 02-Oct-2017 ' 0-9 02-Oct-2017 ' 0-10 02-Oct-2017 ' 0-11 02-Oct-2017 ' 0-12 02-Oct-2017 ' 0-13 02-Oct-2017 ' 0-14 02-Oct-2017 ' 0-15 02-Oct-2017 ' 0-16 02-Oct-2017 ' Ch. Page Date 1 1-1 02-Oct-2017 ' 1-2 02-Oct-2017 ' 1-3 02-Oct-2017 ' 1-4 02-Oct-2017 ' 1-5 02-Oct-2017 ' 1-6 02-Oct-2017 ' 1-7 02-Oct-2017 ' 1-8 02-Oct-2017 ' 1-9 02-Oct-2017 ' 1-10 02-Oct-2017 ' 1-11 02-Oct-2017 ' 1-12 02-Oct-2017 ' 1-13 02-Oct-2017 ' 1-14 02-Oct-2017 ' 1-15 02-Oct-2017 ' 1-16 02-Oct-2017 ' 1-17 02-Oct-2017 ' 1-18 02-Oct-2017 ' 1-19 02-Oct-2017 ' 1-20 02-Oct-2017 ' 1-21 02-Oct-2017 ' 1-22 02-Oct-2017 ' 1-23 02-Oct-2017 ' 1-24 02-Oct-2017 ' Introduction DA 42 NG AFM Page 0 - 6 Rev. 4 02-Oct-2017 Doc. # 7.01.16-E Ch. Page Date 2 appr. 2-1 02-Oct-2017 ' appr. 2-2 02-Oct-2017 ' appr. 2-3 02-Oct-2017 ' appr. 2-4 02-Oct-2017 ' appr. 2-5 02-Oct-2017 ' appr. 2-6 02-Oct-2017 ' appr. 2-7 02-Oct-2017 ' appr. 2-8 02-Oct-2017 ' appr. 2-9 02-Oct-2017 ' appr. 2-10 02-Oct-2017 ' appr. 2-11 02-Oct-2017 ' appr. 2-12 02-Oct-2017 ' appr. 2-13 02-Oct-2017 '
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Page Date 7 7-1 02-Oct-2017 ' 7-2 02-Oct-2017 ' 7-3 02-Oct-2017 ' 7-4 02-Oct-2017 ' 7-5 02-Oct-2017 ' 7-6 02-Oct-2017 ' 7-7 02-Oct-2017 ' 7-8 02-Oct-2017 ' 7-9 02-Oct-2017 ' 7-10 02-Oct-2017 ' 7-11 02-Oct-2017 ' 7-12 02-Oct-2017 ' 7-13 02-Oct-2017 ' 7-14 02-Oct-2017 ' 7-15 02-Oct-2017 ' 7-16 02-Oct-2017 ' 7-17 02-Oct-2017 ' 7-18 02-Oct-2017 ' DA 42 NG AFM Introduction Doc. # 7.01.16-E Rev. 4 02-Oct-2017 Page 0 - 13 Ch. Page Date 7 7-19 02-Oct-2017 ' 7-20 02-Oct-2017 ' 7-21 02-Oct-2017 ' 7-22 02-Oct-2017 ' 7-23 02-Oct-2017 ' 7-24 02-Oct-2017 ' 7-25 02-Oct-2017 ' 7-26 02-Oct-2017 ' 7-27 02-Oct-2017 ' 7-28 02-Oct-2017 ' 7-29 02-Oct-2017 ' 7-30 02-Oct-2017 ' 7-31 02-Oct-2017 ' 7-32 02-Oct-2017 ' 7-33 02-Oct-2017 ' 7-34 02-Oct-2017 ' 7-35 02-Oct-2017 ' 7-36 02-Oct-2017 ' 7-37 02-Oct-2017 ' 7-38 02-Oct-2017 ' 7-39 02-Oct-2017 ' 7-40 02-Oct-2017 ' 7-41 02-Oct-2017 ' 7-42 02-Oct-2017 ' 7-43 02-Oct-2017 ' 7-44 02-Oct-2017 ' 7-45 02-Oct-2017 ' Ch. Page Date 7 7-46 02-Oct-2017 ' 7-47 02-Oct-2017 ' 7-48 02-Oct-2017 ' 7-49 02-Oct-2017 ' 7-50 02-Oct-2017 ' 7-51 02-Oct-2017 ' 7-52 02-Oct-2017 ' 7-53 02-Oct-2017 ' 7-54 02-Oct-2017 ' 7-55 02-Oct-2017 ' 7-56 02-Oct-2017 ' 7-57 02-Oct-2017 ' 7-58 02-Oct-2017 ' 7-59 02-Oct-2017 ' 7-60 02-Oct-2017 ' 7-61 02-Oct-2017 ' 7-62 02-Oct-2017 ' 7-63 02-Oct-2017 ' 7-64 02-Oct-2017 ' 7-65 02-Oct-2017 ' 7-66 02-Oct-2017 ' 7-67 02-Oct-2017 ' 7-68 02-Oct-2017 ' 7-69 02-Oct-2017 ' 7-70 02-Oct-2017 ' 7-71 02-Oct-2017 ' 7-72 02-Oct-2017 ' Introduction DA 42 NG AFM Page 0 - 14 Rev. 4 02-Oct-2017 Doc. # 7.01.16-E Ch. Page Date 7 7-73 02-Oct-2017 ' 7-74 02-Oct-2017 ' 7-75 02-Oct-2017 ' 7-76 02-Oct-2017 ' 7-77 02-Oct-2017 ' 7-78 02-Oct-2017 ' 7-79 02-Oct-2017 ' 7-80 02-Oct-2017 ' 7-81 02-Oct-2017 ' 7-82 02-Oct-2017 ' 7-83 02-Oct-2017 ' 7-84 02-Oct-2017 ' Ch. Page Date 8 8-1 02-Oct-2017 ' 8-2 02-Oct-2017 ' 8-3 02-Oct-2017 ' 8-4 02-Oct-2017 ' 8-5 02-Oct-2017 ' 8-6 02-Oct-2017 ' 8-7 02-Oct-2017 ' 8-8 02-Oct-2017 ' 8-9 02-Oct-2017 ' 8-10 02-Oct-2017 ' 8-11 02-Oct-2017 ' 8-12 02-Oct-2017 ' 8-13 02-Oct-2017 ' 8-14 02-Oct-2017 ' 8-15 02-Oct-2017 ' 8-16 02-Oct-2017 ' Ch. Page Date 9 9-1 02-Oct-2017 ' 9-2 02-Oct-2017 ' 9-3 ' 02-Oct-2017 ' 9-4 ' 02-Oct-2017 ' 9-5 ' 02-Oct-2017 ' 9-6 ' 02-Oct-2017 ' DA 42 NG AFM Introduction Doc. # 7.01.16-E Rev. 4 02-Oct-2017 Page 0 - 15 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 OPERATING LIMITATIONS (an approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 EMERGENCY PROCEDURES (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 NORMAL OPERATING PROCEDURES (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4A ABNORMAL OPERATING PROCEDURES (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4B PERFORMANCE (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 MASS AND BALANCE / EQUIPMENT LIST (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 AIRPLANE HANDLING, CARE AND MAINTENANCE (a non-approved chapter) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 SUPPLEMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 Introduction DA 42 NG AFM Page 0 - 16 Rev. 4 02-Oct-2017 Doc. # 7.01.16-E Intentionally left blank. DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 1 CHAPTER 1 GENERAL Page 1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2 CERTIFICATION BASIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 1.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . . 1-5 1.4 DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 1.5 DEFINITIONS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . 1-8 1.6 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-17 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 G1000 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21 1.9 SOURCE DOCUMENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23 1.9.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23 1.9.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23 1.9.3 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-24 General DA 42 NG AFM Page 1 - 2 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-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. 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 Maximum Landing Mass 1999 kg MÄM 42-659 9 yes 9 no Maximum Take-Off Weight 1999 kg and Maximum Zero Fuel Mass 1835 kg MÄM 42-678 9 yes 9 no Engine Software VC33_2_05_19* ' MÄM 42-938 ' 9 yes ' 9 no ' Garmin Hard- and Software ' Upgrade I (Garmin G1000 NXi) ' MÄM 42-978 ' 9 yes ' 9 no ' Ice Protection System OÄM 42-053 9 yes 9 no Oxygen System OÄM 42-055 9 yes 9 no Auxiliary Fuel Tanks OÄM 42-056 9 yes 9 no Front Seats with Adjustable Backrest OÄM 42-067 9 yes 9 no Electrical Rudder Pedal Adjustment OÄM 42-070 9 yes 9 no DA 42 NG AFM General Modification Source Installed Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 3 Sun Visors OÄM 42-101 OR OÄM 42-142 9 yes 9 no Garmin GWX 68 Weather Radar OÄM 42-119 9 yes 9 no Ice Protection System OÄM 42-160 9 yes 9 no Ice Protection System with TKS Tank in Rear Fuselage OÄM 42-160 AND OÄM 42-203 9 yes 9 no Garmin G1000, SBAS Operation OÄM 42-179 9 yes 9 no Removal of Variable Elevator Stop OÄM 42-199 9 yes 9 no Emergency Axe OÄM 42-205 9 yes 9 no Short Baggage Extension OÄM 42-207 9 yes 9 no Electronic Stability and Protection ' (ESP) ' OÄM 42-209 ' 9 yes ' 9 no ' Mission Alternator ' OÄM 42-218 ' 9 yes ' 9 no ' Removal of Unfeathering Accumulator OÄM 42-224 9 yes 9 no Diesel Operation OÄM 42-251 9 yes 9 no Front Seats with Adjustable ' Backrest - Hydrolok ' OÄM 42-259 ' 9 yes ' 9 no ' Maximum Take-Off Weight 2001 kg / 4411 lb OÄM 42-260 9 yes 9 no Mid Continent MD302 Standby ' Attitude Module ' OÄM 42-270 ' 9 yes ' 9 no ' Garmin GWX 70 Weather Radar ' OÄM 42-273 ' 9 yes ' 9 no ' Gear Warning Mute Function ' OÄM 42-288 ' 9 yes ' 9 no ' Emergency Egress Hammer ' OÄM 42-304 ' 9 yes ' 9 no ' * Or later approved software ' General DA 42 NG AFM Page 1 - 4 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 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. The designated place for the Garmin G1000 Cockpit Reference Guide is the bag on the rear side of the forward left seat. This Airplane Flight Manual is applicable for DA 42 NG airplanes with design change MÄM 42-600 installed. CAUTION The DA 42 NG is a twin 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 it is highly recommended for flights during the night, on top, under IMC, or above terrain which is unsuitable for a landing, to select flight times and flight routes such that reduced performance in case of single engine operation does not constitute a risk. DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 5 1.2 CERTIFICATION BASIS The certification basis is JAR-23, published on 11-Mar-1994, including Amdt. 1, and additional requirements as laid down in CRI A-01. 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. General DA 42 NG AFM Page 1 - 6 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 13.42 m 44 ft : 13.55 m 44.5 ft including ACL Length : 8.56 m 28 ft 1 in Height : 2.49 m 8 ft 2 in Wing Airfoil : Wortmann FX 63-137/20 - W4 Wing Area : 16.29 m² 175.3 sq.ft. Mean aerodynamic chord : 1.271 m 4 ft 2 in Aspect ratio : 11.06 Dihedral : 5° Leading edge sweep : 1° Aileron Area (total, left + right) : 0.66 m² 7.1 sq.ft. DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 7 Wing Flaps Area (total, left + right) : 2.18 m² 23.5 sq.ft. Horizontal Tail Area : 2.35 m 2 25.3 sq.ft. Elevator area : 0.66 m² 7.1 sq.ft. Angle of incidence : -1.1° relative to longitudinal axis of airplane Vertical Tail Area : 2.43 m² 26.2 sq.ft. Rudder area : 0.78 m² 8.4 sq.ft. Landing Gear Track : 2.95 m (9 ft 8 in) Wheelbase : 1.735 m (5 ft 8 in) Nose wheel : 5.00-5, for details refer to the AMM Main wheel : 15x6.0-6, for details refer to the AMM General DA 42 NG AFM Page 1 - 8 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 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 (ISA) at MSL. IAS: Indicated Airspeed as shown on an airspeed indicator. KCAS: CAS in knots. KIAS: IAS in knots. TAS: True Airspeed. The speed of the airplane relative to the air. TAS is CAS corrected for errors due to altitude and temperature. v O: Operating Maneuvering Speed. Full or abrupt control surface movement is not permissible above this speed. v FE: Maximum Flaps Extended Speed. This speed must not be exceeded with the given flap setting. v LE: Maximum Landing Gear Extended Speed. This speed may not be exceeded if the landing gear is extended. vLOE: Maximum Landing Gear Operating Speed for Extension. This speed may not be exceeded during the extension of the landing gear. vLOR : Maximum Landing Gear Operating Speed for Retraction. This speed may not be exceeded during the retraction of the landing gear. vMCA: Minimum Control Speed - Airborne. Minimum speed necessary to be able to control the airplane in case of one engine inoperative. vNE: Never Exceed Speed in smooth air. This speed must not be exceeded in any operation. DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 9 vNO: Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. v S: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. v S0 : Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration. v S1 : Stalling Speed, or the minimum continuous speed at which the airplane is still controllable with flaps and landing gear retracted. v SSE: Minimum Control Speed for Schooling. Minimum speed necessary in case of one engine intentionally inoperative / idle (training purposes). vx: Best Angle-of-Climb Speed. vy: Best Rate-of-Climb Speed. vYSE: Best Rate of-Climb Speed for one engine inoperative. (b) Meteorological Terms ISA: International Standard Atmosphere. Conditions at which air is identified as an ideal dry gas. The temperature at mean sea level is 15 °C (59 °F), air pressure at MSL is 1013.25 hPa (29.92 inHg); the temperature gradient up to the altitude at which the temperature reaches -56.5 °C (-69.7 °F) is -0.0065 °C/m (-0.00357 °F/ft), and above this 0 °C/m (0 °F/ft). MSL: Mean Sea Level. OAT: Outside Air Temperature. General DA 42 NG AFM Page 1 - 10 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 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. Density Altitude: Altitude in ISA conditions at which the air density is equal to the current air density. Indicated Pressure Altitude: Altitude reading with altimeter set to 1013.25 hPa (29.92 inHg). Pressure Altitude: Altitude 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. Wind: The wind speeds which are shown as variables in the diagrams and tables in this manual should be regarded as headwind or tailwind components of the measured wind. (c) Flight Performance and Flight Planning AGL: Above Ground Level. Demonstrated Crosswind Component: The speed of the crosswind component at which adequate maneuverability for take-off and landing has been demonstrated during type certification. DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 11 MET: Weather, weather advice. NAV: Navigation, route planning. RoC: Rate of Climb. (d) Mass and Balance 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. DP: Datum Plane; an imaginary vertical plane from which all horizontal distances for center of gravity calculations are measured. Empty Mass: The mass of the airplane including unusable fuel, all operating fluids and the maximum quantity of oil. Maximum Take-off Mass: The maximum permissible mass for take-off. General DA 42 NG AFM Page 1 - 12 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 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. 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. 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. Useful load: The difference between take-off mass and empty mass. (e) Engine EECU: Electr. Engine Control Unit RPM: Revolutions per minute (rotational speed of the propeller) Engine starting fuel temperature: Above this fuel temperature the engine may be started. Take-off fuel temperature: Above this fuel temperature take-off power setting is permitted. OEI: One engine inoperative DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 13 (f) Designation of the Circuit Breakers on the Instrument Panel LH MAIN BUS: COM1 COM Radio No. 1 GPS/NAV1 Global Positioning System and NAV Receiver No. 1 XPDR Transponder ENG INST Engine Instruments PITOT Pitot Heating System XFER PUMP/DE-ICE Aux Fuel Pump / De-Icing System TAXI/MAP/ACL Taxi-, Map-, Anti Collision Light FLOOD Flood Light PFD Primary Flight Display ADC Air Data Computer AHRS Attitude Heading Reference System GEAR WRN/ELEV. LIMIT Landing Gear Annunciation / Variable Elevator Stop GEAR Landing Gear Control RH MAIN BUS: MFD Multi Function Display AH Artificial Horizon / Standby Attitude Module ' STALL WRN Stall Warning System FLAP Flap System LDG LT/START Landing Light / Start INST LT/ NAV LT Instrument-, Navigation (Position) Light AV/CDU/FAN Avionic-, CDU-Cooling Fans AVIONIC BUS Avionic Bus AV CONT./AP. WRN. Avionic Control / Autopilot Warning (not used) General DA 42 NG AFM Page 1 - 14 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E AVIONICS BUS: COM2 COM Radio No. 2 GPS/NAV2 Global Positioning System and NAV Receiver No. 2 AUDIO Audio Panel AUTO PILOT Auto Pilot System Wx 500 Stormscope ADF Automatic Direction Finder DME Distance Measuring Equipment Wx RDR Weather Radar TAS Traffic Advisory System DATA LINK GDL 69A Data Link System IRIDIUM GSR 56 Satellite Receiver LH ENG ECU BUS: ECU BUS LH ECU Bus ECU B LH ECU B ECU A LH ECU A LH BUS: ALT.LH LH Alternator BATT Battery FUEL PUMPS LH ENGINE: FUEL PUMP A LH ECU A Fuel Pump FUEL PUMP B LH ECU B Fuel Pump DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 15 RH ENG ECU BUS: ECU BUS RH ECU Bus ECU B RH ECU B ECU A RH ECU A RH BUS: ALT.RH RH Alternator BATT Battery FUEL PUMPS RH ENGINE: FUEL PUMP A RH ECU A Fuel Pump FUEL PUMP B RH ECU B Fuel Pump (g) Equipment ELT: Emergency Locator Transmitter (h) Design Change Advisories MÄM: Mandatory Design Change Advisory OÄM: Optional Design Change Advisory VÄM: Variant Design Change Advisory General DA 42 NG AFM Page 1 - 16 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E (i) Miscellaneous ACG: Austro Control GmbH (Austrian Airworthiness Authority) ATC: Air Traffic Control CFRP: Carbon Fiber Reinforced Plastic EASA: European Aviation Safety Agency EPU: External Power Unit GIA: Garmin Integrated Avionics GFRP: Glass Fiber Reinforced Plastic GPS: Global Positioning System IFR: Instrument Flight Rules JAR: Joint Aviation Requirements JC/VP: Joint Certification/Validation Procedure PCA: Primary Certification Authority VFR: Visual Flight Rules DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 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 [ml] milliliter ' [US gal] US gallons [qts] US quarts [oz] ounce ' [l] / 3.7854 = [US gal] [l] / 0.9464 = [qts] [ml] x 0.033814 = [oz] ' 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] [fpm] / 196.85 = [m/s] 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] Tempera- ture [°C] degrees Celsius [°F] degrees Fahrenheit [°C]x1.8 + 32 = [°F] ([°F] - 32)/1.8 = [°C] General DA 42 NG AFM Dimension SI-Units US Units Conversion Page 1 - 18 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E Intensity of electric current [A] ampères -- Electric charge (battery capacity) [Ah] ampère-hours -- Electric potential [V] volts -- Time [sec] seconds -- DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 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 42 NG AFM Page 1 - 20 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 2205 mm (7 ft 3 in) 1950 mm (6 ft 5 in) 2490 mm (8 ft 2 in) 1735 mm (5 ft 8 in) 8560 mm (28 ft 1 in) 1900 mm (6 ft 3 in) 2950 mm (9 ft 8 in) 13420 mm (44 ft 0 in) 13550 mm (44 ft 6 in) including ACL 1.7 THREE-VIEW DRAWING DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 21 1.8 G1000 AVIONICS SYSTEM 1. The G1000 Integrated Avionics System is a fully integrated flight, engine, communication, navigation and surveillance instrumentation system. The system consists of a Primary Flight Display (PFD), Multi-Function Display (MFD), audio panel, Air Data Computer (ADC), Attitude and Heading Reference System (AHRS), engine sensors and processing unit (GEA), and integrated avionics (GIA) containing VHF communications, VHF navigation, and GPS (Global Positioning System). 2. The primary function of the PFD is to provide attitude, heading, air data, navigation, and alerting information to the pilot. The PFD may also be used for flight planning. The primary function of the MFD is to provide engine information, mapping, terrain information, autopilot operation, and for flight planning. The audio panel is used for selection of radios for transmitting and listening, intercom functions, and marker beacon functions. 3. The primary function of the VHF Communication portion of the G1000 is to enable external radio communication. The primary function of the VOR/ILS Receiver portion of the equipment is to receive and demodulate VOR, Localizer, and Glide Slope signals. The primary function of the GPS portion of the system is to acquire signals from the GPS satellites, recover orbital data, make range and Doppler measurements, and process this information in real-time to obtain the user's position, velocity, and time. General DA 42 NG AFM Page 1 - 22 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 4. If the Garmin GWX 68 or the GWX 70 weather radar system is installed, it can be used ' to aid the pilot in avoiding thunderstorms and associated turbulence or for ground mapping. The GWX 68 and the GWX 70 shall be used to avoid severe weather and ' not for penetrating severe weather. Pulse type weather radar systems like the GWX 68 and the GWX 70 detect precipitation only, not clouds or turbulence. The display may ' indicate clear areas between intense returns, but this does not necessarily mean it is safe to fly between them. As installed on the DA 42 NG, the Garmin GWX 68 and ' the GWX 70 has a demonstrated range of 160 nautical miles. Refer to Garmin G1000 ' Pilot's Guide for the DA 42 NG, P/N 190-00962-( ) for Garmin G1000 or ' P/N 190-02237-( ) for G1000 NXi in the latest effective issue for further information. ' 5. If OÄM 42-257 (Garmin GTX 33 ES transponder) and MÄM 42-828 (G1000 Software ' P/N 010-00670-12) are implemented, the installed ADS-B Out system is compliant ' to TSO-C166b / RTCA DO-206B. This constitutes no airworthiness approval. ' DA 42 NG AFM General Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 1 - 23 1.9 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. 1.9.1 ENGINE Address: Austro Engine GmbH Rudolf Diesel-Str. 11 A-2700 Wiener Neustadt AUSTRIA Phone: +43-2622-23 000 Fax: +43-2622-23 000 - 2711 Internet: www.austroengine.at Documents: Operation Manual, E4.01.01, latest revision ' 1.9.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 Atting GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Website: www.mt-propeller.de Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 General DA 42 NG AFM Page 1 - 24 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 1.9.3 AVIONICS SYSTEM Address: Garmin International, Inc. 1200 East 151st Street Olathe, Kansas 66062 USA Phone: +1-(913)-3978200 Fax: +1-(913)-3978282 Website: www.garmin.com Documents: G1000 Cockpit Reference Guide P/N 190-00963-( ), latest revision ' G1000 Pilot’s Guide P/N 190-00962-( ), latest revision ' G1000 Nxi Cockpit Reference Guide ' P/N 190-02238-( ), latest revision ' G1000 NXi Pilot’s Guide ' P/N 190-02237-( ), latest revision ' DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 1 CHAPTER 2 OPERATING LIMITATIONS Page 2.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 2.2 AIRSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 2.3 AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2.4 POWER-PLANT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2.5 ENGINE INSTRUMENT MARKINGS . . . . . . . . . . . . . . . . . . . . . . . 2-12 2.6 WARNING, CAUTION AND ADVISORY ALERTS . . . . . . . . . . . . . 2-14 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 2.6.2 OTHER WARNING ALERTS . . . . . . . . . . . . . . . . . . . . . . . . 2-18 2.7 MASS (WEIGHT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19 2.8 CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 2.9 APPROVED MANEUVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 2.10 MANEUVERING LOAD FACTORS . . . . . . . . . . . . . . . . . . . . . . . . 2-24 2.11 OPERATING ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25 2.12 FLIGHT CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25 2.13 KINDS OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25 2.14 FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-29 2.15 LIMITATION PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 2.16 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38 2.16.1 FUEL TEMPERATURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38 2.16.2 BATTERY CHARGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38 2.16.3 EMERGENCY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38 2.16.4 DOOR LOCKING DEVICE . . . . . . . . . . . . . . . . . . . . . . . . . 2-38 2.16.5 ELECTRONIC EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . 2-39 Operating Limitations DA 42 NG AFM Page 2 - 2 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.16.6 GARMIN G1000 AVIONICS SYSTEM . . . . . . . . . . . . . . . 2-40 2.16.7 AUTOPILOT LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . 2-45 2.16.8 SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-47 2.16.9 GROUND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . 2-47 2.16.10 USE OF THE SUN VISORS . . . . . . . . . . . . . . . . . . . . . . . 2-47 2.16.11 GARMIN GWX 68 / GWX 70 WEATHER RADAR OPERATION ' . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-47 2.16.12 MID CONTINENT MD302 STANDBY ATTITUDE MODULE ' . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-47 DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 3 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual provides operating limitations, instrument markings and placards necessary for the safe operation of the airplane, its powerplants, 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. NOTE Exceeding the operating limitations related to physical properties of the airplane (e.g. speeds, load factors, weights...) requires unscheduled maintenance prior to further operation. Operating Limitations DA 42 NG AFM Page 2 - 4 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.2 AIRSPEED Airspeed KIAS Remarks vO Operating maneuvering speed above 1800 kg (3968 lb) 122 KIAS Do not make full or abrupt control surface movement above this speed. above 1700 kg (3748 lb) to 1800 kg (3968 lb) 119 KIAS up to 1700 kg (3748 lb) 112 KIAS v FE Max. flaps extended speed LDG 113 KIAS Do not exceed these speeds with the given flap setting. APP 133 KIAS v LO Max. landing gear operating speed Extension v LOE 188 KIAS Do not operate the landing gear above this speed. Retraction v LOR 152 KIAS v LE Max. landing gear extended speed 188 KIAS Do not exceed this speed with the landing gear extended. vMCA Minimum control speed airborne APP 68 KIAS With one engine inoperative, keep airspeed above this limit. UP 71 KIAS v NO Max. structural cruising speed 151 KIAS Do not exceed this speed except in smooth air, and then only with caution. vNE Never exceed speed in smooth air 188 KIAS Do not exceed this speed in any operation. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 5 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White arc 62 - 113 KIAS If MÄM 42-678 is carried out: 64 - 113 KIAS Operating range with flaps fully extended. Green arc 68 - 151 KIAS If MÄM 42-678 is carried out: 72 - 151 KIAS Normal operating range. Yellow arc 151 - 188 KIAS ‘Caution’ range - “Only in smooth air”. Blue radial 85 KIAS Best rate of climb speed, single engine. Red radial 71 KIAS Minimum control speed, single engine. Red radial 188 KIAS Maximum speed for all operations - v NE. Operating Limitations DA 42 NG AFM Page 2 - 6 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.4 POWER-PLANT LIMITATIONS a) Number of engines : 2 b) Engine manufacturer : Austro Engine c) Engine designation : E4-C d) RPM limitations (shown as propeller RPM) Maximum take-off (rpm) : 2300 RPM Maximum continuous (rpm) : 2300 RPM Maximum overspeed : 2500 RPM max. 20 sec e) Engine power Max. take-off power : 100% (123.5 kW) max. 5 min Max. continuous power : 92% (114 kW) f) Oil pressure (absolute) Minimum < 1500 RPM : 0.9 bar Minimum >= 1500 RPM : 2.5 bar Maximum : 6.5 bar Normal range : 2.5 bar - 6 bar g) Oil quantity Minimum : 5.0 l Maximum : 7.0 l Maximum oil consumption : 0.1 liter/hr DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 7 h) Oil temperature Minimum : - 30 °C Maximum : 140 °C Normal range : 50 °C - 135 °C i) Gearbox temperature Minimum : - 30 °C Minimum (full load) : 35 °C Maximum : 120 °C NOTE A cautionary (yellow) gearbox temperature range is not imposed by the engine manufacturer. However, there is a delay between power changes and gearbox temperature. Therefore, a cautionary range has been added to the G1000 gearbox temperature instrument solely to make the pilot attentive to the gearbox temperature approaching the maximum allowable limit. There is no specific time limit associated with operating in the cautionary gearbox temperature range. j) Coolant temperature Minimum (at start-up) : - 30 °C Minimum (full load) : 60 °C Maximum : 105 °C Operating Limitations DA 42 NG AFM Page 2 - 8 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E k) Fuel temperature Minimum : - 30 °C Maximum : 60 °C l) Fuel pressure Minimum : 4 bar Maximum : 7 bar NOTE The fuel pressure is not indicated on the G1000; a fuel pressure warning will illuminate on the PFD if the pressure is below limit. m)Voltage Minimum : 24.1 V Maximum : 32.0 V n) Amperage Maximum : 70 A o) Propeller manufacturer : mt-Propeller p) Propeller designation : MTV-6-R-C-F / CF 190-69 q) Propeller diameter : 190 cm r) Prop. pitch angle (@ 0.75 R) : 13° ± 0.2° (low pitch) 80° ± 1° (feathered position) s) Governor : mt-Propeller P-877-16 electrical governor with feather position DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 9 t) Oil specification : SAE Grade 5W-30: SHELL HELIX ULTRA ADDINOL SUPER POWER MV 0537 BP VISCO 5000 ' REPSOL ELITE COMMON RAIL ' GULF FORMULA GMX AEROSHELL Oil Diesel Ultra CASTROL Edge 5W-30 A3 CASTROL Edge Professional A3 G-Energy F Synth TOTAL Quartz 9000 Energy SAE Grade 5W-40: SHELL HELIX ULTRA LIQUI MOLY LEICHTLAUF HIGH TECH ' MEGOL MOTORENOEL HIGH CONDITION PETRONAS Syntium 3000 LUKOIL LUXE SYNTHETIC CASTROL Edge Professional A3 CASTROL Magnatec Professional A3 VALVOLINE SynPower HST VALVOLINE SynPower GULF Formula GX AUSTRO ENGINE Aero ' produced by Liqui Moly ' recommended by Austro Engine GmbH ' SAE Grade 0W-40: CASTROL SLX PROFESSIONAL LONGTEC CASTROL Edge 0W-40 A3/B4 CASTROL Edge Professional A3 SHELL Helix Ultra Operating Limitations DA 42 NG AFM Page 2 - 10 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E CAUTION Only engine oils conforming to MB 229.5 specification are approved by Austro Engine GmbH to be used for operation. Use only one type of approved E4 engine oil for an oil change. NOTE It is not recommended to mix different SAE grades. u) Gearbox oil (propeller gearbox) : SHELL SPIRAX GSX 75W-80 SHELL SPIRAX S6 GXME 75W-80 v) Coolant : Distilled water / cooler protection (BASF Glysantin Protect Plus / G48) 1/1. The freezing point of the coolant is - 38°C. CAUTION If the coolant or gearbox oil level is low the reason must be determined and the problem must be corrected by authorized personnel. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 11 w) Maximum restart altitude : 18,000 ft pressure altitude for immediate restarts 10,000 ft pressure altitude for restarts within two minutes If MÄM 42-938 (engine software ' VC33_2_05_19 or later approved ' software) is installed : 15,000 ft pressure altitude ' for immediate restarts ' Up to 10,000 ft pressure altitude: ' OAT Max. engine ' OFF time ' [° C] ' [° F] ' [minutes] ' below -15 ' below 5 ' 2 ' -15 to -5 ' 5 to 23 ' 5 ' above -5 ' above 23 ' 10 ' x) Restart airspeed (starter) : max. 100 KIAS or airspeed for a stationary propeller, whichever is lower Restart airspeed (windmilling) : 125 KIAS to 145 KIAS y) No intentional shutdown below 3,000 ft AGL and above 10,000 ft pressure altitude. Operating Limitations DA 42 NG AFM Page 2 - 12 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below. Indi- cation Red arc/bar = lower prohibited range Yellow arc/bar = caution range Green arc/bar = normal operating range Yellow arc/bar = caution range Red arc/bar = upper prohibited range RPM -- -- up to 2300 RPM -- above 2300 RPM Oil pressure below 0.9 bar 0.9 to 2.5 bar 2.5 to 6.0 bar 6.0 to 6.5 bar above 6.5 bar Oil temp. below -30°C -30° to 50°C 50° to 135°C 135° to 140°C above 140°C Coolant temp. below -30°C -30° to 60°C 60° to 95°C 95° to 105°C above 105°C Gearbox temp. below -30°C -30° to 35°C 35° to 115°C 115° to 120°C above 120°C Load -- -- up to 92% 92 - 100% -- Fuel *1) ' temp. ' below -30°C -30° to -20°C -20° to 55°C 55° to 60°C above 60°C Fuel *2) ' temp. ' below -30°C ' - ' -30° to 55°C ' 55° to 60°C ' above 60°C ' Ammeter -- -- up to 60A 60 to 70A above 70A Volt- meter below 24.1V 24.1 to 25V 25 to 30V 30 to 32V above 32V DA 42 NG AFM Operating Limitations 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 Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 13 Fuel qty. below 1 US gal -- 1 to 25 US gal -- -- * 1) If G1000 system software prior to P/N 010-00670-12 is installed. ' * 2) If G1000 system software P/N 010-00670-12 or later is installed. ' Operating Limitations DA 42 NG AFM Page 2 - 14 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.6 WARNING, CAUTION AND ADVISORY ALERTS 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 NOTE The alerts described in the following are displayed on the Garmin G1000. Section 7.10 includes a detailed description of the alerts. The following tables show the color and significance of the warning, caution and advisory alerts lights on the G1000. Color and Significance of the Warning Alerts on the G1000 Warning alerts (red) Meaning / Cause WARNING One of the warnings listed below is being indicated. L/R ENG TEMP Left / Right engine coolant temperature is in the upper red range (too high / >105 °C). L/R OIL TEMP Left / Right engine oil temperature is in the upper red range (too high / >140 °C). L/R OIL PRES Left / Right engine oil pressure is in the lower red range (too low / <0.9 bar). L/R FUEL TEMP Left / Right fuel temperature is in the upper red range (too high / >60 °C). L/R GBOX TEMP Left / Right engine gearbox temperature is in the upper red range (too high / >120 °C). L/R FUEL PRESS Left / Right engine fuel pressure is low. DA 42 NG AFM Operating Limitations Warning alerts (red) Meaning / Cause Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 15 L/R ALTN AMPS Left / Right engine alternator output is in the upper red range (too high / >70 Amps). L/R ENG FIRE Left / Right engine fire detected. L/R STARTER Left / Right engine starter is engaged. DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS. AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer. ALTITUDE FAIL The display system is not receiving altitude input from the air data computer. VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer. HDG The display system is not receiving valid heading input from the AHRS. WARN RAIM position warning. The nav deviation bar is removed. Red X or yellow X ' A red or yellow (if MÄM 42-978 is installed) X through any ' display field, such as com frequencies, nav frequencies, or engine data, indicates that the display field is not receiving valid data. Operating Limitations DA 42 NG AFM Page 2 - 16 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E Color and Significance of the Caution Alerts on the G1000 Caution alerts (amber) Meaning / Cause L/R ECU A FAIL A fault has occurred in the left/right engine ECU A (one reset of minor faults is possible) or ECU A is being tested during FADEC-test procedure during the 'Before Take-Off Check'. L/R ECU B FAIL A fault has occurred in the left/right engine ECU B (one reset of minor faults is possible) or ECU B is being tested during FADEC-test procedure during the 'Before Take-Off Check'. L/R FUEL LOW Left / Right main tank fuel quantity is low. L/R ALTN FAIL Left / Right engine alternator has failed. L/R VOLTS LOW Left / Right engine bus voltage is too low (< 25 Volts). L/R COOL LVL Left / Right engine coolant level is low. PITOT FAIL Pitot heat has failed. PITOT HT OFF Pitot heat is OFF. STAL HT FAIL Stall warning heat has failed. STAL HT OFF Stall warning heat is OFF. STICK LIMIT Control stick limiting system (variable elevator stop) has failed. LOI GPS integrity is insufficient for the current phase of flight. AHRS ALIGN: Keep Wings Level The AHRS (Attitude and Heading Reference System) is aligning. L/R AUX FUEL E Left / Right auxiliary fuel tank empty (if installed). DA 42 NG AFM Operating Limitations Caution alerts (amber) Meaning / Cause Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 17 CHECK GEAR Landing gear is not down and locked. DEICE LVL LO De-icing fluid level is low (if installed). DEIC PRES HI De-icing pressure is high (if installed). DEIC PRES LO De-icing pressure is low (if installed). Color and Significance of the Advisory Alerts on the G1000 Advisory alerts (white) Meaning / Cause L/R GLOW ON Left / Right engine glow plug active. L/R AUXPUMP ON Fuel transfer from auxiliary to main tank is in progress (if installed). PFD FAN FAIL Cooling fan for the PFD is inoperative. MFD FAN FAIL Cooling fan for the MFD is inoperative. GIA FAN FAIL Cooling fan for the GIAs is inoperative. Operating Limitations DA 42 NG AFM Page 2 - 18 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.6.2 OTHER WARNING ALERTS Warning Alerts on the Instrument Panel Warning alert (red) Meaning / Cause GEAR UNSAFE WARNING LIGHT Illuminates if the landing gear is neither in the final up nor in the down & locked position. Audible Warning Alerts Audible warning alert Meaning / Cause GEAR RETRACTED CHIME TONE (repeating) Resounds if the landing gear is retracted while the flaps move into position LDG or when the power lever is placed in a position below approx. 20 %. ' DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 19 2.7 MASS (WEIGHT) Value Mass (Weight) Minimum flight mass 1450 kg 3197 lb Maximum take-off mass 1900 kg 4189 lb Maximum take-off mass (if MÄM 42-678 is carried out) 1999 kg 4407 lb Maximum zero fuel mass 1765 kg 3891 lb Maximum zero fuel mass (if MÄM 42-659 is carried out) 1835 kg 4045 lb Maximum landing mass 1805 kg 3979 lb Maximum landing mass (if MÄM 42-659 is carried out) 1999 kg 4407 lb Max. load in nose baggage compartment (in fuselage nose) 30 kg 66 lb Max. load in cabin baggage compartment (behind rear seats) 45 kg 100 lb Max. load in baggage extension (behind cabin baggage compartment) 18 kg 40 lb Max. load, cabin baggage compartment and baggage extension together 45 kg 100 lb if OÄM 42-207 is carried out: Max. load in standard baggage compartment (between rear seats and baggage bulkhead) 30 kg 66 lb Max. load in short baggage extension 15 kg 33 lb WARNING Exceeding the mass limits will lead to overstressing of the airplane as well as to degradation of flight characteristics and flight performance. Operating Limitations DA 42 NG AFM Page 2 - 20 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E NOTE In some countries the beginning of a flight is defined by starting the powerplant. In those countries a ramp mass of maximal MTOM + 8 kg (MTOM + 18 lb) is approved. At the time of lift-off the maximum permitted take-off mass must not be exceeded. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 21 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 floor of the nose baggage compartment. When the floor of the nose baggage compartment is aligned horizontally, the datum plane is vertical. The datum plane is located 2.196 meters (86.46 in) forward of the most forward point of the root rib on the stub wing (refer to figure in Section 6.2). Center of Gravity Limitations The center of gravity (CG position) for flight conditions must be between the following limits: Most forward flight CG: 2.350 m (92.52 in) aft of datum plane at 1450 kg (3197 lb) 2.350 m (92.52 in) aft of datum plane at 1468 kg (3236 lb) 2.418 m (95.20 in) aft of datum plane at max. take-off mass 1900 kg (4189 lb) If MÄM 42-678 is carried out: 2.434 m (95.83 in) aft of datum plane at max. take-off mass 1999 kg (4407 lb) linear variation in between Most rearward flight CG: 2.454 m (96.61 in) aft of datum plane at 1450 kg (3197 lb) 2.480 m (97.64 in) aft of datum plane at 1700 kg (3748 lb) 2.480 m (97.64 in) aft of datum plane at max. take-off mass (see Section 2.7) linear variation in between Refer to Section 6.4.4 for a graphical illustration of the CG limitations. Operating Limitations DA 42 NG AFM Page 2 - 22 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E WARNING Exceeding the center of gravity limitations reduces the controllability and stability of the airplane. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 23 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category in accordance with JAR-23. Approved Maneuvers 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. Stalling with asymmetric power or one engine inoperative is not permitted. CAUTION Intentional negative g - maneuvers are not permitted. Operating Limitations DA 42 NG AFM Page 2 - 24 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.10 MANEUVERING LOAD FACTORS NOTE The tables below show structural limitations. The load factor limits for the engine must also be observed. Refer to the corresponding Operation Manual for the engine. at vO at vNE with flaps in APP or LDG position Positive 3.8 3.8 2.0 Negative -1.52 -1.52 0.0 WARNING Exceeding the maximum structural load factors will lead to overstressing of the airplane. CAUTION Intentional negative g- maneuvers are not permitted. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 25 2.11 OPERATING ALTITUDE The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew : 1 (one person) Maximum number of occupants : 4 (four persons) 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) • take-off and landing on paved surfaces • take-off and landing on grass surfaces Flights into known or forecast 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. Operating Limitations DA 42 NG AFM Page 2 - 26 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000. for daytime VFR flights in addition for night VFR flights in addition for IFR flights Flight & navigation instruments * airspeed indicator (on G1000 PFD or backup) * altimeter (on G1000 PFD or backup) * magnetic compass * 1 headset, used by pilot in command * vertical speed indicator (VSI) * attitude gyro (artificial horizon; on G1000 PFD or backup) * turn & bank indicator (on G1000 PFD) * directional gyro * VHF radio (COM) with speaker and microphone * VOR receiver * transponder (XPDR), mode A and mode C * GPS receiver (part of G1000) * second airspeed indicator (both, on G1000 PFD and backup) * second altimeter (both, on G1000 PFD and backup) * second attitude gyro (both, on G1000 PFD and backup) * second VHF radio (COM) * VOR-LOC-GP receiver * second GPS receiver (part of G1000) DA 42 NG AFM Operating Limitations for daytime VFR flights in addition for night VFR flights in addition for IFR flights Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 27 Engine instruments * fuel qty. (2x) * oil press. (2x) * oil temp. (2x) * coolant temp. (2x) * coolant level indicator (2x) * gearbox temp. (2x) * load (2x) * prop. RPM (2x) * fuel temp. left & right tank * fuel flow (2x) * fuel px warning * ammeter * voltmeter Lighting * position lights * strobe lights (anti collision lights) * landing light * instrument lighting * flood light * flashlight Operating Limitations DA 42 NG AFM for daytime VFR flights in addition for night VFR flights in addition for IFR flights Page 2 - 28 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E Other operational minimum equipment * stall warning system * variable elevator stop * alternate means for fuel quantity indication (see Section 7.9) * safety belts for each occupied seat * Airplane Flight Manual * Pitot heating system * alternate static valve * emergency battery (for backup attitude gyro and flood light) NOTE A list of approved equipment can be found in Chapter 6. Engine Systems and Equipment All engine systems and equipment must be functional prior to airplane take-off. Any engine system or equipment failure must be corrected before next flight. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 29 2.14 FUEL Approved fuel grades: JET A, JET A-1 (ASTM D 1655) TS-1 (Russia, GOST 10227-86) TS-1 (Ukraine, GSTU 320.00149943.011-99) RT (Russia, GOST 10227-86) RT (Ukraine GSTU 320.00149943.007-97) No. 3 Jet Fuel (China, GB 6537-2006) JP-8 (F34) (USA, MIL-DTL-83133G-2010) and blends of the above listed fuel grades. NOTE ' A minimum cetane number of 36 determined acc. to ' EN ISO 5165/ASTM D613 is recommended. ' NOTE Use only uncontaminated fuel from reliable sources. Main Tanks Auxiliary Tanks (if installed) Total US gal liters US gal liters US gal liters Total fuel quantity 2 x 26.0 2 x 98.4 2 x 13.7 2 x 52.0 2 x 39.7 2 x 150.4 Usable fuel 2 x 25.0 2 x 94.6 2 x 13.2 2 x 50.0 2 x 38.2 2 x 144.6 Max. permissible difference LH/RH 5.0 18.9 Operating Limitations DA 42 NG AFM Page 2 - 30 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E Any mixture of the different types of fuel additives is not permitted. OPERATION WITH ANTI-MICROBIAL LIFE FUEL ADDITIVES The application of the following additives is permitted: - KATHON FP 1.5 : max. 100 ppm - BIOBOR JF : max. 270 ppm for initial treatment max. 135 ppm for permanent use after initial treatment CAUTION In case of an unknown or an over dosage of the fuel additives the fuel system must be purged until the dosage is within the permitted limits. NOTE The specified additives are qualified for the operation with the certified fuel grades. To clean the fuel system of the airplane a higher dosage of the specified additive is allowed under consideration of the instructions of the additive supplier. During cleaning the engine must not be operated. NOTE The instructions of the fuel additive supplier must be followed. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 31 OPERATION WITH ANTI-ICING FUEL ADDITIVES The application of the following additive is permitted: - PRIST Hi-Flash : max. 1500 ppm CAUTION The use of PRIST Hi-Flash fuel additive is only permitted with JET A, JET A-1 (ASTM D 1655) and JP-8 (F34). NOTE The instructions of the fuel additive supplier must be followed. Operating Limitations DA 42 NG AFM Page 2 - 32 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.15 LIMITATION PLACARDS All limitation placards are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 7.02.15), Chapter 11. The following limitation placards are in the forward view of the pilot: Limitations for GFC 700 Autopilot System: Autopilot / Yaw Damper DISC during take-off and landing. Do not use AP during single engine operation. Maximum speed for autopilot operation is 180 KIAS. Minimum speed for autopilot operation is 90 KIAS. Minimum Altitude for Autopilot Operation: Cruise, Climb, Descent and Maneuvering : 800 feet AGL Approach : 200 feet AGL Departure : 200 feet AGL This airplane may only be operated in accordance with the Airplane Flight Manual in the "Normal" category. Provided that national operational requirements are met and the appropriate equipment is installed and operational, this airplane is approved for the following kinds of operation: day VFR, night VFR, IFR and flight into known or forecast icing conditions. All aerobatic maneuvers including spinning are prohibited. For further operational limitations refer to the Airplane Flight Manual. Operating maneuvering speed: vO = 122 KIAS (above 1800 kg / 3968 lb) v O = 119 KIAS (above 1700 kg / 3748 lb to 1800 kg / 3968 lb) v O = 112 KIAS (up to 1700 kg / 3748 lb ) DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 33 LANDING GEAR vLE / vLOE = 188 KIAS vLOR = 152 KIAS GPS NOT APPROVED FOR WAAS OPERATIONS EMERGENCY Gear Extension Max. 152 KIAS max. usable fuel: 2 x 25 US gal max. difference LH/RH tank: 5 US gal max. usable fuel main tank: 2 x 25 US gal auxiliary tank: 2 x 13 US gal max. difference LH/RH main tank: 5 US gal If OÄM 42-179 is not incorporated: On the Emergency Landing Gear Extension Lever: On the Instrument Panel: Standard Tank: Auxiliary Tank (if installed): Operating Limitations DA 42 NG AFM Page 2 - 34 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E WARNING APPROVED FUEL JET-A1 or see Airplane Flight Manual (a) Next to Each of the Two Fuel Filler Necks; (b) In Addition Next to Each of the Two Auxiliary Fuel Filler Necks (if installed): In Each Cowling, on the Door for the Oil Filler Neck: ' OIL ' AUSTRO ENGINE ' Aero ' 5W-40 ' or see Airplane ' Flight Manual ' ' OR ' OIL ' SHELL HELIX ' ULTRA ' 5W30 ' or see Airplane ' Flight Manual ' ' DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 35 UP Flaps APP 133 KIAS LDG 113 KIAS Next to the Flap Selector Switch: Next to the Cabin Baggage Compartment: Operating Limitations DA 42 NG AFM Page 2 - 36 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E If OÄM 42-207 is carried out: In the Cabin, on the Left Fuselage Sidewall: DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 37 In the Nose Baggage Compartment: Beside the Door Locking Device Installed in the Passengers' Door: On the Right-Hand Side of the Instrument Panel Above the Circuit Breakers: Max. Baggage: 30 kg [66 lb] EMERGENCY EXIT: The keylock must be unlocked during flight ______ NO SMOKING ______ Operating Limitations DA 42 NG AFM Page 2 - 38 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.16 OTHER LIMITATIONS 2.16.1 FUEL TEMPERATURE From -30 °C to 60 °C (from -22 °F to 140 °F). 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 also not permitted if the subsequent flight is intended to be a Night VFR or 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 DOOR LOCKING DEVICE The canopy and the passenger door must not be blocked by the key lock during operation of the airplane. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 39 2.16.5 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 phones - Remote radio controls - Video screens employing CRTs - Minidisc recorders in record mode This list is not exhaustive. The use of laptop and handheld 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. NOTE ' Refer to EASA AMC 20-25 or FAA AC 120.76A for the use ' of electronic equipment associated to electronic flight bag ' operation. ' Operating Limitations DA 42 NG AFM Page 2 - 40 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 2.16.6 GARMIN G1000 AVIONICS SYSTEM 1. The Garmin G1000 Cockpit Reference Guide, P/N 190-00963-( ) or Garmin G1000 ' NXi Cockpit Reference Guide, P/N 190-02238-00, appropriate revision must be ' immediately available to the flight crew. 2. The G1000 must utilize the software Garmin 010-00670-( ), the Garmin G1000 NXi ' must utilize the software Garmin 010-01916-( ), approved software in accordance with ' the mandatory service bulletin DAI MSB 42-003, latest approved version. ' Software Part Number Approved Version Function System (G1000) ' for approved version see DAI MSB 42NG-003 latest version 010-00670-( ) ' System (G1000 NXi) ' 010-01916-( ) ' Manifest 006-B0093-( ) GPS1, GPS2 006-B0172-( ) GTX1-GIA1, GTX1-GIA2 006-B0190-( ) GIA1, GIA2 006-B0193-( ) GEA1-GIA1; GEA1-GIA2 006-B0203-( ) GMA1-GIA1, GMA1-GAI2 006-B0223-( ) GRS1-GIA1, GRS1-GIA2 006-B0224-( ) GMU1 006-B0319-( ) PFD1, MFD1 006-B0328-( ) 006-B0329-( ) 006-C0048-( ) GMU1 FPGA 006-C0049-( ) GRS1 FPGA 006-C0055-( ) GDC1 FPGA 006-D0159-( ) GRS1 MV DB 006-D0202-( ) 006-B0261-( ) GDC1-GIA1 DA 42 NG AFM Operating Limitations Software Part Number Approved Version Function Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 41 006-B0081-( ) COM1, COM2 006-B0083-( ) GS1, GS2 006-B0082-( ) NAV1, NAV2 NOTE The database version is displayed on the MFD power-up page immediately after system power-up and must be acknowledged. The remaining system software versions can be verified on the AUX group sub-page 5, "AUX-SYSTEM STATUS". 3. IFR enroute, oceanic and terminal navigation predicated upon the G1000 GPS Receiver is prohibited unless the pilot verifies the currency of the database or verifies each selected way point for accuracy by reference to current approved data. 4. Instrument approach navigation predicated upon the G1000 GPS Receiver must be accomplished in accordance with approved instrument approach procedures that are retrieved from the GPS equipment database. The GPS equipment database must incorporate the current update cycle. NOTE Not all published approaches are in the FMS database. The pilot must ensure that the planned approach is in the database. (a) Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Integrity Monitoring (RAIM) must be available at the Final Approach Fix. Operating Limitations DA 42 NG AFM Page 2 - 42 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E (b) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the G1000 GPS receiver is not authorized. (c) Use of the G1000 VOR/ILS receiver to fly approaches not approved for GPS require VOR/ILS navigation data to be present on the display. (d) When an alternate airport is required by the applicable operating rules, it must be served by an approach based on other than GPS or Loran-C navigation, the airplane must have the operational equipment capable of using that navigation aid, and the required navigation aid must be operational. (e) VNAV information may be utilized for advisory information only. Use of VNAV information for Instrument Approach Procedures does not guarantee step-down fix altitude protection, or arrival at approach minimums in normal position to land. (f) RNAV (GPS) approaches must be conducted utilizing the GPS sensor. (g) RNP RNAV operations are not authorized, except as noted in Chapter 1 of this AFM. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 43 5. If not previously defined, the following default settings must be made in the "SYSTEM SETUP" menu of the G1000 prior to operation (refer to Pilot's Guide for procedure if necessary): (a) DIS, SPD : nm, kt (sets navigation units to "nautical miles" and "knots") (b) ALT, VS : ft, fpm (sets altitude units to "feet" and "feet per minute") (c) POSITION : deg-min (sets navigation grid units to decimal minutes) NOTE Navigation Information is referenced to WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conforms to WGS-84 or equivalent. 6. When AHRS is required to meet the items listed in the minimum operational equipment (serviceable) table in Section 2.13 of this AFM, operation is prohibited in the following areas: (a) North of 72° N latitude at all longitudes. (b) South of 70° S latitude at all longitudes. (c) North of 65° N latitude between longitude 75° W and 120° W (Northern Canada). (d) North of 70° N latitude between longitude 70° W and 128° W (Northern Canada). (e) North of 70° N latitude between longitude 85° E and 114° E (Northern Russia). (f) South of 55° S latitude between longitude 120° E and 165° E (Region south of Australia and New Zealand). When day VFR operations are conducted in the above areas, the MFD must be in a non-heading up orientation. Operating Limitations DA 42 NG AFM Page 2 - 44 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 7. The fuel quantity, fuel required, and fuel remaining functions of the FMS are ' supplemental information only and must be verified by the flight crew. 8. The GPS is not approved for WAAS operations: (a) The G1000 integrated avionics system is NOT approved for GPS WAAS operations including GPS WAAS approach procedures such as "LPV", "LNAV/VNAV", and "LNAV +V". (b) SBAS (WAAS & MSAS) functionality must be disabled on the G 1000 GPS Status page (refer to the G1000 Pilot´s Guide for procedure). 9. The availability of SafeTaxi® , ChartView, or FliteCharts® in electronic form on the G1000 is for information purposes only, it is still mandatory to carry another source of charts on-board the airplane. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 45 2.16.7 AUTOPILOT LIMITATIONS 1. It is the responsibility of the pilot in command to monitor the autopilot when it is engaged. The pilot should be prepared to immediately disconnect the autopilot and to take prompt corrective action in the event of unexpected or unusual autopilot behavior. 2. The autopilot and yaw damper must be disconnected (using the DISC button) during take-off, landing and single engine operation. 3. Following an autopilot or electric trim malfunction, reengaging the autopilot or manual electric trim, or resetting the AFCS / ESP / USP circuit breaker is prohibited until the ' cause of the malfunction has been determined and corrected. 4. The Garmin G1000 Cockpit Reference Guide for the Diamond DA 42 NG, P/N 010-00963-( ) or Garmin G1000 NXi Cockpit Reference Guide for the Diamond ' DA 42 NG, P/N 010-02238-( ) approved revision must be immediately available to the ' flight crew. 5. ILS approaches using the GFC700 / flight director are limited to Category I approaches only. 6. Autopilot maximum airspeed: 180 KIAS Autopilot minimum airspeed: 90 KIAS 7. Altitude select captures below 1200 feet AGL are prohibited. 8. The autopilot must be disengaged: - below 200 ft AGL during approach, - below 200 ft AGL during departure, - below 800 ft AGL for all other phases of flight, - during single engine operation. 9. Overriding the autopilot to change pitch or roll attitude is prohibited. (Disengage or press CWS while maneuvering.) Operating Limitations DA 42 NG AFM Page 2 - 46 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E 10. The GFC 700 components must utilize the following or later approved software versions: Sub-System Software Version GDU v9.03 GDC 74 v3.02 GEA 7X v2.07 GPS v3.03 GIA 6X v5.65 GIA Audio v2.03 GMAX347 v4.01 GMU44 v2.01 GRS 77 v2.11 GTX 33X v5.01 GDL 69 v3.20.00 GSA 8X v2.20 GFC 700 v2.00 The system software versions can be verified on the AUX group sub-page 5, "AUX - SYSTEM STATUS". 11. The GFC 700 AFCS pre-flight test must be successfully completed prior to use of the autopilot, flight director, yaw damper or manual electric trim. 12. A pilot with the seat belt fastened must occupy the left pilot's seat during all operations. 13. The yaw damper is an integral part of the autopilot system and must not be used separately. DA 42 NG AFM Operating Limitations Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 EASA approved Page 2 - 47 2.16.8 SMOKING Smoking in the airplane is not permitted. 2.16.9 GROUND OPERATION Take-off and landing has been demonstrated on hard paved surfaces (asphalt, concrete, etc.) and grass runways. 2.16.10 USE OF THE SUN VISORS The sun visors (if installed, OÄM 42-101 or OÄM 42-142) may only be used during cruise. During all other phases of flight the sun visors must be locked in the fully upward position. 2.16.11 GARMIN GWX 68 / GWX 70 WEATHER RADAR OPERATION ' WARNING The Garmin GWX 68 and the GWX 70 weather radar system ' (if installed) must not be operated on ground. If the system is transmitting, it may result in bodily injury if persons are within the minimum safe distance of 2.8 m (9.16 ft) for the ' GWX 68. For the GWX 70 the minimum safe distance is 2.3 m ' (7.4 ft). Never operate the radar in a hangar or other ' enclosure as radiation can be reflected throughout the area. 2.16.12 MID CONTINENT MD302 STANDBY ATTITUDE MODULE ' The Mid Continent MD302 Standby Attitude Module Pilot’s Guide, P/N 9017846, latest ' effective issue must be immediately available to the flight crew. ' Operating Limitations DA 42 NG AFM Page 2 - 48 Rev. 4 02-Oct-2017 EASA approved Doc. No. 7.01.16-E Intentionally left blank. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 1 CHAPTER 3 EMERGENCY PROCEDURES Page 3.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4 3.1.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES . . . . . . . . . . . . . . 3-5 3.1.3 SELECTING EMERGENCY FREQUENCY . . . . . . . . . . . . . . 3-5 3.2 AIRPLANE-RELATED G1000 WARNINGS . . . . . . . . . . . . . . . . . . . 3-6 3.2.1 WARNINGS / GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 3.2.2 L/R ENG TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 3.2.3 L/R OIL TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 3.2.4 L/R OIL PRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9 3.2.5 L/R GBOX TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10 3.2.6 L/R FUEL TEMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 3.2.7 L/R FUEL PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12 3.2.8 L/R ALTN AMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12 3.2.9 L/R ENG FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13 3.2.10 L/R STARTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 3.2.11 DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 3.3 AIRPLANE-RELATED G1000 CAUTIONS . . . . . . . . . . . . . . . . . . . 3-15 3.3.1 L/R ALTN FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15 3.4 G1000 SYSTEM WARNINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.1 RED X / YELLOW X . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 ' 3.4.2 ATTITUDE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.3 AIRSPEED FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.4 ALTITUDE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 3.4.5 VERT SPEED FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 3.4.6 HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 Emergency Procedures DA 42 NG AFM Page 3 - 2 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.5 G1000 FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-18 3.5.1 NAVIGATION INFORMATION FAILURE . . . . . . . . . . . . . . 3-18 3.5.2 PFD OR MFD DISPLAY FAILURE . . . . . . . . . . . . . . . . . . . 3-18 3.5.3 AHRS FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-19 3.5.4 AIR DATA COMPUTER (ADC) FAILURE . . . . . . . . . . . . . . 3-20 3.5.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-20 3.5.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-21 3.6 ABNORMAL ENGINE BEHAVIOUR . . . . . . . . . . . . . . . . . . . . . . . 3-22 3.7 ONE ENGINE INOPERATIVE PROCEDURES . . . . . . . . . . . . . . . 3-23 3.7.1 DETECTING THE INOPERATIVE ENGINE . . . . . . . . . . . . 3-24 3.7.2 ENGINE TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . 3-25 3.7.3 ENGINE SECURING (FEATHERING) PROCEDURE . . . . 3-28 3.7.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-29 3.7.5 ENGINE FAILURE DURING TAKE-OFF . . . . . . . . . . . . . . . 3-33 3.7.6 ENGINE FAILURES IN FLIGHT . . . . . . . . . . . . . . . . . . . . . 3-36 3.7.7 LANDING WITH ONE ENGINE INOPERATIVE . . . . . . . . . 3-38 3.7.8 GO-AROUND / BALKED LANDING WITH ONE ENGINE INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-41 3.7.9 FLIGHT WITH ONE ENGINE INOPERATIVE . . . . . . . . . . . 3-44 3.8 ENGINES OUT LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-46 3.9 LANDING GEAR SYSTEM FAILURES . . . . . . . . . . . . . . . . . . . . . 3-48 3.9.1 LANDING GEAR UNSAFE WARNING . . . . . . . . . . . . . . . . 3-48 3.9.2 MANUAL EXTENSION OF THE LANDING GEAR . . . . . . . 3-50 3.9.3 LANDING WITH GEAR UP . . . . . . . . . . . . . . . . . . . . . . . . . 3-52 3.9.4 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-53 3.9.5 LANDING WITH DEFECTIVE BRAKES . . . . . . . . . . . . . . . 3-54 3.10 FAILURES IN THE ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . 3-55 DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 3 3.10.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . 3-55 3.10.2 HIGH CURRENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-56 3.10.3 STARTER MALFUNCTION . . . . . . . . . . . . . . . . . . . . . . . . 3-57 3.11 SMOKE AND FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-58 3.11.1 ENGINE FIRE ON GROUND . . . . . . . . . . . . . . . . . . . . . . . 3-58 3.11.2 ENGINE FIRE DURING TAKE-OFF . . . . . . . . . . . . . . . . . . 3-59 3.11.3 ENGINE FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . 3-60 3.11.4 ELECTRICAL FIRE ON GROUND . . . . . . . . . . . . . . . . . . . 3-61 3.11.5 ELECTRICAL FIRE IN FLIGHT . . . . . . . . . . . . . . . . . . . . . 3-62 3.12 OTHER EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-63 3.12.1 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-63 3.12.2 UNLOCKED DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-64 3.12.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-66 3.12.4 UNINTENTIONAL FLIGHT INTO ICING . . . . . . . . . . . . . . . 3-69 3.12.5 FUEL SUPPLY FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . 3-70 3.12.6 RECOVERY FROM AN UNINTENTIONAL SPIN . . . . . . . . 3-71 3.12.7 EMERGENCY DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . 3-73 3.12.8 EMERGENCY EXIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-73 3.12.9 AUTOPILOT OR ELECTRIC TRIM MALFUNCTION / FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-74 NOTE Procedures for uncritical system faults are given in Chapter 4B - ABNORMAL OPERATING PROCEDURES. Emergency Procedures DA 42 NG AFM Page 3 - 4 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 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 in this chapter 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 airplane"). 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. This should prevent a situation where the pilot is faced with an emergency he cannot handle calmly and with determination. DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 5 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event One engine inoperative minimum control speed (air) v MCA Flaps UP 71 KIAS Flaps APP 68 KIAS One engine inoperative speed for best rate of climb vYSE 85 KIAS 3.1.3 SELECTING EMERGENCY FREQUENCY In an in-flight emergency, depressing and holding the Com transfer button »º on the G1000 for 2 seconds will tune the emergency frequency of 121.500 MHz. If the display is available, it will also show it in the "Active" frequency window. Emergency Procedures DA 42 NG AFM Page 3 - 6 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.2 AIRPLANE-RELATED G1000 WARNINGS 3.2.1 WARNINGS / GENERAL "Warning" means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety. The warning text is displayed in red color. A warning chime tone of 1.5 seconds duration will sound and repeat without delay until the alarm is acknowledged by the crew. 3.2.2 L/R ENG TEMP L/R ENG TEMP Left / Right engine coolant temperature is in the upper red range (too high / above 105 °C) Coolant temperatures above the limit value of 105 °C can lead to a total loss of power due to engine failure. - Check G1000 for L/R COOL LVL caution message (low coolant level) L/R COOL LVL caution message not displayed: During climb: - Reduce power on affected engine by 10 % or more as required. - Increase airspeed by 10 KIAS or more as required. - If the coolant temperature does not reach the green range within 60 seconds, reduce power on affected engine as far as possible and increase airspeed. CONTINUED DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 7 During cruise: - Reduce power on affected engine. - Increase airspeed. - Check coolant temperature in green range. CAUTION If high coolant temperature is indicated and the L/R COOL LVL caution message is not displayed, it can be assumed that there is no technical defect in the cooling system and that the above mentioned procedure can decrease the temperature(s). This might not be the case if the coolant temperature does not return to the green range. In this case perform a precautionary landing on the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST L/R COOL LVL caution message displayed: - Reduce power on affected engine. - Expect loss of coolant. WARNING A further increase in coolant temperature must be expected. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 8 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.2.3 L/R OIL TEMP L/R OIL TEMP Left / Right engine oil temperature is in the upper red range (too high / above 140 °C). Oil temperatures above the limit value of 140 °C can lead to a total loss of power due to engine failure. - Check oil pressure. If the oil pressure is outside of the green range (lower limit): - Reduce power on affected engine. - Expect loss of engine oil. WARNING A further increase in oil temperature must be expected. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. If the oil pressure is within the green range: - Reduce power on affected engine. - Increase airspeed. CONTINUED DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 9 CAUTION If high oil temperature is announced and the oil pressure indication is within the green range, it can be assumed that there is no technical defect in the engine oil system and that the above mentioned procedure can decrease the temperature(s). This might not be the case if the oil temperature does not return to the green range. In this case perform a precautionary landing on the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST 3.2.4 L/R OIL PRES L/R OIL PRES Left / Right engine oil pressure is in the lower red range (too low / below 0.9 bar). Oil pressures below the limit value of 0.9 bar can lead to a total loss of power due to engine failure. - Reduce power on affected engine. - Expect loss of oil. WARNING Land at the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 10 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.2.5 L/R GBOX TEMP L/R GBOX TEMP Left / Right engine gearbox temperature is in the upper red range (too high / above 120 °C). Gearbox temperatures above the limit value of 120 °C can lead to a total loss of power due to engine failure. - Reduce power on affected engine. - Increase airspeed. CAUTION At high ambient temperature conditions and/or at low airspeeds with high power settings, it can be assumed that there is no technical defect in the gearbox and that the above mentioned procedure will decrease the temperature(s). This might not be the case if the gearbox temperature does not return to the green range. In this case perform a precautionary landing on the nearest suitable airfield. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURES IN FLIGHT. END OF CHECKLIST DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 11 3.2.6 L/R FUEL TEMP L/R FUEL TEMP Left / Right fuel temperature is in the upper red range (too high / above 60 °C). Fuel temperatures above the limit value of 60 °C can lead to a noticeable reduction of the high pressure pump efficiency. - Reduce power on affected engine. - Increase airspeed. CAUTION At high ambient temperature conditions and/or at low airspeeds with high power settings and low fuel quantities, it can be assumed that the above mentioned procedure will decrease the temperature(s). If the fuel temperature does not return to the green range, perform a precautionary landing on the nearest suitable airfield. NOTE Increased fuel temperature can occur when the fuel quantity in the main tank is low. If the auxiliary tank is installed the fuel temperature can be decreased by transferring fuel from the auxiliary to the main tank. END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 12 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.2.7 L/R FUEL PRESS L/R FUEL PRESS Left / Right engine fuel pressure is low. 1. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . check 2. FUEL SELECTOR of affected engine . . . . . . check ON 3. Fuel pump of affected engine . . . . . . . . . . . . ON if L/R FUEL PRESS warning remains: 4. FUEL SELECTOR of affected engine . . . . . . CROSSFEED if L/R FUEL PRESS warning still remains: WARNING Imminent engine failure must be expected. Prepare for an engine failure in accordance with 3.7.6 - ENGINE FAILURE IN FLIGHT. END OF CHECKLIST 3.2.8 L/R ALTN AMPS L/R ALTN AMPS Left / Right engine alternator output is in the upper red range (too high / above 70 Amps). Proceed according to: 3.10.2 - HIGH CURRENT END OF CHECKLIST DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 13 3.2.9 L/R ENG FIRE L/R ENG FIRE Left / Right engine fire detected. Engine fire can lead to a total loss of power due to engine failure as well as severe structural damage. Proceed according to the following procedures as applicable: 3.11.1 - ENGINE FIRE ON GROUND 3.11.2 - ENGINE FIRE DURING TAKE-OFF 3.11.3 - ENGINE FIRE IN FLIGHT END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 14 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.2.10 L/R STARTER L/R STARTER Left / Right engine starter is engaged. Proceed according to: 3.10.3 - STARTER MALFUNCTION END OF CHECKLIST 3.2.11 DOOR OPEN DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. Proceed according to: 3.12.2 - UNLOCKED DOORS END OF CHECKLIST DA 42 NG AFM Emergency Procedures Doc. No. 7.01.16-E Rev. 4 02-Oct-2017 Page 3 - 15 3.3 AIRPLANE-RELATED G1000 CAUTIONS 3.3.1 L/R ALTN FAIL L/R ALTN FAIL Left / Right engine alternator has failed. (a) One Alternator Failed Proceed according to: 4B.4.6 - L/R ALTN FAIL (b) Both Alternators Failed WARNING If both alternators fail at the same time, reduce all electrical equipment to a minimum. Expect battery power to last 30 minutes and land the airplane as soon as possible. Expect engine stoppage after this period of time. 1. AVIONICS MASTER . . . . . . . . . . . . . . . . . . . OFF 2. LH / RH Alternator . . . . . . . . . . . . . . . . . . . . OFF 3. XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY 4. LANDING GEAR . . . . . . . . . . . . . . . . . . . . . . down, when down and locked pull Emergency Release 5. Stall / Pitot heat . . . . . . . . . . . . . . . . . . . . . . OFF 6. All lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF END OF CHECKLIST Emergency Procedures DA 42 NG AFM Page 3 - 16 Rev. 4 02-Oct-2017 Doc. No. 7.01.16-E 3.4 G1000 SYSTEM WARNINGS 3.4.1 RED X / YELLOW X ' A red or yellow X through any display field, such as COM frequencies, NAV frequencies, ' or engine data, indicates that display field is not receiving valid data. 3.4.2 ATTITUDE FAIL ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS; accompanied by the removal of sky/ground presentation and a red X over the attitude area. Revert to the standby attitude indicator. 3.4.3 AIRSPEED FAIL AIRSPEED FAIL The display system is not receiving airspeed input from the air data computer; accompanied by a red X through the airspeed display. Revert to the standby airspeed ind
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