DA 42 AFM

Diamond DA42 NG · Parts Catalog

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Overview

The document is the Airplane Flight Manual (AFM) for the Diamond DA42 NG aircraft, detailing operational procedures and limitations. It is intended for pilots to familiarize themselves with the aircraft's systems and ensure safe operation.

Valid for DA42 airplanes with KAP 140 or no autopilot system.
Pilots must familiarize themselves with the entire manual before first flight.
The manual is protected by copyright.
Revisions must be recorded in the manual.
Approved chapters are validated by EASA.
Temporary revisions provide interim information until permanent updates.
Contact information for Diamond Aircraft Industries is provided.

Document

Source

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

View original at goldwings.pl

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Document details

Type: Parts Catalog
Year: 2015
File size: 3.0 MB
Publisher: goldwings.pl
Language: en

About this document

What is the DA 42 AFM?

The DA 42 AFM is a parts catalog for the Diamond DA42 NG, dated 2015.

Where does the DA 42 AFM come from?

This copy of the DA 42 AFM was originally published by goldwings.pl and is hosted on Sprinkle as a free, searchable reference copy.

What year was the DA 42 AFM published?

The DA 42 AFM — the Diamond DA42 NG parts catalog on file — is dated 2015.

Documentation completeness

6/7

Most owners only have the POH. Here's the essential set for the Diamond DA42 NG.

More Diamond DA42 NGmanuals & documents

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In this document

Approval

The content of approved chapters is approved by EASA, while other content is approved by DAI under EASA DOA No. EASA.21J.052.

Record of Revisions

All revisions must be recorded, with new text indicated by a vertical line on the left side of the page.

Foreword

Congratulates the owner on acquiring the DA42 and emphasizes the importance of familiarization for safety.

Copyright Notice

List of Effective Pages

A list detailing the effective pages and their revision dates is included.

Temporary Revisions

Temporary revisions are used to provide information on systems or equipment until the next permanent revision.

Full document text

Introduction DA 42 AFM Page 0 - 0a Rev. 5 15 Nov 2007 Doc. # 7.01.05-E NOTE This airplane flight manual is valid for DA42 airplanes with a KAP 140 or no autopilot system installed. Refer to the airplane flight manual “DA42 with Garmin GFC 700 (OÄM 42-102)”, Doc. No. 7.01.06-E for airplanes with a Garmin Autopilot system installed. DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 1 FOREWORD We congratulate you on the acquisition of your new DIAMOND DA 42. 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. 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 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 AFM Page 0 - 2 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-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; the following pages of the Temporary Revision are inserted in front of the corresponding pages of this AFM. 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. Example: Revision 3 covers OÄM 42-053, therefore the Temporary Revision TR-OÄM-42-053 is superseded by the 'permanent' Revision 3. DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 3 Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Verification Date Inserted Signature 1 IFR certification; corrections all all except cover page 1 Dec 2004 2005-196 [Ing. Andreas Winkler for ACG] 2 MÄM 42-034 (elevator stop); OÄM 42-060 (T&B coordinat.); Take-off diagrams 0 4A 4B 5 6 7 0-3, 0-5, 0-7, 0-8, 0-9 4A-9 4B-25 5-11, 5-12 6-18 7-7 28 Jan 2005 [10 Feb 2005 Dipl.-Ing. (FH) Manfred Reichel for DAI] 3 FAA Certification MÄM 42- -062, -070/a, -079, -080, -091, -101, -111/b (TR-MÄM- 42-111/a), -115 OÄM 42- -053, -056, -057, -059, -079 Corrections all all 15 Oct 2005 [25 Oct 2005 Ing. Andreas Winkler for ACG] Introduction DA 42 AFM Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Verification Date Inserted Signature Page 0 - 4 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 4 MÄM 42- -037, -046, -063, -088, OÄM 42- -054, -077, -080 corrections 0 0-3 thru 0-10 30 Nov 2005 EASA A.C. Ø2618 [20 Dec 2005 Ing. Andreas Winkler for ACG] 1 1-2, 1-11 2 2-2, 2-4, 2-7, 2-8, 2-10, 2- 14, 2-15, 2-18, 2-21 thru 2- 23, 2-26, 2-27, 2- 32 3 3-30, 3-31, 3-32, 3-38 0,16667 all (4A-1 thru 4A-40) 4B 4B-2, 4B-13, 4B-25, 4B-27, 4B-30 thru 4B-34 5 all (5-1 thru 5-34) 6 6-5, 6-8, 6-10 thru 6- 14, 6-16, 6-20 7 7-1, 7-2, 7-40 thru 7-66 8 8-4, 8-12 9 39692 DA 42 AFM Introduction Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Verification Date Inserted Signature Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 5 5 MÄM 42- -174/a, -186, -198/b, -206, -240, -254, -258/a, OÄM 42- -055/a, -056/d, -062, -065, -066, -067, -070, -074, -082, -092, -094, -095, -099, -101, -105, -112, -116, -121, -129, corrections all all except cover page 15 Nov 2007 Revision No. 5 of the AFM Doc. No. 7.01.05-E is approved under the authority of DOA No. EASA.21J. 052 Introduction DA 42 AFM Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Verification Date Inserted Signature Page 0 - 6 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 6 MÄM 42- -268/a, -270, -272, -284, -292, -301, -304, -310, -336, -347, -377, -405, -443, OÄM 42- -053/d & -054/d, -056/e, -074/a, -106/a, -107/d, -108/a, -109/a, -111/a & -158, -116/a, -125, -127, -130, -141, -142, -145, -146/a, -175, -188, -195, -205, -208, VÄM 42-002, corrections all all except cover page 30 Apr 2011 Revision No. 6 of the AFM Doc. No. 7.01.05-E is approved under the authority of DOA No. EASA.21J. 052 DA 42 AFM Introduction Rev. No. Reason Chap- ter Page(s) Date of Revision Approval Verification Date Inserted Signature Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 7 7 ' ' MÄM 42- ' -529, -542, ' -545/a, -546, ' -575, -584/a, ' -641, -685, ' -716, -756, '

Show full text

-764/c, -814, ' -861, ' ' OÄM 42- ' -055/d, ' -056/f, ' -094/a, ' -107/f, ' -111/b& ' -158/a&-246, ' -119, -178, ' -185, -215, ' -252, -253, ' -259, -279, ' -280, ' ' corrections ' ' all ' all ' except cover ' page ' 30 Nov ' 2015 ' Revision ' No. 7 of the ' AFM Doc. ' No. ' 7.01.05-E is ' approved ' under the ' authority of ' DOA No. ' EASA.21J. ' 052 ' ''' Introduction DA 42 AFM Page 0 - 8 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 0.3 LIST OF EFFECTIVE PAGE Ch. Page Date 0 0-0 15 Nov 2007 0-0a 15 Nov 2007 0-1 30-Nov-2015 ' 0-2 30-Nov-2015 ' 0-3 30-Nov-2015 ' 0-4 30-Nov-2015 ' 0-5 30-Nov-2015 ' 0-6 30-Nov-2015 ' 0-7 30-Nov-2015 ' 0-8 30-Nov-2015 ' 0-9 30-Nov-2015 ' 0-10 30-Nov-2015 ' 0-11 30-Nov-2015 ' 0-12 30-Nov-2015 ' 0-13 30-Nov-2015 ' 0-14 30-Nov-2015 ' 0-15 30-Nov-2015 ' 0-16 30-Nov-2015 ' 0-17 30-Nov-2015 ' 0-18 30-Nov-2015 ' Ch. Page Date 1 1-1 30-Nov-2015 ' 1-2 30-Nov-2015 ' 1-3 30-Nov-2015 ' 1-4 30-Nov-2015 ' 1-5 30-Nov-2015 ' 1-6 30-Nov-2015 ' 1-7 30-Nov-2015 ' 1-8 30-Nov-2015 ' 1-9 30-Nov-2015 ' 1-10 30-Nov-2015 ' 1-11 30-Nov-2015 ' 1-12 30-Nov-2015 ' 1-13 30-Nov-2015 ' 1-14 30-Nov-2015 ' 1-15 30-Nov-2015 ' 1-16 30-Nov-2015 ' 1-17 30-Nov-2015 ' 1-18 30-Nov-2015 ' 1-19 30-Nov-2015 ' 1-20 30-Nov-2015 ' 1-21 30-Nov-2015 ' 1-22 30-Nov-2015 ' 1-23 30-Nov-2015 ' 1-24 30-Nov-2015 ' 1-25 30-Nov-2015 ' 1-26 30-Nov-2015 ' DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 9 Ch. Page Date 2 appr. 2-1 30-Nov-2015 ' appr. 2-2 30-Nov-2015 ' appr. 2-3 30-Nov-2015 ' appr. 2-4 30-Nov-2015 ' appr. 2-5 30-Nov-2015 ' appr. 2-6 30-Nov-2015 ' appr. 2-7 30-Nov-2015 ' appr. 2-8 30-Nov-2015 ' appr. 2-9 30-Nov-2015 ' appr. 2-10 30-Nov-2015 ' appr. 2-11 30-Nov-2015 ' appr. 2-12 30-Nov-2015 ' appr. 2-13 30-Nov-2015 ' appr. 2-14 30-Nov-2015 ' appr. 2-15 30-Nov-2015 ' appr. 2-16 30-Nov-2015 ' appr. 2-17 30-Nov-2015 ' appr. 2-18 30-Nov-2015 ' appr. 2-19 30-Nov-2015 ' appr. 2-20 30-Nov-2015 ' appr. 2-21 30-Nov-2015 ' appr. 2-22 30-Nov-2015 ' appr. 2-23 30-Nov-2015 ' appr. 2-24 30-Nov-2015 ' appr. 2-25 30-Nov-2015 ' appr. 2-26 30-Nov-2015 ' appr. 2-27 30-Nov-2015 ' appr. 2-28 30-Nov-2015 ' Ch. Page Date 2 appr. 2-29 30-Nov-2015 ' appr. 2-30 30-Nov-2015 ' appr. 2-31 30-Nov-2015 ' appr. 2-32 30-Nov-2015 ' appr. 2-33 30-Nov-2015 ' appr. 2-34 30-Nov-2015 ' appr. 2-35 30-Nov-2015 ' appr. 2-36 30-Nov-2015 ' appr. 2-37 30-Nov-2015 ' appr. 2-38 30-Nov-2015 ' Introduction DA 42 AFM Page 0 - 10 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Ch. Page Date 3 3-1 30-Nov-2015 ' 3-2 30-Nov-2015 ' 3-3 30-Nov-2015 ' 3-4 30-Nov-2015 ' 3-5 30-Nov-2015 ' 3-6 30-Nov-2015 ' 3-7 30-Nov-2015 ' 3-8 30-Nov-2015 ' 3-9 30-Nov-2015 ' 3-10 30-Nov-2015 ' 3-11 30-Nov-2015 ' 3-12 30-Nov-2015 ' 3-13 30-Nov-2015 ' 3-14 30-Nov-2015 ' 3-15 30-Nov-2015 ' 3-16 30-Nov-2015 ' 3-17 30-Nov-2015 ' 3-18 30-Nov-2015 ' 3-19 30-Nov-2015 ' 3-20 30-Nov-2015 ' 3-21 30-Nov-2015 ' 3-22 30-Nov-2015 ' 3-23 30-Nov-2015 ' 3-24 30-Nov-2015 ' 3-25 30-Nov-2015 ' 3-26 30-Nov-2015 ' 3-27 30-Nov-2015 ' 3-28 30-Nov-2015 ' Ch. Page Date 3 3-29 30-Nov-2015 ' 3-30 30-Nov-2015 ' 3-31 30-Nov-2015 ' 3-32 30-Nov-2015 ' 3-33 30-Nov-2015 ' 3-34 30-Nov-2015 ' 3-35 30-Nov-2015 ' 3-36 30-Nov-2015 ' 3-37 30-Nov-2015 ' 3-38 30-Nov-2015 ' 3-39 30-Nov-2015 ' 3-40 30-Nov-2015 ' 3-41 30-Nov-2015 ' 3-42 30-Nov-2015 ' 3-43 30-Nov-2015 ' 3-44 30-Nov-2015 ' 3-45 30-Nov-2015 ' 3-46 30-Nov-2015 ' 3-47 30-Nov-2015 ' 3-48 30-Nov-2015 ' 3-49 30-Nov-2015 ' 3-50 30-Nov-2015 ' 3-51 30-Nov-2015 ' 3-52 30-Nov-2015 ' 3-53 30-Nov-2015 ' 3-54 30-Nov-2015 ' 3-55 30-Nov-2015 ' 3-56 30-Nov-2015 ' DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 11 Ch. Page Date 3 3-57 30-Nov-2015 ' 3-58 30-Nov-2015 ' 3-59 30-Nov-2015 ' 3-60 30-Nov-2015 ' 3-61 30-Nov-2015 ' 3-62 30-Nov-2015 ' 3-63 30-Nov-2015 ' 3-64 30-Nov-2015 ' 3-65 30-Nov-2015 ' 3-66 30-Nov-2015 ' 3-67 30-Nov-2015 ' 3-68 30-Nov-2015 ' Ch. Page Date 4A 4A-1 30-Nov-2015 ' 4A-2 30-Nov-2015 ' 4A-3 30-Nov-2015 ' 4A-4 30-Nov-2015 ' 4A-5 30-Nov-2015 ' 4A-6 30-Nov-2015 ' 4A-7 30-Nov-2015 ' 4A-8 30-Nov-2015 ' 4A-9 30-Nov-2015 ' 4A-10 30-Nov-2015 ' 4A-11 30-Nov-2015 ' 4A-12 30-Nov-2015 ' 4A-13 30-Nov-2015 ' 4A-14 30-Nov-2015 ' 4A-15 30-Nov-2015 ' 4A-16 30-Nov-2015 ' 4A-17 30-Nov-2015 ' 4A-18 30-Nov-2015 ' 4A-19 30-Nov-2015 ' 4A-20 30-Nov-2015 ' 4A-21 30-Nov-2015 ' 4A-22 30-Nov-2015 ' 4A-23 30-Nov-2015 ' 4A-24 30-Nov-2015 ' 4A-25 30-Nov-2015 ' 4A-26 30-Nov-2015 ' 4A-27 30-Nov-2015 ' 4A-28 30-Nov-2015 ' Introduction DA 42 AFM Page 0 - 12 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Ch. Page Date 4A 4A-29 30-Nov-2015 ' 4A-30 30-Nov-2015 ' 4A-31 30-Nov-2015 ' 4A-32 30-Nov-2015 ' 4A-33 30-Nov-2015 ' 4A-34 30-Nov-2015 ' 4A-35 30-Nov-2015 ' 4A-36 30-Nov-2015 ' 4A-37 30-Nov-2015 ' 4A-38 30-Nov-2015 ' 4A-39 30-Nov-2015 ' 4A-40 30-Nov-2015 ' 4A-41 30-Nov-2015 ' 4A-42 30-Nov-2015 ' 4A-43 30-Nov-2015 ' 4A-44 30-Nov-2015 ' Ch. Page Date 4B 4B-1 30-Nov-2015 ' 4B-2 30-Nov-2015 ' 4B-3 30-Nov-2015 ' 4B-4 30-Nov-2015 ' 4B-5 30-Nov-2015 ' 4B-6 30-Nov-2015 ' 4B-7 30-Nov-2015 ' 4B-8 30-Nov-2015 ' 4B-9 30-Nov-2015 ' 4B-10 30-Nov-2015 ' 4B-11 30-Nov-2015 ' 4B-12 30-Nov-2015 ' 4B-13 30-Nov-2015 ' 4B-14 30-Nov-2015 ' 4B-15 30-Nov-2015 ' 4B-16 30-Nov-2015 ' 4B-17 30-Nov-2015 ' 4B-18 30-Nov-2015 ' 4B-19 30-Nov-2015 ' 4B-20 30-Nov-2015 ' 4B-21 30-Nov-2015 ' 4B-22 30-Nov-2015 ' 4B-23 30-Nov-2015 ' 4B-24 30-Nov-2015 ' 4B-25 30-Nov-2015 ' 4B-26 30-Nov-2015 ' 4B-27 30-Nov-2015 ' 4B-28 30-Nov-2015 ' DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 13 Ch. Page Date 4B 4B-29 30-Nov-2015 ' 4B-30 30-Nov-2015 ' 4B-31 30-Nov-2015 ' 4B-32 30-Nov-2015 ' 4B-31 30-Nov-2015 ' 4B-32 30-Nov-2015 ' 4B-33 30-Nov-2015 ' 4B-34 30-Nov-2015 ' Ch. Page Date 5 5-1 30-Nov-2015 ' 5-2 30-Nov-2015 ' 5-3 30-Nov-2015 ' 5-4 30-Nov-2015 ' 5-5 30-Nov-2015 ' 5-6 30-Nov-2015 ' 5-7 30-Nov-2015 ' 5-8 30-Nov-2015 ' 5-9 30-Nov-2015 ' 5-10 30-Nov-2015 ' 5-11 30-Nov-2015 ' 5-12 30-Nov-2015 ' 5-13 30-Nov-2015 ' 5-14 30-Nov-2015 ' 5-15 30-Nov-2015 ' 5-16 30-Nov-2015 ' 5-17 30-Nov-2015 ' 5-18 30-Nov-2015 ' 5-19 30-Nov-2015 ' 5-20 30-Nov-2015 ' 5-21 30-Nov-2015 ' 5-22 30-Nov-2015 ' 5-23 30-Nov-2015 ' 5-24 30-Nov-2015 ' 5-25 30-Nov-2015 ' 5-26 30-Nov-2015 ' 5-27 30-Nov-2015 ' 5-28 30-Nov-2015 ' Introduction DA 42 AFM Page 0 - 14 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Ch. Page Date 5 5-29 30-Nov-2015 ' 5-30 30-Nov-2015 ' 5-31 30-Nov-2015 ' 5-32 30-Nov-2015 ' 5-33 30-Nov-2015 ' 5-34 30-Nov-2015 ' 5-35 30-Nov-2015 ' 5-36 30-Nov-2015 ' Ch. Page Date 6 6-1 30-Nov-2015 ' 6-2 30-Nov-2015 ' 6-3 30-Nov-2015 ' 6-4 30-Nov-2015 ' 6-5 30-Nov-2015 ' 6-6 30-Nov-2015 ' 6-7 30-Nov-2015 ' 6-8 30-Nov-2015 ' 6-9 30-Nov-2015 ' 6-10 30-Nov-2015 ' 6-11 30-Nov-2015 ' 6-12 30-Nov-2015 ' 6-13 30-Nov-2015 ' 6-14 30-Nov-2015 ' 6-15 30-Nov-2015 ' 6-16 30-Nov-2015 ' 6-17 30-Nov-2015 ' 6-18 30-Nov-2015 ' 6-19 30-Nov-2015 ' 6-20 30-Nov-2015 ' 6-21 30-Nov-2015 ' 6-22 30-Nov-2015 ' 6-23 30-Nov-2015 ' 6-24 30-Nov-2015 ' 6-25 30-Nov-2015 ' 6-26 30-Nov-2015 ' 6-27 30-Nov-2015 ' 6-28 30-Nov-2015 ' DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 15 Ch. Page Date 6 6-29 30-Nov-2015 ' 6-30 30-Nov-2015 ' 6-31 30-Nov-2015 ' 6-32 30-Nov-2015 ' 6-33 30-Nov-2015 ' 6-34 30-Nov-2015 ' Ch. Page Date 7 7-1 30-Nov-2015 ' 7-2 30-Nov-2015 ' 7-3 30-Nov-2015 ' 7-4 30-Nov-2015 ' 7-5 30-Nov-2015 ' 7-6 30-Nov-2015 ' 7-7 30-Nov-2015 ' 7-8 30-Nov-2015 ' 7-9 30-Nov-2015 ' 7-10 30-Nov-2015 ' 7-11 30-Nov-2015 ' 7-12 30-Nov-2015 ' 7-13 30-Nov-2015 ' 7-14 30-Nov-2015 ' 7-15 30-Nov-2015 ' 7-16 30-Nov-2015 ' 7-17 30-Nov-2015 ' 7-18 30-Nov-2015 ' 7-19 30-Nov-2015 ' 7-20 30-Nov-2015 ' 7-21 30-Nov-2015 ' 7-22 30-Nov-2015 ' 7-23 30-Nov-2015 ' 7-24 30-Nov-2015 ' 7-25 30-Nov-2015 ' 7-26 30-Nov-2015 ' 7-27 30-Nov-2015 ' 7-28 30-Nov-2015 ' Introduction DA 42 AFM Page 0 - 16 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Ch. Page Date 7 7-29 30-Nov-2015 ' 7-30 30-Nov-2015 ' 7-31 30-Nov-2015 ' 7-32 30-Nov-2015 ' 7-33 30-Nov-2015 ' 7-34 30-Nov-2015 ' 7-35 30-Nov-2015 ' 7-36 30-Nov-2015 ' 7-37 30-Nov-2015 ' 7-38 30-Nov-2015 ' 7-39 30-Nov-2015 ' 7-40 30-Nov-2015 ' 7-41 30-Nov-2015 ' 7-42 30-Nov-2015 ' 7-43 30-Nov-2015 ' 7-44 30-Nov-2015 ' 7-45 30-Nov-2015 ' 7-46 30-Nov-2015 ' 7-47 30-Nov-2015 ' 7-48 30-Nov-2015 ' 7-49 30-Nov-2015 ' 7-50 30-Nov-2015 ' 7-51 30-Nov-2015 ' 7-52 30-Nov-2015 ' 7-53 30-Nov-2015 ' 7-54 30-Nov-2015 ' 7-55 30-Nov-2015 ' 7-56 30-Nov-2015 ' Ch. Page Date 7 7-57 30-Nov-2015 ' 7-58 30-Nov-2015 ' 7-59 30-Nov-2015 ' 7-60 30-Nov-2015 ' 7-61 30-Nov-2015 ' 7-62 30-Nov-2015 ' 7-63 30-Nov-2015 ' 7-64 30-Nov-2015 ' 7-65 30-Nov-2015 ' 7-66 30-Nov-2015 ' 7-67 30-Nov-2015 ' 7-68 30-Nov-2015 ' 7-69 30-Nov-2015 ' 7-70 30-Nov-2015 ' 7-71 30-Nov-2015 ' 7-72 30-Nov-2015 ' 7-73 30-Nov-2015 ' 7-74 30-Nov-2015 ' DA 42 AFM Introduction Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 0 - 17 Ch. Page Date 8 8-1 30-Nov-2015 ' 8-2 30-Nov-2015 ' 8-3 30-Nov-2015 ' 8-4 30-Nov-2015 ' 8-5 30-Nov-2015 ' 8-6 30-Nov-2015 ' 8-7 30-Nov-2015 ' 8-8 30-Nov-2015 ' 8-9 30-Nov-2015 ' 8-10 30-Nov-2015 ' 8-11 30-Nov-2015 ' 8-12 30-Nov-2015 ' 8-13 30-Nov-2015 ' 8-14 30-Nov-2015 ' 8-15 30-Nov-2015 ' 8-16 30-Nov-2015 ' Ch. Page Date 9 9-1 30-Nov-2015 ' 9-2 30-Nov-2015 ' 9-3 30-Nov-2015 ' 9-4 30-Nov-2015 ' 9-5 30-Nov-2015 ' 9-6 30-Nov-2015 ' Introduction DA 42 AFM Page 0 - 18 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 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 DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 1 CHAPTER 1 GENERAL Page 1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2 CERTIFICATION BASIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 1.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . . 1-6 1.4 DIMENSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7 1.5 DEFINITIONS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . 1-9 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-24 1.9.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-24 1.9.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-25 1.9.3 AVIONICS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-25 General DA 42 AFM Page 1 - 2 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 1.1 INTRODUCTION This Airplane Flight Manual has been prepared in order to provide pilots and instructors with all the information required for the safe and efficient operation of the airplane. The Airplane Flight Manual includes all the data which must be made available to the pilot according to the JAR-23 requirement. Beyond this, it contains further data and operating instructions which, in the manufacturer’s opinion, could be of value to the pilot. This Airplane Flight Manual is valid for all serial numbers with a KAP 140 or no autopilot system installed. 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 Use of Diesel Fuel MÄM 42-037 9 yes 9 no Increased Take-Off Mass MÄM 42-088 9 yes 9 no New Engine Instrument Markings MÄM 42-101 9 yes 9 no Autopilot Static Source MÄM 42-186 9 yes 9 no TAE 125-02-99 Engine MÄM 42-198 9 yes 9 no ECU Backup Battery MÄM 42-240 9 yes 9 no Firmware 2.7, Mapping O28V273DA42 MÄM 42-284 9 yes 9 no Firmware 2.91, Mapping O28V291DA42 MÄM 42-304 9 yes 9 no DA 42 AFM General Modification Source Installed Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 3 ECU Firmware TAE-125 m2.91, ECU Mapping R28V291DIA MÄM 42-310 9 yes 9 no Firmware 2.91, ' Mapping O28V294DA42 ' MÄM 42-529 ' 9 yes ' 9 no ' Ice Protection System OÄM 42-053 9 yes 9 no Ice Protection System (Known Icing) OÄM 42-054 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 Mission Power Supply System OÄM 42-074/a 9 yes 9 no Removable Fuselage Nose Cone OÄM 42-077 9 yes 9 no Operator Desk (Full CFRP Version) OÄM 42-111 9 yes 9 no Operator Desk (CFRP Version with Aluminum Joint) OÄM 42-111/a 9 yes 9 no Garmin GWX 68 Weather Radar ' OÄM 42-119 ' 9 yes ' 9 no ' ECU Backup Battery OÄM 42-129 9 yes 9 no Exhaust End Pipe OÄM 42-130 9 yes 9 no DA 42 M - IFR OÄM 42-141 9 yes 9 no Operator Desk (Full Aluminum Version) OÄM 42-158 9 yes 9 no General DA 42 AFM Modification Source Installed Page 1 - 4 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Increase of Maximum Zero Fuel Mass OÄM 42-188 9 yes 9 no Maximum Landing Mass 1785 kg OÄM 42-195 9 yes 9 no Emergency Axe OÄM 42-205 9 yes 9 no TAE 125-02-114 Engine ' OÄM 42-252 ' 9 yes ' 9 no ' Front Seats with Adjustable ' Backrest - Hydrolok ' OÄM 42-259 ' 9 yes ' 9 no ' NOTE The use of ECU Mapping O28V273DA42, ECU Mapping O28V291DA42 and ECU Mapping O28V294DA42 ' is limited to TAE 125-02-99 engines (MÄM 42-198, latest revision carried out). NOTE The use of ECU Mapping R28V291DIA is limited to TAE 125-01 engines. 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. DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 5 CAUTION The DA 42 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. General DA 42 AFM Page 1 - 6 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 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. DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 7 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 13.42 m 44.0 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. General DA 42 AFM Page 1 - 8 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Wing Flaps Area (total, left + right) : 2.18 m² 23.4 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* ' Main wheel : 15x6.0-6* ' * for details refer to the Airplane Maintenance ' Manual, Doc. No. 7.02.01, latest revision ' DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 9 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 A: 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 LO: Maximum Landing Gear Operating Speed. This speed may not be exceeded during the extension or retraction of the landing gear. v LE: Maximum Landing Gear Extended Speed. This speed may not be exceeded if the landing gear is extended. vmCA: Minimum Control Speed. Minimum speed necessary to be able to control the airplane in case of one engine inoperative. v NE: Never Exceed Speed in smooth air. This speed must not be exceeded in any operation. v NO: Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. General DA 42 AFM Page 1 - 10 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E vS: 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). v x: 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 1,013.25 hPa (29.92 inHg); the temperature gradient up to the altitude at which the temperature reaches -56.5 °C (-69.7 °F) is -0.0065 °C/m (-0.00357 °F/ft), and above this 0 °C/m (0 °F/ft). MSL: Mean Sea Level. OAT: Outside Air Temperature. QNH: Theoretical atmospheric pressure at MSL, calculated from the elevation of the measuring point above MSL and the actual atmospheric pressure at the measuring point. DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 11 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 1,013.25 hPa (29.92 inHg). Pressure Altitude: Altitude indicated by a barometric altimeter, which is set to 1,013.25 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 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. MET: Weather, weather advice. NAV: Navigation, route planning. RoC: Rate of Climb. General DA 42 AFM Page 1 - 12 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E (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. 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. DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 13 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 ECU: Engine Control Unit. FADEC: Full Authority Digital Engine Control. 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. General DA 42 AFM Page 1 - 14 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E (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 XFR PUMP/DE-ICE Fuel Transfer Pump / De-Icing System TAXI/MAP/ACL Taxi-, Map-, Anti Collision Light FLOOD/OXY Flood Light / Oxygen System 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 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. Avionic Control DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 15 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 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 RH BUS: ALT.RH RH Alternator BATT Battery General DA 42 AFM Page 1 - 16 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E RH ENG ECU BUS: ECU BUS RH ECU Bus ECU B RH ECU B ECU A RH ECU A (g) Equipment ELT: Emergency Locator Transmitter. (h) Design Change Advisories MÄM: Mandatory Design Change Advisory. OÄM: Optional Design Change Advisory. (i) Miscellaneous ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation). ATC: Air Traffic Control. CFRP: Carbon Fiber Reinforced Plastic. EASA: European Aviation Safety Agency. EPU: External Power Unit. GIA: Garmin Integrated Avionics. GFRP: Glass Fiber Reinforced Plastic. JAR: Joint Aviation Requirements. JC/VP: Joint Certification/Validation Procedure. PCA: Primary Certification Authority. DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 Page 1 - 17 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeters [m] meters [km] kilometers [in] inches [ft] feet [NM] nautical miles [mm] / 25.4 = [in] [m] / 0.3048 = [ft] [km] / 1.852 = [NM] Volume [l] liters [US gal] US gallons [qts] US quarts [l] / 3.7854 = [US gal] [l] / 0.9464 = [qts] Speed [km/h] kilometers per hour [m/s] meters per second [kts] knots [mph] miles per hour [fpm] feet per minute [km/h] / 1.852 = [kts] [km/h] / 1.609 = [mph] [m/s] x 196.85 = [fpm] Speed of rotation [RPM] revolutions per minute -- Mass [kg] kilograms [lb] pounds [kg] x 2.2046 = [lb] Force, weight [N] newtons [lbf] pounds force [N] x 0.2248 = [lbf] Pressure [hPa] hecto- pascals [mbar] millibars [bar] bars [inHg] inches of mercury [psi] pounds per square inch [hPa] = [mbar] [hPa] / 33.86 = [inHg] [bar] x 14.504 = [psi] Tempera- ture [°C] degrees Celsius [°F] degrees Fahrenheit [°C]x1.8 + 32 = [°F] ([°F] - 32)/1.8 = [°C] General DA 42 AFM Dimension SI-Units US Units Conversion Page 1 - 18 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E Intensity of electric current [A] ampères -- Electric charge (battery capacity) [Ah] ampère-hours -- Electric potential [V] volts -- Time [sec] seconds -- DA 42 AFM General Doc. No. 7.01.05-E Rev. 7 30-Nov-2015 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 AFM Page 1 - 20 Rev. 7 30-Nov-2015 Doc. No. 7.01.05-E 1.7 THREE-VIEW DRAWING 2950 mm (9 ft 8 in) 1870 mm (6 ft 2 in) 13420 mm (44 ft 0 in) 1735 mm 8560 mm (28 ft 1 in) 2490 mm (8 ft 2 in) 1950 mm (6 ft 5 in) 2205 mm (7 ft 3 in) (5 ft 8 in) 13550 mm (44.5 ft) including ACL

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