AIRPLANE FLIGHT MANUAL
Diamond DA42 VI · Pilot's Operating Handbook
Overview
This Airplane Flight Manual (AFM) is designed for the Diamond DA42 L360, providing essential information for pilots and instructors regarding the safe and efficient operation of the aircraft. It includes operating limitations, emergency procedures, performance data, mass and balance information, and details about the airplane's systems. The manual is applicable to DA42 aircraft modified by specific STC numbers and must be kept on board at all times. It emphasizes the importance of familiarization with the manual's contents for safe operation and compliance with regulatory requirements.
- The Diamond DA42 L360 is a twin-engine aircraft with specific operating limitations that must be followed for safe operation.
- Pilots must familiarize themselves with the AFM before operating the aircraft for the first time.
- Emergency procedures are critical and must be reviewed regularly to ensure readiness in case of an emergency.
- Performance data, including takeoff and landing distances, is essential for flight planning and safety.
- The aircraft's mass and balance must be calculated accurately to ensure safe flight operations.
Document
Source
Originally published by irp.cdn-website.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Pilot's Operating Handbook
- Year
- 2012
- Pages
- 352
- File size
- 8.7 MB
- Publisher
- irp.cdn-website.com
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)
Diamond DA42 VI for sale now
Free — save the DA42 to your watchlist and track it in one place.
More Diamond DA42 VImanuals & documents
See all 36 →- DA42-VI THE DEFINITION OF PERFECTIONSystems Description
- Airworthiness Directive Schedule Aeroplanes Diamond DA 42 and DA 42 NGService Bulletins
- Pilot’s Operating HandbookPilot's Operating Handbook
- Pilot’s Operating Handbook DA42 SeriesChecklist
- Polish Defence and Security Equipment Catalogue 2024Specifications
- TCDS No. EASA.A.005 DA 42 - SeriesType Certificate
- DA42-VI EXTERIOR & INTERIOR DESIGNWiring Diagram
- DA42-VISystems Description
- Airplane Flight Manual DA 42 TDIFlight Manual
- Garmin G1000 Cockpit Reference Guide for the Diamond Da42Checklist
- DA42-VI, SN 42.N474, OE-UDOSpecifications
- Airworthiness Directives; Diamond Aircraft Industries GmbH AirplanesAirworthiness Directives
If you fly the Diamond DA42 VI, you may also be researching these.
In this document
General
This section introduces the manual and outlines its purpose, which is to provide comprehensive information for the safe operation of the Diamond DA42 L360. It includes certification basis, warnings, cautions, and notes, as well as dimensions and definitions relevant to the aircraft.
Operating Limitations
This section details the operational limits of the DA42 L360, including maximum takeoff and landing weights, airspeed limitations, and other critical parameters that must be adhered to for safe flight.
Emergency Procedures
This section outlines the procedures to follow in various emergency situations, including engine failure, system malfunctions, and other critical scenarios that require immediate action from the pilot.
Performance
This section provides performance data for the DA42 L360, including takeoff and landing distances, climb rates, and fuel consumption under various conditions.
Mass and Balance & Equipment List
This section includes information on the aircraft's mass and balance requirements, as well as a detailed equipment list that may vary by serial number.
Description of the Airplane and Systems
This section describes the various systems of the DA42 L360, including the avionics, engine, and other critical components necessary for operation.
Airplane Handling, Care and Maintenance
This section provides guidelines for the proper handling, care, and maintenance of the aircraft to ensure safety and longevity.
Supplements
This section lists any additional supplements or modifications that may be applicable to the DA42 L360, including updates to the AFM.
Safety notes
- Engine failure is possible; pilots should plan routes that minimize risk in case of single-engine operation.
- Always keep the AFM on board the aircraft and ensure it is up to date with the latest revisions.
Full document text
REV 7 AIRPLANE FLIGHT MANUAL Re-issue: 18 Aug 10 23 May 12 DA42 L360 D42L-AFM-002 DIAMOND AIRCRAFT INDUSTRIES INC. 1560 CRUMLIN SIDEROAD, LONDON, ONTARIO CANADA N5V 1S2 All rights reserved. No part of this manual may be reproduced or copied in any form or by any means without written permission of DIAMOND AIRCRAFT INDUSTRIES INC. Copyright © 2012 by Diamond Aircraft Industries, London, ON, Canada D42L AFM Re-issue: 18 Aug 10 23 May 12 D42L-AFM-002 Rev 7 DIAMOND AIRCRAFT INDUSTRIES INC. 1560 CRUMLIN SIDEROAD London, Ontario, Canada N5V 1S2 http://www.diamondair.com/ For more information contact: DIAMOND AIRCRAFT INDUSTRIES INC. Technical Publications +1-519-457-4030 Ext.3173 techpubs@diamondair.com Introduction D42L AFM Page 0 - 2 D42L-AFM-002 Intentionally left blank Rev. 6 18-Aug-10 Page 0 - 3 Introduction D42L AFM D42L-AFM-002 Rev. 6 18-Aug-10 FOREWORD We congratulate you on the acquisition of your new DIAMOND DA42 L360 airplane. 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 DA42 L360. 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 DA42 L360 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 INC. 1560 Crumlin Sideroad London, Ontario, Canada N5V 1S2 Phone : (519) 457-4000 Fax : (519) 457-4021 E-Mail : custsupp@diamondair.com Tech Pubs : techpubs@diamondair.com Introduction D42L AFM Page 0 - 4 D42L-AFM-002 18-Aug-10 Rev. 6 0.1 RECORD OF REVISIONS All revisions of this manual, with the exception of - - Temporary Revisions - Updates of the modification level (Section 1.1) - Updated mass and balance information (Section 6.3) - Updates of the Equipment Inventory (Section 6.5), and - Updates of the List of Supplements (Section 9.2). must be recorded in the following table. Revisions of approved Chapters require the countersignature of the responsible airworthiness authority. The new or amended text is indicated by a vertical black line at the left hand side of the revised page, with the revision number and date appearing at the bottom of the page. If pages are revised which contain information valid for your particular serial number (modification level of the airplane, weighing data, Equipment Inventory, List of Supplements), then this information must be transferred to the new pages in hand-writing. Temporary Revisions, if applicable, are inserted into this manual. Temporary Revisions are used to provide information on systems or equipment until the next 'permanent' Revision of the Airplane Flight Manual. Page 0 - 5 Introduction D42L AFM D42L-AFM-002 Rev. 6 18-Aug-10 RECORD OF REVISIONS Approved Rev. No. Affected Pages Date Name Rev. 3 ALL 16-Jul-09 R. Walker A/Chief, Flight Test Transport Canada Rev. 4 Cover Page, Pages 0-5 to 0-14 Pages 4A-46, 4A-47 Pages 5-1, 5-5, 5-6. 18-Aug-09 Michel Brulotte A/Chief, Flight Test Transport Canada Rev. 5 Cover Page and Back side Pages 0-5 to 0-18 Pages 1-11, 1-12 Pages 2-7, 2-8 Pages 3-23 to 3-24 Pages 3-27 to 3-68 Pages 4A-5 to 4A-10 Pages 4A-21, 4A-22 Pages 4A-35 to 4A-60 Pages 4B-9, 4B-14 Pages 4B-19, 4B-20 Pages 5-1, 5-2 Pages 5-9, 5-10 Pages 5-39 to 5-48 Pages 6-11, 6-12 Pages 7-7, 7-8 Pages 7-21, 7-22 Pages 7-31, 7-32 Pages 7-53 to 7-56 03-Nov-09 Michel Brulotte A/Chief, Flight Test Transport Canada TR 09-01 Pages 0-5 and 0-6 Pages 9-1 and 9-2 Pages 9-S1-1 to 9-S1-26 15-Nov-09 Thomas Gretton A/Chief, Flight Test Transport Canada Introduction D42L AFM Page 0 - 6 D42L-AFM-002 23-May-12 Rev. 7 TR 09-02 Pages 0-5 and 0-6 Pages 9-1 and 9-2 Pages 9-S2-1 to 9-S2-16 10-Dec-09 Thomas Gretton Chief, Flight Test Transport Canada Rev. 6 ALL 15-Dec-10 Walter Istchenko Chief, Flight Test For Director, National Aircraft Certification Transport Canada TR 10-01 Pages 0-5 and 0-6 Pages 2-29 through 2-34 18-Apr-11 Thomas Gretton Chief, Flight Test Transport Canada TR 11-01 Pages 0-5 and 0-6 Pages 2-5 and 2-6 Pages 9-1 to 9-4 28-Jun-11 Thomas Gretton Chief, Flight Test Transport Canada Approved Rev. No. Affected Pages Date Name • Diamond D42L AFM Introduction AIRCRAFT Cover Page and Back side Pages 0-6 to 0-20 Pages 1-11,1-12. and 1-19. Pages 2-5,2-12,2-15,2-18, 2-21, 2-29, 2-30, 2-32 and 2-33. Chief, Flight Test Pages 3-34 and 3-54. or Director, National Aircraf Pages 4A-4, 4A-9, 4A-12, Certification4A-13, 4A-18, 4A-19, 4A-45 TRANSPORT CANAOARev 7 and 4A-51 50 4A-54. Pages 4B-2 and 4B-24. Pages 5-13 to 5-15,5-17 to 5-19,5-21 to 5-23,5-25 to 5-27 and 5-29 to 5-31. Page 6-10. Pages 7-7,7-19,7-27,7-28, 7-32, and 7-41 to 7-45. Pages 8-5 and 8-13. Pages 9-1 to 9-3. D42L-AFM-002 Rev. 7 23-May-12 Page 0-7 Introduction D42L AFM Page 0 - 8 D42L-AFM-002 Intentionally left blank Rev. 7 23-May-12 Page 0 - 9 Revision 7 Revision Highlights D42L AFM D42L-AFM-002 Rev. 7 23 May 12 REVISION HIGHLIGHTS 0.1. GENERAL The table below highlights the changes that have been incorporated into Revision 7. CHAPTER PAGES HIGHLIGHTS Cover Page Cover Page Revised to show Rev. 7 with the revision date. Front Matter 0-6 to 0-20 Record of Revisions, Revision Highlights and LOEP pages were revised. TOC moved due to pagination. 1 1-11 and 1-12 Change to circuit breaker designations. 1-19 Documents references revised
Show full textShow less
2 2-5 Table values revised for white band and green band. 2-12 Documents references revised 2-15 Paragraph reference revised. 2-18 “according to VFR” changed to “according to NVFR”. 2-21 Approved fuel grade of AVGAS 100 added with a Note. 2-29 and 2-30 Table for 2.16.7 GARMIN G1000 updated. 2-32 MAP DATUM removed and Note added. 2-33 Para (f) revised and Para (i) added. 3 3-34 Para 1.B removed as it is not relevant for the 42L configuration. 3-54 Notes added to Para 3.8 Smoke and Fire. 4A 4A-4 Documents references revised 4A-9 Revised procedural step (6). 4A-12 Pagination change. Data moved to Page 4-13. 4A-13 and 4A-18 Caution added and procedure revised for checking the engine oil. Revision 7 Revision Highlights D42L AFM Page 0 - 10 D42L-AFM-002 23 May 12 Rev. 7 4A-19 Pagination change. Data moved from Page 4-18. 4A-45 Fuel imbalance procedure with aux tanks added. 4A-51 Note added after Mixture Control Levers to Rich. 4A-51 Note added after Propeller RPM levers to High RPM. 4A-52 Pagination change. Data moved from Page 4A-51. 4A-53 Item (a) Mixture Control levers step added with Note. 4A-53 Item (b) Propeller RPM Levers step added. 4A-54 Pagination change. Data moved from Page 4A-53. 4B 4B-2 TOC revised to add L/R AUX FUEL TRANSFER FAIL. 4B-24 Procedure 4B.9 added L/R AUX FUEL TRANSFER FAIL 5 5-13 to 5-15 Table Title revised. 5-17 to 5-19 Table Title added to the table on each page. 5-21 to 5-23 Table Title added to the table on each page. 5-25 to 5-27 Table Title added to the table on each page. 5-29 to 5-31 Table Title added to the table on each page. 6 6-10 AVGAS 100 data added to usable fuel tank information. 7 7-7 Description for the Rudder Pedal Adjustment revised. 7-19 Para added to better describe the propeller. 7-27 Note added for Approved fuel grade of AVGAS 100. 7-28 Typo corrected. feedl to feed. 7-32 Alternate means for fuel quantity indication for the main fuel tanks revised. CHAPTER PAGES HIGHLIGHTS Page 0 - 11 Revision 7 Revision Highlights D42L AFM D42L-AFM-002 Rev. 7 23 May 12 7-41 to 7-43 G1000 Warnings, Cautions and Alerts brought up to date with the Garmin G1000 Cockpit Reference Guide. for the DA42-L360, Part Number 190-01062-02. Note revised for documents references. 7-44 Pagination change. Data moved from 7-45 to 7-44. 7-45 Documents references revised. 8 8-5 Caution added before checking the engine oil level. 8-13 Manufacturer data added for AL-5 (DTD 406B). 9 9-1 Table of Contents revised. List of Supplements broken into TCCA and EASA categories. 9-2 Table lists only TCCA Approved Supplements. 9-3 Table lists only EASA Approved Supplements. Temporary Revisions 10-01, 11-01 and 11-02 have been incorporated into Revision 7. CHAPTER PAGES HIGHLIGHTS Revision 7 Revision Highlights D42L AFM Page 0 - 12 D42L-AFM-002 Intentionally left blank Rev. 7 23 May 12 Introduction D42L AFM Page 0 - 13 D42L-AFM-002 Rev. 7 23 May 12 0.2 LIST OF EFFECTIVE PAGES Pages that are DOT-approved (appr) pages are shown before the page number: LIST OF EFFECTIVE PAGES Ch. Page Date 0 0-1 18-Aug-10 0-2 18-Aug-10 0-3 18-Aug-10 0-4 18-Aug-10 0-5 18-Aug-10 0-6 23-May-12 0-7 23-May-12 0-8 23-May-12 0-9 23-May-12 0-10 23-May-12 0-11 23-May-12 0-12 23-May-12 0-13 23-May-12 0-14 23-May-12 0-15 23-May-12 0-16 23-May-12 0-17 23-May-12 0-18 23-May-12 0-19 23-May-12 0-20 23-May-12 1 1-1 18-Aug-10 1-2 18-Aug-10 1-3 18-Aug-10 1-4 18-Aug-10 1-5 18-Aug-10 1-6 18-Aug-10 1-7 18-Aug-10 1 1-8 18-Aug-10 1-9 18-Aug-10 1-10 18-Aug-10 1-11 23-May-12 1-12 23-May-12 1-13 18-Aug-10 1-14 18-Aug-10 1-15 18-Aug-10 1-16 18-Aug-10 1-17 18-Aug-10 1-18 18-Aug-10 1-19 23-May-12 1-20 18-Aug-10 2 DOT-appr 2-1 18-Aug-10 DOT-appr 2-2 18-Aug-10 DOT-appr 2-3 18-Aug-10 DOT-appr 2-4 18-Aug-10 DOT-appr 2-5 23-May-12 DOT-appr 2-6 18-Aug-10 DOT-appr 2-7 18-Aug-10 DOT-appr 2-8 18-Aug-10 DOT-appr 2-9 18-Aug-10 DOT-appr 2-10 18-Aug-10 DOT-appr 2-11 18-Aug-10 DOT-appr 2-12 23-May-12 DOT-appr 2-13 18-Aug-10 DOT-appr 2-14 18-Aug-10 DOT-appr 2-15 23-May-12 DOT-appr 2-16 18-Aug-10 DOT-appr 2-17 18-Aug-10 DOT-appr 2-18 23-May-12 LIST OF EFFECTIVE PAGES Ch. Page Date Introduction D42L AFM Page 0 - 14 D42L-AFM-002 23 May 12 Rev. 7 2 DOT-appr 2-19 18-Aug-10 DOT-appr 2-20 18-Aug-10 DOT-appr 2-21 23-May-12 DOT-appr 2-22 18-Aug-10 DOT-appr 2-23 18-Aug-10 DOT-appr 2-24 18-Aug-10 DOT-appr 2-25 18-Aug-10 DOT-appr 2-26 18-Aug-10 DOT-appr 2-27 18-Aug-10 DOT-appr 2-28 18-Aug-10 DOT-appr 2-29 23-May-12 DOT-appr 2-30 23-May-12 DOT-appr 2-31 18-Aug-10 DOT-appr 2-32 23-May-12 DOT-appr 2-33 23-May-12 DOT-appr 2-34 18-Aug-10 3 DOT-appr 3-1 18-Aug-10 DOT-appr 3-2 18-Aug-10 DOT-appr 3-3 18-Aug-10 DOT-appr 3-4 18-Aug-10 DOT-appr 3-5 18-Aug-10 DOT-appr 3-6 18-Aug-10 DOT-appr 3-7 18-Aug-10 DOT-appr 3-8 18-Aug-10 DOT-appr 3-9 18-Aug-10 DOT-appr 3-10 18-Aug-10 DOT-appr 3-11 18-Aug-10 DOT-appr 3-12 18-Aug-10 DOT-appr 3-13 18-Aug-10 DOT-appr 3-14 18-Aug-10 DOT-appr 3-15 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date 3 DOT-appr 3-16 18-Aug-10 DOT-appr 3-17 18-Aug-10 DOT-appr 3-18 18-Aug-10 DOT-appr 3-19 18-Aug-10 DOT-appr 3-20 18-Aug-10 DOT-appr 3-21 18-Aug-10 DOT-appr 3-22 18-Aug-10 DOT-appr 3-23 18-Aug-10 DOT-appr 3-24 18-Aug-10 DOT-appr 3-25 18-Aug-10 DOT-appr 3-26 18-Aug-10 DOT-appr 3-27 18-Aug-10 DOT-appr 3-28 18-Aug-10 DOT-appr 3-29 18-Aug-10 DOT-appr 3-30 18-Aug-10 DOT-appr 3-31 18-Aug-10 DOT-appr 3-32 18-Aug-10 DOT-appr 3-33 18-Aug-10 DOT-appr 3-34 23-May-12 DOT-appr 3-35 18-Aug-10 DOT-appr 3-36 18-Aug-10 DOT-appr 3-37 18-Aug-10 DOT-appr 3-38 18-Aug-10 DOT-appr 3-39 18-Aug-10 DOT-appr 3-40 18-Aug-10 DOT-appr 3-41 18-Aug-10 DOT-appr 3-42 18-Aug-10 DOT-appr 3-43 18-Aug-10 DOT-appr 3-44 18-Aug-10 DOT-appr 3-45 18-Aug-10 DOT-appr 3-46 18-Aug-10 DOT-appr 3-47 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date Introduction D42L AFM Page 0 - 15 D42L-AFM-002 Rev. 7 23 May 12 3 DOT-appr 3-48 18-Aug-10 DOT-appr 3-49 18-Aug-10 DOT-appr 3-50 18-Aug-10 DOT-appr 3-51 18-Aug-10 DOT-appr 3-52 18-Aug-10 DOT-appr 3-53 18-Aug-10 DOT-appr 3-54 23-May-12 DOT-appr 3-55 18-Aug-10 DOT-appr 3-56 18-Aug-10 DOT-appr 3-57 18-Aug-10 DOT-appr 3-58 18-Aug-10 DOT-appr 3-59 18-Aug-10 DOT-appr 3-60 18-Aug-10 DOT-appr 3-61 18-Aug-10 DOT-appr 3-62 18-Aug-10 DOT-appr 3-63 18-Aug-10 DOT-appr 3-64 18-Aug-10 DOT-appr 3-65 18-Aug-10 DOT-appr 3-66 18-Aug-10 DOT-appr 3-67 18-Aug-10 DOT-appr 3-68 18-Aug-10 4A DOT-appr 4A-1 18-Aug-10 DOT-appr 4A-2 18-Aug-10 DOT-appr 4A-3 18-Aug-10 DOT-appr 4A-4 23-May-12 DOT-appr 4A-5 18-Aug-10 DOT-appr 4A-6 18-Aug-10 DOT-appr 4A-7 18-Aug-10 DOT-appr 4A-8 18-Aug-10 DOT-appr 4A-9 23-May-12 DOT-appr 4A-10 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date 4A DOT-appr 4A-11 18-Aug-10 DOT-appr 4A-12 23-May-12 DOT-appr 4A-13 23-May-12 DOT-appr 4A-14 18-Aug-10 DOT-appr 4A-15 18-Aug-10 DOT-appr 4A-16 18-Aug-10 DOT-appr 4A-17 18-Aug-10 DOT-appr 4A-18 23-May-12 DOT-appr 4A-19 23-May-12 DOT-appr 4A-20 18-Aug-10 DOT-appr 4A-21 18-Aug-10 DOT-appr 4A-22 18-Aug-10 DOT-appr 4A-23 18-Aug-10 DOT-appr 4A-24 18-Aug-10 DOT-appr 4A-25 18-Aug-10 DOT-appr 4A-26 18-Aug-10 DOT-appr 4A-27 18-Aug-10 DOT-appr 4A-28 18-Aug-10 DOT-appr 4A-29 18-Aug-10 DOT-appr 4A-30 18-Aug-10 DOT-appr 4A-31 18-Aug-10 DOT-appr 4A-32 18-Aug-10 DOT-appr 4A-33 18-Aug-10 DOT-appr 4A-34 18-Aug-10 DOT-appr 4A-35 18-Aug-10 DOT-appr 4A-36 18-Aug-10 DOT-appr 4A-37 18-Aug-10 DOT-appr 4A-38 18-Aug-10 DOT-appr 4A-39 18-Aug-10 DOT-appr 4A-40 18-Aug-10 DOT-appr 4A-41 18-Aug-10 DOT-appr 4A-42 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date Introduction D42L AFM Page 0 - 16 D42L-AFM-002 23 May 12 Rev. 7 4A DOT-appr 4A-43 18-Aug-10 DOT-appr 4A-44 18-Aug-10 DOT-appr 4A-45 23-May-12 DOT-appr 4A-46 18-Aug-10 DOT-appr 4A-47 18-Aug-10 DOT-appr 4A-48 18-Aug-10 DOT-appr 4A-49 18-Aug-10 DOT-appr 4A-50 18-Aug-10 DOT-appr 4A-51 23-May-12 DOT-appr 4A-52 23-May-12 DOT-appr 4A-53 23-May-12 DOT-appr 4A-54 23-May-12 DOT-appr 4A-55 18-Aug-10 DOT-appr 4A-56 18-Aug-10 DOT-appr 4A-57 18-Aug-10 DOT-appr 4A-58 18-Aug-10 4B DOT-appr 4B-1 18-Aug-10 DOT-appr 4B-2 23-May-12 DOT-appr 4B-3 18-Aug-10 DOT-appr 4B-4 18-Aug-10 DOT-appr 4B-5 18-Aug-10 DOT-appr 4B-6 18-Aug-10 DOT-appr 4B-7 18-Aug-10 DOT-appr 4B-8 18-Aug-10 DOT-appr 4B-9 18-Aug-10 DOT-appr 4B-10 18-Aug-10 DOT-appr 4B-11 18-Aug-10 DOT-appr 4B-12 18-Aug-10 DOT-appr 4B-13 18-Aug-10 DOT-appr 4B-14 18-Aug-10 DOT-appr 4B-15 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date 4B DOT-appr 4B-16 18-Aug-10 DOT-appr 4B-17 18-Aug-10 DOT-appr 4B-18 18-Aug-10 DOT-appr 4B-19 18-Aug-10 DOT-appr 4B-20 18-Aug-10 DOT-appr 4B-21 18-Aug-10 DOT-appr 4B-22 18-Aug-10 DOT-appr 4B-23 18-Aug-10 DOT-appr 4B-24 23-May-12 5 DOT-appr 5-1 18-Aug-10 DOT-appr 5-2 18-Aug-10 DOT-appr 5-3 18-Aug-10 DOT-appr 5-4 18-Aug-10 DOT-appr 5-5 18-Aug-10 DOT-appr 5-6 18-Aug-10 DOT-appr 5-7 18-Aug-10 DOT-appr 5-8 18-Aug-10 DOT-appr 5-9 18-Aug-10 DOT-appr 5-10 18-Aug-10 DOT-appr 5-11 18-Aug-10 DOT-appr 5-12 18-Aug-10 DOT-appr 5-13 23-May-12 DOT-appr 5-14 23-May-12 DOT-appr 5-15 23-May-12 DOT-appr 5-16 18-Aug-10 DOT-appr 5-17 23-May-12 DOT-appr 5-18 23-May-12 DOT-appr 5-19 23-May-12 DOT-appr 5-20 18-Aug-10 DOT-appr 5-21 23-May-12 DOT-appr 5-22 23-May-12 LIST OF EFFECTIVE PAGES Ch. Page Date Introduction D42L AFM Page 0 - 17 D42L-AFM-002 Rev. 7 23 May 12 5 DOT-appr 5-23 23-May-12 DOT-appr 5-24 18-Aug-10 DOT-appr 5-25 23-May-12 DOT-appr 5-26 23-May-12 DOT-appr 5-27 23-May-12 DOT-appr 5-28 18-Aug-10 DOT-appr 5-29 23-May-12 DOT-appr 5-30 23-May-12 DOT-appr 5-31 23-May-12 DOT-appr 5-32 18-Aug-10 DOT-appr 5-33 18-Aug-10 DOT-appr 5-34 18-Aug-10 DOT-appr 5-35 18-Aug-10 DOT-appr 5-36 18-Aug-10 DOT-appr 5-37 18-Aug-10 DOT-appr 5-38 18-Aug-10 DOT-appr 5-39 18-Aug-10 DOT-appr 5-40 18-Aug-10 6 DOT-appr 6-1 18-Aug-10 DOT-appr 6-2 18-Aug-10 DOT-appr 6-3 18-Aug-10 DOT-appr 6-4 18-Aug-10 DOT-appr 6-5 18-Aug-10 DOT-appr 6-6 18-Aug-10 DOT-appr 6-7 18-Aug-10 DOT-appr 6-8 18-Aug-10 DOT-appr 6-9 18-Aug-10 DOT-appr 6-10 23-May-12 DOT-appr 6-11 18-Aug-10 DOT-appr 6-12 18-Aug-10 DOT-appr 6-13 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date 6 DOT-appr 6-14 18-Aug-10 DOT-appr 6-15 18-Aug-10 DOT-appr 6-16 18-Aug-10 DOT-appr 6-17 18-Aug-10 DOT-appr 6-18 18-Aug-10 DOT-appr 6-19 18-Aug-10 DOT-appr 6-20 18-Aug-10 7 7-1 18-Aug-10 7-2 18-Aug-10 7-3 18-Aug-10 7-4 18-Aug-10 7-5 18-Aug-10 7-6 18-Aug-10 7-7 23-May-12 7-8 18-Aug-10 7-9 18-Aug-10 7-10 18-Aug-10 7-11 18-Aug-10 7-12 18-Aug-10 7-13 18-Aug-10 7-14 18-Aug-10 7-15 18-Aug-10 7-16 18-Aug-10 7-17 18-Aug-10 7-18 18-Aug-10 7-19 23-May-12 7-20 18-Aug-10 7-21 18-Aug-10 7-22 18-Aug-10 7-23 18-Aug-10 7-24 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date Introduction D42L AFM Page 0 - 18 D42L-AFM-002 23 May 12 Rev. 7 7 7-25 18-Aug-10 7-26 18-Aug-10 7-27 23-May-12 7-28 23-May-12 7-29 18-Aug-10 7-30 18-Aug-10 7-31 18-Aug-10 7-32 23-May-12 7-33 18-Aug-10 7-34 18-Aug-10 7-35 18-Aug-10 7-36 18-Aug-10 7-37 18-Aug-10 7-38 18-Aug-10 7-39 18-Aug-10 7-40 18-Aug-10 7-41 23-May-12 7-42 23-May-12 7-43 23-May-12 7-44 23-May-12 7-45 23-May-12 7-46 18-Aug-10 7-47 18-Aug-10 7-48 18-Aug-10 8 8-1 18-Aug-10 8-2 18-Aug-10 8-3 18-Aug-10 8-4 18-Aug-10 8-5 23-May-12 8-6 18-Aug-10 8-7 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date 8 8-8 18-Aug-10 8-9 18-Aug-10 8-10 18-Aug-10 8-11 18-Aug-10 8-12 18-Aug-10 8-13 23-May-12 8-14 18-Aug-10 9 9-1 23-May-12 9-2 23-May-12 9-3 23-May-12 9-4 18-Aug-10 LIST OF EFFECTIVE PAGES Ch. Page Date Page 0 - 19 Introduction D42L AFM D42L-AFM-002 Rev. 7 23 May 12 0.3 TABLE OF CONTENTS Chapter GENERAL......................................................................................................... 1 OPERATING LIMITATIONS .............................................................................. 2 EMERGENCY PROCEDURES ........................................................................ 3 NORMAL OPERATING PROCEDURES ........................................................4A ABNORMAL OPERATING PROCEDURES....................................................4B PERFORMANCE .............................................................................................. 5 MASS AND BALANCE & EQUIPMENT LIST ................................................... 6 DESCRIPTION OF THE AIRPLANE AND SYSTEMS...................................... 7 AIRPLANE HANDLING, CARE AND MAINTENANCE ..................................... 8 SUPPLEMENTS ............................................................................................... 9 Introduction D42L AFM Page 0 - 20 D42L-AFM-002 Intentionally left blank Rev. 7 23 May 12 Page 1 - 1 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 CHAPTER 1 GENERAL TABLE OF CONTENTS PAGE 1.1 INTRODUCTION ................................................................................... 2 1.2 CERTIFICATION BASIS ........................................................................ 3 1.3 WARNINGS, CAUTIONS AND NOTES................................................. 3 1.4 DIMENSIONS ........................................................................................ 4 1.5 DEFINITIONS AND ABBREVIATIONS .................................................. 6 1.6 UNITS OF MEASUREMENT ............................................................... 14 1.6.1 CONVERSION FACTORS ...................................................... 14 1.6.2. CONVERSION CHART - LITERS / US GALLONS................. 15 1.7 THREE-VIEW DRAWING .................................................................... 16 1.8 G1000 AVIONICS SYSTEM................................................................. 17 1.9 SOURCE DOCUMENTATION ............................................................. 18 1.9.1 ENGINE .................................................................................. 18 1.9.2 PROPELLER........................................................................... 18 1.9.3 AVIONICS SYSTEM ............................................................... 19 General D42L AFM Page 1 - 2 D42L-AFM-002 18 Aug 10 Rev. 6 1.1 INTRODUCTION This Airplane Flight Manual (AFM) has been prepared in order to provide pilots and instructors with all the information required for the safe and efficient operation of the airplane. It is applicable to Diamond DA42 aircraft that have been modified by TCCA STC number SA09-54 and FAA STC number SA02725NY which installs the Lycoming IO-360 engines. It replaces in its entirety the original DA42 Airplane Flight Manual. The AFM includes all the data which must be made available to the pilot according to the Transport Canada CAR-523 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 Paragraph 6.5. The modification level is recorded in the following table (as far as necessary for this manual). This Airplane Flight Manual must be kept on board the airplane at all times. Its designated place is the side pocket of the forward left seat. The designated place for the Garmin G1000 Cockpit Reference Guide is in the bag on the rear side of the forward left seat. Modification Source Installed Increased Take-Off Mass [ ] Yes [ ] No New Engine Instrument Markings [ ] Yes [ ] No Autopilot Static Source [ ] Yes [ ] No Ice Protection System [ ] Yes [ ] No Oxygen System [ ] Yes [ ] No Auxiliary Fuel Tanks [ ] Yes [ ] No Front Seats with Adjustable Backrest [ ] Yes [ ] No Electrical Rudder Pedal Adjustment [ ] Yes [ ] No Mission Power Supply System [ ] Yes [ ] No Removable Fuselage Nose Cone [ ] Yes [ ] No Page 1 - 3 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 THE DA42 L360 IS A TWIN ENGINE AIRPLANE. WHEN THE OPERATING LIMITATIONS AND MAINTENANCE REQUIREMENTS ARE COMPLIED WITH, IT HAS A HIGH DEGREE OF RELIABILITY. NEVERTHELESS, AN ENGINE FAILURE IS NOT COMPLETELY IMPOSSIBLE. FOR THIS REASON IT IS HIGHLY RECOMMENDED FOR VFR FLIGHTS ON TOP, 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. 1.2 CERTIFICATION BASIS This airplane certification basis is Transport Canada AWM Chapter 523, up to and including Change 523-7 and AWM 516 at Change 516-7. 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: A WARNING MEANS THAT THE NON-OBSERVATION OF THE CORRESPONDING PROCEDURE LEADS TO AN IMMEDIATE OR IMPORTANT DEGRADATION IN FLIGHT SAFETY. A 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. CAUTION WARNING CAUTION General D42L AFM Page 1 - 4 D42L-AFM-002 18 Aug 10 Rev. 6 A Note draws the attention to any special item not directly related to safety but which is important or unusual. 1.4 DIMENSIONS All dimensions shown below are approximate. NOTE NOTE Overall dimensions Span : 13.42 m 44 ft 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 ft² Mean aerodynamic chord (MAC) 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 ft² Page 1 - 5 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 Wing flaps : Area (total, left + right) 2.18 m² 23.4 ft² Horizontal tail : Area : 2.35 m² 25.3 ft² Elevator area : 0.66 m² Angle of incidence -1.1° relative to longitudinal axis of airplane Vertical tail Area : 2.43 m² 26.2 ft² Rudder area : 0.78 m² 8.4 ft² Landing gear Track : 2.894 m 9 ft 6 in. Wheelbase : 1.735 m 5 ft 8 in. Nose Wheel : 5.00-5; 10 PR, 120 mph Main Wheel : 15x6.0-6; 6 PR, 120 mph General D42L AFM Page 1 - 6 D42L-AFM-002 18 Aug 10 Rev. 6 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. VA : 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. V LO: Maximum Landing Gear Operating Speed. This speed may not be exceeded during the extension or retraction of the landing gear. V MCA : 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. V R: Rotation Speed or Takeoff Speed V REF : Reference Speed V S: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. Page 1 - 7 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 VSI: Stalling Speed or the minimum continuous speed at which the airplane is still controllable with flaps and landing gear retracted. VSO: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration. VSSE: 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 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). ISA: International Standard Atmosphere. Conditions at which air is identified as an ideal dry gas. The temperature at mean sea level is 15 o C (59 o 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 o C (69.7 o F) is 0.0065 o C/m (-0.00357 o F/ft), and above this 0 o C/m (0 o F/ft). MSL: Mean Sea Level. OAT: Outside Air Temperature. Pressure Altitude: Altitude above MSL, indicated by a barometric altimeter which is set to 1013.25 hPa (29.92 inHg). The Pressure Altitude is the Indicated Pressure Altitude corrected for installation and instrument errors. In this AFM altimeter instrument errors are regarded as zero. General D42L AFM Page 1 - 8 D42L-AFM-002 18 Aug 10 Rev. 6 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. Wind: The wind speeds which are shown as variables in the diagrams in this manual should be regarded as headwind or downwind components of the measured wind. (c) Flight Performance and Flight Planning 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. (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 Limits: The Center of Gravity range within which the airplane, at a given mass, must be operated. 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. DP: Datum Plane; an imaginary vertical plane from which all horizontal distances for center of gravity calculations are measured. Page 1 - 9 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 Empty Mass: The mass of the airplane including unusable fuel, all operating consumables and the maximum quantity of oil. 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. Maximum Take-off Mass: The maximum permissible mass for take-off. Moment: The mass of a component multiplied by its moment arm. Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravity of a component. Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight. Usable Fuel: The quantity of fuel available for flight planning. Useful Load: The difference between take-off mass and empty mass. General D42L AFM Page 1 - 10 D42L-AFM-002 18 Aug 10 Rev. 6 (e) Engine AEO: All Engines Operating BHP: Brake Horse Power CHT: Cylinder Head Temperature. EGT: Exhaust Gas Temperature. MCP: Maximum Continuous Power: Maximum permissible engine output power used continuously during flight. OEI: One Engine Inoperative RPM: Revolutions per minute (rotational speed of the propeller). Take-off Power: Maximum permissible engine output power for take-off. Page 1 - 11 General D42L AFM D42L-AFM-002 Rev. 7 23 May 12 (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 Rcvr No.1 XPDR Transponder LH ENG INST Left Hand Side Engine Instruments PITOT Pitot Heating System XFR PUMP/DE-ICE Fuel Transfer Pump / De-Ice 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 and Stick Limiter 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 Avionics-, CDU-Cooling Fans AVIONIC BUS Avionic Bus AV CONT./AP. WRN. Avionic Control / Autopilot Warning RH ENG INST Right Hand Side Engine Instruments General D42L AFM Page 1 - 12 D42L-AFM-002 23 May 12 Rev. 7 AVIONICS BUS: COM2 COM Radio No. 2 GPS/NAV2 Global Positioning System and NAV ReceiverNo 2 AUDIO Audio Panel AUTO PILOT Auto Pilot System DATA LINK Data Link System GDL 49 Wx 500 Stormscope TAS Traffic Alert System ADF Automatic Direction Finder DME Distance Measuring Equipment LH MAIN BUS: FUEL PUMP Fuel Pump ALT CONT Alternator Control ALT PROT Alternator Protection LH: ALT. LH Alternator LH. BATT Battery RH: BATT Battery ALT. RH RH Alternator RH MAIN BUS: ALT PROT Alternator Protection ALT CONT Alternator Control FUEL PUMP Fuel Pump Page 1 - 13 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 (g) Equipment ELT: Emergency Locator transmitter ACL: Anti-Collision Lights (h) Design Change Advisories MÄM: Mandatory Design Change Advisory (Provided by Diamond Austria). OÄM: Optional Design Change Advisory (Provided by Diamond Austria). (i) Miscellaneous ATC: Air Traffic Control. CAR: Canadian Aviation Regulations. CFRP: Carbon Fiber Reinforced Plastic. EASA: European Aviation Safety Agency EPU: External Power Unit GFRP: Glass Fiber Reinforced Plastic. JAR: Joint Aviation Requirements. JC/VP: Joint Certification/Validation Procedure. PCA: Primary Certification Authority. TCCA: Transport Canada Civil Aviation General D42L AFM Page 1 - 14 D42L-AFM-002 18 Aug 10 Rev. 6 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension Sl-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] hectopascals [mbar] millibars [bar] bars [inHg] inches of mercury [psi] pounds per square inch [hPa] = [mbar] [hPa] / 33.86 = [inHg] [bar] x 14.504 = [psi] Temperature [o C] degrees Celsius [o F] degrees Fahrenheit [o C] x 1.8 + 32 = [o F] ([ o F] - 32) / 1.8 = [ o C] Intensity of electric current [A] ampères -- Electric charge (battery capacity) [Ah] ampère-hours -- Electric potential [V] volts -- Time [sec] seconds -- Page 1 - 15 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 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 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 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 28 106 110 29.1 30 113.6 120 31.7 32 121.1 130 34.3 34 128.7 140 37 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 D42L AFM Page 1 - 16 D42L-AFM-002 18 Aug 10 Rev. 6 1.7 THREE-VIEW DRAWING 3.29 m (10.79 ft) 8.56 m (28.08 ft) 13.42 m (44.03 ft) 1830 mm (72.05 in.) Aircraft with mt Propeller 2.95 m (9.68 ft) 2.49 m 8.17 ft Page 1 - 17 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 1.8 G1000 AVIONICS SYSTEM (a) 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). (b) 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, and for flight planning. The audio panel is used for selection of radios for transmitting and listening, intercom functions, and marker beacon functions. (c) 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. (d) Provided a Garmin G1000 GPS receiver is receiving adequate usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications for: (1) VFR/IFR enroute, oceanic, terminal, and non-precision instrument approach GPS, Loran-C, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation within the U.S. National Airspace System in accordance with AC 20-138A. (2) RNAV (GPS) Approaches - The G1000 GPS meets the requirements of AC 20 138(A) for GPS based RNAV approaches. This includes RNAV approaches labeled as RNAV (GPS), provided GPS sensor data is valid. (3) The systems meets RNP5 airspace (BRNAV) requirements of AC 90-96 and in accordance with AC 20-138A, EASA AMC 20-4, and FAA Order 8110.60 for oceanic and remote airspace operations provided it is receiving usable navigation information from the GPS receiver. Navigation is accomplished using the WGS-84 (NAD-83) coordinate reference datum. GPS navigation data is based upon use of only the GPS operated by the United States of America. General D42L AFM Page 1 - 18 D42L-AFM-002 18 Aug 10 Rev. 6 1.9 SOURCE DOCUMENTATION This section lists documents, manuals and other literatures 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: Textron Lycoming 652 Oliver Street WILLIAMSPORT, PA 17701USA Phone: +1-570-323-6181 Documents: a) Textron Lycoming Operator's Manual, Aircraft Engines IO-360-MIA - Part No. 60297-12 LIO-360-MIA - Part No. 60297-36 b) Service Bulletins (SB) Service Instructions (SI); (e.g. SI 1014, SI 1070) Service Letters (SL); (e.g. SL114 (subscriptions)). 1.9.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 Atting GERMANY Phone: +49-(9429)-9409-0 Internet: www.mt-propeller.com Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 Page 1 - 19 General D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 1.9.3 AVIONICS SYSTEM Address: Garmin International, Inc. 1200 East 151st Street Olathe, Kansas 66062 USA Phone: +1-(913)-3978200 Documents: Garmin G1000 Cockpit Reference Guide for the DA42 L360 P/N 190-01062-XX (Current Revision) Garmin G1000 Pilot's Guide for the Diamond DA42 L360 P/N 190-01061-XX (Current Revision) General D42L AFM Page 1 - 20 D42L-AFM-002 Intentionally left blank Rev. 6 18 Aug 10 Page 2 - 1 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved CHAPTER 2 OPERATING LIMITATIONS TABLE OF CONTENTS PAGE 2.1 INTRODUCTION ................................................................................... 3 2.2 AIRSPEEDS .......................................................................................... 4 2.3 AIRSPEED INDICATOR MARKINGS .................................................... 5 2.4 POWER-PLANT LIMITATIONS.............................................................. 6 2.5 ENGINE INSTRUMENT MARKINGS..................................................... 9 2.6 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000..... 10 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000........................................................ 10 2.6.2 OTHER WARNING ALERTS .................................................. 12 2.7 MASS (WEIGHT) ................................................................................. 13 2.8 CENTER OF GRAVITY........................................................................ 15 2.9 APPROVED MANEUVERS ................................................................. 16 2.10 MANEUVERING LOAD FACTORS...................................................... 17 2.11 OPERATING ALTITUDE ...................................................................... 18 2.12 FLIGHT CREW .................................................................................... 18 2.13 KINDS OF OPERATION ...................................................................... 18 2.14 FUEL.................................................................................................... 21 2.15 LIMITATION PLACARDS ..................................................................... 22 Operating Limitations D42L AFM Page 2 - 2 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved PAGE 2.16 OTHER LIMITATIONS ..........................................................................28 2.16.1 TEMPERATURE ......................................................................28 2.16.2 BATTERY CHARGE ................................................................28 2.16.3 EMERGENCY SWITCH...........................................................28 2.16.4 DOOR LOCKING DEVICE.......................................................28 2.16.5 AUTOPILOT USAGE ...............................................................28 2.16.6 ELECTRONIC EQUIPMENT ...................................................29 2.16.7 GARMIN G1000 AVIONICS SYSTEM .....................................29 2.16.8 SMOKING ................................................................................34 2.16.9 GROUND OPERATION ...........................................................34 2.16.10 USE OF THE SUN VISORS ....................................................34 Page 2 - 3 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual includes operating limitations, instrument markings, and placards necessary for safe operation of the airplane, its power-plant, standard systems and standard equipment. The limitations included in this Chapter are approved. OPERATION OF THE AIRPLANE OUTSIDE OF THE APPROVED OPERATING LIMITATIONS IS NOT PERMISSIBLE. WARNING Operating Limitations D42L AFM Page 2 - 4 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 2.2 AIRSPEEDS Airspeed IAS Remarks VA Maneuvering speed above 3400 lbs (1542 kg) 126 KIAS Do not make full or abrupt control surface movements above this speed up to 3400 lbs (1542 kg) 120 KIAS VFE Max. flaps extended speed LDG 111 KIAS Do not exceed these speeds with the given flap setting APP 137 KIAS VLE Max. landing gear extended speed 194 KIAS Do not exceed this speed with the landing gear extended VLO Max. landing gear operating speed Extension VLOE 194 KIAS Do not operate the landing gear above this speed Retraction VLOR 156 KIAS VMCA Minimum control speed airborne 65 KIAS With one engine inoperative, keep airspeed above this limit VNE Never exceed speed in smooth air 194 KIAS Do not exceed this speed in any operation VNO Max. structural cruising speed 155 KIAS Do not exceed this speed except in smooth air, and then only with caution VSSE Minimum Control Speed for Safe single engine training 80 KIAS Minimum speed authorized in case of one engine intentionally inoperative/idle (training purposes) VYSE Best Rate-of-Climb Speed 90 KIAS Best rate-of-climb speed on one engine Page 2 - 5 Operating Limitations D42L AFM D42L-AFM-002 Rev. 7 23 May 12 DOT Approved 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White band 57 - 111 KIAS Operating range with flaps fully extended. Green band 64 - 155 KIAS Normal operating range. Yellow band 155 - 194 KIAS ‘Caution’ range - “Only in smooth air”. Blue band 90 KIAS Best rate of climb speed, single engine. Red band 65 KIAS Minimum control speed, single engine. Red band 194 KIAS Maximum speed for all operations V NE. Operating Limitations D42L AFM Page 2 - 6 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 2.4 POWER-PLANT LIMITATIONS (a) Number of engines : 2 (b) Engine manufacturer : Textron Lycoming (c) Engine designation Left Hand Engine : IO-360-M1A Right Hand Engine : LIO-360-M1A (d) RPM limitations Max. Continuous RPM : 2700 RPM Max. (e) Manifold pressure limitations Takeoff Power : FULL throttle All Engines Operating (AEO) : 5 minutes One Engine Inoperative (OEI) : No limit Maximum Continuous Power All engines : 160 horsepower (Sea Level-Standard Day) Refer to Section 5.3.2 (Performance) for further information. (f) Oil pressure Minimum (IDLE) : 25 psi / 1.72 bar Maximum : 115 psi / 7.93 bar Normal operating range : 55 to 95 psi / 3.8 to 6.55 bar NOTE Page 2 - 7 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved (g) Oil quantity Minimum : 4 qts / 3.8 liters Maximum : 8 qts / 7.6 liters (h) Oil temperature Maximum :.245 °F (118 °C) (i) Fuel pressure Minimum :. 14 psi / 0.97 bar Maximum :. 35 psi / 2.4 bar (j) Cylinder head temperature Maximum :. 500 °F (260 °C) (k) The operation of both engines with both fuel selectors in the crossfeed position, other than for specific test purposes, is prohibited. MT PROPELLER (a) Propeller manufacturer : mt-Propeller (b) Propeller designation : MTV-12-B-C-F/CF 183-59b and : MTV-12-B-C-F/CFL 183-59b (c) Propeller diameter : 72.05 in. (183 cm) Operating Limitations D42L AFM Page 2 - 8 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved Oil specification: Airplane engine oil should be used which meets SAEJ1899 (MIL-L-22851) Standard (ashless dispersant type). During the first 50 hours of operation of a new or newly overhauled engine, or after replacement of a cylinder, airplane engine oil should be used which meets SAEJ1966 (MIL-L-6082) Standard (straight mineral type). The viscosity should be selected according to the recommendation given in the following table: OAT at ground level During the first 50 hours: SAEJ1966 / MIL-L-6082 Mineral Oil After 50 hours: SAEJ1899 / MIL-L-22851 Ashless Dispersant Oil All temperatures SAE 20-W50 TYPE M SAE 15-W50, SAE 20-W50 above 80 °F (above 27 °C) SAE 60 SAE 60 above 60 °F (above 16 °C) SAE 50 SAE 40 or SAE 50 30 °F to 90 °F (-1 °C to 32 °C) SAE 40 SAE 40 0 °F to 70 °F (-18 °C to 21 °C) SAE 30 SAE 30, SAE 40 or SAE 20-W40 below 10 °F (below -12 °C) SAE 20 SAE 30 or SAE 20-W30 Page 2 - 9 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below: When an indication lies outside the upper or lower range, the numerical indication will begin flashing as well. NOTE Indication Red arc/bar = lower prohibited range Yellow arc/bar = caution range Green arc/bar = normal operating range Yellow arc/bar = caution range Red arc/bar = upper prohibited range Manifold Pressure -- -- 12 - 31 inHg -- -- RPM -- -- 500 - 2700 RPM -- above 2700 RPM Oil Temp. -- -- 149 - 230 OF 231 - 245 OF above 245 O F Cylinder Head Temp -- -- 150 - 475 O F 475 - 500 O F above 500 OF Oil Pressure < 25 psi 25 - 55 psi 56 - 95 psi 96 - 97 psi above 97 psi Fuel Flow -- -- 1 - 25 US gal/hr -- -- Voltage < 24.1 V 24.1 - 25 V 25.1 - 30 V 30.1 - 32 V above 32 V Ammeter -- -- 2 - 75 A -- -- Fuel Quantity 0 US gal -- 1 - 25 US gal -- -- Operating Limitations D42L AFM Page 2 - 10 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 2.6 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 The following tables show the color and significance of the Warning, Caution and Advisory alert 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. AP TRIM FAIL Autopilot automatic trim is inoperative DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. L/R ALTN FAIL Left / Right engine alternator has failed. L/R FUEL PR HI Left / Right engine fuel pressure is greater than 35 psi. L/R FUEL PR LO Left / Right engine fuel pressure is less than 14 psi. L/R OIL PRES Left / Right engine oil pressure is less than 25 psi. L/R STARTER Left / Right engine starter is engaged. When an LRU or an LRU function fails, a large red ‘X’ is typically displayed on windows associated with the failed data, as follows: AIRSPEED FAIL The display system is not receiving airspeed input from the airdata computer. ALTITUDE FAIL The display system is not receiving altitude input from the air data computer. ATTITUDE FAIL The display system is not receiving attitude reference information from the AHRS. GPS ENR Does not show the red X through the display. The system will flag GPS ENR and the G1000 will no longer provide GPS based navigational guidance HDG The display system is not receiving valid heading input from the AHRS. Page 2 - 11 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved Color and significance of the Caution alerts on the G1000 OAT Display system is not receiving valid OAT information from the air data computer. TAS Display system is not receiving valid true airspeed information from the air data computer VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer. WARN RAIM position warning. The nav deviation bar is removed. XPDR FAIL Display system is not receiving valid transponder information. Caution alerts (amber) Meaning / Cause AHRS ALIGN: Keep Wings Level The AHRS (Attitude and Heading Reference System) is aligning. DEIC PRES HI De-icing system pressure is high. (if De-icing system is installed) DEIC PRES LO De-icing system pressure is low. (if De-icing system is installed) DEICE LVL LO De-icing fluid level is low. (if De-icing system is installed) INTEG RAIM not available RAIM (Receiver Autonomous Integrity Monitor) is not available. L/R AUX FUEL E Left / Right fuel tank empty, displayed only when FUEL L/R FUEL LOW Left / Right engine main tank fuel quantity is low. L/R VOLTS LOW Left / Right engine bus voltage is too low (below 25 volts). 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 Stick limiting system has failed. Warning alerts (red) Meaning / Cause Operating Limitations D42L AFM Page 2 - 12 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved Color and significance of the Advisory alerts on the G1000 A full list of G1000 system message advisories are available in the Garmin G1000 Pilot's Guide for the Diamond DA42-L360, Part Number 190-01061-XX (Current Revision) and in the Garmin G1000 Cockpit Reference Guide for the DA42-L360, Part Number 190-01062-XX (Current Revision). 2.6.2 OTHER WARNING ALERTS Warning alerts on the instrument panel Audible Warning alerts Caution alerts (amber) Meaning / Cause GIA FAN FAIL Cooling fan for the GIAs is inoperative. L/R FUEL XFER Fuel transfer from auxiliary to main tank is in progress. MFD FAN FAIL Cooling fan for the MFD is inoperative. PFD FAN FAIL Cooling fan for the PFD is inoperative. NOTE Caution alerts (amber) Meaning / Cause GEAR UNSAFE WARNING LIGHT (red) Illuminates if the landing gear is neither in the final up or down & locked position. Caution alerts (amber) Meaning / Cause GEAR RETRACTED CHIME TONE (repeating) Resounds if the landing gear is retracted while the flaps move into the LDG position or when the throttle is placed in a position forward of IDLE, but below approximately 14 inches of manifold pressure. Page 2 - 13 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 2.7 MASS (WEIGHT) EXCEEDING THE MASS LIMITS WILL LEAD TO AN OVERSTRESSING OF THE AIRPLANE AS WELL AS TO A DEGRADATION OF FLIGHT CHARACTERISTICS AND FLIGHT PERFORMANCE. At the time of lift-off the maximum permitted take-off mass must not be exceeded. Value Mass (kg) Weight (lb) Maximum Ramp 1795 3957 Maximum Take-Off 1785 3935 Maximum Landing 1700 3748 Maximum Zero Fuel 1650 3638 Minimum Flight 1365 3009 Max. Load in Nose Baggage Compartment (in fuselage nose) 30 66 Max. Load in Cockpit Baggage Compartment (behind rear seats) 45 100 Max. Load in Baggage Extension (behind cockpit baggage compartment) 18 40 Max. Load, Cockpit Baggage Compartment and Baggage Extension Together 45 100 WARNING NOTE Operating Limitations D42L AFM Page 2 - 14 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved A landing with a mass between 1700 kg (3748 lb) and 1785 kg (3935 lb) is permissible. It constitutes an abnormal landing. A "Hard Landing Check" (refer to section 05-50 of the AMM) is only required after a hard landing regardless of the actual landing mass. NOTE Page 2 - 15 Operating Limitations D42L AFM D42L-AFM-002 Rev. 7 23 May 12 DOT Approved 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 the 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 (aft of datum plane): Most aft flight CG (aft of datum plane): Refer to Paragraph 6.4.3 for a graphical illustration of the CG limitations. CG Mass (Weight) (m) (in) (kg) (lb) 2.365 93.11 1365 3009 2.365 93.11 1550 3417 2.388 94.02 1700 3748 2.425 95.47 1785 3935 CG Mass (Weight) (m) (in) (kg) (lb) 2.437 95.93 1365 3009 2.451 96.5 1785 3935 Operating Limitations D42L AFM Page 2 - 16 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved EXCEEDING THE CENTER OF GRAVITY LIMITATIONS REDUCES THE CONTROLLABILITY AND STABILITY OF THE AIRPLANE. 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category in accordance with JAR-23. (a) Approved maneuvers (1) All normal flight maneuvers; (2) Stalling (with the exception of power on stalls with a fuel imbalance); 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. AEROBATICS, SPINNING, AND FLIGHT MANEUVERS WITH MORE THAN 60 DEGREES OF BANK ARE NOT PERMITTED IN THE NORMAL CATEGORY. STALLING WITH ASYMMETRIC POWER OR ONE ENGINE INOPERATIVE IS NOT PERMITTED. LARGE SUSTAINED SIDESLIPS ARE PROHIBITED. THEY MAY RESULT IN ENGINE FUEL PRESSURE REDUCTION. RECOVERY FROM THE SIDESLIP IMMEDIATELY CORRECTS CONDITION. WARNING CAUTION CAUTION Page 2 - 17 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 2.10 MANEUVERING LOAD FACTORS The tables below show aircraft structural limitations. AVOID EXTENDED NEGATIVE G-LOADS DURATION. EXTENDED NEGATIVE G-LOADS CAN CAUSE PROPELLER CONTROL PROBLEMS AND ENGINE SURGING. EXCEEDING THE MAXIMUM LOAD FACTORS WILL LEAD TO AN OVERSTRESSING OF THE AIRPLANE. NOTE CAUTION at VA at VNE with flaps in APP or LDG position Positive 3.8 3.8 2.0 Negative -1.52 0 WARNING Operating Limitations D42L AFM Page 2 - 18 D42L-AFM-002 23 May 12 Rev. 7 DOT Approved 2.11 OPERATING ALTITUDE The maximum operating altitude is 18,000 ft (5,486 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew number :1 (one person) Maximum number of occupants :Including Pilot - 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 Night 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 runways. Flights into known or forecast icing conditions are prohibited. Flights into known thunderstorms are prohibited. Page 2 - 19 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 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. Many of the items of minimum equipment listed in the following table are integrated in the G1000. NOTE 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 * one 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) Operating Limitations D42L AFM Page 2 - 20 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved engine instruments * fuel qty. (2x) * oil press. (2x) * oil temp. (2x) * cylinder head temperature (2x) * manifold pressure (2x) * prop. RPM (2x) * Ammeter * Voltmeter lighting * position lights * strobe lights (anti collision lights) * landing light * instrument lighting * flood light * flashlight other operational minimum equipment * stall warning system * fuel quantity measuring device * safety belts for each occupied seat * Airplane Flight Manual * Pitot heating system * Alternate static valve * emergency battery (for backup attitude gyro and flood light) for daytime VFR flights in addition for night VFR flights in addition for IFR flights Page 2 - 21 Operating Limitations D42L AFM D42L-AFM-002 Rev. 7 23 May 12 DOT Approved A list of approved equipment can be found in Chapter 6. 2.14 FUEL Approved fuel grade AVGAS 100 or AVGAS 100LL Although AVGAS 100LL is a better choice of fuel because the lower lead content reduces both the combustion chamber deposits as well as the spark plug deposits, the Lycoming (L) IO-360-M1A engine is approved by Lycoming to run on AVGAS 100 meeting US ASTM D910 specifications. Refer to section 2-9 APPROVED MANEUVERS for additional information on fuel imbalance. NOTE Main Tanks Auxilliary 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 Maximum permissable difference LH/RH 5.0 18.9 NOTE NOTE Operating Limitations D42L AFM Page 2 - 22 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 2.15 LIMITATION PLACARDS All limitation placards are shown below. A list of all placards is included in the Aircraft Maintenance Manual (D42L-AMM-001), Chapter 11 or in the Airplane Maintenance Manual (Doc. No. 7.02.01), Chapter 11. On the instrument panel: THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE FLIGHT MANUAL. IT CAN BE OPERATED IN THE "NORMAL" CATEGORY IN NON-ICING CONDITIONS. PROVIDED THAT NATIONAL OPERATIONAL REQUIREMENTS ARE MET AND THE APPROPRIATE EQUIPMENT IS INSTALLED, THIS AIRPLANE IS APPROVED FOR THE FOLLOWING KIND OF OPERATION: DAY VFR, NIGHT VFR AND IFR. ALL AEROBATIC MANEUVERS INCLUDING SPINNING ARE PROHIBITED. FOR FURTHER OPERATIONAL LIMITATIONS REFER TO THE AIRPLANE FLIGHT MANUAL. MANEUVERING SPEED: VA = 126 KIAS (ABOVE 1542 KG / 3400 LB) VA = 120 KIAS (UP TO 1542 KG / 3400 LB) LANDING GEAR VLE / VLOE = 194 KIAS VLOR = 156 KIAS Page 2 - 23 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved On the Emergency Landing Gear Extension Lever: On the instrument panel, next to the fuel quantity indication: (a) Main Tanks (on those aircraft that do not have auxiliary tanks): OR (b) Auxiliary Tanks (on those aircraft that have auxiliary tanks): EMERGENCY Gear Extension Max. 156 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 Operating Limitations D42L AFM Page 2 - 24 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved Next to each of the two fuel filler necks: (a) Main Tanks: (b) Auxiliary Tanks: WARNING APPROVED FUEL AVGAS 100LL or see Airplane Flight Manual WARNING APPROVED FUEL AVGAS 100LL or see Airplane Flight Manual Page 2 - 25 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved In each cowling, on the inside of the door for the oil filler neck: Next to flap selector switch: OIL SAE 15W50 ashless dispersant aviation grade oil (SAE Standard J1899) or AFM chapter 2 VFR Min./Max.: 4/8 qts (3.8/7.6 liters) IFR Min./Max.: 6/8 qts (5.7/7.6 liters) D41-1126-20-21 Rev. "e" UP Flaps APP 137 KIAS LDG 111 KIAS Operating Limitations D42L AFM Page 2 - 26 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved In the cockpit, on the left fuselage sidewall: Next to the cockpit baggage compartment: BAGGAGE EXTENSION MAX. 18 kg [40 lb] ARM: 4.54 m [178.7"] COCKPIT BAGGAGE COMPARTMENT MAX. 45 kg [100 lb] ARM: 3.89 m [153.1"] MAX. BAGGAGE TOTAL (COCKPIT BAGGAGE COMPARTMENT & EXTENSION): 45 kg [100 lb] CAUTION: OBSERVE WEIGHT AND BALANCE LIMITATIONS SEE AIRPLANE FLIGHT MANUAL CHAPTER 6 Page 2 - 27 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 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 D42L AFM Page 2 - 28 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 2.16 OTHER LIMITATIONS 2.16.1 TEMPERATURE With the outside temperature is below +15 °C (+59 °F) the use of the winter kit for the aircraft is recommended. 2.16.2 BATTERY CHARGE Taking off for a Night VFR or IFR flight with a discharged battery is not permitted. The use of an external power supply for engine starting with a discharged airplane battery is not permitted if the subsequent flight is intended to be an IFR flight. In this case the airplane battery must first be charged. 2.16.3 EMERGENCY SWITCH IFR flights are not permitted when the seal on the emergency switch is broken. 2.16.4 DOOR LOCKING DEVICE The canopy and the passenger door must not be locked by the key lock during operation of the airplane. 2.16.5 AUTOPILOT USAGE At the first indication of an engine failure, the pilot must disengage the autopilot. Use of the AFCS for OEI operations is prohibited. Page 2 - 29 Operating Limitations D42L AFM D42L-AFM-002 Rev. 7 23 May 12 DOT Approved 2.16.6 ELECTRONIC EQUIPMENT The use and switching on of electronic equipment other than that which is part of the equipment of the airplane is not permitted, as it could lead to interference with the airplane's avionics. Examples of undesirable items of equipment are: - Mobile telephones - Remote radio controls - Video screens employing CRTs - Minidisc recorders when in the record mode. This list is not exhaustive. The use of laptop computers, including those with CD-ROM drives, CD and minidisc players in the replay mode, cassette players and video cameras is permitted. All this equipment however should be switched off for take-off and landing. 2.16.7 GARMIN G1000 AVIONICS SYSTEM (a) The Garmin G1000 Cockpit Reference Guide for the DA42 L360, P/N 190-01062-XX (Current Revision) must be immediately available to the flight crew. Software Part Number Approved Version Function System ( ) For the Software Part Number and the Approved Version see the latest Diamond DA42 L360 “Software for the Garmin G1000 System” Service Bulletin. 006-B1054-( ) DA42-L360 System Manifest 006-B0328-( ) GTX 33 MODE S TRANSPONDER 006-B0193-( ) GEA 71 ENGINE AIRFRAME UNIT, NO. 1 006-B0193-( ) GEA 71 ENGINE AIRFRAME UNIT, NO. 2 006-B0261-( ) 006-C0055-( ) GDC 74A AIR DATA COMPUTER Operating Limitations D42L AFM Page 2 - 30 D42L-AFM-002 23 May 12 Rev. 7 DOT Approved 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". 006-B0224-( ) 006-C0048-( ) ( ) For the Software Part Number and the Approved Version see the latest Diamond DA42 L360 “Software for the Garmin G1000 System” Service Bulletin. GMU 44 MAGNETOMETER 006-B0319-( ) GDU 1040 DISPLAY UNIT, PFD 006-B0319-( ) GDU 1040 DISPLAY UNIT, MFD 006-B0544-( ) 006-D0425-( ) GIA 63 AVIONICS INTEGRATION UNIT NO. 1 006-B0544-( ) 006-D0425-( ) GIA 63 AVIONICS INTEGRATION UNIT NO. 2 006-B0223-( ) 006-C0049-( ) GRS 77 ATTITUDE HEADING REFERENCE SYSTEM 006-B0203-( ) GMA 1347 AUDIO PANEL 006-B0317-( ) GDL 69 DATA LINK NOTE Software Part Number Approved Version Function Page 2 - 31 Operating Limitations D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved (b) 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. (c) 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. Not all published approaches are in the FMS database. The pilot must ensure that the planned approach is in the database. (1) 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. (2) 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. (3) 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. (4) 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. (5) 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. (6) RNAV (GPS) approaches must be conducted utilizing the GPS sensor. (7) RNP RNAV operations are not authorized, except as noted in Chapter 1 of this AFM. NOTE Operating Limitations D42L AFM Page 2 - 32 D42L-AFM-002 23 May 12 Rev. 7 DOT Approved (d) 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): (1) DIS, SPD : nm, kt (sets navigation units to "nautical miles" and "knots") (2) ALT, VS : ft, fpm (sets altitude units to "feet" and "feet per minute") (3) POSITION : deg-min (sets navigation grid units to decimal minutes) 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. (e) When AHRS is required to meet the items listed in the Minimum operational equipment (serviceable) table in Paragraph 2.13 of this AFM, operation is prohibited in the following areas: (1) north of 70° N and south of 70° S latitudes, (2) north of 65° N between 75° W and 120° W longitude, and (3) south of 55° S between 120° E and 165° E longitude. When day VFR operations are conducted in the above areas, the MFD must be in a non-Heading Up orientation. NOTE Page 2 - 33 Operating Limitations D42L AFM D42L-AFM-002 Rev. 7 23 May 12 DOT Approved (f) If the CDI source is changed when the autopilot is engaged in NAV mode, the autopilot lateral mode will revert to ROLL ATTITUDE mode and NAV mode must be manually reselected by the pilot. The autopilot LOC mode is designed to engage at the Outer Marker using expanded roll authority to capture the LOC, then uses a limited roll authority to maintain the beam. The Autopilot roll commands may lack authority and become unstable in high crosswinds during coupled LOC operations outside the Outer Marker. If this occurs, use Heading mode to establish an intercept with the beam, then re-engage LOC. (g) The fuel quantity, fuel required, and fuel remaining functions on the Fuel Page (displayed when pushing the FUEL button) of the FMS are supplemental information only and must be verified by the flight crew. (h) The pilot's altimeter is the primary altitude reference during all operations using advisory vertical navigation (VNAV) information and the autopilot. A flight altitude selected via the autopilot must be verified and corrected according to the indication of the calibrated altimeter. The barometric correction and the altitude preselect are not synchronized between Garmin and Bendix/King units. (i) The availability of Safe Taxi® , 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. NOTE NOTE Operating Limitations D42L AFM Page 2 - 34 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 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 may only be used during cruise. During all other phases of flight the sun visors must be locked in the fully upward position. Page 3 - 1 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved CHAPTER 3 EMERGENCY PROCEDURES TABLE OF CONTENTS PAGE 3.1 INTRODUCTION ......................................................................................5 3.1.1 GENERAL.................................................................................5 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES.............................6 3.1.3 SELECTING EMERGENCY FREQUENCY..............................6 3.2 AIRPLANE-RELATED G1000 WARNINGS ..............................................7 3.2.1 WARNINGS/GENERAL ............................................................7 3.2.2 L/R OIL PRESS ........................................................................7 3.2.3 L/R FUEL PR HI .......................................................................8 3.2.4 L/R FUEL PR LO ......................................................................8 3.2.5 L/R STARTER...........................................................................9 3.2.6 L/R ALTN FAIL ........................................................................10 3.2.7 DOOR OPEN ..........................................................................11 3.2.8 AP TRIM FAIL .........................................................................11 3.3 G1000 SYSTEM WARNINGS.................................................................12 3.3.1 RED X .....................................................................................12 3.3.2 GPS ENR................................................................................12 3.3.3 ATTITUDE FAIL ......................................................................12 3.3.4 AIRSPEED FAIL .....................................................................12 Emergency Procedures D42L AFM Page 3 - 2 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved PAGE 3.3.5 ALTITUDE FAIL ......................................................................13 3.3.6 VERTICAL SPEED FAIL.........................................................13 3.3.7 HEADING FAIL .......................................................................13 3.4 G1000 FAILURES...................................................................................14 3.4.1 NAVIGATION INFORMATION FAILURE ................................14 3.4.2 PFD OR MFD DISPLAY FAILURE .........................................14 3.4.3 AHRS FAILURE......................................................................15 3.4.4 AIR DATA COMPUTER (ADC) FAILURE ...............................15 3.4.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS............................................................16 3.4.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS................................17 3.5 ENGINE INOPERATIVE PROCEDURES...............................................18 3.5.1 DETECTING THE INOPERATIVE ENGINE ...........................18 3.5.2 ENGINE SECURING (FEATHERING) PROCEDURE............19 3.5.3 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT .......................................................22 3.5.4 ENGINE FAILURE DURING TAKE-OFF ................................24 3.5.5 ENGINE PROBLEMS ON THE GROUND .............................27 3.5.6 ENGINE PROBLEMS IN FLIGHT...........................................28 3.5.7 ENGINE TROUBLESHOOTING.............................................35 3.5.8 DEFECTIVE ENGINE CONTROLS........................................37 3.5.9 ONE ENGINE INOPERATIVE - FLIGHT ................................38 3.5.10 ONE ENGINE INOPERATIVE - LANDING .............................39 Page 3 - 3 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved PAGE 3.5.11 ONE ENGINE INOPERATIVE GO-AROUND / BALKED LANDING .......................................42 3.6 LANDING GEAR SYSTEM FAILURES...................................................44 3.6.1 LANDING GEAR UNSAFE WARNING...................................44 3.6.2 MANUAL EXTENSION OF THE LANDING GEAR.................45 3.6.3 LANDING GEAR UP LANDING..............................................47 3.6.4 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR ............................................48 3.6.5 LANDING WITH DEFECTIVE BRAKES .................................49 3.7 FAILURES IN THE ELECTRICAL SYSTEM ...........................................50 3.7.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM .......50 3.7.2 STARTER MALFUNCTION ....................................................52 3.7.3 OVERVOLTAGE .....................................................................53 3.8 SMOKE AND FIRE .................................................................................54 3.8.1 ENGINE FIRE ON THE GROUND .........................................54 3.8.2 ENGINE FIRE DURING TAKE-OFF .......................................55 3.8.3 ENGINE FIRE DURING FLIGHT ............................................57 3.8.4 ELECTRICAL FIRE ON GROUND .........................................58 3.8.5 ELECTRICAL FIRE IN FLIGHT ..............................................59 3.9 OTHER EMERGENCIES ........................................................................60 3.9.1 ICING ......................................................................................60 3.9.2 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN .........................................61 3.9.3 RECOVERY FROM AN UNINTENTIONAL SPIN...................62 3.9.4 UNLOCKED DOORS..............................................................63 Emergency Procedures D42L AFM Page 3 - 4 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved PAGE 3.9.5 DEFECTIVE PROPELLER RPM REGULATING SYSTEM.........................................................65 3.9.6 EMERGENCY DESCENT ......................................................66 3.9.7 EMERGENCY EXIT................................................................67 Procedures for non-critical system faults are given in Chapter 4B ABNORMAL OPERATING PROCEDURES. NOTE Page 3 - 5 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.1 INTRODUCTION 3.1.1 GENERAL This Chapter contains checklists as well as the description of recommended procedures to be followed in the event of an emergency. Engine failure or other airplane-related emergencies are most unlikely to occur if the prescribed procedures for pre-flight checks and airplane maintenance are followed. If, nonetheless, an emergency does arise, the guidelines given here should be followed and applied in order to clear the problem. As it is impossible to foresee all kinds of emergencies and cover them in this Airplane Flight Manual, a thorough understanding of the airplane by the pilot is, in addition to his knowledge and experience, an essential factor in the solution of any problems which may arise. Emergency Procedures D42L AFM Page 3 - 6 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved IN EACH EMERGENCY, CONTROL OVER THE FLIGHT ATTITUDE AND THE PREPARATION OF A POSSIBLE EMERGENCY LANDING HAVE PRIORITY OVER ATTEMPTS TO SOLVE THE CURRENT PROBLEM ("FIRST FLY THE AIRCRAFT"). PRIOR TO THE FLIGHT THE PILOT MUST CONSIDER THE SUITABILITY OF THE TERRAIN FOR AN EMERGENCY LANDING FOR EACH PHASE OF THE FLIGHT. FOR A SAFE FLIGHT THE PILOT MUST CONSTANTLY KEEP A SAFE MINIMUM FLIGHT ALTITUDE. SOLUTIONS FOR VARIOUS ADVERSE SCENARIOS SHOULD BE THOUGHT OVER IN ADVANCE. THUS IT SHOULD BE GUARANTEED THAT THE PILOT IS AT NO TIME SHOCKED BY AN ENGINE FAILURE AND THAT HE CAN ACT CALMLY AND WITH DETERMINATION. 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES EVENT AIRSPEED One engine inoperative minimum control speed (Air) V MCA ....................................65 KIAS One engine inoperative speed for best rate of climb VYSE ...................................... 90 KIAS 3.1.3 SELECTING EMERGENCY FREQUENCY In an in-flight emergency, depressing and holding the Com transfer button on the G1000 for two 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. WARNING Page 3 - 7 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 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 shown in red in the annunciation window. A continuous chime tone will sound with a flashing "WARNING" softkey annunciation. Pressing the WARNING Softkey acknowledges the presence of the warning alert and stops the aural chime. 3.2.2 L/R OIL PRESS L/R OIL PRES Left / Right engine oil pressure is less than 25 psi. Oil pressures below the limit value of 25 psi can lead to a total loss of power due to engine failure. (a) Check the oil pressure warning light and the oil pressure indicator (b) Check the oil temperature (1) If the oil pressure indication drops below the green sector and the oil temperature is normal (oil pressure warning light does not illuminate or flash): (A) Monitor the oil pressure warning light: it is probable that the oil pressure indication is defective (B) Monitor the oil and cylinder head temperatures. (2) If the oil pressure indication drops below the green sector while the oil or cylinder head temperature is rising, or if the oil pressure warning light illuminates or flashes, or if both of these occur together: (A) Reduce engine power to the minimum required. (B) Land as soon as possible. (C) Be prepared for an engine failure and emergency landing. CONTINUED Emergency Procedures D42L AFM Page 3 - 8 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved (3) If Oil pressure tending to zero combined with: Vibration, loss of oil, possibly unusual metallic noise and smoke: (A) A mechanical failure in the engine is apparent. (B) Shut off the engine immediately and (C) Carry out emergency landing in accordance with Paragraph 3.5.10 - ONE ENGINE INOPERATIVE - LANDING. END OF CHECKLIST 3.2.3 L/R FUEL PR HI L/R FUEL PR HI Left / Right engine fuel pressure is greater than 35 psi. - Turn off the fuel pump for the affected engine, if the fuel pump is selected ON. - Reduce power on the affected engine by reducing the THROTTLE lever as required. END OF CHECKLIST 3.2.4 L/R FUEL PR LO L/R FUEL PR LO Left / Right engine fuel pressure is less than 14 psi. - Turn on the electric fuel pump for the affected engine. END OF CHECKLIST Page 3 - 9 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.2.5 L/R STARTER L/R STARTER Left / Right engine starter is engaged. If the starter does not disengage from the engine after starting (starter warning message (START) on the G1000 remains illuminated or flashing after the engine has started): (a) THROTTLE lever............................................... IDLE (b) MIXTURE control lever...................................... IDLE cut-off (c) Ignition switch.................................................... OFF (d) ELECT. MASTER switch................................... OFF Terminate flight preparation. END OF CHECKLIST Emergency Procedures D42L AFM Page 3 - 10 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.2.6 L/R ALTN FAIL L/R ALTN FAIL Left / Right engine alternator has failed. (a) One alternator failed (1) ALT PROT/ALT CONT circuit breakers....... check affected side (2) ALTERNATOR ON/OFF switch................... cycle affected side If the alternator does not come back on line: (3) ALTERNATOR ........................................... OFF/affected side (A) Bus voltage.......................... monitor (4) Electrical consumers................................... reduce as practicable. (b) Both alternators failed: 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. REFER TO PARAGRAPH 3.7.1 (G) - COMPLETE FAILURE OF THE ELECTRICAL SYSTEM. END OF CHECKLIST WARNING Page 3 - 11 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.2.7 DOOR OPEN DOOR OPEN Front and/or rear canopy and/or baggage door are/is not closed and locked. (a) Airspeed ............................................................ reduce (b) Canopy .............................................................. check visually if closed (c) Rear passenger door......................................... check visually if closed NEVER UNLOCK THE REAR PASSENGER DOOR DURING FLIGHT. IT CAN BREAK AWAY AND CAUSE DAMAGE TO THE AIRCRAFT AND PERSONAL INJURY. (d) Front baggage doors ......................................... check visually if closed (e) Land at the nearest suitable airfield. END OF CHECKLIST 3.2.8 AP TRIM FAIL AP TRIM FAIL The autopilot automatic trim is inoperative. Disconnect the autopilot and fly the airplane manually. Trim the airplane manually as required. END OF CHECKLIST WARNING Emergency Procedures D42L AFM Page 3 - 12 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.3 G1000 SYSTEM WARNINGS 3.3.1 RED X A red X through any display field, such as COM frequencies, NAV frequencies, TAS, OAT or engine data, indicates that display field is not receiving valid data. 3.3.2 GPS ENR GPS ENR Does not show the red X through the display. The system will flag GPS ENR and no longer provide GPS based navigational guidance. Revert to the G1000 VOR/ILS receivers or an alternate means of navigation other than the G1000 GPS receivers. 3.3.3 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. 3.3.4 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 indicator. Page 3 - 13 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.3.5 ALTITUDE FAIL ALTITUDE FAIL The display system is not receiving altitude input from the air data computer; accompanied by a red X through the altimeter display. Revert to the standby altimeter. 3.3.6 VERTICAL SPEED FAIL VERTICAL SPEED FAIL The display system is not receiving vertical speed input from the air data computer; accompanied by a red X through the vertical speed display. Determine vertical speed based on the change of altitude information. 3.3.7 HEADING FAIL HEADING FAIL The display system is not receiving valid heading input from the AHRS; accompanied by a red X through the HDG display. Revert to the emergency compass. Emergency Procedures D42L AFM Page 3 - 14 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.4 G1000 FAILURES 3.4.1 NAVIGATION INFORMATION FAILURE If Garmin G1000 GPS navigation information is not available or invalid, utilize the remaining operational navigation equipment as required. 3.4.2 PFD OR MFD DISPLAY FAILURE (a) DISPLAY BACKUP button on audio panel........ PUSH (b) Automatic Entry of Display Failure If the PFD and MFD have automatically entered reversionary mode, use the following procedure: (1) DISPLAY BACKUP button on the audio panel ........................... PUSH (Button will be out) After automatic entry of reversionary mode, the pilot must press the DISPLAY BACKUP button on the audio panel. After the DISPLAY BACKUP button has been pushed, the system will remain in reversionary mode even if the problem causing the automatic entry of reversionary mode is resolved. A maximum of one attempt to return to normal mode is approved using the following procedure. (2) DISPLAY BACKUP button on the audio panel ........................... PUSH (Button will be in) - If the system returns to normal mode, leave the DISPLAY BACKUP button IN and continue. - lf the system remains in reversionary mode, or abnormal display behavior such as display flashing occurs, then return the DISPLAY BACKUP button to the OUT position. NOTE Page 3 - 15 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.4.3 AHRS FAILURE A failure of the Attitude and Heading Reference System (AHRS) is indicated by a removal of the sky/ground presentation and a red X and a yellow "AHRS FAILURE" shown on the PFD. The digital heading presentation will be replaced with a yellow "HDG" and the compass rose digits will be removed. The course pointer will indicate straight up and course may be set using the digital window. (a) Use the standby attitude indicator, emergency compass and Navigation Map (b) Course............................................................... Set using digital window. 3.4.4 AIR DATA COMPUTER (ADC) FAILURE A Complete loss of the Air Data Computer is indicated by a red X and yellow text over the airspeed, altimeter, vertical speed, TAS and OAT displays. Some FMS functions, such as true airspeed and wind calculations, will also be lost. (a) Use the standby airspeed indicator and altimeter. NOTE NOTE Emergency Procedures D42L AFM Page 3 - 16 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.4.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS Loss of an engine parameter is indicated by a red X through the data field. Erroneous information may be identified by indications which do not agree with other system information. Erroneous indications may be determined by comparing a display with other displays and other system information. (a) Set power based on THROTTLE lever position, engine noise and speed. (b) Monitor other indications to determine the health of the engine. (c) Use known power settings and performance data refer to Paragraph 5.3.2 - FUEL FLOW DIAGRAM for approximate fuel flow values. (d) Use other system information, such as annunciator messages, fuel quantity and flow, to safely complete the flight. NOTE Page 3 - 17 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.4.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present. An erroneous annunciator may be identified when an annunciator appears which does not agree with other displays or system information. (a) If an annunciator appears, treat it as if the condition exists. Refer to Chapter 3 - EMERGENCY PROCEDURES or Chapter 4B - ABNORMAL OPERATING PROCEDURES. (b) If a display indicates an abnormal condition but no annunciator is present, use other system information, such as engine displays, GPS, fuel quantity and flow, to determine if the condition exists. If it cannot be determined that the condition does not exist, treat the situation as if the condition exists. Refer to Chapter 3 - EMERGENCY PROCEDURES or Chapter 4B - ABNORMAL OPERATING PROCEDURES. NOTE Emergency Procedures D42L AFM Page 3 - 18 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.5 ENGINE INOPERATIVE PROCEDURES IN CERTAIN COMBINATIONS OF AIRCRAFT WEIGHT, CONFIGURATION, AMBIENT CONDITIONS, SPEED AND PILOT SKILL, NEGATIVE CLIMB PERFORMANCE MAY RESULT. REFER TO CHAPTER 5 PERFORMANCE FOR ONE ENGINE INOPERATIVE PERFORMANCE DATA. IN ANY EVENT THE SUDDEN APPLICATION OF POWER DURING ONE-ENGINE INOPERATIVE OPERATION MAKES THE CONTROL OF THE AIRCRAFT MORE DIFFICULT. 3.5.1 DETECTING THE INOPERATIVE ENGINE One engine inoperative means an asymmetric loss of thrust, resulting in uncommanded yaw and roll in direction of the so- called "dead" engine (with coordinated controls). To handle this situation it is indispensable to maintain directional control by mainly rudder and additional aileron input. The following mnemonic trick can help to identify the failed engine: "Dead foot - dead engine" This means that, once directional control is re-established, you feel the control force on your foot pushing the rudder- pedal on the side of the operative engine, while the foot on the side of the failed engine feels no force. Further, the engine instruments can help to analyze the situation. WARNING NOTE Page 3 - 19 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved 3.5.2 ENGINE SECURING (FEATHERING) PROCEDURE Depending on the situation, attempts can be made to restore engine power prior to securing the engine. The minimum control speed (V MC ) with one engine inoperative (windmill) and 5 o bank angle towards the good engine is 65 KIAS. The climb speed with one engine inoperative (feather) is 90 KIAS (V YSE ). (a) Maintain lateral & directional control. (b) MIXTURE control levers.................................... full forward (c) PROPELLER RPM levers ................................. full forward (d) THROTTLE levers............................................. full forward (e) LANDING GEAR & FLAPS ............................... UP (f) Inoperative engine............................................. identify and verify Shut down and feathering of the affected engine: (g) Operative engine ............................................... Apply maximum power or power as required to keep safe flight Securing the feathered engine: (h) THROTTLE lever............................................... affected engine IDLE CONTINUED NOTE Emergency Procedures D42L AFM Page 3 - 20 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved THE DESIGN OF THE PROPELLER FEATHERING SYSTEM DOES NOT ALLOW THE FEATHERING OF A PROPELLER WHICH IS NOT TURNING. FOR THIS REASON, IT IS VERY IMPORTANT THAT IF THE PROPELLER IS TO BE FEATHERED, THIS IS DONE BEFORE IT STOPS TURNING, OR FEATHERING WILL NOT BE POSSIBLE. (i) PROPELLER RPM lever ................................... affected engine - FEATHER (j) MIXTURE control lever ..................................... affected engine - IDLE cut-off (k) Ignition switch (magneto) .................................. affected engine - OFF (l) ALTERNATOR .................................................. affected engine - OFF (m) FUEL PUMP...................................................... inoperative engine - OFF (n) FUEL SELECTOR............................................. inoperative engine - OFF (o) THROTTLE control lever on dead engine ......... up enough to silence the gear horn. CONTINUED CAUTION Page 3 - 21 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved REMOVAL OF GEAR HORN POWER, BY PULLING THE GEAR HORN CB, WILL ALSO REMOVE POWER TO THE STICK LIMITER. The remaining fuel in the tank of the failed engine can be used for the good engine, to extend the range and maintain lateral balance, by setting the good engine fuel selector in the CROSSFEED position. The engine performance data will not be valid if an engine has been stopped and the propeller is not feathered. END OF CHECKLIST CAUTION NOTE NOTE Emergency Procedures D42L AFM Page 3 - 22 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.5.3 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT Restarting the engine is possible at all airspeeds above a safe flying airspeed up to V NE (194 KIAS) and up to the maximum demonstrated operating altitude. (a) Preparation: (1) Airspeed...................................................... 90 KIAS minimum (2) FUEL SELECTORS.................................... ON (3) FUEL PUMP ............................................... check ON (4) THROTTLE lever ........................................ set (3-4 cm forward of IDLE) (5) ALTERNATE AIR ........................................ as required (b) Unfeathering the engine: (1) PROPELLER RPM Lever ........................... Fully forward (c) Starting the windmilling engine: (1) MIXTURE control lever ............................... Rich (2) Ignition switch ............................................. BOTH (3) ALTERNATOR ............................................ ON (d) If the engine does not windmill: (1) Ignition switch ............................................. START, until propeller windmills CONTINUED NOTE Page 3 - 23 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved (e) If the engine does not start: (1) MIXTURE control lever ............................... IDLE cut-off (2) MIXTURE control lever ............................... advance forward slowly until the engine starts. IF THE OIL PRESSURE HAS NOT MOVED INTO THE GREEN SECTOR WITHIN 15 SECONDS AFTER STARTING, SWITCH OFF THE ENGINE. If it is not possible to start the engine, continue with Paragraph 3.5.2 - ENGINE SECURING (FEATHERING) PROCEDURE. END OF CHECKLIST WARNING NOTE Emergency Procedures D42L AFM Page 3 - 24 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved 3.5.4 ENGINE FAILURE DURING TAKE-OFF (a) Engine failure with the landing gear extended. During ground roll: - abort takeoff (1) THROTTLE levers ...................................... IDLE / BOTH (2) Rudder ........................................................ maintain directional control (3) Brakes......................................................... as required If remaining runway / surface is inadequate to stop continue straight ahead, keep clear of obstacles. IF SUFFICIENT TIME IS REMAINING, THE RISK OF FIRE IN THE EVENT OF A COLLISION WITH OBSTACLES CAN BE REDUCED AS FOLLOWS: (4) FUEL SELECTORS.................................... OFF (5) MIXTURE control levers ............................. IDLE cut-off (6) Ignition switches ......................................... OFF (7) ELECT. MASTER........................................ OFF. END OF CHECKLIST CAUTION Page 3 - 25 Emergency Procedures D42L AFM D42L-AFM-002 Rev. 6 18 Aug 10 DOT Approved (b) Engine Failure after lift-off If the landing gear is still down and the remaining runway/surface is adequate: - abort the takeoff and land straight ahead, turning to avoid obstacles If the remaining runway / surface is inadequate: - decide whether to abort or to continue the take-off. IN CERTAIN COMBINATIONS OF AIRCRAFT WEIGHT, CONFIGURATION, AMBIENT CONDITIONS, SPEED AND PILOT SKILL, THE RESULTING CLIMB PERFORMANCE MAY NEVERTHELESS BE INSUFFICIENT TO CONTINUE THE TAKE-OFF SUCCESSFULLY. THEREFORE, A CONTINUED TAKEOFF WITH A FAILED ENGINE HAS TO BE AVOIDED IF AT ALL POSSIBLE. REFER TO CHAPTER 5 PERFORMANCE, FOR ONE ENGINE INOPERATIVE PERFORMANCE DATA. Continued takeoff: (1) MIXTURE control levers ............................. full forward (2) PROPELLER RPM levers........................... full forward (3) THROTTLE levers ...................................... full forward (4) Rudder ........................................................ maintain directional control (5) Airspeed...................................................... Vyse 90 KIAS / as required (6) Ignition switches.......................................... check BOTH (7) FUEL PUMPS ............................................. ON CONTINUED WARNING Emergency Procedures D42L AFM Page 3 - 26 D42L-AFM-002 18 Aug 10 Rev. 6 DOT Approved (8) FLAPS ........................................................ verify UP (9) Landing Gear .............................................. UP to achieve a positive ROC (10)Failed Engine.............................................. identify For the failed engine, move the controls and switches as follows: (11)THROTTLE lever ........................................ IDLE, then move it up enough to silence the gear warning horn (12)PROPELLER RPM lever ............................ FEATHER (13)MIXTURE control lever ...................
283 Diamond DA42 VI parts for sale
See all →
Parts listed for sale by vetted eBay sellers — confirmed on eBay at checkout.