Diamond Aircraft DA 40 NG Airplane Maintenance Manual
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Diamond Aircraft DA 40 NG Airplane Maintenance Manual

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AIRCRAFT
DA 40 NG
AIRPLANE MAINTENANCE MANUAL
Copyright © by DIAMOND AIRCRAFT INDUSTRIES, Wiener Neustadt, Austria

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  • Page 1 AIRCRAFT DA 40 NG AIRPLANE MAINTENANCE MANUAL Copyright © by DIAMOND AIRCRAFT INDUSTRIES, Wiener Neustadt, Austria...
  • Page 2 Introduction DA 40 NG AMM AIRCRAFT 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.
  • Page 3 Time Limits and Maintenance Checks 05-10 Time Limits 05-20 Scheduled Maintenance Checks 05-21 Flight-Line Checks 05-25 Drain Holes Inspection Checklist and Report 05-28 Maintenance Checklist DA 40 NG 05-50 Unscheduled Maintenance Checks 06-00 Dimensions and Areas 07-00 Lifting and Shoring 07-10 Jacking 08-00...
  • Page 4 Table of Contents DA 40 NG AMM AIRCRAFT 21-00 Air Conditioning, Heating and Ventilation 21-50 Cooling 21-51 Cooling (OÄM 40-316/i or later installed) 22-00 Auto Flight 22-10 Autopilot, GFC 700 22-11 Autopilot, KAP 140 23-00 Communications 23-10 Speech Communication with G1000 System Installed...
  • Page 5 Table of Contents DA 40 NG AMM AIRCRAFT 32-00 Landing Gear 32-10 Main Landing Gear 32-20 Nose Landing Gear 32-40 Wheels and Brakes 33-00 Lights 33-10 Lights - Flight Compartment 33-40 Exterior Lights 34-00 Navigation 34-10 Flight Environment Data 34-20...
  • Page 6 Table of Contents DA 40 NG AMM AIRCRAFT 56-00 Windows 56-10 Flight Compartment Windows 57-00 Wings 57-10 Wing Structure 57-50 Flaps 57-60 Aileron 61-00 Propeller 61-10 Propeller Assembly 61-20 Propeller Control 71-00 Power Plant 71-10 Engine Cowling 71-20 Engine Mounting...
  • Page 7 Record of Revision DA 40 NG AMM AIRCRAFT Record of Revision 1. Record of Revision Use this check list to record and control all of the revisions which you put in this Airplane Maintenance Manual (AMM). Put the affected pages of the revision into the AMM as soon as you get them. Remove and destroy the pages which are superseded.
  • Page 8 Record of Revision DA 40 NG AMM AIRCRAFT 2. Record of Incorporated Temporary Revisions The following Temporary Revisions are incorporated into the DA 40 NG AMM by Revision 1: Temporary Revision Number Description of Temporary Revision AMM-TR-MÄM 40-434 Cowling Redesign AMM-TR-MÄM 40-434/a...
  • Page 9 Record of Revision DA 40 NG AMM AIRCRAFT The following Temporary Revisions are incorporated into the DA 40 NG AMM by Revision 2: Temporary Revision Number Description of Temporary Revision AMM-TR-MÄM 40-502/a & Replacement of Charged Air Hoses with Tube AMM-TR-MÄM 40-506/a...
  • Page 10 Record of Revision DA 40 NG AMM AIRCRAFT The following Temporary Revisions are incorporated into the DA 40 NG AMM by Revision 3: Temporary Revision Number Description of Temporary Revision AMM-TR-MÄM 40-561 New GFC 700 Autopilot Hardware AMM-TR-MÄM 40-619 Passenger Door Improvement AMM-TR-MÄM 40-635...
  • Page 11 Record of Revision DA 40 NG AMM AIRCRAFT Temporary Revision Number Description of Temporary Revision AMM-TR-MÄM 40-865 Conservation of Exterior Parts AMM-TR-MÄM 40-868 Garmin Hard- und Software Upgrade I AMM-TR-MÄM 40-874 Engine Oils AMM-TR-MÄM 40-899 Improved Air Charge Hose AMM-TR-OÄM 40-251 Electrical Pedal Adjustment AMM-TR-OÄM 40-258...
  • Page 12 Record of Revision DA 40 NG AMM AIRCRAFT Intentionally left blank Page x Doc # 6.02.15 01 Sep 2017 Rev. 3...
  • Page 13 List of Effective Pages DA 40 NG AMM AIRCRAFT LIST OF EFFECTIVE PAGES 1. General The list of effective pages uses this abbreviation: Table of Contents. Record of Revisions. LOEP List of Effective Pages. All Sections have a Title Page and a Table of Contents. The TOC can have one page or it can have many pages.
  • Page 14 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 03-00 01 Sep 2017 05-10 01 Sep 2017 05-28-00 01 Sep 2017 03-00 01 Sep 2017...
  • Page 15 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 05-28-50 01 Sep 2017 05-50 01 Sep 2017 08-00 Title 1 01 Sep 2017 05-50 01 Sep 2017...
  • Page 16 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 09-00 01 Sep 2017 11-20 01 Sep 2017 12-10 01 Sep 2017 09-10 01 Sep 2017...
  • Page 17 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 20-00 TOC 1 01 Sep 2017 21-00 01 Sep 2017 21-51 01 Sep 2017 21-00 01 Sep 2017...
  • Page 18 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 22-10 01 Sep 2017 22-11 01 Sep 2017 23-10 01 Sep 2017 22-10 01 Sep 2017...
  • Page 19 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 23-51 01 Sep 2017 24-30 01 Sep 2017 24-33 01 Sep 2017 24-30 01 Sep 2017...
  • Page 20 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 24-60 01 Sep 2017 25-10 01 Sep 2017 25-60 01 Sep 2017 24-60 01 Sep 2017...
  • Page 21 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 27-10 01 Sep 2017 27-20 01 Sep 2017 27-38 01 Sep 2017 27-20 01 Sep 2017...
  • Page 22 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 27-50 01 Sep 2017 28-10 01 Sep 2017 28-20 01 Sep 2017 27-50 01 Sep 2017...
  • Page 23 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 28-40 01 Sep 2017 31-20 01 Sep 2017 31-40 01 Sep 2017 31-40 01 Sep 2017...
  • Page 24 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 32-10 01 Sep 2017 32-20 01 Sep 2017 32-40 01 Sep 2017 32-10 01 Sep 2017...
  • Page 25 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 33-40 01 Sep 2017 34-00 01 Sep 2017 34-22 01 Sep 2017 34-10 01 Sep 2017...
  • Page 26 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 34-42 01 Sep 2017 34-56 01 Sep 2017 51-20 01 Sep 2017 34-42 01 Sep 2017...
  • Page 27 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 51-30 01 Sep 2017 52-00 TOC 2 01 Sep 2017 52-10 01 Sep 2017 52-00 01 Sep 2017...
  • Page 28 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 53-10 01 Sep 2017 55-20 01 Sep 2017 56-10 01 Sep 2017 53-10 01 Sep 2017...
  • Page 29 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 57-10 01 Sep 2017 61-10 01 Sep 2017 61-20 01 Sep 2017 61-10 01 Sep 2017...
  • Page 30 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 71-00 01 Sep 2017 71-60 01 Sep 2017 72-00 01 Sep 2017 71-00 01 Sep 2017...
  • Page 31 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 75-00 01 Sep 2017 76-00 TOC 2 01 Sep 2017 77-40 01 Sep 2017 76-00 01 Sep 2017...
  • Page 32 List of Effective Pages DA 40 NG AMM AIRCRAFT Chapter Page Revision Chapter Page Revision Chapter Page Revision Section Date Section Date Section Date 78-00 01 Sep 2017 81-00 TOC 1 01 Sep 2017 92-00 01 Sep 2017 79-00 Title 1 01 Sep 2017...
  • Page 33 Introduction DA 40 NG AMM AIRCRAFT CHAPTER 01 INTRODUCTION Doc # 6.02.15 Page 1 01-TITLE Rev. 3 01 Sep 2017...
  • Page 34 Introduction DA 40 NG AMM AIRCRAFT Intentionally left blank Page 2 Doc # 6.02.15 01-TITLE Rev. 3 01 Sep 2017...

  • Page 35: Table Of Contents

    Introduction DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 01 INTRODUCTION General ............1 Revision Service .
  • Page 36 Introduction DA 40 NG AMM AIRCRAFT Intentionally left blank Page 2 Doc # 6.02.15 01-CONTENTS Rev. 3 01 Sep 2017...

  • Page 37: Introduction

    This Airplane Maintenance Manual contains the data necessary to do the maintenance of the DA 40 NG. It contains a full description of the systems, trouble shooting procedures, removal and installation procedures and maintenance instructions. It does not contain maintenance data for components removed from the airplane (maintenance shop data).

  • Page 38: Manual Configuration

    Introduction DA 40 NG AMM AIRCRAFT 4. Manual Configuration This manual is written using the regulations of the Air Transport Association of America Specification 100 (ATA 100). Each system is given a chapter number from the ATA 100. Where applicable, a chapter contains sections for each sub-system.
  • Page 39 Introduction DA 40 NG AMM AIRCRAFT A. The ATA100 Numbering System The ATA100 numbering system uses 3 pairs of numbers, for example: 57-50-xx Chapter / System Section / Subsystem Unit / Subject Number (Wings) (Flaps) (Not normally used) The first pair of numbers show the system. System 57 is the Wings. Chapter 57 contains the data for the wings.
  • Page 40 Introduction DA 40 NG AMM AIRCRAFT The main contents of each group of chapters is given below: (1) Group A - Introduction Chapter 1 tells you about the Airplane Maintenance Manual, and Chapter 2 tells you how to use the Airplane Maintenance Manual.
  • Page 41 Introduction DA 40 NG AMM AIRCRAFT (5) Group E - Propeller Chapter 61 contains the maintenance procedures for the propeller. Refer to the propeller manufacturer’s manual for other data. (6) Group F - Power Plant This group of chapters describes the engine and its systems which make the Power Plant. It contains the maintenance procedures for maintenance on the airplane.

  • Page 42: Page Numbering System

    Introduction DA 40 NG AMM AIRCRAFT 5. Page Numbering System This manual uses the ATA 100 page block-numbering system. The page number is at the bottom on the outer edge. It is adjacent to the chapter/section number. Each topic in a section has numbers from these page blocks: Description and Operation - Pages 1 to 99.
  • Page 43 Manual Organization DA 40 NG AMM AIRCRAFT CHAPTER 02 ORGANIZATION AND HANDLING OF THE MANUAL Doc # 6.02.15 Page 1 02-TITLE Rev. 3 01 Sep 2017...
  • Page 44 Manual Organization DA 40 NG AMM AIRCRAFT Intentionally left blank Page 2 Doc # 6.02.15 02-TITLE Rev. 3 01 Sep 2017...
  • Page 45 Manual Organization DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 02 ORGANIZATION AND HANDLING OF THE MANUAL General ............1 Applicability .
  • Page 46 Manual Organization DA 40 NG AMM AIRCRAFT Intentionally left blank Page 2 Doc # 6.02.15 02-CONTENTS Rev. 3 01 Sep 2017...

  • Page 47: Organization And Handling Of The Manual

    Manual Organization DA 40 NG AMM AIRCRAFT CHAPTER 02 ORGANIZATION AND HANDLING OF THE MANUAL 1. General For data about a system, look in the list of chapters and find the chapter number. The first page of each chapter after the title page shows the contents.

  • Page 48: Service Bulletins

    Manual Organization DA 40 NG AMM AIRCRAFT 5. Service Bulletins Service Bulletins get issued when necessary. They give the operator more information on inspections, maintenance, repairs or modifications. Service Bulletins have 4 categories: A. Alert Service Bulletins Alert Service Bulletins are issued if there is an immediate danger (risk of damage or total loss).

  • Page 49: Service Information

    Manual Organization DA 40 NG AMM AIRCRAFT 6. Service Information A Service Information tells the operator about permitted installations or provided information to installed or additional equipment. It also gives the applicable technical data. 7. Concession-Reports and Non-Conformance-Reports Concession- and Non-Conformance-Reports are tools to approve and document deviations from the standard manufacturing processes during construction and assembly of an individual airplane (for example, handling of a mis-drilled hole in the fuselage).

  • Page 50: Abbreviations

    Manual Organization DA 40 NG AMM AIRCRAFT 8. Abbreviations Where possible, the abbreviations used correspond with the related regulations. Ampere Anti-Collision Light Automatic Direction Finder A.M.E. Aircraft Maintenance Engineer Ampere-Hour A&P Aircraft and Power Plant Mechanic Airspeed Indicator Controller Area Network...
  • Page 51 Manual Organization DA 40 NG AMM AIRCRAFT Secondary Engine Display Serial Number Time Between Overhaul TSMOH Time Since Major Overhaul Ultra High Frequency TTSN Total Time Since New TTSO Total Time Since Overhaul Volt Visual Flight Rules Very High Frequency...

  • Page 52: Conversion Factors And Abbreviations

    Manual Organization DA 40 NG AMM AIRCRAFT 9. Conversion Factors and Abbreviations Dimension Conversion Factor Conversion Factor Unit [Abbreviation] SI to US/Imperial US/Imperial to SI Length [m] / 0.3048 = [ft] Meter [m] [mm] / 25.4 = [in] Millimeter [mm] [km] / 1.852 = [nm]...
  • Page 53 Manual Organization DA 40 NG AMM AIRCRAFT Dimension Conversion Factor Conversion Factor Unit [Abbreviation] SI to US/Imperial US/Imperial to SI Force or Weight Newton [N] [N] / 4.448 = [lb] Decanewton [daN] [daN] / 0.4448 = [lb] Pound [lb] [lb] x 4.448 = [N] [lb] x 0.4448 = [daN]...

  • Page 54: Torque Conversion Graphs

    Manual Organization DA 40 NG AMM AIRCRAFT 10. Torque Conversion Graphs Use Figure 1 for conversion of torque values Nm - lbf.ft. Use Figure 2 for conversion of Nm - lbf.in. 10 15 20 25 30 45 50 55 60 65 70 75 80 85 90 95 100 Newton.Metre (Nm)
  • Page 55 Manual Organization DA 40 NG AMM AIRCRAFT 0.5 1.0 1.5 2.0 2.5 3.0 4.5 5.0 5.5 6.0 6.5 7.0 7.5 8.0 8.5 9.0 9.5 10.0 Newton.Metre (Nm) Figure 2: Nm - lbf.in. Find the Nm value on the horizontal axis. Move vertically to the solid black diagonal line. Then move horizontally to the vertical axis.
  • Page 56 Manual Organization DA 40 NG AMM AIRCRAFT Intentionally left blank Page 10 Doc # 6.02.15 02-00-00 01 Sep 2017 Rev. 3...
  • Page 57 General Description DA 40 NG AMM AIRCRAFT CHAPTER 03 GENERAL DESCRIPTION OF THE AIRPLANE Doc # 6.02.15 Page 1 03-TITLE Rev. 3 01 Sep 2017...
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  • Page 59 General Description DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 03 GENERAL DESCRIPTION OF THE AIRPLANE General ............1 Description .
  • Page 60 General Description DA 40 NG AMM AIRCRAFT Intentionally left blank Page 2 Doc # 6.02.15 03-CONTENTS Rev. 3 01 Sep 2017...

  • Page 61: General

    DA 40 NG airplane. 2. Description The DA 40 NG is a single-engine, four seat, low-wing monoplane. It has a cantilever wing and a ‘T’ tail. The airplane structure is fiber-reinforced plastic composite. This gives a very strong but light structure.
  • Page 62 The nose leg attaches to the forward fuselage. Each main wheel has a disc brake on the inside. Hydraulic pressure operates each disc brake. The flight control system uses conventional ailerons, elevator and rudder. The DA 40 NG has two control sticks and two rudder pedal assemblies to operate the primary flight-controls. Push-pull rods operate the ailerons and elevator.
  • Page 63 A starter key controls the engine starter motor. It also serves as ELECTRIC MASTER key switch. The DA 40 NG has a full range of flight instruments. These include Pitot/static instruments to show airspeed and altitude, as well as electrically driven instruments to show direction. If the G1000 system is installed most indications are shown on the G1000 and only the backup instruments are installed on the instrument panel.

  • Page 64: Equipment Data

    AIRCRAFT 3. Equipment Data The table below gives you the name and address of the manufacturers who supply systems and/or equipment for the DA 40 NG. This will help you get more data on a system and/or equipment. Equipment/System Address...
  • Page 65 General Description DA 40 NG AMM AIRCRAFT Equipment/System Address Chapter Autopilot System Bendix/King (if KAP 140 A/P is installed): 400 North Rogers Road Olathe, Kansas 66062-1212 Tel: (913) 782-0400 (USA and Canada) (913) 782-0700 (other countries) Website: www.bendixking.com Battery: Concorde Battery Corp.
  • Page 66 General Description DA 40 NG AMM AIRCRAFT Equipment/System Address Chapter Backup Attitude Gyro: Mid-Continent Instrument Co., Inc. 7706 E, Osie, Wichita, Kansas 67207 Tel: (316) 683-5619 Fax: (316) 683-1861 Website: www.mcico.com Wheels and Brakes: Parker Hannifin Corporation Aircraft Wheel and Brake Division...

  • Page 67: Handling Of Identification Data

    General Description DA 40 NG AMM AIRCRAFT Equipment/System Address Chapter Austro Engines E4-A Engine: Austro Engine GmbH Rudolf Diesel-Str. 11 A-2700 Wiener Neustadt Austria Tel: +43 (2622) 23 000 Fax: +43 (2622) 23 000 - 2711 Homepage: www.austroengine.at 4. Handling of Identification Data...
  • Page 68 General Description DA 40 NG AMM AIRCRAFT Intentionally left blank Page 8 Doc # 6.02.15 03-00-00 01 Sep 2017 Rev. 3...
  • Page 69 Airworthiness DA 40 NG AMM Limitations CHAPTER 04 AIRWORTHINESS LIMITATIONS Doc # 6.02.15 Page 1 04-TITLE Rev. 3 01 Sep 2017...
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  • Page 71 Airworthiness DA 40 NG AMM Limitations TABLE OF CONTENTS CHAPTER 04 AIRWORTHINESS LIMITATIONS Airworthiness Limitations ..........3 Continued Airworthiness .
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  • Page 73 Airworthiness DA 40 NG AMM Limitations CHAPTER 04 AIRWORTHINESS LIMITATIONS THIS AIRWORTHINESS LIMITATIONS SECTION IS APPROVED BY EUROPEAN AVIATION SAFETY AGENCY (EASA) IN ACCORDANCE WITH THE APPLICABLE CERTIFICATION PROCEDURES AND THE TYPE CERTIFICATION BASIS. IT SPECIFIES THE AIRWORTHINESS LIMITATIONS REQUIRED BY JAR 23.
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  • Page 75 Note: Regular inspections of the airplane including replacement and overhaul of certain components are required to ensure Continued Airworthiness of the DA 40 NG. For possible airworthiness limitations of engine, propeller, components and vendor equipment refer to the applicable Maintenance data as listed in Section 05-00.
  • Page 76 (2) Life Time Limit / Structure Checks There is no structural life limit. Note: The DA 40 NG has been designed and tested under a 'damage tolerant structure' philosophy. Therefore the structural inspections given in Chapter 05 cover all required structure checks.
  • Page 77 Limitations C. Color of Airframe It is mandatory to paint the DA 40 NG white as described in Chapter 51 of this manual. This will prevent the temperature of the structure from becoming too high. Examples of approves shades are:...
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  • Page 79 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT CHAPTER 05 TIME LIMITS AND MAINTENANCE CHECKS Doc # 6.02.15 Page 1 05-TITLE Rev. 3 01 Sep 2017...
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  • Page 81 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT TABLE OF CONTENTS CHAPTER 05 TIME LIMITS AND MAINTENANCE CHECKS General ............1 Chapter Configuration .
  • Page 82 Drain Holes Inspection Checklist ........1 Section 05-28 Maintenance Checklist DA 40 NG Section 05-28-00 Maintenance Checklist Engine General .
  • Page 83 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28-91 Engine Ground Test Report Engine Ground Test Report ......... . 1...
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  • Page 85: Time Limits And Maintenance Checks

    TIME LIMITS AND MAINTENANCE CHECKS 1. General This Chapter will help to do the maintenance of the DA 40 NG correctly. Refer to Sections 04-00 and 05-00 for maintenance and inspections. The times given in this Chapter are times recommended by the airplane manufacturer. Do the scheduled maintenance at the given times, because they are the minimum required to keep the airplane in a good technical condition.
  • Page 86 Maintenance Checks AIRCRAFT E. Section 05-28 Section 05-28 contains the Maintenance Checklist for the DA 40 NG airplane. The Section is subdivided into engine and airframe sections and provides checklists for the engines and the airframe and the corresponding reports.
  • Page 87 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT G. Referenced Maintenance Data Use latest revision of referenced maintenance data. Supplier Document Name Document No. Artex Installation and Maintenance Manual for the 570-1600 ME406 ELT Austro Engine Austro Engine Operation Manual AE300 E4.01.01...

  • Page 88: Definitions

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 3. Definitions In this Airplane Maintenance Manual, the words that follow have special meanings: Adjust. To put to a specified position or condition. For example, adjust the clearance to 1 mm.
  • Page 89 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Task. An assigned work or a procedure. For example, each step of the task has an identification letter. Test. That which you do when you operate or examine an item to make sure that it agrees with the applicable specifications.
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  • Page 91: Time Limits

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-10 Time Limits 1. General This Section lists time limits for scheduled Maintenance on airframe and components, and replacement or overhaul of components directly or by reference. Obey the time limits in this Section to keep the airplane in a technical good condition.
  • Page 92 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT If an inspection is carried out earlier than allowed by the specified tolerance, all subsequent inspection intervals are counted from that inspection. For example: If the 100 hour inspection was done at 83 hours, the next inspection must be done at 183 hours.

  • Page 93: Component Time Limits

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 3. Component Time Limits A. Maintenance Requirements The following table lists airplane components and systems which require overhaul or specific checks. Where an interval is given in both flight time and calendar years, the limit which is reached first must be used.
  • Page 94 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Kind Interval Component Maintenance Requirement hrs. yrs. Ope. Fire extinguisher. Overhaul. ± 60 days Check valve in front of fuel Clean check valve mesh. 1000 transfer pump. ± 50 Pitot-static system.
  • Page 95 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT B. Airplane Life-Limited Components The following table lists life limited airplane components which must be replaced at a specific time. Where an interval is given in both flight time and calendar years, the limit which is reached first must be applied.
  • Page 96 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Replacement Time Kind of Component Operation hrs. yrs. Co-incident Fuel bypass valve. with engine TBO. Fuel tank vent hoses. 8 ± 60 days Fuel filter element. 100 ± 10 1 ± 30 days...

  • Page 97: Component Time Tracking

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 4. Component Time Tracking To make sure that components overhaul/replacement is done at the correct time you must record the data that follows in the Airplane Maintenance Log for each component requiring overhaul/replacement: Serial Number.
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  • Page 99: Scheduled Maintenance Checks

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-20 Scheduled Maintenance Checks 1. General Do the scheduled maintenance checks in this Section at the intervals (flight hours and calendar time) stated in Section 05-10, Paragraph 3. Note: Only persons or maintenance organizations authorized by national Regulatory Authorities of the country where the airplane is registered may do these checks.

  • Page 100: Maintenance Checklist Organization

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 2. Maintenance Checklist Organization Do the scheduled maintenance checks with reference to the Maintenance Checklist in this Section. Before starting a check, complete the requirements of Paragraphs 2 and 3 of the checklist. In parallel do the scheduled drain hole checks with reference to the Drain Holes Inspection Checklist and Report.

  • Page 101: Major Structural Inspection

    The Major Structural Inspection (MSI) is an important part of the infinite lifetime concept of the DA 40 NG. It is required to prove the structural integrity of the airframe. It must be carried out at the intervals shown in Section 05-20.
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  • Page 103: Flight-Line Checks

    DO ALL THE STEPS OF THE DAILY CHECK CAREFULLY. ACCIDENTS CAN OCCUR IF THE DAILY CHECK IS NOT DONE CORRECTLY. The schedule for the pilot's daily check is in the Airplane Flight Manual for the DA 40 NG. 3. Post-Flight Check Do the post-flight check after the last flight of the day.
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  • Page 105: Drain Holes Inspection Checklist And Report

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-25 Drain Holes Inspection Checklist and Report 1. General Do a check of the drain holes. The drain holes must not be blocked by dirt or other residues. Make sure to remove all foreign objects and clean the drain holes to their full diameter.

  • Page 106: Drain Holes Inspection Checklist

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Drain Holes Inspection Checklist Drain Hole Location Ref. Hours Initials 1.14 On lowest point of the fin 1.15 On lowest point of the EPC connector 1.16 In rudder bolt mounting shell (on top of the rudder) 1.17...
  • Page 107 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Drain Holes Inspection Checklist Ref. Drain Hole Location Hours Initials ELEVATOR TRIM TAB 5.01 Lower shell, leading edge section, LH & RH 5.02 Lower shell, in front of trailing edge bonding, LH & RH RUDDER 6.01...
  • Page 108 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 1.22 1.16 To be checked only in production or repair 1.18 1.15 1.17 1.20 1.21 1.19 1.26 1.23 1.25 1.11 1.14 1.12 To be checked only Maintenance Access in production or repair...
  • Page 109 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 1.02 1.10 1.06 1.09 1.01 1.04 1.07 1.13 1.24 1.03 1.05 1.08 1.13 1.01 1.04 1.06 1.10 1.09 1.02 100 Hours Check Horizontal Drainage Hole 200 Hours Check Vertical Drainage Hole...
  • Page 110 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 2.02 2.01 2.01 2.02 100 Hours Check Horizontal Drainage Hole 200 Hours Check Vertical Drainage Hole 2000 Hours Check Exterior Drainage Hole Drainage Hole Inside the Structure Figure 3: Drain Holes Canopy Page 6 Doc # 6.02.15...
  • Page 111 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 2.03 100 Hours Check Horizontal Drainage Hole 200 Hours Check Vertical Drainage Hole 2000 Hours Check Exterior Drainage Hole Drainage Hole Inside the Structure Figure 4: Drain Holes Passenger Door Doc # 6.02.15...
  • Page 112 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 3.07 3.02 3.07 3.06 3.06 3.09 3.09 3.05 3.01 3.05 3.08 3.08 3.04 3.04 4.01 4.01 4.02 4.02 3.03 3.07 5.01 5.01 5.02 5.02 100 Hours Check Horizontal Drainage Hole...
  • Page 113 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT View on Arrow A 6.01 6.01 100 Hours Check Horizontal Drainage Hole 200 Hours Check Vertical Drainage Hole 2000 Hours Check Exterior Drainage Hole Drainage Hole Inside the Structure Figure 6: Drain Holes Rudder Doc # 6.02.15...
  • Page 114 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Maintenance Access Maintenance Access 7.11 7.09 7.08 7.07 7.12 7.10 7.03 7.01 9.02 7.12 7.04 7.09 7.09 7.08 7.07 9.04 7.05 7.06 9.03 7.02 9.01 8.01 View A 7.06 7.09...

  • Page 115: Maintenance Checklist Da 40 Ng

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28 Maintenance Checklist DA 40 NG Section 05-28-00 Maintenance Checklist Engine 1. General Enter the applicable data in the blocks below: Registration _________________ Date _________________ Airplane S/N _________________ Engine S/N...

  • Page 116: Preparation

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 2. Preparation CAUTION: OBSERVE THE COMPONENT TIME LIMITS STATED IN SECTIONS 04-00 AND 05-10 OF THIS AIRPLANE MAINTENANCE MANUAL. Do the following items before you start the applicable check: Interval (Flight Hours)

  • Page 117: Engine Ground Test

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 3. Engine Ground Test Do an engine ground test as follows (complete a copy of the Engine Ground Test Record as part of the engine ground test. (Refer to Section 05-28-91):...

  • Page 118: Engine Maintenance Checklist

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 4. Engine Maintenance Checklist 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials WARNING: MAKE SURE THE EXHAUST SYSTEM IS COOL BEFORE YOU DO MAINTENANCE ON THE ENGINE.
  • Page 119 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials Verify proper mixture ratio of the coolant. Refer to the AE Maintenance Manual, latest revision.
  • Page 120 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials Examine the bonding cables and their connectors in the engine area: S Look specially for rub marks and damage.
  • Page 121 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials Examine the air intake and turbo-charging system: Look specially for signs of chafing or damage on these items: S Air filter.
  • Page 122 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials % % % % % % Inspect the V-clamp on the pressure side of the turbo...
  • Page 123 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials % % % % Perform a coolant tank pressure relief valve test.
  • Page 124 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Engine 100 200 1000 2000 Time Initials Examine the engine mounts. Look specially for: S Cracks or corrosion. No cracks or corrosion allowed.

  • Page 125: Propeller

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 5. Propeller 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items, Propeller 100 200 1000 2000 Time Initials WARNING: DO NOT LET PERSONS GO INTO THE DANGER AREA OF THE PROPELLER.
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  • Page 127: Maintenance Checklist Airframe

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28-50 Maintenance Checklist Airframe Note: The items of the Major Structural Inspection (MSI) are included in the maintenance checklist of the airframe and identified by the term ‘MSI’ in the ‘Time’ column.
  • Page 128 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Do a function test of the door unlocked warning light system.
  • Page 129 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Remove the main and nose wheels. S Clean and lubricate the bearings (Refer to Section 12-20).
  • Page 130 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials  Examine the mounting for the landing gear. Look specially for: S Incorrect attachment.
  • Page 131 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials  Remove the access panel for the nose landing gear leg.
  • Page 132 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the elastomer pack center tube (if OÄM 40-379 is NOT installed): S Remove elastomer pack.
  • Page 133 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials % % % If OÄM 40-379 is installed: Remove and examine the damper assembly and lower attachment brackets: S Check for damage.

  • Page 134: Cockpit

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 2. Cockpit 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials WARNING: DO NOT LOOSEN THE LEVER FOR THE ADJUSTABLE BACKREST OF THE FRONT SEATS UNINTENTIONALLY.
  • Page 135 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the aileron and elevator control system. Look specially for incorrect attachment and loose or missing lock devices.
  • Page 136 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the brake fluid reservoirs on the co-pilot's side. Make sure the fluid level is correct: S The fluid level must be 12 mm to 25 mm (½...
  • Page 137 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the alternate static valve. Make sure that: S The valve is correctly attached.
  • Page 138 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the trim control in the center console. Make sure that: S There is full and free movement.

  • Page 139: Center Fuselage, Internal

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials If the emergency axe (OÄM 40-326) is installed: S Check attachments for looseness.
  • Page 140 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the cabin baggage compartment. Look specially for damage and insecure attachment. Inspect the following components: S Baggage compartment structure.
  • Page 141 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the flap-actuator indicator and position switches. Look specially for incorrect attachment and operation.
  • Page 142 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Check the following components for wear and/or corrosion, if installed: S Servo.

  • Page 143: Rear Fuselage

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 4. Rear Fuselage 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the complete surface of the rear fuselage.
  • Page 144 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the ECU backup battery: S Check for leakage, damage, insecure mounting, and loose connectors.

  • Page 145: Tail

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 5. Tail 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the complete surface of the aft part of the fuselage, vertical stabilizer, and horizontal stabilizer.
  • Page 146 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the bottom edge of the rudder. Look specially for cracks and deformation.
  • Page 147 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Inspect the interior structure of the horizontal stabilizer through all access holes with mirror and flashlight.
  • Page 148 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Inspect the inner skin of the rear fuselage through all access holes with mirror and flashlight.

  • Page 149: Wings

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 6. Wings 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the complete surface of the wings. Look specially for damage (dents, cracks, holes and delamination).
  • Page 150 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Remove the flap and aileron bellcrank access panels in the wing (Refer to Section 52-40).
  • Page 151 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Inspect the interior structure of the wing through all access holes with mirror and flashlight. Check for damage, cracks, delamination and disbonding from the wing skin.
  • Page 152 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials WARNING: DO NOT GET FUEL ON YOU. FUEL CAN CAUSE SKIN DISEASE. DO NOT ALLOW FIRE NEAR FUEL.
  • Page 153 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Examine the fuel tanks: S Remove the fuel tanks. S Look specially for corrosion, leaks and other damage.

  • Page 154: General

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 7. General 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials If necessary, inspect optional equipment. Refer to Chapter 9 of the Airplane Flight Manual (Supplements).
  • Page 155 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 100 hr items marked X* apply to US registered airplanes only Interval Inspection Items 100 200 1000 2000 Time Initials Lower the airplane off jacks. (Refer to Section 07-10). Do an operational test of the external lights.
  • Page 156 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Note: If a Maintenance Check was done, complete the Maintenance Report. Refer to Section 05-28-90. Note: If a Major Structural Inspection (MSI) was done, complete the Findings Report for the Major Structural Inspection (MSI). Refer to Section 05-28-93.

  • Page 157: Maintenance Report

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28-90 Maintenance Report 1. Maintenance Report Complete a copy of the Maintenance Report after all of the applicable maintenance tasks in the Maintenance Checklist have been initialed. DA 40 NG...
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  • Page 159 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28-91 Engine Ground Test Report 1. Engine Ground Test Report Do the engine test in accordance with Section 71-00 and record results and comments. WARNING: DO NOT STAND WITHIN THE DANGER AREA OF THE PROPELLER.
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  • Page 161 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28-92 Check Flight Report 1. Check Flight Report CHECK FLIGHT DA 40 NG AIRCRAFT (See Maintenance Checklist for Applicability) Page 1 of 4 Registration: Pilot: Airdrome: Date: Take-Off: Landing:...
  • Page 162 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT CHECK FLIGHT DA 40 NG AIRCRAFT (See Maintenance Checklist for Applicability) Page 2 of 4 Registration: Pilot: Airdrome: Date: Take-Off: Landing: Findings Functional Check, Flight Behavior Engine oil temperature indicator...
  • Page 163 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT CHECK FLIGHT DA 40 NG AIRCRAFT (See Maintenance Checklist for Applicability) Page 3 of 4 Registration: Pilot: Airdrome: Date: Take-Off: Landing: Findings Functional Check, Flight Behavior Autopilot (if GFC 700 is installed): S HDG mode.
  • Page 164 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT CHECK FLIGHT DA 40 NG AIRCRAFT (See Maintenance Checklist for Applicability) Page 4 of 4 Registration: Pilot: Airdrome: Date: Take-Off: Landing: Findings Functional Check, Flight Behavior Pitot heat Stall warning...

  • Page 165: Major Structural Inspection Check Findings Report

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-28-93 Major Structural Inspection Check Findings Report 1. General Complete the Findings Report and report the following: Defects found during the Major Structural Inspection (MSI). Structural defects found during the associated 2000 hour inspection.
  • Page 166 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Enter the applicable data in the blocks below: FINDINGS REPORT DA 40 NG AT MAJOR STRUCTURAL INSPECTION (MSI) Registration __________________ Date _______________ Airplane Airplane S/N _________________ Operating Hours _______________ AMM Rev.
  • Page 167 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT defect/finding repair method, remarks at TSN All defects have been repaired. The airplane is airworthy with respect to its maintenance condition. Place: _____________________________________ Date: _____________________________________ Authorized: _____________________________________ Doc # 6.02.15...
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  • Page 169: Unscheduled Maintenance Checks

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Section 05-50 Unscheduled Maintenance Checks 1. General Unscheduled maintenance checks are necessary after any incident that could cause damage to the airplane. 2. Hard Landing Check Figure 1 shows the hard landing check areas. You must do a hard landing check when the pilot makes a report of a hard landing or when ground handling applies unusual loads.
  • Page 170 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Detail Steps/Work Items Key Items Examine the tires. Look specially for cuts in the Refer to Section 32-40. side walls. Examine the wheel rims. Look specially for cracks and deformation of the flanges.
  • Page 171 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Detail Steps/Work Items Key Items (11) If OÄM 40-379 is installed: Remove and examine the damper assembly: S Check for damage. S Check for looseness of spring. S Check damper for leakage.
  • Page 172 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Detail Steps/Work Items Key Items If the adjustable front seats (OÄM 40-252 or OÄM 40-375) are installed: WARNING: DO NOT ENGAGE THE LEVER OR BUTTON FOR THE ADJUSTABLE BACKREST OF THE FRONT SEATS UNINTENTIONALLY. THE SPRING LOADED BACKREST MAY SNAP FORWARD AND CAN CAUSE INJURY.
  • Page 173 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Firewall Top Hat Profile Closing Rib Bearings for Nose Gear Assembly Nose Gear Assembly Rear Main Bulkhead Front Closing Rib Main Landing Gear Rib Reinforcement Rib (if installed) Inner Mounting...
  • Page 174 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Firewall Top Hat Profile NLG Damper Closing Rib Bearings for Nose Gear Assembly Nose Gear Assembly Rear Main Bulkhead Front Closing Rib Main Landing Gear Ribs Inner Mounting Outer Mounting...

  • Page 175: Propeller Strike

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 3. Propeller Strike A propeller strike can be a moving propeller (engine running) which has hit a solid object. Or it can be a moving object that hits a propeller that is not moving.

  • Page 176: Engine Fire

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 4. Engine Fire WARNING: BEFORE YOU DO WORK ON THE AIRPLANE MAKE SURE THE FIRE HAS BEEN EXTINGUISHED. LET THE ENGINE COOL AND DISCONNECT THE BATTERY. WARNING: FIRE CAN SERIOUSLY WEAKEN CFRP. IF YOU FIND ANY DAMAGE TO CFRP, DO NOT OPERATE THE AIRPLANE.
  • Page 177 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Detail Steps/Work Items Key Items Examine the fuselage compartment. Look specially for: S Blisters on the paint or burn marks. S Disbonding of the nacelle skin from the firewall. If you find any damage, ask the airplane manufacturer for advice.

  • Page 178: Lightning Strike

    Refer to the Wiring Diagrams for data about the electrical wiring. Note: If you find any lightning damage you must make a record of the damage and ask Diamond Aircraft for advice before you repair or operate the airplane. Page 10 Doc # 6.02.15...
  • Page 179 S Propeller and spinner. Make a record of the damage you find S Exhaust pipes. and ask Diamond Aircraft for advice before you repair or operate the S Engine breather. airplane. S Canopy handles.
  • Page 180 S Pitot head. Make a record of the damage you find S Static discharge wicks. and ask Diamond Aircraft for advice before you repair or operate the S Wing tip. airplane. S Strobe lights.
  • Page 181 Make a record of the damage you find S Horizontal stabilizer tip. and ask Diamond Aircraft for advice S Static discharge wicks. before you repair or operate the airplane. S Trailing edge.
  • Page 182 Key Items Examine the metal conduction tubes and Make a record of any damage you find bonding strips in the fuselage and in the wings. and ask Diamond Aircraft for advice Look specially for: before you repair or operate the airplane.
  • Page 183 Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Detail Steps/Work Items Key Items (13) Do a test of these attitude and direction systems: S Magnetic compass. S Directional gyro. S Artificial horizon. S Turn & bank indicator. (14) Operate the engine power controls through their Refer to Section 76-10.

  • Page 184: Over Temperature

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT Detail Steps/Work Items Key Items (19) Do an ECU test. Refer to Section 71-00. (20) Do an ECU VOTER test. Refer to Section 71-00. (21) Contact the engine manufacturer. (22) Do a compass check swing.

  • Page 185: Oil Pressure Loss

    Time Limits and DA 40 NG AMM Maintenance Checks AIRCRAFT 8. Oil Pressure Loss Detail Steps/Work Items Key Items Check the oil quantity. Check the indication. Check the wiring. Check if negative g-load flights have been conducted. (Visual inspection of the breather outlet for oil contamination).
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  • Page 187 Dimensions and Areas DA 40 NG AMM AIRCRAFT CHAPTER 06 DIMENSIONS AND AREAS Doc # 6.02.15 Page 1 06-TITLE Rev. 3 01 Sep 2017...
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  • Page 189 Dimensions and Areas DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 06 DIMENSIONS AND AREAS General ............1 Dimensions .
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  • Page 191 DIMENSIONS AND AREAS 1. General The DA 40 NG uses the System Internationale (SI) for dimensions and areas. Imperial dimensions are also given in brackets. For example: Wing span 11.63 m (38.16 ft). Conversions between SI units and imperial units are given in Chapter 02.
  • Page 192 Ø 1.90 m (74.8 in) 2.97 m (9.7 ft) 11.63 m (38.15 ft) Ground Line, Static 3.29 m (10.8 ft) Figure 1: DA 40 NG, Overall Dimensions (Approximate Values) Page 2 Doc # 6.02.15 06-00-00 01 Sep 2017 Rev. 3...
  • Page 193 Goodyear 8.50-6; 6 PR, TT 3. Adjustment Values The measurements of the DA 40 NG are recorded on an Adjustment Report at the factory when the airplane is built. See Figure 2 and 3. These Reports become part of the airplane records.
  • Page 194 Dimensions and Areas DA 40 NG AMM AIRCRAFT Figure 2: Control Surface Adjustment Report Page 4 Doc # 6.02.15 06-00-00 01 Sep 2017 Rev. 3...
  • Page 195 Dimensions and Areas DA 40 NG AMM AIRCRAFT Adjustment Report Registration Date Horizontal Main Landing Gear (at Empty Rudder Wings Stabilizer Weight, on Glide Sheets) Controls Cable Angle of Camber Leading Edge Dihedral Tension Incidence (Wing Supported) Sweep Back Differ-...
  • Page 196 Dimensions and Areas DA 40 NG AMM AIRCRAFT Main Landing Gear Wheel Track and Camber Report (for test/adjustment procedure refer to Section 32-10 Paragraph 3 Check procedure Measured data Perform check at empty weight (fuel tank empty) Set airplane MLG wheels on relocatable plates (2 steel plates 250 x 300 x 2 mm;...
  • Page 197 Dimensions and Areas DA 40 NG AMM AIRCRAFT dvs = 0° +1°/-0° (Track Sum) ±1° ±1° FS 2194 Main Landing Gear Loaded with Empty Weight ° ° 1° 1° ° ° S (Track) S+200 (Total Track Distance) Figure 4: Main Landing Gear Track and Camber Doc # 6.02.15...
  • Page 198 Dimensions and Areas DA 40 NG AMM AIRCRAFT 4. Weight and Static Moments of Control Surfaces WARNING: IF YOU REPAINT (OR DO REPAIRS TO) THE CONTROL SURFACES, YOU MUST MAKE SURE THAT THE WEIGHTS AND STATIC MOMENTS OF THE CONTROL SURFACES ARE IN THE LIMITS IN THE CONTROL SURFACE BALANCING REPORT.
  • Page 199 Lifting and Shoring DA 40 NG AMM AIRCRAFT CHAPTER 07 LIFTING AND SHORING Doc # 6.02.15 Page 1 07-TITLE Rev. 3 01 Sep 2017...
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  • Page 201 Lifting and Shoring DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 07 LIFTING AND SHORING General ............1...
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  • Page 203 LIFTING AND SHORING 1. General The DA 40 NG has no hoisting points. Use straps to lift the airplane. You can use your hands to lift the wings and the horizontal stabilizer. Section 07-10 tells you how to lift the airplane with jacks.
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  • Page 205 Jacking 1. General The DA 40 NG has three jacking points. There are main jacking points under each stub-wing. The tie-down hole in the lower fin makes the tail jacking point. For maintenance lift the fuselage with the three hydraulic jacks. Use a trestle with a special former to hold the front of the fuselage. Use standard trestles under the wings at the position where the tips connect to the wing.
  • Page 206 Lifting and Shoring DA 40 NG AMM AIRCRAFT Nose Wing Trestle Wing Trestle Main Jack Main Jack Trestle Tail Jacking Main Jacking Point Point LH & RH Nose Tail Jack Trestle Figure 1: Lifting the Airplane on Jacks Page 2 Doc # 6.02.15...
  • Page 207 Lifting and Shoring DA 40 NG AMM AIRCRAFT B. Lifting the Airplane Detail Steps/Work Items Key Items/References CAUTION: IF THE AIRPLANE IS IN THE OPEN THEN ALIGN IT INTO THE WIND. MAXIMUM WIND SPEED: 10 KM/H (6 KTS). Apply the parking brake. Put chocks under the main wheels.
  • Page 208 Lifting and Shoring DA 40 NG AMM AIRCRAFT C. Lowering the Airplane Detail Steps/Work Items Key Items/References WARNING: MAKE SURE THAT THE AREA UNDER THE AIRPLANE IS CLEAR BEFORE YOU LOWER THE AIRPLANE. Remove the nose trestle from under the fuselage.
  • Page 209 Weighing and Levelling DA 40 NG AMM AIRCRAFT CHAPTER 08 WEIGHING AND LEVELLING Doc # 6.02.15 Page 1 08-TITLE Rev. 3 01 Sep 2017...
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  • Page 211 Weighing and Levelling DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 08 WEIGHING AND LEVELLING General ............1...
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  • Page 213 Weighing and Levelling DA 40 NG AMM AIRCRAFT CHAPTER 08 WEIGHING AND LEVELLING 1. General This Chapter tells you how to weigh the airplane. It also tells you how to level the airplane. Use the procedures in Section 08-10 to weigh the airplane and to calculate the airplane moment. Use the procedures in Section 08-20 to level the airplane.
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  • Page 215 Figure 6). The reference plane for the DA 40 NG is a transverse, vertical plane in front of the airplane. It is at right angles to the horizontal reference line. The reference plane lies 2,194 mm (86.38 in) in front of the stub-wing leading edge at the wing joint on each side.
  • Page 216 Weighing and Levelling DA 40 NG AMM AIRCRAFT Spirit Level Horizontal Part of Baggage Compartment Frame Figure 1: Level the Airplane Laterally for Weighing 600 mm (23.62 in.) Sprit Level 31 mm (1.22 in.) Wedge Figure 2: Level the Airplane Longitudinally for Weighing Page 2 Doc # 6.02.15...
  • Page 217 Weighing and Levelling DA 40 NG AMM AIRCRAFT 2. Weighing with Electronic Weighing Units at the Jacking Points If you can use electronic weighing units to weigh the airplane, you can use the jacks to make the airplane level. You must obey the manufacturers' instructions on the weighing units.
  • Page 218 Weighing and Levelling DA 40 NG AMM AIRCRAFT Reference Plane Arm - Empty Weight X 2194 mm (86.38 in.) 2394 mm (94.25 in.) X 7312 mm (287.87 in.) Legend: = Arm, Reference Plane to Center Line of Main Jacking Points.
  • Page 219 Weighing and Levelling DA 40 NG AMM AIRCRAFT B. Weighing Procedure with Electronic Weighing Units at the Jacking Points Detail Steps/Work Items Key Items/References Note: Weigh the airplane in a closed room. This will avoid any wind causing weighing errors.
  • Page 220 Weighing and Levelling DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (11) Read the value from the right main jack weighing unit. Enter the value on the Weighing Report under MAIN G Gross. (12) Read the value from the tail jack weighing unit.
  • Page 221 DA 40 NG AMM AIRCRAFT WEIGHING REPORT Model: DA 40 NG Serial Number:___________ Registration:_____________ Data with reference to the Type Certificate Data Sheet and the Airplane Flight Manual. Reference Plane: Vertical plane 2194 mm (86.38 in) in front of the leading edge of wing at the root rib.
  • Page 222 Weighing and Levelling DA 40 NG AMM AIRCRAFT Reference Plane Arm - Empty Weight X 2194 mm (86.38 in.) If necessary, use blocks under wheels to ensure horizontal alignment Ramp same Height as Nose Scale Legend: = Arm, Reference Plane to center line of main wheels.
  • Page 223 Weighing and Levelling DA 40 NG AMM AIRCRAFT 3. Weighing with Mechanical Scales Under the Wheels If you use mechanical scales to weigh the airplane, you must also use wooden blocks under the wheels to level the airplane. You must obey the manufacturers' instructions on the scales.
  • Page 224 Weighing and Levelling DA 40 NG AMM AIRCRAFT B. Weighing Procedure with Mechanical Scales Under the Wheels Detail Steps/Work Items Key Items/References Note: Weigh the airplane in a closed room. This will avoid any wind causing weighing errors. Make a copy of the Weighing Report form.
  • Page 225 Weighing and Levelling DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (13) Make the airplane level longitudinally: Refer to Figure 2. S Place a wedge on the rear fuselage with the thin end forward. S Place a spirit level on the wedge.
  • Page 226 Weighing and Levelling DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (20) Use the plumb line to mark the position of the reference plane on the floor: S Hold the plumb line against the leading edge Do this on each side.
  • Page 227 Weighing and Levelling DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (32) Calculate the Empty Weight, G, from the Net values. Net G + Net G + Net G (33) Calculate the Empty Weight Moment, M. )+( G...
  • Page 228 DA 40 NG AMM AIRCRAFT WEIGHING REPORT Model: DA 40 NG Serial Number:___________ Registration:_____________ Data with reference to the Type Certificate Data Sheet and the Airplane Flight Manual. Reference Plane: Vertical plane 2194 mm (86.38 in) in front of the leading edge of wing at the root rib.
  • Page 229 Weighing and Levelling DA 40 NG AMM AIRCRAFT Section 08-20 Levelling 1. General These procedures tell you how to make the airplane level. See Section 07-10 for lifting the airplane with jacks. Make the airplane level with jacks unless you are weighing the airplane. If you weigh the airplane, change the airplane tire pressures or use blocks to make the airplane level (see Section 08-10).
  • Page 230 Weighing and Levelling DA 40 NG AMM AIRCRAFT Spirit Level Horizontal Part of Baggage Compartment Frame Figure 1: Level the Airplane Laterally 600 mm (23.62 in.) Sprit Level 31 mm (1.22 in.) Wedge Figure 2: Level the Airplane Longitudinally Page 2 Doc # 6.02.15...
  • Page 231 Weighing and Levelling DA 40 NG AMM AIRCRAFT B. Level the Airplane with Jacks Procedure Detail Steps/Work Items Key Items/References Note: Level the airplane in a closed room. This will avoid any wind causing levelling errors. Lift the airplane on jacks.
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  • Page 233 Towing and Taxiing DA 40 NG AMM AIRCRAFT CHAPTER 09 TOWING AND TAXIING Doc # 6.02.15 Page 1 09-TITLE Rev. 3 01 Sep 2017...
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  • Page 235 Towing and Taxiing DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 09 TOWING AND TAXIING General ............1...
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  • Page 237 Towing and Taxiing DA 40 NG AMM AIRCRAFT CHAPTER 09 TOWING AND TAXIING 1. General You can move the airplane on the ground by hand or by taxiing it. Use the procedures in Section 09-10 and Section 09-20 to move the airplane safely. Section 09-10 tells you how to tow the airplane. Section 09-20 tells you how to taxi the airplane.
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  • Page 239 Towing 1. General You can move the airplane without using a tow bar. You can push or pull the DA 40 NG at the wing tip, at the wing nose, and at the propeller blades near the spinner. 2. Towing Procedure WARNING: DO NOT PUSH ON THE SPINNER.
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  • Page 241 Section 09-20 Taxiing 1. General When you taxi the DA 40 NG you use the toe operated brakes to steer the airplane. To make the airplane turn operate the left or the right toe brake. WARNING: YOU MUST NOT TAXI THE AIRPLANE UNLESS YOU HAVE BEEN TRAINED TO TAXI AND HAVE BEEN AUTHORIZED BY YOUR AIRWORTHINESS AUTHORITY.
  • Page 242 Towing and Taxiing DA 40 NG AMM AIRCRAFT Key Items/References Detail Steps/Work Items WARNING: MAKE SURE THE BRAKES OPERATE CORRECTLY WHEN YOU TAXI THE AIRPLANE. IF THE BRAKES SHOULD FAIL, YOU MUST BE ABLE TO STOP THE AIRPLANE BEFORE YOU HIT PERSONS OR EQUIPMENT.
  • Page 243 Towing and Taxiing DA 40 NG AMM AIRCRAFT Figure 1: The Safety Range for Taxiing the DA 40 NG Airplane Doc # 6.02.15 Page 3 09-20-00 Rev. 3 01 Sep 2017...
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  • Page 245 Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT CHAPTER 10 PARKING, MOORING, STORAGE AND RETURN TO SERVICE Doc # 6.02.15 Page 1 10-TITLE Rev. 3 01 Sep 2017...
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  • Page 247 Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 10 PARKING, MOORING, STORAGE AND RETURN TO SERVICE General ............1...
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  • Page 249: General

    1. General Always park or moor the DA 40 NG when it is not in use. Use the procedures in Section 10-10 for parking the airplane. Use the procedure in Section 10-20 to moor the airplane. If the airplane is parked over-night, we recommend that you moor the airplane.
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  • Page 251: Parking And Storage

    5 to 30 days. Use the storage procedure if the airplane will be parked for more than 30 days. All pilots and all maintenance staff for the DA 40 NG must know the procedures in this Section. CAUTION: MAKE SURE THAT THE AIRPLANE IS CORRECTLY MOORED AND PROTECTED IF STRONG WINDS ARE FORECAST.
  • Page 252 Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References CAUTION: DO NOT SET THE PARKING BRAKE WHEN THE BRAKES ARE OVER-HEATED. THE BRAKES CAN SEIZE ON. Set the parking brake ON. Pull the lever fully aft, and push both brake pedals at least two times.
  • Page 253 Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT C. Long-Term Parking CAUTION: MAKE SURE TO PERFORM THE LONG TERM PARKING PROCEDURE WHEN THE AIRPLANE IS PARKED FOR A LONG TIME. IF THE PROCEDURE IS NOT FOLLOWED CORRECTLY, DAMAGE TO THE AIRPLANE CAN OCCUR.

  • Page 254: Storage

    Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT 2. Storage If the airplane is parked (or not operated) for more than 30 days, you have to do this storage procedure. A. Equipment and Material Item Quantity Part Number Wheel chocks.

  • Page 255: Mooring

    Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT Section 10-20 Mooring 1. General CAUTION: IF THE AIRPLANE MUST BE STORED OUTSIDE FOR A LONG TIME, THEN YOU MUST MOOR IT. STRONG WINDS OR GUSTS CAN CAUSE DAMAGE TO AN AIRPLANE WHICH IS NOT MOORED.
  • Page 256 Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT Wing Tie-Down Point Wing Tie-Down Point Mooring Ring Mooring Ring Rear Tie-Down Point Figure 1: Location of Mooring Points on the Airplane Page 2 Doc # 6.02.15 10-20-00 01 Sep 2017 Rev. 3...

  • Page 257: Return To Service

    Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT Section 10-30 Return to Service 1. General Do this procedure when the airplane has been parked (or stored) for more than 5 days. 2. Return to Service Procedure A. Storage Time Less Than One Year...
  • Page 258 Parking, Mooring, etc. DA 40 NG AMM AIRCRAFT B. Storage Time One Year and More Detail Steps/Work Items Key Items/References Contact the engine manufacturer Austro Engine GmbH. If necessary, install loose equipment which was removed for storage. If the battery has been removed: Refer to Section 24-31.
  • Page 259 Placards and Markings DA 40 NG AMM AIRCRAFT CHAPTER 11 PLACARDS AND MARKINGS Doc # 6.02.15 Page 1 11-TITLE Rev. 3 01 Sep 2017...
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  • Page 261 Placards and Markings DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 11 PLACARDS AND MARKINGS General ............1...
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  • Page 263 Placards and Markings DA 40 NG AMM AIRCRAFT CHAPTER 11 PLACARDS AND MARKINGS 1. General Placards are used for identification and indication. They show the function, operation and operating limitations of systems and equipment. Note: Placards must not be removed, exchanged or altered unless approved by the national Airworthiness Authority.
  • Page 264 Placards and Markings DA 40 NG AMM AIRCRAFT B. Replace a Placard Use this procedure for both internal and external foil placards. Detail Steps/Work Items Key Items/References Remove the old placard: S Heat the placard with a hot air blower.
  • Page 265 Exterior Placards and Markings 1. General Figure 1 and 2 show the exterior markings and placards for the DA 40 NG. For the safety walk adhesive strips are installed. Refer to the Maintenance Practices for more details about the positioning of the safety walk adhesive strips.
  • Page 266 Placards and Markings DA 40 NG AMM AIRCRAFT WARNING If neither OÄM 40-339 OÄM 40-400 APPROVED FUEL: installed JET-A1 If OÄM 40-348 and or see Airplane Flight Manual OÄM 40-130 is If OÄM 40-339 or installed OÄM 40-400 is installed Usable Fuel Qty.:...
  • Page 267 Placards and Markings DA 40 NG AMM AIRCRAFT Basic 3.3 bar / 48 psi If OÄM 40-334 is installed 1.2 bar / 17 psi Basic 3.1 bar / 45 psi If OÄM 40-334 is installed 1.2 bar / 17 psi If MÄM 40-574 &...
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  • Page 269 Placards and Markings DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General This Section tells you how to replace safety walk adhesive strips. 2. Replace the Safety Walk Adhesive Strips A. Equipment Item Quantity Part Number Safety walk template. D44-1127-10-52.
  • Page 270 Placards and Markings DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Remove the adhesives layer of the safety walk adhesive strips from surface: S Use fresh acetone or Socomore® cleaning cloth (P/N: 29003-C86-C10) to remove the adhesive layer. Do not use cleaning or polishing agents which contain silicon.
  • Page 271 Placards and Markings DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (16) Place the safety walk adhesive strips into Start from the most forward end of template. the slots of the safety walk template . Refer to Figure 3.
  • Page 272 Placards and Markings DA 40 NG AMM AIRCRAFT Prefabricated Strips Root Rib 10mm Place Safety Template Walk Cover to Trailing Edge Place Safety Template Walk Cover to Trailing Edge 10mm Root Rib Prefabricated Strips Figure 3: Safety Walk Template Positioning Page 204 Doc # 6.02.15...
  • Page 273 Placards and Markings DA 40 NG AMM AIRCRAFT Section 11-30 Interior Placards and Markings 1. General Figure 1 shows the interior placards and markings. Figures 2 thru 4 show the instrument panel placards, if the G1000 system is installed. Figures 5 shows the instrument panel placards, if the conventional cockpit is installed.
  • Page 274 Placards and Markings DA 40 NG AMM AIRCRAFT If OÄM 42-252 or Side Wall of Baggage Rear Wall of Baggage Compartment Compartment - Optional Optional OÄM 42-375 is installed BA GGAGE STAND ARD BAG G AGE C OCKPIT B AGGAGE...
  • Page 275 Placards and Markings DA 40 NG AMM AIRCRAFT Optional, if GFC 700 is installed Limitations for GFC 700 Autopilot System: Do not use AP if “Alternate Static” is open. Conduct AP and trim check prior to each flight (see AFM).
  • Page 276 Placards and Markings DA 40 NG AMM AIRCRAFT EECU BUS FUEL FUEL EECU A EECU B EECU A EECU B PUMP A PUMP B ESSENTIAL BUS HORIZON AHRS COM1 GPS/NAV1 MASTER CONTROL MAIN BUS ENGINE AVIONICS BUS VOTER MA STER...
  • Page 277 Placards and Markings DA 40 NG AMM AIRCRAFT M anouvering speed: L imitations fo r G FC 700 Auto pi lot Sys tem: =11 1 KIA S (above 1036 up to 1200 kg / above 2284 up to 2646 lb) Do not use AP i f “Alte rnate S t atic”...
  • Page 278 Placards and Markings DA 40 NG AMM AIRCRAFT OPERATING MANEUVERING SPEED: INSTRUMENT v = 113 KIAS (ABOVE 1180 KG / ABOVE 2601 LB) v = 108 KIAS (ABOVE 1080 KG TO 1180 KG / ABOVE 2381 LB TO 2601 LB) ELECTRIC ESS.
  • Page 279 Servicing DA 40 NG AMM AIRCRAFT CHAPTER 12 SERVICING Doc # 6.02.15 Page 1 12-TITLE Rev. 3 01 Sep 2017...
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  • Page 281 Servicing DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 12 SERVICING General ............1...
  • Page 282 Servicing DA 40 NG AMM AIRCRAFT Section 12-30 Unscheduled Servicing General ............1 Exterior Cleaning .

  • Page 283: Servicing

    Servicing DA 40 NG AMM AIRCRAFT CHAPTER 12 SERVICING 1. General This Chapter gives these servicing tasks which apply to the whole airplane: Section 12-10. Replenishing procedures for fluid systems. Section 12-20. Lubrication data. Section 12-30. Cleaning and snow and ice removal.
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  • Page 285: Replenishing

    Servicing DA 40 NG AMM AIRCRAFT Section 12-10 Replenishing 1. General Use the procedures in this Section to replenish the fluid systems on the airplane. Figures 1 thru 2 show the location of the servicing points. 2. Fuel System The fuel tanks are located in each wing between the two main spars. They consist of one (Standard Tank configuration) or two (Long Range Tank configuration) interconnected chambers.
  • Page 286 Servicing DA 40 NG AMM AIRCRAFT WARNING: MAKE SURE THAT A FIRE EXTINGUISHER IS AVAILABLE. WARNING: TURN OFF ALL GROUND EQUIPMENT IN THE REFUELING AREA. WARNING: DO NOT OPERATE ELECTRICAL SWITCHES IN THE AIRPLANE. CAUTION: USE ONLY FUEL TYPES GIVEN IN CHAPTER 2 OF THE AIRPLANE FLIGHT MANUAL.

  • Page 287: Refueling/Defueling

    Servicing DA 40 NG AMM AIRCRAFT 3. Refueling/Defueling A. Refueling Detail Steps/Work Items Key Items/References Shut down the engine. Set ENGINE MASTER OFF. All occupants leave the airplane. Ground the airplane electrically. At the refueling connection. Ground the refueling vehicle electrically.

  • Page 288: Fuel Contamination Test

    Servicing DA 40 NG AMM AIRCRAFT 4. Fuel Contamination Test A. Equipment Item Quantity Part Number Glass container. Commercial. B. Fuel Contamination Test Procedure Detail Steps/Work Items Key Items/References Put the glass container under the fuel tank drain valve that you will take the fuel from.

  • Page 289: Engine Oil System

    ENGINE OPERATION WITH NO ENGINE OIL (OR VERY LOW OIL LEVEL) WILL CAUSE ENGINE MALFUNCTION OR FAILURE. The engine installed on the DA 40 NG has a wet-sump oil system. The oil capacities are given in the following table: Oil Sump Capacity...

  • Page 290: Gearbox Oil

    Servicing DA 40 NG AMM AIRCRAFT Coolant Gearbox Oil Engine Oil Figure 2: Replenishment Points 2 Page 6 Doc # 6.02.15 12-10-00 01 Sep 2017 Rev. 3...
  • Page 291 Servicing DA 40 NG AMM AIRCRAFT 6. Gearbox Oil WARNING: ENGINE OPERATION WITH NO GEARBOX OIL (OR VERY LOW OIL LEVEL) WILL CAUSE ENGINE MALFUNCTION OR FAILURE. The gearbox oil level can be checked through an oil level window at the front side of the engine.
  • Page 292 Servicing DA 40 NG AMM AIRCRAFT Filler Cap To Thermostat Silicate Pouch Cartridge Max. Coolant Level Marking Plate Expansion Tank Pressure Relief Valve Coolant Level Sensor Coolant Bypass Hose Figure 3: Engine Coolant Expansion Tank / Filler Cap (if MÄM 40-763 is installed) Page 8 Doc # 6.02.15...

  • Page 293: Engine Coolant

    ENGINE WITH A FAULTY COOLING SYSTEM CAN DAMAGE THE ENGINE. The DA 40 NG engine uses liquid coolant to cool the engine and supply heating to the cabin. The coolant is circulated around the engine in an integral water jacket. When the coolant is at normal engine operating temperature a thermostatic valve directs the coolant to flow through a heat exchanger.
  • Page 294 Servicing DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Remove the pressure cap from the coolant tank: S Turn the cap counter-clockwise a small distance to release the pressure. S When the pressure has fully released, turn the cap fully counter-clockwise.
  • Page 295 Servicing DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References WARNING: DO NOT REMOVE THE PRESSURE CAP FROM THE COOLANT TANK IF THE ENGINE IS HOT. THE PRESSURE IN THE SYSTEM CAN FORCE HOT COOLANT TO COME OUT AND CAUSE INJURY TO PERSONS.

  • Page 296: Brake System

    Servicing DA 40 NG AMM AIRCRAFT 8. Brake System The brake fluid reservoirs are located on the brake master cylinders on the co-pilot’s side. You get access in the cockpit below the instrument panel. WARNING: DO NOT GET BRAKE FLUID ON YOUR SKIN OR IN YOUR MOUTH.

  • Page 297: Tires

    DA 40 NG AMM AIRCRAFT 9. Tires The DA 40 NG has these tires: Main tires: 15 x 6.0 - 6, 6PR, TT, 160 mph, TSO C62; pressure (loaded): 3.3 bar (48 PSI). Nose tire: 5.00 - 5, 6PR, TT, 120 mph; TSO C62; pressure (loaded): 3.1 bar (45 PSI).
  • Page 298 Servicing DA 40 NG AMM AIRCRAFT A. Examine the Tires and Measure the Pressure Detail Steps/Work Items Key Items/References Examine the tires. Look specially for: Move the airplane as necessary so that each part of each tire can be seen.

  • Page 299: Scheduled Servicing

    Servicing DA 40 NG AMM AIRCRAFT Section 12-20 Scheduled Servicing 1. General This Section gives lubrication data. It tells you where components are located. It gives a list of approved lubricants. It also gives the components which MUST NOT be lubricated.

  • Page 300: Lubrication Schedule

    Servicing DA 40 NG AMM AIRCRAFT 2. Lubrication Schedule Table 2 shows the lubrication schedule. Clean each lubrication point before lubrication. See Figures 1 thru 3 for the location of lubrication points listed on the left side of the table. The center columns show the type of lubricant.
  • Page 301 Servicing DA 40 NG AMM AIRCRAFT Notes: Lubricate at the time shown or at every disassembly/assembly. Lubricate more frequently in severe climates or operating conditions. Lubricate at the time shown and at Annual Inspection. Do not get grease on the threads. It will reduce the friction of the lock-nut.
  • Page 302 Servicing DA 40 NG AMM AIRCRAFT Table 3 - Lubricant Specifications Specification Product Manufacturer TYPE 1 MIL-G-3545 (obsolete) AeroShell Grease 5 Shell Oil Company (Warm climates only) GOST 6267-74 Grease CIATIM 201 RUSMA LLC Company GOST 9433-80 Grease CIATIM 221...
  • Page 303 Servicing DA 40 NG AMM AIRCRAFT 8 - If OÄM 40-379 is installed (Hydraulic Damper) Elastomer Pads Figure 1: Lubrication Points Sheet 1 Doc # 6.02.15 Page 5 12-20-00 Rev. 3 01 Sep 2017...
  • Page 304 Servicing DA 40 NG AMM AIRCRAFT 10 & 12 11 & 13 Figure 2: Lubrication Points Sheet 2 Page 6 Doc # 6.02.15 12-20-00 01 Sep 2017 Rev. 3...

  • Page 305: Exterior Cleaning

    2. Exterior Cleaning The outer surfaces of the DA 40 NG must be kept clean to keep the good performance characteristics of the airplane. The leading edges of the wings are specially important. Protect all control surface bearings and other lubricated components before cleaning the airplane.

  • Page 306: Interior Cleaning

    Servicing DA 40 NG AMM AIRCRAFT 4. Interior Cleaning Clean the interior with a flame-proof vacuum cleaner. All plastic surfaces should be wiped clean using a damp cloth without any cleaning agents. CAUTION: IF INSTALLED, THE PFD AND MFD DISPLAYS OF THE GARMIN G1000...

  • Page 307: Snow And Ice Removal

    Servicing DA 40 NG AMM AIRCRAFT 6. Snow and Ice Removal Remove snow and ice as soon as possible to prevent melted water from freezing later and causing damage. CAUTION: DO NOT USE SHARP OBJECTS TO REMOVE SNOW OR ICE. YOU CAN DAMAGE THE AIRPLANE STRUCTURE.

  • Page 308: Conservation Of Exterior Parts

    Servicing DA 40 NG AMM AIRCRAFT 7. Conservation of Exterior Parts This section tells you which exterior parts are protected with an anti-corrosion coating, when and how a new anti-corrosion coating must be applied. A. Anti-Corrosion Coating Check Check the protected exterior parts (refer to the Anti-Corrosion Checklist and Figures 1 through 11) for a film of the anti-corrosion coating.
  • Page 309 Servicing DA 40 NG AMM AIRCRAFT C. Apply the Anti-Corrosion Coating CAUTION: YOU MUST USE THE APPROVED ANTI-CORROSION COATINGS IN ORDER TO PREVENT DAMAGE TO OTHER PARTS OF THE AIRPLANE. Approved anti-corrosion coatings are: Ardrox® AV 30 (color: red; recommended for not visible parts) Socopac 65H (color: red;...
  • Page 310 Servicing DA 40 NG AMM AIRCRAFT Anti-Corrosion Coating Checklist Figure Part / Location Initials FLAPS LH/RH Control rod eye end fitting (2) Ball joint bolt and nut (2) AILERONS LH/RH Control rod eye end fitting (2) Ball joint bolt and nut (2)
  • Page 311 Servicing DA 40 NG AMM AIRCRAFT LH Shown, RH Similar Control Rod, Flaps LH & RH Anti-corrosion coating according to Section 12-30-00 of this AMM Figure 1: Anti-Corrosion Coating - Control Rods Flaps LH/RH Doc # 6.02.15 Page 7 12-30-00 Rev.
  • Page 312 Servicing DA 40 NG AMM AIRCRAFT LH Shown, RH Similar Control Rod, Ailerons LH & RH Anti-corrosion coating according to Section 12-30-00 of this AMM Figure 2: Anti-Corrosion Coating - Control Rods Ailerons LH/RH Page 8 Doc # 6.02.15 12-30-00 01 Sep 2017 Rev.
  • Page 313 Servicing DA 40 NG AMM AIRCRAFT Main Landing Gear Leg LH Shown, RH Similar Anti-corrosion coating according to Section 12-30-00 of this AMM Keep Caliper, Brake Disk, and Tyre free of Anti-corrosion Coating Figure 3: Anti-Corrosion Coating - Main Landing Gear LH/RH (1) Doc # 6.02.15...
  • Page 314 Servicing DA 40 NG AMM AIRCRAFT Main Landing Gear Leg LH Shown, RH Similar Anti-corrosion coating according to Section 12-30-00 of this AMM Anti-corrosion coating according to Section 12-30-00 of this AMM Figure 4: Anti-Corrosion Coating - Main Landing Gear LH/RH (2) Page 10 Doc # 6.02.15...
  • Page 315 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM Coating with Preventives according to Section 12-30-00 of this AMM Keep Elevator Trim System free of Preventives Coating with Preventives according to Section 12-30-00 of this AMM...
  • Page 316 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM Figure 6: Anti-Corrosion Coating - Elevator and Elevator Trim System (2) Page 12 Doc # 6.02.15 12-30-00 01 Sep 2017 Rev. 3...
  • Page 317 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Coating with Preventives according to Section 12-30-00 of this AMM Section 12-30-00 of this AMM Figure 7: Anti-Corrosion Coating - Elevator and Elevator Trim System (3) Doc # 6.02.15...
  • Page 318 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM Figure 8: Anti-Corrosion Coating - Elevator Controls Page 14 Doc # 6.02.15 12-30-00 01 Sep 2017 Rev. 3...
  • Page 319 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM Coating with Preventives according to Section 12-30-00 of this AMM Apply Preventives on complete surface of Pedestal Keep Rods free of Preventives Figure 9: Anti-Corrosion Coating - Rudder Pedestal Doc # 6.02.15...
  • Page 320 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM Apply Coating with Preventives on both sides of the Bearing Figure 10: Anti-Corrosion Coating - Rudder Page 16 Doc # 6.02.15 12-30-00 01 Sep 2017...
  • Page 321 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM Coating with Preventives according to Section 12-30-00 of this AMM Coating with Preventives according to Section 12-30-00 of this AMM Figure 11: Anti-Corrosion Coating - Nose Landing Gear Doc # 6.02.15...
  • Page 322 Servicing DA 40 NG AMM AIRCRAFT Coating with Preventives according to Section 12-30-00 of this AMM LH shown, RH similar Figure 12: Anti-Corrosion Coating - Foot Step Screws Page 18 Doc # 6.02.15 12-30-00 01 Sep 2017 Rev. 3...
  • Page 323 DA 40 NG AMM Standard Practices AIRCRAFT CHAPTER 20 STANDARD PRACTICES Doc # 6.02.15 Page 1 20-TITLE Rev. 3 01 Sep 2017...
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  • Page 325 DA 40 NG AMM Standard Practices AIRCRAFT TABLE OF CONTENTS CHAPTER 20 STANDARD PRACTICES - AIRFRAME General ............1...
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  • Page 327: Standard Practices - Airframe

    AIRCRAFT CHAPTER 20 STANDARD PRACTICES - AIRFRAME 1. General This Chapter gives you the standard practices for the DA 40 NG airplane. Use industry standard practice where no specific practice is given. This Chapter has the following Sections: Section 20-10.
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  • Page 329: Standard Practices - Airframe

    Standard Practices - Airframe 1. General There are no Maintenance Practices which apply to the DA 40 NG airframe and its systems in general. This Chapter only has data about standard threaded fasteners. Always tighten the nut or bolt to the torque shown in the tables below. Always use the correct locking device with the nut or bolt.

  • Page 330: Standard Torque Values

    Standard Practices DA 40 NG AMM AIRCRAFT 3. Standard Torque Values These tables show the correct torque values for bolts and nuts to AN and DIN specifications. Use the following torque values for all bolts, nuts and screws which meet the specifications unless they are in the list of special torque values below.

  • Page 331: Special Torque Values

    DA 40 NG AMM Standard Practices AIRCRAFT C. DIN and LN Specifications Metric Thread Torque (Nm) Torque (lbf.ft.) 11.8 23.6 44.3 4. Special Torque Values Part Torque (Nm) Torque (lbf.ft.) Alternator bracket bolts 25 ± 3 18.4 ± 2.2 Propeller governor nut torque.

  • Page 332: Torque Measurement

    Standard Practices DA 40 NG AMM AIRCRAFT Part Torque (Nm) Torque (lbf.ft.) Main landing gear inner fitting attachment bolts 11.1 (6x M8 per side). Main landing gear inner height of spring 4 mm 0.16 in attaching bolt. washers (+0.5 mm / -0 mm) (+0.02 in / -0 in)

  • Page 333: Standard Practices - Electrical

    AC 43-13.1B. Any time you work on the engine harness refer to AE Maintenance Manual, Doc. No. E4.08.04, latest revision. The satisfactory performance of a modern airplane, like the DA 40 NG, depends to a great extent, on reliability of its electrical systems. Improperly or carelessly maintained wiring can be a source of potential danger, and many malfunctions and failures of an electrical system can be traced to this cause.
  • Page 334 DA 40 NG AMM AIRCRAFT A. Crimp Tools Following crimp tools are commonly used for crimp contacts in the DA 40 NG. Refer to the equipment manufacturer for more details of the tools and their use. Tyco, P/N 69478-1 Tyco CERTI-LOK, P/N 169400...
  • Page 335 A single center conductor with a metallic braided outer conductor (coaxial cable). Two or more insulated conductors contained in a common covering (multi conductor cable). One or more insulated conductors with an overall shield (shielded cable). Approved cables for the DA 40 NG are: M27500 M17/60-RG142 M17/128-RG400...
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  • Page 337: Standard Practices - Engine

    Standard Practices - Engine 1. General This Section gives you data about the fasteners used on the AE E4-B engine installed in the DA 40 NG airplane. It also gives you the procedures for tightening the fasteners. Refer to the AE Maintenance Manual, latest revision for more data.
  • Page 338 Standard Practices DA 40 NG AMM AIRCRAFT Table 1 - Standard Torque Values for Engine Bolts and Nuts INCH THREAD TORQUE (Nm) TORQUE (lbf.ft.) 5/16 7/16 9/16 Table 2 - Standard Torque Values for Engine Pipe Plugs TAPER THREAD TORQUE (Nm) TORQUE (lbf.ft.)
  • Page 339 DA 40 NG AMM Standard Practices AIRCRAFT Table 3 - Standard Torque Values for Engine Crush-Type Asbestos Gaskets THREAD PITCH ANGLE OF TURN THREADS PER INCH ALUMINUM ASBESTOS COPPER ASBESTOS 135° 67° 135° 67° 180° 90° 180° 90° 270° 135°...
  • Page 340 Standard Practices DA 40 NG AMM AIRCRAFT Table 5 - Special Torque Values for the Engine ITEM THREAD TORQUE (Nm) TORQUE (lbf.ft.) Engine oil filter 18.5 Coolant silicate pouch 32.5 ± 2.5 24.0 ± 1.8 cartridge Coolant tank filler cap 12-15 8.85-11.06...

  • Page 341: Installation And Tightening Torques Of Worm Drive Clamps

    DA 40 NG AMM Standard Practices AIRCRAFT 4. Installation and Tightening Torques of Worm Drive Clamps The Figures and tables show the proper installation and the tightening torques of worm drive clamps. A. Single Worm Drive Clamp CAUTION: DO NOT PLACE A WORM DRIVE CLAMP ON A TUBE BEAD. THIS CAN DAMAGE THE HOSE AND MAY (IN CASE OF ENGINE CHARGE AIR INSTALLATION) CAUSE LOSS OF ENGINE POWER.
  • Page 342 Standard Practices DA 40 NG AMM AIRCRAFT B. Two Worm Drive Clamps (1) Axial Placement CAUTION: DO NOT PLACE A WORM DRIVE CLAMP ON A TUBE BEAD. THIS CAN DAMAGE THE HOSE AND MAY (IN CASE OF ENGINE CHARGE AIR INSTALLATION) CAUSE LOSS OF ENGINE POWER.
  • Page 343 DA 40 NG AMM Standard Practices AIRCRAFT Expansion Bellows Maximum Insertion Aluminium Tube Beads Aluminium Tube Spring Steel Support Ring Silicon Hose Worm Drive Clamps Figure 4: Installation with Two Worm Drive Clamps, Two Beads (Axial Placement) and a Hose with Flexible Bellows (if MÄM 40-820 is installed)
  • Page 344 Standard Practices DA 40 NG AMM AIRCRAFT C. Tightening Torques for Worm Drive Clamps CAUTION: WORM DRIVE CLAMPS MUST BE TIGHTENED ACCORDING TO THE TABLE BELOW. OVER-TIGHTENING A WORM DRIVE CLAMP CAN DAMAGE THE HOSE AND MAY (IN CASE OF ENGINE INSTALLATIONS) CAUSE LOSS OF ENGINE POWER.
  • Page 345 Air Conditioning DA 40 NG AMM AIRCRAFT CHAPTER 21 AIR CONDITIONING, HEATING AND VENTILATION Doc # 6.02.15 Page 1 21-TITLE Rev. 3 01 Sep 2017...
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  • Page 347 Air Conditioning DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 21 HEATING AND VENTILATION General ............1 Description and Operation .
  • Page 348 Air Conditioning DA 40 NG AMM AIRCRAFT Section 21-51 Cooling (OÄM 40-316/i or later installed) General ............1 Description .
  • Page 349 RACC system. 2. Description and Operation The DA 40 NG has two separate systems, one for heating and one for cooling/ventilating the cabin. Figure 1 shows the heating system and Figure 2 shows the cooling and ventilation system.
  • Page 350 Air Conditioning DA 40 NG AMM AIRCRAFT Canopy Defrost Hot Air Instrument Panel Cover CABIN HEAT Firewall Control Levers Intake CABIN HEAT DEFROST Cabin Heat Exchanger FLOOR Passengers Floor Hot Air Pilots Floor Hot Air Floor Heat/Defrost Distributor Valve Bowden Cables...
  • Page 351 Air Conditioning DA 40 NG AMM AIRCRAFT If the heat valve is set to OFF, the hot air is released into the bottom of the engine cowling. If it is set to ON, the hot air is guided through the firewall to the distributor valve. The valve can be set to any position between OFF and ON.
  • Page 352 Air Conditioning DA 40 NG AMM AIRCRAFT Cabin Air Control Cabin Air Exhaust NACA Air Inlet NACA Air Inlet Sealed Cabin Air Control RH Rear Cabin Air Control Rear Cabin Air Control Cabin Air Sealed Exhaust Cabin Air Control LH...

  • Page 353: General

    Air Conditioning DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the air conditioning system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 355: General

    Air Conditioning DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General This Section gives you the Maintenance Practices for the cabin heating system and tells you how to replace outlets for the cooling system. Refer to Section 75-00 for maintenance data on the heat-exchanger.
  • Page 356 Air Conditioning DA 40 NG AMM AIRCRAFT Distributor Valve Instrument Panel Cover Control Cable Defrost Hose Heat Valve Control Cable Swivel Defrost Fitting Heat Valve Control Hose Cable Lock-Nut Firewall Hot Air Hose to Passenger Swivel Fitting Foot Wells Cable Binder...
  • Page 357 Air Conditioning DA 40 NG AMM AIRCRAFT B. Install the Heat Valve Detail Steps/Work Items Key Items/References Examine the copper seal between the distributor Replace defective seal. Use self- valve and the firewall. adhesive copper tape. Put the heat valve in position on the firewall.

  • Page 358: Test/Adjust The Heat Valve

    Air Conditioning DA 40 NG AMM AIRCRAFT 3. Test/Adjust the Heat Valve WARNING: MAKE SURE THAT THE FLAP ON THE HEAT VALVE FULLY CLOSES THE FIREWALL OUTLET WHEN YOU SET THE CABIN HEAT CONTROL LEVER TO 'OFF'. THIS IS TO STOP FIRE OR EXHAUST FUMES FROM ENTERING THE COCKPIT IN AN EMERGENCY.

  • Page 359: Remove/Install The Distributor Valve

    Air Conditioning DA 40 NG AMM AIRCRAFT 4. Remove/Install the Distributor Valve Refer to Figure 3. A. Remove the Distributor Valve Detail Steps/Work Items Key Items/References Remove the engine cowlings. Refer to Section 71-10. Disconnect the battery. Refer to Section 24-31.
  • Page 360 Air Conditioning DA 40 NG AMM AIRCRAFT B. Install the Distributor Valve Detail Steps/Work Items Key Items/References Hold the distributor valve in front of the firewall. Attach the 2 hot air hoses which go from the Use cable binders. passengers' footwells to the bottom outlets.
  • Page 361 Air Conditioning DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (11) Install the 2 attaching bolts and washers. In the side walls of the floor panel in the cockpit. Torque: 6.4 Nm (4.7 lbf.ft.). (12) Install a new copper seal between the distributor Use self-adhesive copper tape.

  • Page 362: Test/Adjust The Distributor Valve

    Air Conditioning DA 40 NG AMM AIRCRAFT 5. Test/Adjust the Distributor Valve Detail Steps/Work Items Key Items/References Set the distribution control lever in the cockpit There should be a gap of about 3 mm to DEFROST. (1/8 in) between the back of the lever and the cockpit stop.
  • Page 363 Air Conditioning DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Note: If you cannot get bounce at both ends of the range of movement, adjust the cable to give bounce at the DEFROST end. Do steps 8 and 9 as necessary to get the correct adjustment.
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  • Page 365: Cooling

    Air Conditioning DA 40 NG AMM AIRCRAFT Section 21-50 Cooling 1. General If OÄM 40-316 is installed, a recirculating air - cabin cooling (RACC) system is installed. The RACC system is an independent subsystem of the airplane and is electrically powered. It consists of the central unit (installed aft of baggage compartment) and a control panel (in the cabin, center console).
  • Page 366 Air Conditioning DA 40 NG AMM AIRCRAFT Compartment Fan Airplane Central Unit Cabin Cabin Fan (Radial) in Short Compressor Baggage Extension Evaporator Cabin Fan (Radial) Condenser Fan (Axial) Expansion Valve Condenser Filter / Drier / Collector Air Intake Air Exhaust...
  • Page 367 Air Conditioning DA 40 NG AMM AIRCRAFT B. Control Panel The control panel is situated on the center console in the cabin. It is electrically connected to the RACC controller and provides all necessary elements to control the center unit. An integrated display shows the preset air temperature.

  • Page 368: Operation

    Air Conditioning DA 40 NG AMM AIRCRAFT 3. Operation If electrical power is provided to the RACC system, the blue LED on the control panel flashes. The control panel of the RACC system in the center console allows the crew to control the fan speed and the cabin temperature.

  • Page 369: Trouble Shooting

    Air Conditioning DA 40 NG AMM AIRCRAFT Trouble Shooting 1. General The table below lists the defects you could have with the control panel in the center console. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
  • Page 370 Air Conditioning DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair Insufficient cooling. Air inlet filter contaminated. Clean or replace filter. Hot air outlet on LH fuselage Remove blockage. blocked. Leak in refrigerant circuit. Perform a leak test. Repair leak.

  • Page 371: Maintenance Practices

    Air Conditioning DA 40 NG AMM AIRCRAFT Maintenance Practices 1. Remove/ Install the Central Unit A. Remove the Central Unit Detail Steps/Work Items Key Items/References Remove the passenger seats. Refer to Section 25-10. Remove the seatbelt pulleys of the passenger Refer to Section 25-10.
  • Page 372 Air Conditioning DA 40 NG AMM AIRCRAFT Compartment Fan Overhead Air Duct Air Outlet Warm Air Exhaust RACC Central Unit Outside Air Intake Figure 3: RACC Central Unit Installation Page 202 Doc # 6.02.15 21-50-00 01 Sep 2017 Rev. 3...
  • Page 373 Air Conditioning DA 40 NG AMM AIRCRAFT B. Install the Central Unit Detail Steps/Work Items Key Items/References Lift the RACC central unit into the airplane. Slide the RACC central unit backward. Make sure to position the mounting panel on the mounting panel supports in the fuselage.
  • Page 374 Air Conditioning DA 40 NG AMM AIRCRAFT Control Box Cabin Air Out Evaporator Outside Air Outlet Condenser Outside Air Inlet Figure 4: Central Unit - Front and LH Side Page 204 Doc # 6.02.15 21-50-00 01 Sep 2017 Rev. 3...
  • Page 375 Air Conditioning DA 40 NG AMM AIRCRAFT Control Box Cabin Air In Condenser Compressor Filter Drier / Collector Bottle Figure 5: Central Unit Back and RH Side Doc # 6.02.15 Page 205 21-50-00 Rev. 3 01 Sep 2017...

  • Page 376: Remove/Install The Control Panel

    Air Conditioning DA 40 NG AMM AIRCRAFT 2. Remove/Install the Control Panel A. Remove the Control Panel Detail Steps/Work Items Key Items/References Remove the center console. Refer to Section 25-10. Unplug the electrical connectors of the control panel. Unclip the RACC control panel from the center console.

  • Page 377: Racc System Test Procedure

    Air Conditioning DA 40 NG AMM AIRCRAFT 3. RACC System Test Procedure Detail Steps/Work Items Key Items/References Perform an engine ground test. Refer to Section 71-00. Set the engine to 1000 to 1200 RPM. Set the AUX POWER switch to ON.

  • Page 378: Remove/Install Parts Of The Refrigerant Circuit

    Air Conditioning DA 40 NG AMM AIRCRAFT 4. Remove/Install Parts of the Refrigerant Circuit Note: The refrigerant vapor cooling system is a hermetically sealed and pressurized circuit and contains the refrigerant R134a. WARNING: ALL MAINTENANCE AND REPLENISHMENT WHICH REQUIRES TO...
  • Page 379 Air Conditioning DA 40 NG AMM AIRCRAFT (3) Charge the Refrigerant Circuit Detail Steps/Work Items Key Items/References Make sure that all connectors of the refrigerant circuit are tight. Charge the refrigerant circuit. Follow the instructions of the discharge/charging station. Print the protocol of the discharge/charging...
  • Page 380 Air Conditioning DA 40 NG AMM AIRCRAFT B. Remove/Install the Compressor (1) Remove the Compressor Detail Steps/Work Items Key Items/References Discharge the refrigerant circuit. Refer to Paragraph 4A (2). Unplug the electrical connectors from the compressor. Loosen the hose connections of the refrigerant Use caps to plug the hose connectors.
  • Page 381 Air Conditioning DA 40 NG AMM AIRCRAFT C. Remove/Install the Filler/Drier Assembly (1) Remove the Filler/Drier Assembly Detail Steps/Work Items Key Items/References Discharge the refrigerant circuit. Refer to Paragraph 4A (2). Remove the electrical connectors from the pressure sensor. Loosen the hose connections of the refrigerant Use caps to plug the hose connectors.
  • Page 382 Air Conditioning DA 40 NG AMM AIRCRAFT D. Remove/Install the Expansion Valve (1) Remove the Expansion Valve Detail Steps/Work Items Key Items/References Discharge the refrigerant circuit. Refer to Paragraph 4A (2). Loosen the hose connections of the refrigerant Use caps to plug the hose connectors.

  • Page 383: Cooling (Oäm 40-316/I Or Later Installed)

    Air Conditioning DA 40 NG AMM AIRCRAFT Section 21-51 Cooling (OÄM 40-316/i or later installed) 1. General If OÄM 40-316/i or later is installed, an improved recirculating air - cabin cooling (RACC) system is installed. The RACC system is an independent subsystem of the airplane and is electrically powered.
  • Page 384 Air Conditioning DA 40 NG AMM AIRCRAFT AIRPLANE Evaporator Fan CABIN (Radial) Vents (x6) Cold Air Compressor Evaporator Duct Compartment Deventilation via Tail Spar Condenser Expansion Valve Receiver/Drier Condenser Fan (Radial) Compartment Exhaust Refrigerant Circuit Ventilation (1 x Ø150mm) (1 x Ø100mm) Air Flow Figure 1: RACC System Schematic (OÄM 40-316/i or later installed)
  • Page 385 Air Conditioning DA 40 NG AMM AIRCRAFT B. Control Panel The control panel is situated on the center console in the cabin. It is electrically connected to the RACC controller and provides all necessary elements to control the center unit. An integrated display shows the preset air temperature.

  • Page 386: Operation

    Air Conditioning DA 40 NG AMM AIRCRAFT 3. Operation If electrical power is provided to the RACC system, the power status LED on the control panel flashes. The control panel of the RACC system in the center console allows the crew to control the fan speed and the cabin temperature.

  • Page 387: Trouble Shooting

    Air Conditioning DA 40 NG AMM AIRCRAFT Trouble Shooting 1. General The table below lists the defects you could have with the control panel in the center console. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
  • Page 388 Air Conditioning DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair Insufficient cooling. Hot air outlet on fuselage Remove blockage. bottom blocked. Leak in refrigerant circuit. Perform a leak test. Repair leak. Charge the system. Condenser faulty. Check condenser coils for dirt accumulation and remove dirt.

  • Page 389: Maintenance Practices

    Air Conditioning DA 40 NG AMM AIRCRAFT Maintenance Practices 1. Remove/ Install the Central Unit A. Remove the Central Unit Detail Steps/Work Items Key Items/References Remove the passenger seats. Refer to Section 25-10. Remove the seatbelt pulleys of the passenger Refer to Section 25-10.
  • Page 390 Air Conditioning DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (11) Lift the RACC central unit clear of the airplane. RACC Compartment Ventilation Inlet (Drip Tray incl. Filter behind) Flexible Cold Air Hose Overhead Cold Air Duct C-Profile...
  • Page 391 Air Conditioning DA 40 NG AMM AIRCRAFT B. Install the Central Unit Detail Steps/Work Items Key Items/References Lift the RACC central unit into the airplane. Slide the RACC central unit backward. Make sure to position the baseplate of the RACC central unit above the RACC brackets and trailing edge of the baseplate inside the C-profile.
  • Page 392 Air Conditioning DA 40 NG AMM AIRCRAFT Cabin Cold Air Out Condenser Evaporator Evaporator Fan Condenser Fan Electric Fan with Control Box behind Figure 4: Central Unit - Front and LH Side (if OÄM 40-316/i or later installed) Page 204 Doc # 6.02.15...
  • Page 393 Air Conditioning DA 40 NG AMM AIRCRAFT Expansion Valve Evaporator Cover Drier / Receiver Bottle Compressor Figure 5: Central Unit Back and RH Side (if OÄM 40-316/i or later installed) Doc # 6.02.15 Page 205 21-51-00 Rev. 3 01 Sep 2017...

  • Page 394: Remove/Install The Control Panel

    Air Conditioning DA 40 NG AMM AIRCRAFT 2. Remove/Install the Control Panel A. Remove the Control Panel Detail Steps/Work Items Key Items/References Remove the center console. Refer to Section 25-10. Unplug the electrical connectors of the control panel. Unclip the RACC control panel from the center console.

  • Page 395: Racc - System Test Procedure

    Air Conditioning DA 40 NG AMM AIRCRAFT 3. RACC - System Test Procedure Detail Steps/Work Items Key Items/References Perform an engine ground test. Refer to Section 71-00. Set the engine to 1000 to 1200 RPM. The test procedure may be alternatively performed with power supplied by a GPU.

  • Page 396: Remove/Install Parts Of The Refrigerant Circuit

    Make sure to obey the regulations for handling the refrigerant. If the refrigerant circuit is open for more than 30 min and the filter /dryer assy is not sealed, Diamond Aircraft recommends to replace the filter/dryer assy by a new one. A. Discharge/Charge the Refrigerant Circuit...
  • Page 397 Air Conditioning DA 40 NG AMM AIRCRAFT (3) Charge the Refrigerant Circuit Detail Steps/Work Items Key Items/References Make sure that all connectors of the refrigerant circuit are tight. Charge the refrigerant circuit with R134a Follow the instructions of the (500 ± 25 g if OÄM 40-316/i and subsequent or discharge/charging station.
  • Page 398 Air Conditioning DA 40 NG AMM AIRCRAFT (4) Leakage Test of the Refrigerant Circuit After every discharge/charge of the refrigerant system it must be checked for leakages. Most of the charging stations run automatically a leakage check before charging the air condition system.
  • Page 399 Air Conditioning DA 40 NG AMM AIRCRAFT B. Remove/Install the Compressor (1) Remove the Compressor Detail Steps/Work Items Key Items/References Discharge the refrigerant circuit. Refer to Paragraph 4A(2). Unplug the electrical connectors from the compressor. Loosen the hose connections of the refrigerant Use caps to plug the hose connectors.
  • Page 400 Air Conditioning DA 40 NG AMM AIRCRAFT C. Remove/Install the Filler/Drier Assembly (1) Remove the Filler/Drier Assembly Detail Steps/Work Items Key Items/References Discharge the refrigerant circuit. Refer to Paragraph 4A(2). Remove the electrical connectors from the pressure sensor. Loosen the hose connections of the refrigerant Use caps to plug the hose connectors.
  • Page 401 Air Conditioning DA 40 NG AMM AIRCRAFT D. Remove/Install Parts of the Refrigerant Circuit (1) Remove the Expansion Valve Detail Steps/Work Items Key Items/References Discharge the refrigerant circuit. Refer to Paragraph 4A(2). Open latches of evaporator cover and remove cover.
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  • Page 403 Auto Flight DA 40 NG AMM AIRCRAFT CHAPTER 22 AUTO FLIGHT Doc # 6.02.15 Page 1 22-TITLE Rev. 3 01 Sep 2017...
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  • Page 405 Auto Flight DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 22 AUTO FLIGHT General ............1...
  • Page 406 Auto Flight DA 40 NG AMM AIRCRAFT Section 22-11 Autopilot, KAP 140 General ............1 Description .
  • Page 407 AUTO FLIGHT 1. General This Chapter tells you about the auto flight (autopilot) system which may be installed in the DA 40 NG airplane. This Chapter tells you about the components of the GFC 700 autopilot system of the airplane.
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  • Page 409: Autopilot, Gfc 700

    Autopilot, GFC 700 1. General This Section tells you about the GFC 700 autopilot system which may be installed in the DA 40 NG. 2. Description The GFC 700 autopilot system is a digital flight control system that provides roll, pitch, pitch trim with altitude control.
  • Page 410 Auto Flight DA 40 NG AMM AIRCRAFT Reversionary Switch 10XX 10XX GMU 44 GRS 7X GDC 7X GIA 63 W GIA 63 W 1347 GSA 81 Roll Servo GSA 81 Pitch Servo GSA 81 Pitch Trim Servo G1000 LRU Digital Communication...
  • Page 411 A. GFC 700 Flight Control For details about operation and the indications concerning GFC 700 functions refer to Garmin DA 40 NG Pilot's Guide, latest revision. B. GSA 81 Roll Servo The roll servo is located behind the rear main bulkhead on the right side. It is mounted on a mounting plate which is made from sheet aluminum.
  • Page 412 Auto Flight DA 40 NG AMM AIRCRAFT Figure 2: Roll Servo Installation Page 4 Doc # 6.02.15 22-10-00 01 Sep 2017 Rev. 3...

  • Page 413: Maintenance Practices

    Auto Flight DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to install the components of the autopilot system. They also tell you how to test and adjust the autopilot system. 2. Remove/Install the Roll Servo A.

  • Page 414: Remove/Install The Roll Servo Clutch

    Auto Flight DA 40 NG AMM AIRCRAFT 3. Remove/Install the Roll Servo Clutch A. Equipment Item Quantity Part Number Cable tension gauge. Commercial. B. Remove the Roll Servo Clutch Detail Steps/Work Items Key Items/References Remove the roll servo. Refer to Paragraph 2.
  • Page 415 Auto Flight DA 40 NG AMM AIRCRAFT C. Install the Roll Servo Clutch Detail Steps/Work Items Key Items/References Remove the pilot's seat or the co-pilot's seat. Refer to Section 25-10. To give access for the rigging pin. Put the clutch in place on the mounting plate.

  • Page 416: Remove/Install The Pitch Servo

    Auto Flight DA 40 NG AMM AIRCRAFT 4. Remove/Install the Pitch Servo A. Remove the Pitch Servo Detail Steps/Work Items Key Items/References Remove the trim/cover from the front face of the baggage compartment and remove the lower access panel from the baggage compartment insert.
  • Page 417 Auto Flight DA 40 NG AMM AIRCRAFT Figure 3: Pitch Servo Installation Doc # 6.02.15 Page 205 22-10-00 Rev. 3 01 Sep 2017...

  • Page 418: Remove/Install The Pitch Servo Clutch

    Auto Flight DA 40 NG AMM AIRCRAFT 5. Remove/Install the Pitch Servo Clutch A. Equipment Item Quantity Part Number Cable tension gauge. Commercial. B. Remove the Pitch Servo Clutch Detail Steps/Work Items Key Items/References Remove the pitch servo. Refer to Paragraph 4.
  • Page 419 Auto Flight DA 40 NG AMM AIRCRAFT C. Install the Pitch Servo Clutch Detail Steps/Work Items Key Items/References Remove the pilot's seat or the co-pilot's seat. Refer to Section 25-10. To give access for the rigging pin. Put the clutch in place on the mounting plate.
  • Page 420 Auto Flight DA 40 NG AMM AIRCRAFT Figure 4: Pitch Trim Servo Installation Page 208 Doc # 6.02.15 22-10-00 01 Sep 2017 Rev. 3...

  • Page 421: Remove/Install The Pitch Trim Servo

    Auto Flight DA 40 NG AMM AIRCRAFT 6. Remove/Install the Pitch Trim Servo A. Remove the Pitch Trim Servo Detail Steps/Work Items Key Items/References Remove the co-pilot's seat. Refer to Section 25-10. Dis-connect the connector from the servo. Remove the mounting screws (2 or 4) which Hold the servo.

  • Page 422: Remove/Install The Pitch Trim Servo Clutch

    Auto Flight DA 40 NG AMM AIRCRAFT 7. Remove/Install the Pitch Trim Servo Clutch A. Remove the Pitch Trim Servo Clutch Detail Steps/Work Items Key Items/References CAUTION: DO NOT APPLY STRONG FORCES TO THE CARDAN SHAFT. THE UPPER CARDAN JOINT CONNECTS TO A PART WHICH IS WEAK...

  • Page 423: Adjust The Bridle Cable Tension Of The Roll And Pitch Servos

    Auto Flight DA 40 NG AMM AIRCRAFT 8. Adjust the Bridle Cable Tension of the Roll and Pitch Servos A. Equipment Item Quantity Part Number Cable tension gauge. Commercial. B. Adjustment Procedure Detail Steps/Work Items Key Items/References Loosen the bolts in the clamps which connect Do not remove the bolts.

  • Page 424: Adjust/Check The Servo Clutch Torques

    Auto Flight DA 40 NG AMM AIRCRAFT 9. Adjust/Check the Servo Clutch Torques A. Equipment Item Quantity Part Number Garmin slip clutch adjustment fixture. T10-00110-01. B. Adjustment/Check Procedure Detail Steps/Work Items Key Items/References Remove the clutch from the airplane. Refer to this Section.

  • Page 425: Mechanical Check Of The Autopilot System (If Mäm 40-561 (Gsm 86 Servo Mounts) Is Not Installed)

    Auto Flight DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Remove the clutch assembly from the slip clutch test stand. Apply grease to the servo output gears. Install the clutch to the airplane. Refer to this Section. 10. Mechanical Check of the Autopilot System (if MÄM 40-561 (GSM 86 Servo Mounts) is not installed) Do this check at the intervals given in Section 05-10.

  • Page 426: Slip Clutch Override Procedure

    Auto Flight DA 40 NG AMM AIRCRAFT 12. Slip Clutch Override Procedure Detail Steps/Work Items Key Items/References With the autopilot disengaged, check freedom of control movement in all control axes, including pitch trim. Power up the Garmin G1000 in Configuration Refer to G1000 System Maintenance Mode.

  • Page 427: Autopilot, Kap 140

    1. General This Section tells you about the KAP 140 autopilot system in the DA 40 NG airplane. 2. Description The KAP 140 autopilot system is a digital flight control system that provides roll, pitch, and pitch trim steering with altitude preselect.
  • Page 428 Auto Flight DA 40 NG AMM AIRCRAFT Garmin 1000 Integrated Cockpit System Turn & Bank Indicator D .C . E LE C . TU R N C O OR D IN ATO R 2 MIN. N O P IT CH...
  • Page 429 Auto Flight DA 40 NG AMM AIRCRAFT Figure 2 shows the Bendix/King KAP 140 flight control computer. It is located in the instrument panel, at the bottom. The Bendix/King KAP 140 has the following annunciators on the front panel, above the AP button: P (pitch axis) annunciator.
  • Page 430 Auto Flight DA 40 NG AMM AIRCRAFT Altitude Alerter/ Vertical Speed/ Baro Setting Pitch Trim Display Annunciation Pitch and Roll Altitude Alert Altitude Arm Baro Set Mode Displays Annunciation Button Button Pitch Axis BENDIX/KING KAP 140 10.500 Annunciator ALERT Roll Axis...
  • Page 431 Auto Flight DA 40 NG AMM AIRCRAFT ALERT (altitude alert) annunciation. This annunciation is used when the altitude preselect option is installed. It illuminates continuously in the region of from 200 to 1000 feet from the selected altitude if the airplane was previously outside of this region.
  • Page 432 Auto Flight DA 40 NG AMM AIRCRAFT APR (approach) mode selector button. When pushed, it will select the navigation mode. The mode provides automatic beam capture and tracking of VOR, GPS, LOC, and glideslope (GS) on an ILS, as selected for presentation on the ICS. APR mode tracking sensitivity is recommended for instrument approaches.
  • Page 433 B. KCM 100 Configuration Module The data which is specific to the DA 40 NG (for example: gain settings) is stored in the KCM 100 configuration module. It is located on the instrument panel floor, between the instrument panel and the instrument panel frame.
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  • Page 435: Maintenance Practices

    Auto Flight DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to install the components of the autopilot system. They also tell you how to test and adjust the autopilot system. 2. Remove/Install the Flight Control Computer A.
  • Page 436 Auto Flight DA 40 NG AMM AIRCRAFT B. Install the Flight Control Computer Detail Steps/Work Items Key Items/References Remove the protective covers from the connectors on the replacement unit. Slide the unit into the rack. Engage the locking screw so that the latch front-lobe touches the rack.

  • Page 437: Remove/Install The Kcm 100 Configuration Module

    Auto Flight DA 40 NG AMM AIRCRAFT 3. Remove/Install the KCM 100 Configuration Module A. Remove the KCM 100 Configuration Module Detail Steps/Work Items Key Items/References Open the AUTOPILOT circuit-breaker. Instrument panel, right side. Remove the instrument panel cover. Refer to Section 25-10.
  • Page 438 MUST MAKE SURE THAT IT HAS THE PART NUMBER WHICH IS SHOWN IN THE EQUIPMENT LIST IN CHAPTER 6 OF THE AIRPLANE FLIGHT MANUAL. THE CONFIGURATION MODULE CONTAINS INFORMATION WHICH IS SPECIFIC FOR THE DA 40 NG AIRPLANE. Slide the KCM 100 into position. Connect the electric cable and engage the two locking screws.

  • Page 439: Remove/Install The Roll Servo

    Auto Flight DA 40 NG AMM AIRCRAFT 4. Remove/Install the Roll Servo A. Remove the Roll Servo Detail Steps/Work Items Key Items/References Remove the passengers' seat. Refer to Section 25-10. Dis-connect the connector from the servo. Remove the 2 screws which attach the servo to Hold the servo.

  • Page 440: Remove/Install The Roll Servo Clutch

    Auto Flight DA 40 NG AMM AIRCRAFT 5. Remove/Install the Roll Servo Clutch A. Equipment Item Quantity Part Number Cable tension gauge. Commercial. B. Remove the Roll Servo Clutch Detail Steps/Work Items Key Items/References Remove the roll servo. Refer to Paragraph 3.
  • Page 441 Auto Flight DA 40 NG AMM AIRCRAFT C. Install the Roll Servo Clutch Detail Steps/Work Items Key Items/References Remove the pilot's seat or the co-pilot's seat. Refer to Section 25-10. To give access for the rigging pin. Put the clutch in place on the mounting plate.

  • Page 442: Remove/Install The Pitch Servo

    Auto Flight DA 40 NG AMM AIRCRAFT 6. Remove/Install the Pitch Servo A. Remove the Pitch Servo Detail Steps/Work Items Key Items/References Remove the trim/cover from the front face of the baggage compartment and remove the lower access panel from the baggage compartment insert.

  • Page 443: Remove/Install The Pitch Servo Clutch

    Auto Flight DA 40 NG AMM AIRCRAFT 7. Remove/Install the Pitch Servo Clutch A. Equipment Item Quantity Part Number Cable tension gauge. Commercial. B. Remove the Pitch Servo Clutch Detail Steps/Work Items Key Items/References Remove the pitch servo. Refer to Paragraph 5.
  • Page 444 Auto Flight DA 40 NG AMM AIRCRAFT C. Install the Pitch Servo Clutch Detail Steps/Work Items Key Items/References Remove the pilot's seat or the co-pilot's seat. Refer to Section 25-10. To give access for the rigging pin. Put the clutch in place on the mounting plate.

  • Page 445: Remove/Install The Pitch Trim Servo

    Auto Flight DA 40 NG AMM AIRCRAFT 8. Remove/Install the Pitch Trim Servo A. Remove the Pitch Trim Servo Detail Steps/Work Items Key Items/References Remove the co-pilot's seat. Refer to Section 25-10. Dis-connect the connector from the servo. Remove the 2 screws which attach the servo to Hold the servo.

  • Page 446: Remove/Install The Pitch Trim Servo Clutch

    Auto Flight DA 40 NG AMM AIRCRAFT 9. Remove/Install the Pitch Trim Servo Clutch A. Remove the Pitch Trim Servo Clutch Detail Steps/Work Items Key Items/References CAUTION: DO NOT APPLY STRONG FORCES TO THE CARDAN SHAFT. THE UPPER CARDAN JOINT CONNECTS TO A PART WHICH IS WEAK...

  • Page 447: Adjust The Bridle Cable Tension

    Auto Flight DA 40 NG AMM AIRCRAFT 10. Adjust the Bridle Cable Tension A. Equipment Item Quantity Part Number Cable tension gauge. Commercial. B. Adjustment Procedure Detail Steps/Work Items Key Items/References Loosen the bolts in the clamps which connect Do not remove the bolts. Loosen just the bridle cable to the push-rod.

  • Page 448: Adjust The Servo Clutch Torques

    Auto Flight DA 40 NG AMM AIRCRAFT 11. Adjust the Servo Clutch Torques A. Equipment Item Quantity Part Number Goodrich slip clutch test stand. 20-9855-03. B. Adjustment Procedure Detail Steps/Work Items Key Items/References Remove the clutch from the airplane. Refer to this Section.

  • Page 449: Mechanical Test Of The Autopilot

    Auto Flight DA 40 NG AMM AIRCRAFT 12. Mechanical Test of the Autopilot Do this check at the intervals given in Section 05-10. Detail Steps/Work Items Key Items/References Check bridle cable tension for the roll servo, Refer to this Section.
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  • Page 451 DA 40 NG AMM Communications AIRCRAFT CHAPTER 23 COMMUNICATIONS Doc # 6.02.15 Page 1 23-TITLE Rev. 3 01 Sep 2017...
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  • Page 453 DA 40 NG AMM Communications AIRCRAFT TABLE OF CONTENTS CHAPTER 23 COMMUNICATIONS General ............1 Description .
  • Page 454 Communications DA 40 NG AMM AIRCRAFT Maintenance Practices General ............201 Remove/Install the NAV/COM Unit .
  • Page 455 DA 40 NG AMM Communications AIRCRAFT Maintenance Practices General ............201 Remove/Install the PM 1000 II Intercom .
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  • Page 457 COMMUNICATIONS 1. General This Chapter tells you about the communications system in the DA 40 NG. This Section tells you about the intercom system which lets the pilots and passengers talk to each other. It also tells you about the radio system which lets the pilots talk to the ground and other airplane.
  • Page 458 Communications DA 40 NG AMM AIRCRAFT B. Communication System if Conventional Cockpit Is Installed The DA 40 NG communication system can have these components: NAV/COM transceiver. Intercom system. COM VHF antenna. NAV (VOR/LOC/GS) antenna. Push-to-talk (PTT) switches. A PTT switch is located on each of the pilots' control sticks.
  • Page 459 G1000 System Installed 1. General This Section tells you about the speech communication system in the DA 40 NG. It does not tell you about the speech communication equipment. Refer to the equipment manufacturers' manuals for more data about the equipment.
  • Page 460 Communications DA 40 NG AMM AIRCRAFT Manouvering speed : Limita tio ns for GFC 7 00 Au top ilot Sys te m: =11 1 KIA S (above 1036 u p to 1200 kg / above 2284 up t o 2646 lb) Do not use AP i f “Alternate S t atic”...
  • Page 461 VOL knob. Press the knob to toggle the ON/OFF selection of the automatic squelch control. The pilots use the audio control panel to control all the audio systems of the DA 40 NG. Both speech and navigational audio can be sent to the pilots or passengers headphones. Or can be played on the cockpit loudspeaker.
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  • Page 463 DA 40 NG AMM Communications AIRCRAFT Trouble-Shooting 1. General This table tells you how to trouble-shoot the speech communication system. See Section 23-50 for trouble-shooting the audio integrating system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 465 DA 40 NG AMM Communications AIRCRAFT Maintenance Practices 1. General This Section tells you how to replace the main components of the speech communication system. Refer to the equipment manufacturers' manuals for more data about the equipment. The communications transceivers are integral with the GIA 63 integrated avionics units (IAU). Refer to Section 31-40 for data about replacing the GIA 63 IAUs.
  • Page 466 Communications DA 40 NG AMM AIRCRAFT B. Install a COM VHF Antenna Detail Steps/Work Items Key Items/References Carefully remove any sealant from the area Take care not to damage the fuselage. where the antenna attaches to the fuselage. If necessary, use a commercial solvent.
  • Page 467 DA 40 NG AMM Communications AIRCRAFT 3. Remove/Install a PTT Switch Use this procedure for both pilot’s and co-pilot’s switches. A. Remove a PTT Switch Detail Steps/Work Items Key Items/References Set the ELECTRIC MASTER key switch to OFF. Instrument panel, center.
  • Page 468 Communications DA 40 NG AMM AIRCRAFT B. Install a PTT Switch Detail Steps/Work Items Key Items/References Install the electrical cable, if removed before: S Push the cable through the inside of the Through the hole in the stick. stick. S Connect the lower end of cable.
  • Page 469 DA 40 NG AMM Communications AIRCRAFT 4. Remove/Install the Cabin Speaker A. Remove the Cabin Speaker Detail Steps/Work Items Key Items/References Remove the map light for the passenger Clean up the silicone from the hole. compartment from the overhead console.
  • Page 470 Communications DA 40 NG AMM AIRCRAFT B. Install the Cabin Speaker Detail Steps/Work Items Key Items/References Install the cabin speaker in the overhead console. Connect the cabin speaker connector. Install the cabin speaker cover. Connect the map light for the co-pilot.
  • Page 471 Conventional Cockpit Installed 1. General This Section tells you about the speech communication system in the DA 40 NG with conventional cockpit installed. It does not tell you about the speech communication equipment. Refer to the equipment manufacturers' manuals for more data about the equipment.
  • Page 472 Communications DA 40 NG AMM AIRCRAFT COMM 1 VHF- NAV Transponder/DME COMM 1 VHF- NAV Transponder Figure 1: Antenna Locations Page 2 Doc # 6.02.15 23-11-00 01 Sep 2017 Rev. 3...
  • Page 473 DA 40 NG AMM Communications AIRCRAFT Active Standby Function Bearing To/From Graphic Frequency Frequency Annunciators Indication Photocell Transmit Annunciator Small PULL SQUELCH Inner Power/ Knob Volume/ Squelch Large Outer Frequency Comm System Ident Enter Knob Flip/Flop Radio Radio Settings Select...
  • Page 474 Communications DA 40 NG AMM AIRCRAFT 2. Description The Garmin SL 30 NAV/COM consists of a transmitter/receiver for communication (COM) and a receiver for navigation information (NAV). These are combined with operating controls and course deviation indicator (CDI) in one unit. For the COM part 760 channels are spaced 25 kHz apart and cover a frequency range from 118.000 MHz to 136.975 MHz.
  • Page 475 DA 40 NG AMM Communications AIRCRAFT ID. Press ID to select the NAV audio and toggle between voice or ident. Pressing ID will cancel the VOR monitor function. Selecting the monitor function will suspend the ID function until the monitor function is disabled.
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  • Page 477 DA 40 NG AMM Communications AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the speech communication system. Refer to Section 34-52 for Trouble-Shooting the VOR/LOC/GS system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 479 DA 40 NG AMM Communications AIRCRAFT Maintenance Practices 1. General This Section tells you how to remove/install the main components of the speech communication system. Refer to the equipment manufacturer's manuals for more data about the equipment. 2. Remove/Install the NAV/COM Unit A.
  • Page 480 Communications DA 40 NG AMM AIRCRAFT B. Install the NAV/COM Unit Detail Steps/Work Items Key Items/References Remove the protective covers from the connectors on the rear of the unit. Slide the unit into the rack. Engage the locking screw so that the lobe of the front latch touches the rack.
  • Page 481 DA 40 NG AMM Communications AIRCRAFT 3. Remove/Install a COM VHF Antenna A. Remove a COM VHF Antenna Detail Steps/Work Items Key Items/References Remove the screws which attach the antenna to the fuselage. Carefully pull the antenna clear of the fuselage If necessary, carefully cut the sealant and hold it.
  • Page 482 Communications DA 40 NG AMM AIRCRAFT 4. NAV/COM Test If possible, do an operational flight check after the radio has been replaced. Alternatively use a NAV/COM test set to make sure that the system operates correctly. Refer to the manufacturer's Installation Manual for performance specifications.
  • Page 483 G1000 System Installed 1. General The DA 40 NG has a voice-operated (VOX) intercom. This gives full hands-free intercom when head-sets are used. The pilot controls the intercom system with the audio control panel. The audio control panel is located in the instrument panel between the integrated cockpit system (ICS) display screens.
  • Page 484 Communications DA 40 NG AMM AIRCRAFT Manouvering speed: Limita tio ns for GFC 7 00 Autopi lot Sys tem: =11 1 KIA S (above 1036 up to 1200 kg / above 2284 up to 2646 lb) Do not use AP i f “Alterna te S t atic” is o pen .
  • Page 485 2. Description and Operation Figure 1 shows the GMA 1347 Audio Control Panel of the DA 40 NG airplane. The audio control panel is powered with the Garmin 1000 ICS and is an integral component of the integrated cockpit system.
  • Page 486 DA 40 NG AMM AIRCRAFT PA key. This key is not active in the DA 40 NG installation. SPKR key. Press this key to select the cabin speaker. When selected, the cabin speaker will broadcast all the selected audio channels and all unswitched/unmuted audio warnings. The speaker will be muted when a COM microphone is keyed.
  • Page 487 DA 40 NG AMM Communications AIRCRAFT PILOT, COPLT keys. These keys control the intercom system (ICS) isolation system. The ICS isolation system has four modes of operation which can all be selected using a combination of the PILOT and COPLT keys. The system has these modes of operation: Pilot Mode.
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  • Page 489 DA 40 NG AMM Communications AIRCRAFT Trouble-Shooting 1. General This table tells you how to trouble-shoot the audio integrating system. See Section 23-10 for trouble-shooting the speech communication system. If you find the trouble in column 1 do the repair given in column 3.
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  • Page 491 DA 40 NG AMM Communications AIRCRAFT Maintenance Practices 1. General This Section tells you how to remove/install the GMA 1347 audio control panel. It also tells you how to adjust/test the ICS. Refer to the equipment manufacturers manuals for more data about the audio integrating system.
  • Page 492 Communications DA 40 NG AMM AIRCRAFT B. Install the GMA 1347 Audio Control Panel Detail Steps/Work Items Key Items/References Examine the connectors at the rear of the audio control panel. Look specially for bent or damaged pins. Insert a 3/32 in hexagonal drive wrench into the access hole in the front of the panel and rotate the locking mechanism 90°...
  • Page 493 Conventional Cockpit Installed 1. General The audio system in the DA 40 NG with conventional cockpit has the following components: PM 1000 II voice-activated (VOX) intercom, see Figure 1. Sockets for four head-sets on the rear face of the center console.
  • Page 494 Communications DA 40 NG AMM AIRCRAFT Squelch Control Squelch Control Pilot Co-Pilot PM1000II PWR/XMT PILOT CO-PILOT VOLUME SQUELCH VOLUME SQUELCH Volume Control Mode Switch Volume Control Pilot Co-Pilot Figure 1: PM 1000 II Intercom Page 2 Doc # 6.02.15 23-51-00 01 Sep 2017 Rev.
  • Page 495 DA 40 NG AMM Communications AIRCRAFT 2. Description A. PM 1000 II Intercom Figure 1 shows the PM 1000 II Intercom. It is mounted above the NAV/COM 1 set in the avionics rack in the instrument panel, see Chapter 31.
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  • Page 497 DA 40 NG AMM Communications AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the audio integrating system and the marker beacon receiver system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column.
  • Page 498 Communications DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair No audio on co-pilot’s or Open audio line. Do a test of the head-set audio passenger headsets. wiring. Refer to Chapter 92 for the wiring diagrams. Faulty intercom. Replace the intercom.
  • Page 499 DA 40 NG AMM Communications AIRCRAFT Maintenance Practices 1. General This Section tells you how to remove/install the intercom. It also tells you how to test the intercom. Refer to the equipment manufacturers' manuals for more data about the audio integrating system.
  • Page 500 Communications DA 40 NG AMM AIRCRAFT B. Install the PM 1000 II Intercom Detail Steps/Work Items Key Items/References Put the PM 1000 II in position in the instrument panel. Install the attaching screws and knobs. Connect the connector to the PM 1000 II.
  • Page 501 DA 40 NG AMM Communications AIRCRAFT 3. Test the PM 1000 II Intercom Detail Steps/Work Items Key Items/References Make sure all the head-sets are connected. Select the mode switch to ALL. Turn the VOLUME control to switch the unit ON.
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  • Page 503 The static discharging system removes the electro-static charge which collects on the airplane surfaces. The composite structure of the DA 40 NG does not let electricity flow through it. The airplane surfaces are covered with a special conductive filler through which the electricity flows to the static discharge wick.
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  • Page 505 Electrical Power DA 40 NG AMM AIRCRAFT CHAPTER 24 ELECTRICAL POWER Doc # 6.02.15 Page 1 24-TITLE Rev. 3 01 Sep 2017...
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  • Page 507 Electrical Power DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 24 ELECTRICAL POWER General ............1 28 VDC System Description and Operation .
  • Page 508 Electrical Power DA 40 NG AMM AIRCRAFT General ............101 Maintenance Practices General .

  • Page 509: Trouble-Shooting

    Electrical Power DA 40 NG AMM AIRCRAFT Maintenance Practices General ............201 Electrical Safety .
  • Page 510 Electrical Power DA 40 NG AMM AIRCRAFT Maintenance Practices General ............201 Electrical Safety .

  • Page 511: Electrical Power

    ELECTRICAL POWER 1. General The DA 40 NG has a 28 VDC electrical system. This Chapter describes the complete system from the power supplies to the circuit-breakers or other interface with the consumers. This Chapter has only simplified schematic diagrams and location diagrams. Refer to Chapter 92 for the wiring diagrams.
  • Page 512 Electrical Power DA 40 NG AMM AIRCRAFT INSTRUMENT PANEL ENGINE COMPARTMENT Avionic Relay AV. BUS Alternator Starter To Avionic Switch Current Sensor Power Relay Aux Power To Alt. Reg. Plug Field To Starter Relay To Battery Starter To Starter Relay...
  • Page 513 Electrical Power DA 40 NG AMM AIRCRAFT ENGINE COMPARTMENT FUSE PANEL Power Relay Current Sensor 100A Starter Alternator Relay Engine Electric Starter START Master Master Field Enable Ground Alt. Reg. Ess Tie Power Relay MAIN Plug Battery Relay Main Battery...
  • Page 514 Electrical Power DA 40 NG AMM AIRCRAFT ENGINE COMPARTMENT Avionic FUSE PANEL Relay AV. BUS To Avionic Switch Power Relay Current Sensor 100A Starter Alternator Relay Engine Electric Starter START Master Master Field Enable Ground Alt. Reg. Ess Tie Power...
  • Page 515 Electrical Power DA 40 NG AMM AIRCRAFT INSTRUMENT PANEL ENGINE COMPARTMENT Avionic Relay Alternator AV. BUS Starter Current Sensor Avionic Switch Power Excitation Relay Supply Lamp Ground Usense 100A Starter Relay Engine Electric START Master Master Battery Relay Main Battery...

  • Page 516: Vdc System Description And Operation

    Electrical Power DA 40 NG AMM AIRCRAFT 2. 28 VDC System Description and Operation Figure 1 shows the electrical system schematic diagram, if the G1000 system with GFC 700 autopilot is installed. Figure 2 shows the electrical system schematic diagram, if the conventional cockpit (OÄM 40-321 is installed).
  • Page 517 Electrical Power DA 40 NG AMM AIRCRAFT B. Power Supply Control (1) Battery Relay The battery relay is located in the relay junction box on the baggage compartment frame. The output connects directly to the relay junction box bus bar. The coil + of the battery relay is tied to the battery + connection to the relay.
  • Page 518 Electrical Power DA 40 NG AMM AIRCRAFT (5) ECU Bus The ECU bus is located at the circuit breakers. The ECU bus has power when the any one of the following are connected to the ECU bus: The main battery.
  • Page 519 Electrical Power DA 40 NG AMM AIRCRAFT (9) Essential Bus Switch (Marked ESS BUS) The ESS BUS switch is located in the switch panel at the bottom left of the instrument panel. In the OFF position, the ESS BUS switch gives a ground to the power relay coil. The relay closes and connects the battery bus in the instrument panel to the main bus.
  • Page 520 Electrical Power DA 40 NG AMM AIRCRAFT (13) ENGINE MASTER Switch The ENGINE MASTER switch is located on the left, center of the instrument panel switch panel. It has four sets of contacts. When set to ON, each set of contacts connects one input to one output as follows: ECU A power supply to ECU A.

  • Page 521: Dc Generation

    Electrical Power DA 40 NG AMM AIRCRAFT Section 24-30 DC Generation 1. General The DC generation system for the DA 40 NG has these components: Alternator. Alternator current sensor. Alternator fuse. Voltage regulator. Alternator excitation battery (ECU backup battery). This Section gives you only the simplified description, Trouble-Shooting and Maintenance Practices for the generating system.
  • Page 522 Electrical Power DA 40 NG AMM AIRCRAFT INSTRUMENT PANEL ENGINE COMPARTMENT Power Relay Current Sensor Alternator START To Hot To Alt. Reg. 100A Electric Master Battery Main Battery Relay 24V / 13.6Ah Essential Tie Relay MAIN 100A Essential Bus Switch...
  • Page 523 Electrical Power DA 40 NG AMM AIRCRAFT ENGINE COMPARTMENT FUSE PANEL Power Relay Current Sensor 100A Alternator Electric Master Field Enable Ground Alt. Reg. Ess Tie Relay MAIN Battery Relay Main Battery Essential 100A INSTRUMENT PANEL FUSELAGE LEGEND MAIN Circuit-Breaker with Name and Rating...

  • Page 524: Description And Operation

    Electrical Power DA 40 NG AMM AIRCRAFT 2. Description and Operation Figure 1 shows the generation system simplified schematic diagram if the G1000 system with GFC 700 autopilot is installed. Figure 2 shows the generation system simplified schematic diagram if the conventional cockpit (OÄM 40-321), G1000 system with KAP 140 autopilot (OÄM 40-329) or G1000 system without...

  • Page 525: Trouble-Shooting

    Electrical Power DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the generating system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 527: Maintenance Practices

    2. Electrical Safety The DA 40 NG has a low voltage DC electrical system. When correctly maintained it is safe to work on. The battery can supply heavy current through low resistance circuits (for example, if you ground the positive output with a wrench by accident).

  • Page 528: Installed

    Electrical Power DA 40 NG AMM AIRCRAFT 3. Replace the Alternator Fuse if OÄM 40-321, OÄM 40-329, OÄM 40-330 Are Not Installed Detail Steps/Work Items Key Items/References Disconnect the airplane main battery: S Disconnect the negative cable from the battery.

  • Page 529: Installed

    Electrical Power DA 40 NG AMM AIRCRAFT 4. Replace the Alternator Fuse if OÄM 40-321, OÄM 40-329 or OÄM 40-330 Is Installed Detail Steps/Work Items Key Items/References Disconnect the airplane main battery: S Disconnect the negative cable from the battery.

  • Page 530: Replacement Of The Alternator Cable

    Electrical Power DA 40 NG AMM AIRCRAFT 5. Replacement of the Alternator Cable Detail Steps/Work Items Key Items/References Disconnect the airplane main battery: Refer to Section 24-31. S Disconnect the negative cable from the battery. S Disconnect the positive cable from the battery.
  • Page 531 Electrical Power DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (10) Remove the screws, washers and locknuts connecting the current sensor to the instrument panel floor. (11) Disconnect the current sensor at the in-line connector. (12) Remove the alternator cable clear of the airplane and discard (except the insulating boot).
  • Page 532 Electrical Power DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (23) Install the instrument panel cover. Refer to Section 25-10. (24) Connect the cables to the ECU backup battery: Refer to Section 24-31. S Connect the positive cable to the battery.

  • Page 533: Battery System

    Battery System 1. General This Section tells you about the battery systems for DA 40 NG airplanes. See Sections 24-00 and 24-32 for the description and operation of the battery in the electrical generation system. The airplane has three batteries: A main battery located in the rear fuselage behind the baggage compartment frame.
  • Page 534 Electrical Power DA 40 NG AMM AIRCRAFT Positive Terminal Battery Negative Terminal Hold-Down Strap Figure 1: Main Battery Installation Page 2 Doc # 6.02.15 24-31-00 01 Sep 2017 Rev. 3...

  • Page 535: Ecu Backup Battery Description And Operation

    Electrical Power DA 40 NG AMM AIRCRAFT 3. ECU Backup Battery Description and Operation The ECU backup battery consists of two 12 V, 7.2 Ah sealed units connected in series. A tray behind the first ring spar holds the battery. The positive and negative cables attach to terminals at the top of the battery.
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  • Page 537: General

    Electrical Power DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the battery system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 539 Electrical Power DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General Keep the battery clean. Remove grease and other contaminants from the battery case. Remove dirt from the area of the terminals. Protect the terminals and cable lugs with Dow Corning compound 4 (DC4).
  • Page 540 Electrical Power DA 40 NG AMM AIRCRAFT B. Install the Battery in the Airplane Detail Steps/Work Items Key Items/References Make sure that the battery is clean and dry. Move the battery into position in the battery mount. CAUTION: MAKE SURE THAT YOU CONNECT THE CABLES TO THE CORRECT TERMINALS.
  • Page 541 Electrical Power DA 40 NG AMM AIRCRAFT 4. Disconnect/Connect the Battery for Maintenance A. Disconnect the Battery for Maintenance Detail Steps/Work Items Key Items/References Remove the baggage extension and baggage Refer to Section 25-10. tray. Disconnect the negative cable from the battery.
  • Page 542 Electrical Power DA 40 NG AMM AIRCRAFT 5. Remove/Install the Battery Relay A. Remove the Battery Relay Detail Steps/Work Items Key Items/References Remove the baggage extension and baggage Refer to Section 25-10. tray. Disconnect the main battery: S Disconnect the negative cable from the battery.
  • Page 543 Electrical Power DA 40 NG AMM AIRCRAFT B. Install the Battery Relay Detail Steps/Work Items Key Items/References Put the relay in position in the relay box and Check for correct polarity. connect the control cables to the terminal block. Connect the battery positive cable and the...
  • Page 544 Electrical Power DA 40 NG AMM AIRCRAFT 6. Battery Relay Functional Test Detail Steps/Work Items Key Items/References Set the ELECTRIC MASTER key switch to ON. The voltmeter must indicate the battery voltage. Set the ELECTRIC MASTER key switch to OFF.
  • Page 545 Emergency Battery System 1. General This Section tells you about the emergency battery system for DA 40 NG airplanes (if G1000 is installed). Regular maintenance of the emergency battery system is necessary. Refer to Chapter 92 for the wiring diagrams.
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  • Page 547 Electrical Power DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the emergency battery system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 549 Electrical Power DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General This Section tells you how to replace the emergency battery pack. It also tells you how to test the emergency battery system. Refer to Chapter 92 for the wiring diagrams.
  • Page 550 Electrical Power DA 40 NG AMM AIRCRAFT Washer Safety Cover Artificial Horizon Horizon Emergency Switch Emergency Power Pack Dry Cells (x10) Figure 1: Emergency Battery Pack Doc # 6.02.15 Page 202 24-32-00 Rev. 3 01 Sep 2017...
  • Page 551 Electrical Power DA 40 NG AMM AIRCRAFT B. Install the Battery Pack CAUTION: USE ONLY NEW BATTERY PACKS. REFER TO THE EQUIPMENT LIST IN THE AIRPLANE FLIGHT MANUAL, SECTION 6.5, FOR THE CORRECT BATTERY TYPE. CAUTION: DO NOT SHORT CIRCUIT THE BATTERY PACK.
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  • Page 553 Electrical Power DA 40 NG AMM AIRCRAFT Section 24-33 Additional Alternator 1. General If OÄM 40-314 is carried out, an additional alternator is installed. The additional alternator generates electrical DC - power for optional airplane equipment. The additional alternator and its consumers form an additional electrical system which is not connected to the airplanes standard electrical system.
  • Page 554 Electrical Power DA 40 NG AMM AIRCRAFT Figure 1: Additional Alternator Electrical System Schematic Diagram Doc # 6.02.15 Page 2 24-33-00 Rev. 3 01 Sep 2017...
  • Page 555 Electrical Power DA 40 NG AMM AIRCRAFT 2. Description and Operation Figure 1 shows the additional alternator electrical system schematic diagram. A. Additional Alternator The additional alternator is mounted to the engine gearbox and to the forward RH engine mounting arm.
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  • Page 557 Electrical Power DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have in the additional alternator electrical system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair in the Repair column.
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  • Page 559: Electrical Safety

    AFTER DOING ELECTRICAL MAINTENANCE ALWAYS DO A CONFIDENCE TEST OF THE SYSTEM WITH A 24 VOLT POWER SUPPLY THAT HAS OVER-CURRENT PROTECTION. DO THIS BEFORE CONNECTING THE BATTERY. CAUTION: USE ONLY DA 40 NG SPARE PARTS APPROVED BY THE MANUFACTURER. Doc # 6.02.15 Page 201 24-33-00 Rev.
  • Page 560 Electrical Power DA 40 NG AMM AIRCRAFT 3. Remove/Install the AUX POWER Switch A. Remove the AUX POWER Switch Detail Steps/Work Items Key Items/References Remove the center console. Refer to Section 25-10. Unplug the electrical connector of the AUX POWER switch.
  • Page 561 Electrical Power DA 40 NG AMM AIRCRAFT 4. Remove/Install the Additional Alternator Regulator A. Remove the Voltage Regulator Detail Steps/Work Items Key Items/References WARNING: MAKE SURE THAT THE ENGINE IS SAFE BEFORE YOU DO ANY WORK ON THE ADDITIONAL ALTERNATOR REGULATOR. IF THE ENGINE IS TURNED, THE PROPELLER CAN CAUSE INJURY OR DEATH.
  • Page 562 Electrical Power DA 40 NG AMM AIRCRAFT B. Install the Voltage Regulator Detail Steps/Work Items Key Items/References WARNING: MAKE SURE THAT THE ENGINE IS SAFE BEFORE YOU DO ANY WORK ON THE ADDITIONAL ALTERNATOR REGULATOR. IF THE ENGINE IS TURNED, THE PROPELLER CAN CAUSE INJURY OR DEATH.
  • Page 563 1. General The DA 40 NG has an external power socket located on the left side of the fuselage, near the relay junction box. It is a standard 28 Volt DC power socket. When you connect external power to the external power socket, the external power control relay is energized and the external power comes on-line.
  • Page 564 Electrical Power DA 40 NG AMM AIRCRAFT FUSELAGE To Hot Bus Battery Main Battery Relay 24V / 13.6Ah Starter Relay Starter Relay EPU Plug Figure 1: External Power System Schematic Diagram Page 2 Doc # 6.02.15 24-40-00 01 Sep 2017...
  • Page 565 Electrical Power DA 40 NG AMM AIRCRAFT 3. Operation When you connect a 24 to 28 V DC power supply to the external power socket these things happen: Current can flow from the small positive pin to the solenoid, the solenoid operates and closes the relay.
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  • Page 567 Electrical Power DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the external power system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 569 2. Electrical Safety The DA 40 NG has a low voltage DC electrical system. When correctly maintained it is safe to work on. The battery can supply heavy current through low resistance circuits (for example, if you ground the positive output with a wrench by accident).

  • Page 570: Remove/Install The External Power Relay

    Electrical Power DA 40 NG AMM AIRCRAFT 3. Remove/Install the External Power Relay A. Remove the External Power Relay Detail Steps/Work Items Key Items/References Remove the baggage extension and baggage Refer to Section 25-10. tray. Disconnect the battery: S Disconnect the negative cable from the battery.
  • Page 571 Electrical Power DA 40 NG AMM AIRCRAFT B. Install the External Power Relay Detail Steps/Work Items Key Items/References Put the relay in position in the relay junction box Check for correct polarity. and connect the control cables to the terminal block.
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  • Page 573: Dc Electrical Load Distribution

    Electrical Power DA 40 NG AMM AIRCRAFT Section 24-60 DC Electrical Load Distribution 1. General This Section tells you about the system which supplies DC electrical power for other systems. The DC electrical load distribution system has these components: Main bus.
  • Page 574 Electrical Power DA 40 NG AMM AIRCRAFT INSTRUMENT PANEL ENGINE COMPARTMENT Avionic Relay AV. BUS Alternator To Avionic Switch Current Sensor Power Relay To Alt. Reg. 100A Essential Tie Relay MAIN FUSELAGE Engine Master Engine Essential Bus Master Switch To Alt. Reg. Enable...
  • Page 575 Electrical Power DA 40 NG AMM AIRCRAFT Man ou ver ing speed: Limitations for GF C 700 A utopilot System: =111 KIAS ( ab ove 1036 u p to 1200 kg / a bo ve 228 4 up to 26 46 lb) D o not use A P i f “...
  • Page 576 Electrical Power DA 40 NG AMM AIRCRAFT ENGINE COMPARTMENT FUSE PANEL Power Relay Current Sensor 100A Alternator Field Enable Ground Alt. Reg. Ess Tie Relay MAIN Essential Avionic Engine Master Relay AV. BUS Engine Master MASTER CONTROL EECU Backup Avionic...
  • Page 577 Electrical Power DA 40 NG AMM AIRCRAFT PM1000II P W R /X MT PILO T CO -PIL OT IS O AL L O FF VOLU ME SQUEL CH VO LU ME SQUEL CH AIRSPEED INSTRUMENT CALI BRA TED 20 ,000 F EET...
  • Page 578 Electrical Power DA 40 NG AMM AIRCRAFT ENGINE COMPARTMENT Avionic FUSE PANEL Relay AV. BUS To Avionic Switch Power Relay Current Sensor 100A Alternator Field Enable Ground Alt. Reg. Ess Tie Relay MAIN Essential Engine Master To Avionic Relay Engine...

  • Page 579: General

    Electrical Power DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General Make sure that the alternator is supplying power and that there is 28 VDC on the main bus. Refer to Section 24-32. For faults on a piece of equipment, or a system, refer to the applicable Chapter. For example, for no oil pressure indication, see Chapter 77 - Engine Indicating.
  • Page 580 Electrical Power DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair There is 28 VDC on the battery Power relay defective. Replace the power relay. bus but not an the main bus 5 A power relay fuse failed. Replace the power relay fuse.
  • Page 581 2. Electrical Safety The DA 40 NG has a low voltage DC electrical system. When correctly maintained it is safe to work on. The battery can supply heavy current through low resistance circuits (for example, if you ground the positive output with a wrench by accident).

  • Page 582: Remove/Install The Avionics Master Relay

    Electrical Power DA 40 NG AMM AIRCRAFT 3. Remove/Install the Avionics Master Relay A. Remove the Avionics Master Relay Detail Steps/Work Items Key Items/References Disconnect the battery for maintenance. Refer to Section 24-31. Remove the instrument panel cover. Refer to Section 25-10.

  • Page 583: Remove/Install A Circuit-Breaker

    Electrical Power DA 40 NG AMM AIRCRAFT 4. Remove/Install a Circuit-Breaker A. Remove a Circuit-Breaker Detail Steps/Work Items Key Items/References Remove the baggage extension and baggage Refer to Section 25-10. tray. Disconnect the main battery: Refer to Section 24-31. S Disconnect the negative cable from the battery.
  • Page 584 Electrical Power DA 40 NG AMM AIRCRAFT B. Install a Circuit-Breaker Detail Steps/Work Items Key Items/References Put the circuit-breaker in position in the instrument panel. Move the copper bus bar forward together with the remaining circuit-breakers. Connect the wires to the circuit breaker.

  • Page 585: Remove /Install An Instrument Panel Switch

    Electrical Power DA 40 NG AMM AIRCRAFT 5. Remove /Install an Instrument Panel Switch This procedure applies to the following switches: PITOT. LANDING, TAXI, POSITION and STROBE lights. ESS. BUS. AVIONIC MASTER. FUEL TRANS ». A. Remove an Instrument Panel Switch...
  • Page 586 Electrical Power DA 40 NG AMM AIRCRAFT B. Install an Instrument Panel Switch Detail Steps/Work Items Key Items/References Hold the spring clips on the switch compressed From the front of the instrument panel. and put the switch in position in the instrument Make sure that the clips have expanded panel.

  • Page 587: Remove /Install The Engine Switch

    Electrical Power DA 40 NG AMM AIRCRAFT 6. Remove /Install the ENGINE Switch A. Remove the ENGINE Switch Detail Steps/Work Items Key Items/References Remove the baggage extension and baggage Refer to Section 25-10. tray. Disconnect the battery: Refer to Section 24-31.
  • Page 588 Electrical Power DA 40 NG AMM AIRCRAFT B. Install the ENGINE Switch Detail Steps/Work Items Key Items/References Put the switch in position adjacent to the switch electrical cables. Connect the electrical cables to the switch. Refer to Chapter 92 for the Wiring Diagrams.
  • Page 589 DA 40 NG AMM Equipment/Furnishings AIRCRAFT CHAPTER 25 EQUIPMENT/FURNISHINGS Doc # 6.02.15 Page 1 25-TITLE Rev. 3 01 Sep 2017...
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  • Page 591 DA 40 NG AMM Equipment/Furnishings AIRCRAFT TABLE OF CONTENTS CHAPTER 25 EQUIPMENT/FURNISHINGS - GENERAL General ............1...
  • Page 592 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Section 25-60 Emergency General ............1 Description .

  • Page 593: Equipment/Furnishings - General

    Emergency Location Transmitter (ELT). Note: Equipment which is certified for installation in the DA 40 NG is listed in Section 6.5 of the Airplane Flight Manual. Such equipment may be installed in accordance with the Airplane Maintenance Manual.
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  • Page 595: Flight Compartment

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT Section 25-10 Flight Compartment 1. General The flight compartment contains fixed seats for two pilots and two passengers. Each seat has a safety belt. If OÄM 40-252 or OÄM 40-375 is carried out, the pilots’ seats are equipped with adjustable backrests.
  • Page 596 Equipment/Furnishings DA 40 NG AMM AIRCRAFT (2) Pilots’ Seats with Adjustable Backrest (if OÄM 40-252 or OÄM 40-375 is carried out) Figure 1, 2 and 3 show the variants of pilots’ seats with adjustable backrest installations. Each pilots’ seat consists of a seat pan and a backrest made of GFRP/Carbon/Kevlar. Rivets attach a metal plate to the bottom of the seat pan at the back.
  • Page 597 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Gaiter for Control Stick Bolt Washer Anchor Plate Press Studs for Seat Cushion Washer Bolt Inner Crash Element Front Main Bulkhead Outer Crash Element Rear Face of the Floor Panel Figure 1: Pilot’s Seat Installation Doc # 6.02.15...
  • Page 598 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Padded Cushion Lumbar Support Cushion Flexible Gaiter Backrest Lumbar Support Cover (2 per seat) Inboard Hinge Lamella Package Seat Pan Friction Adjustment Screw Seat Lever Outboard Hinge Bowden Cable Lumbar Support Lever Figure 2: Pilot’s Seat Installation (if OÄM 40-252 is installed) Page 4 Doc # 6.02.15...
  • Page 599 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Padded Cushion Lumbar Support Cushion Flexible Gaiter Backrest Lumbar Support Hydraulic Cylinder RH Inboard Hinge Hydraulic Cylinder LH Seat Pan Bowden Cable Outboard Hinge Lumbar Support Lever Release Button Figure 3: Pilot’s Seat Installation (if OÄM 40-252 is installed) Doc # 6.02.15...
  • Page 600 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Bolt Bolt Washer Washer Bolt Washer Crash Element Anchor Plate Rear Main Bulkhead Figure 4: Passenger Seat Installation Page 6 Doc # 6.02.15 25-10-00 01 Sep 2017 Rev. 3...
  • Page 601 DA 40 NG AMM Equipment/Furnishings AIRCRAFT B. Passenger Seat Figure 4 shows the passenger seat installation. The passenger seat has three main parts. It has a double seat pan which is the full width of the cockpit. The rear part of the seat pan also makes the baggage compartment floor.
  • Page 602 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Figure 5: Safety Belt Installation Page 8 Doc # 6.02.15 25-10-00 01 Sep 2017 Rev. 3...
  • Page 603 DA 40 NG AMM Equipment/Furnishings AIRCRAFT D. Safety Belts Figure 5 shows the safety belt installation. Each seat has a fixed lap belt and an inertia sensitive shoulder strap. The lap belt has two straps. The outboard strap has an adjuster to tighten the belt in use.
  • Page 604 Equipment/Furnishings DA 40 NG AMM AIRCRAFT H. Baggage Extension and Baggage Tray Baggage extension and baggage tray are optional equipment. The baggage extension has a door that may be hinged up to keep items from sliding aft or hinged down to carry long items. The baggage extension also has a removable panel in the bottom to allow access for inspection of the rear fuselage area.

  • Page 605: Maintenance Practices

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove/install the seats, the safety belts and other furnishings. See Section 25-60 for data about the ELT. 2. Remove/Install a Pilot’s Seat Note: Some maintenance procedures described in this AMM require the removal of a front seat.
  • Page 606 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Remove the 2 bolts with washer plates which From the passenger compartment attach the anchor plates to the front main behind the pilot’s seat. bulkhead. Remove the 2 bolts with washer plates which attach the front of the seat to the rear wall of the floor panel.
  • Page 607 DA 40 NG AMM Equipment/Furnishings AIRCRAFT B. Install a Pilot’s Seat Detail Steps/Work Items Key Items/References If the adjustable front seats (OÄM 40-252 or OÄM 40-375) are installed: WARNING: DO NOT ENGAGE THE LEVER OR THE BUTTON FOR THE A D J U S T A B L E...

  • Page 608: Additional Maintenance Practices For Seats With Adjustable Backrest

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 3. Additional Maintenance Practices for Seats with Adjustable Backrest Perform the following test of the Adjustable Backrest Mechanism. If the test fails refer to Paragraphs (2) and (3). (1) Test Procedures (a) Test the Backrest Adjustment Mechanism of a Front Seat (if OÄM 40-252 or OÄM 40-375 is installed)
  • Page 609 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Detail Steps/Work Items Key Items/References Allow the backrest to move forward to the upright position: S Check for interference. S Check for lack of spring force. The spring must be strong enough to move the backrest from the full rearward...
  • Page 610 Equipment/Furnishings DA 40 NG AMM AIRCRAFT (2) Adjust the Friction of the Backrest (if OÄM 40-252 is installed) Detail Steps/Work Items Key Items/References WARNING: DO NOT ENGAGE THE LEVER OR THE BUTTON FOR THE ADJUSTABLE BACKREST FRONT SEATS UNINTENTIONALLY. THE SPRING LOADED BACKREST MAY SNAP FORWARD AND CAN CAUSE INJURY.
  • Page 611 DA 40 NG AMM Equipment/Furnishings AIRCRAFT (3) Visual Inspection of the Adjustment Mechanism (if OÄM 40-252 is installed) Detail Steps/Work Items Key Items/References Remove seat from airplane. Remove seat lever from seat: S Remove plug from lever. S Remove lever mounting screw.
  • Page 612 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Re-install the leather lining to the seat: S Attach the leather lining to the cover using the velcro fasteners. S Tie the backrest cushion to the seat pan with the 3 strings.
  • Page 613 DA 40 NG AMM Equipment/Furnishings AIRCRAFT (5) Disassemble/Assemble the Adjustable Backrest Mechanism Backrest Seat Pan Lamella Package Clamping 0.5mm Disc, Backrest 0.3mm Strong Inner 0.5mm 0.3mm Disc, Backrest 0.5mm Strong Outer 0.3mm 0.5mm Fitting Backrest Lamella, Backrest (x20) Hexagon Screw 1.6mm...
  • Page 614 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Backrest Seat Pan Release Button 35 mm (1.38 in) Hydrolok Fixing Bracket Hydraulic Cylinder Bush PAF Bush Backrest Bracket Side Bracket Seat Side Bush Bracket Seat Side PAF Bush Figure 7: Seat Adjustment Mechanism (if OÄM 40-375 is installed) Page 210 Doc # 6.02.15...
  • Page 615 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Hydrolok Fixing Bracket Bolt x 1 Washer x 1 Bolt x 3 Hydraulic Cylinder Backrest Washer x 2 Bolt x 2 Backrest Bracket Side Bracket Seat Side Washer x 5 Bolt x 5 Seat Pan Figure 8: Adjustable Backrest Assembly (if OÄM 40-375 is installed)
  • Page 616 Equipment/Furnishings DA 40 NG AMM AIRCRAFT (a) Remove Backrest Assembly from Seat (if OÄM 40-252 is installed) Each seat contains a left and right side mechanism. Before you can disassemble the backrest mechanism you must carry out the following steps:...
  • Page 617 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Detail Steps/Work Items Key Items/References Remove the nine hexagon screws on both sides of each seat fitting. Remove the eight hexagon screws on both sides of the backrest fitting. Remove the LH and the RH mechanism.
  • Page 618 Equipment/Furnishings DA 40 NG AMM AIRCRAFT (b) Remove Backrest Assembly from Seat (if OÄM 40-375 is installed) Each seat contains a left and right side mechanism. Before you can disassemble the backrest mechanism you must carry out the following steps:...
  • Page 619 DA 40 NG AMM Equipment/Furnishings AIRCRAFT (d) Assemble the Adjustable Backrest Mechanism (if OÄM 40-252 is installed) The following table describes the assembling of a single backrest mechanism. The assembly procedure is used for both sides. Step Seat Fitting Thickness...
  • Page 620 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Step Seat Fitting Thickness Backrest Fitting Thickness Remark Disc, Backrest 4 mm (21) Strong Inner Screw the hexagon screw (M5x6) with the washer (17 mm) into the thread of the bolt (22) and apply Loctite 262 screw locking or equivalent.
  • Page 621 DA 40 NG AMM Equipment/Furnishings AIRCRAFT (e) Assemble the Adjustable Backrest Mechanism (if OÄM 40-375 is installed) The following table describes the assembling of a single backrest mechanism. The assembly procedure is used for both sides. Detail Steps/Work Items Key Items/References Screw the Hydrolok hydraulic cylinder into the Refer to Figure 7.
  • Page 622 Equipment/Furnishings DA 40 NG AMM AIRCRAFT (f) Assemble a Pilots’ Seat (if OÄM 40-252 is installed) After assembling the adjustable backrest mechanism carry out following steps: Detail Steps/Work Items Key Items/References Fix the inboard mechanism with the 17 hexagonal screws.
  • Page 623 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Detail Steps/Work Items Key Items/References Install the seat lever: S Put the lever onto the adjustment mechanism in correct position. S Install the lever mounting screw. S Install plug to lever. (g) Assemble a Pilots’ Seat (if OÄM 40-375 is installed) After assembling the adjusting mechanisms on both sides install the backrest using the steps in the opposite sequence as described in Paragraph 5.(b).

  • Page 624: Remove/Install A Pilot's Seat Access Panel (If Installed)

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 4. Remove/Install a Pilot’s Seat Access Panel (if installed) A. Remove a Pilot’s Seat Access Panel Detail Steps/Work Items Key Items/References Remove the cloth coating from the seat. Remove the 12 (10) bolts which attach the access panel to the seat.

  • Page 625: Remove/Install The Access Panel Of The Passenger Seat (If Installed)

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT 5. Remove/Install the Access Panel of the Passenger Seat (if installed) A. Remove the Passenger Seat Access Panel Detail Steps/Work Items Key Items/References Remove the cloth coating from the passenger seat. Remove the 12 fixing bolts of the access panel.

  • Page 626: Remove/Install The Access Panel In The Baggage Extension

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 6. Remove/Install the Access Panel in the Baggage Extension A. Remove the Access Panel in the Baggage Extension Detail Steps/Work Items Key Items/References Fold rear seat-backs forward. Peel back each side of baggage extension carpet Carpet is held with velcro.

  • Page 627: Remove/Install The Baggage Extension And Baggage Tray

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT 7. Remove/Install the Baggage Extension and Baggage Tray A. Remove the Baggage Extension and Baggage Tray Detail Steps/Work Items Key Items/References Remove access panel. Refer to Paragraph 6A. Release 4 screws with washers which attach the front of the baggage tray (if fitted) to the rear seats.

  • Page 628: Remove/Install The Short Baggage Extension And Baggage Tray

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 8. Remove/Install the Short Baggage Extension and Baggage Tray (OÄM 40-331 is installed) A. Remove the Short Baggage Extension and Baggage Tray Detail Steps/Work Items Key Items/References Remove access panel. Refer to Paragraph 6A.
  • Page 629 DA 40 NG AMM Equipment/Furnishings AIRCRAFT B. Install the Short Baggage Extension and Baggage Tray Detail Steps/Work Items Key Items/References Do a check for unwanted items in the area below For example: tools. the short baggage extension. Put the short baggage extension in place in the Do not damage the upholstery.
  • Page 630 Equipment/Furnishings DA 40 NG AMM AIRCRAFT 9. Remove/Install the Passenger Seat A. Remove the Passenger Seat Detail Steps/Work Items Key Items/References Release the press-studs at the front of the seat Refer to Figure 4. Move the cushion cushion. back far enough to give access to the attaching bolts for the seat.

  • Page 631: Remove/Install The Passenger Seat

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT B. Install the Passenger Seat Detail Steps/Work Items Key Items/References Examine the crash elements. Look specially for Refer to Figure 4. delamination and buckling. Do a check for unwanted items in the area below For example: tools.
  • Page 632 Equipment/Furnishings DA 40 NG AMM AIRCRAFT 10. Remove/Install a Safety Belt This procedure applies to the pilots' seats and the passenger seat. A. Remove a Safety Belt Detail Steps/Work Items Key Items/References Remove the seat. Refer to Paragraph 2 or 3.

  • Page 633: Remove/Install A Safety Belt

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT B. Install a Safety Belt Detail Steps/Work Items Key Items/References Install the bolt and washer which attach the inertia Refer to Figure 5. reel and its cover to the structure. Install the bolt, washer plate and spring washer For the pilots' seats only.

  • Page 634: Remove/Install The Instrument Panel Cover

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 11. Remove/Install the Instrument Panel Cover A. Remove the Instrument Panel Cover Detail Steps/Work Items Key Items/References Remove the screws which attach the instrument panel cover to the instrument panel and the fuselage. Lift the cover far enough to give access to the defrost hoses.

  • Page 635: Cleaning

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT 12. Cleaning A. Seats The seat cushions are made from a fire-resistant material. Clean the cushions with a vacuum cleaner. Use a mild soap solution to remove stains. Make sure that the area is well ventilated after cleaning to remove all moisture.
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  • Page 637: Emergency

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT Section 25-60 Emergency 1. General This Section tells you about the optional Emergency Location Transmitter (ELT) Artex ME 406. It also tells you about the Remote Control switch (RCS) for the Artex ME 406. Refer to the manufacturer's Operator’s Manual for more data.
  • Page 638 Equipment/Furnishings DA 40 NG AMM AIRCRAFT B. ELT Batteries The ELT has its own battery pack to supply electrical power. When the ELT is ON and transmitting the batteries will keep the ELT transmitting until battery power is gone on the 121.5 MHz frequency and for up to 24 hours on the 406 MHz frequency.
  • Page 639 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Panel Mounted Switch LED Indicator ARTEX Remote Switch TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM ELT Unit (Front View) Main Switch LED Indicator Antenna Connector Electric Connector Figure 1: ELT Artex ME 406 Doc # 6.02.15...

  • Page 640: Operation

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 3. Operation A. ELT The ELT has a switch with these two positions: OFF/ARM. The ON position is for ground test. When the airplane is in use the switch must be in the ARM position.

  • Page 641: Replace The Elt Batteries

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT Trouble-Shooting 1. General If you find the trouble given in the Trouble column, do the Repair in column 3. Trouble Possible Cause Repair ELT does not operate on test. ELT batteries discharged. Replace the ELT batteries.
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  • Page 643 DA 40 NG AMM Equipment/Furnishings AIRCRAFT Maintenance Practices 1. General This Section tells you how to remove and install the ELT and the RCS. It tells you how to test the ELT in the airplane. It also tells you how replace the batteries in the ELT. This Section also gives you the periodic maintenance necessary to maintain the ELT equipment in a serviceable condition.
  • Page 644 Equipment/Furnishings DA 40 NG AMM AIRCRAFT Figure 2: Artex ME 406 ELT Installation Page 202 Doc # 6.02.15 25-60-00 01 Sep 2017 Rev. 3...
  • Page 645 DA 40 NG AMM Equipment/Furnishings AIRCRAFT B. Install the ELT Detail Steps/Work Items Key Items/References WARNING: IF THE ELT IS MOVED TO A DIFFERENT AIRPLANE THAN WHICH IT WAS ORIGINALLY REGISTERED WITH, THE ELT MUST BE RE-REGISTERED AND THE PRODUCT LABEL RE-MARKED TO INDICATE THE NEW PROGRAMMING AND/OR NEW COUNTRY OF REGISTRY.
  • Page 646 Equipment/Furnishings DA 40 NG AMM AIRCRAFT 3. ELT Functional Test Note: Do this test only during the first 5 minutes of each hour. If you are at a location with a control tower or other monitoring facility, tell them before you do the test.
  • Page 647 DA 40 NG AMM Equipment/Furnishings AIRCRAFT 4. Replace the ELT Batteries You must only use a battery pack that is supplied by the equipment manufacturer. Note: The battery pack contains components that are sensitive to static electricity. You must take electro-static discharge precautions before doing work on the battery pack.

  • Page 648: Remove/Install The Rcs

    Equipment/Furnishings DA 40 NG AMM AIRCRAFT 5. Remove/Install the RCS A. Remove the RCS Detail Steps/Work Items Key Items/References Remove the instrument panel cover. Refer to Section 25-10. Disconnect the electrical cable from the rear of At the in-line connector.

  • Page 649: Elt Periodic Inspection

    DA 40 NG AMM Equipment/Furnishings AIRCRAFT 6. ELT Periodic Inspection The ELT installation must be inspected at least once every 12 months to maintain serviceability. Detail Steps/Work Items Key Items/References Examine the ELT and the ELT mounting tray, look specially for: S Security of the fasteners.
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  • Page 651 Fire Protection DA 40 NG AMM AIRCRAFT CHAPTER 26 FIRE PROTECTION Doc # 6.02.15 Page 1 26-TITLE Rev. 3 01 Sep 2017...
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  • Page 653 Fire Protection DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 26 FIRE PROTECTION - GENERAL General ............1 Description .
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  • Page 655 Note: Equipment which is certified for installation in the DA 40 NG is listed in Section 6.5 of the Airplane Flight Manual. Such equipment may be installed in accordance with the Airplane Maintenance Manual.
  • Page 656 Fire Protection DA 40 NG AMM AIRCRAFT Release Lever Pressure Safety Guard Carry Handle Gauge Seal Wire Container Nozzle Screw Washer Extinguisher Mount Figure 1: Fire Extinguisher Installation Page 2 Doc # 6.02.15 26-00-00 Rev. 3 01 Sep 2017...
  • Page 657 Flight Controls DA 40 NG AMM AIRCRAFT CHAPTER 27 FLIGHT CONTROLS Doc # 6.02.15 Page 1 27-TITLE Rev. 3 01 Sep 2017...
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  • Page 659 Flight Controls DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 27 FLIGHT CONTROLS General ............1 Description .
  • Page 660 Flight Controls DA 40 NG AMM AIRCRAFT Section 27-20 Flight Controls - Rudder General ............1 Description .
  • Page 661 Flight Controls DA 40 NG AMM AIRCRAFT Section 27-38 Flight Controls - Elevator Trim General ............1 Description .
  • Page 662 Flight Controls DA 40 NG AMM AIRCRAFT Section 27-50 Flight Controls - Flaps General ............1 Description .

  • Page 663: Flight Controls

    Flaps attached to the trailing edge of each wing give extra lift for landing and for take-off. The DA 40 NG has a control stick for each pilot. The pilot can set the elevator trim with a control wheel in the center console.
  • Page 664 Flight Controls DA 40 NG AMM AIRCRAFT Fixed Fork-End Fitting Welded into Place Control Rod Threaded End Fitting Welded into Place Safety Test Hole Toothed Washer Jam-Nut Eye-End Fitting with Spherical Bearing Figure 1: Standard Push-Rod Page 2 Doc # 6.02.15...

  • Page 665: Push-Rods

    4. Control Rigging The flight controls of the DA 40 NG have been designed to make correct rigging as easy as possible. All levers and bellcranks have holes for rigging pins. The rigging pins lock the levers in the neutral position.
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  • Page 667: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to do procedures (such as push-rod adjustment) which apply to all of the control systems. 2. Push-Rod Adjustment WARNING: IF YOU DO AN ADJUSTMENT OF A PUSH-ROD, YOU MUST MAKE SURE THAT THE PUSH-ROD IS STILL IN SAFETY.

  • Page 668: Remove/Install Bellcranks And Levers

    3. Remove/Install Bellcranks and Levers The DA 40 NG has standard attachments for bellcranks and levers in the flight control systems. Refer to the tables at the end of each Section for access data. Refer to the Figures in the related Section for the correct orientation.

  • Page 669: Flight Controls - Ailerons And Tabs

    Flight Controls - Ailerons and Tabs 1. General The DA 40 NG has two control sticks that operate the ailerons. The aileron control system uses push-rods and bellcranks. Figure 1 shows the aileron controls in the fuselage. Figure 2 shows the aileron controls in the wing.
  • Page 670 Flight Controls DA 40 NG AMM AIRCRAFT Flap Torsion Tube Push Rod to Right Wing Balance Springs Push Rod to Left Wing Rigging Pin Hole Rear Bellcrank Push Rod from Idler Lever Rear Bulkhead Front Bulkhead Control Bulkhead Left Stick...

  • Page 671: Description

    AIRCRAFT 2. Description The DA 40 NG has a control stick for each pilot for the aileron and elevator controls. Aileron push-rods connect to the bottom of the control sticks. The push-rods connect to the aileron front bellcrank at the control bulkhead.
  • Page 672 Flight Controls DA 40 NG AMM AIRCRAFT Push Rod to Right Wing Rigging Pin Hole Push Rod to Wing Root Rib Left Wing Aileron Bellcrank 2 Guide Rollers Guide Rollers Flap Control Rib Guide Rollers Support Bracket Aileron Rigging Pin Hole...
  • Page 673 Flight Controls DA 40 NG AMM AIRCRAFT 3. Operation If you move the control sticks to the left: The push-rods connected to the stick move to the right. The front bellcrank moves the push-rod below the center console to the rear.
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  • Page 675: Trouble-Shooting

    Flight Controls DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have in the aileron control system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair in the Repair column.
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  • Page 677: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to do tests on the aileron control system. They also tell you how to adjust the aileron control system. Refer to Paragraphs 4 and 5 for removal, installation and access data on the push-rods and bellcranks.

  • Page 678: Aileron Control System Test For Correct Range Of Movement

    Flight Controls DA 40 NG AMM AIRCRAFT 2. Aileron Control System Test for Correct Range of Movement A. Equipment Item Quantity Part Number Control stick rigging pins. Ruler. Commercial. B. Aileron Control Test Procedure Note: Use a ruler to make all measurements at the aileron control surfaces. Make the measurement between the top surface of the aileron, and the top surface of the wing tip.
  • Page 679 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References WARNING: WHEN YOU DO WORK ON THE AIRPLANE CONTROLS, YOU MUST MAKE SURE THE AREAS AROUND THE CONTROLS/CONTROL SURFACES ARE CLEAR OF PERSONS/EQUIPMENT. IF YOU DO NOT DO THIS, INJURY TO PERSONNEL AND DAMAGE TO CONTROL SURFACES CAN OCCUR.

  • Page 680: Aileron Control System Adjustments

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Aileron Control System Adjustments If you cannot get the correct range of movement of the aileron control system, use this procedure to adjust the system. Gust travel refers to the amount of travel remaining at the control surface with the control stick held against the cockpit stop.
  • Page 681 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Note: Keep the aileron rigging pins in position until you have completed the adjustments. You can do the procedure with 3 rigging pins. Lock each lever or bellcrank in sequence.
  • Page 682 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References If necessary, adjust the aileron stop bolts in the Refer to Figure 1. torque tube assembly: S Release the jam-nut on the stop bolt. S Adjust the stop bolt to give the correct range The aileron positions must be the of movement.

  • Page 683: Aileron Push-Rod Access

    Flight Controls DA 40 NG AMM AIRCRAFT 4. Aileron Push-Rod Access Aileron Push-Rod Remove/Install Access References Between the control stick and the Pilots’ seats. Refer to Section 25-10. bellcrank at the control bulkhead. Between the bellcrank at the control Pilots’ seats.
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  • Page 685: Flight Controls - Rudder

    Flight Controls - Rudder 1. General The DA 40 NG has the usual rudder control system. Each pilot has a rudder pedal assembly. The pilot can adjust the pedal position. Control cables connect the pedal assembly to the rudder. A fixed trim tab gives a small amount of adjustment to the rudder trim.
  • Page 686 Flight Controls DA 40 NG AMM AIRCRAFT Rudder Lower Mounting-Bracket Rudder Pedestal Turnbuckles Teflon Tubes which Guide Cockpit Cables Pulley Fuselage Cables with Guide Tubes Yoke Control Bulkhead Co-Pilot's Rudder Pedal Assembly Outboard Control Cable Inboard Control Cable Figure 1: Rudder Control System Page 2 Doc # 6.02.15...

  • Page 687: Description

    2. Description The DA 40 NG has a set of rudder control pedals for each pilot. The pedal assembly can be adjusted. Figures 1, 4, and 5 show you the rudder control system. Figure 2 shows you the rudder pedal assembly with manual pedal adjustment.

  • Page 688: Operation

    Flight Controls DA 40 NG AMM AIRCRAFT Two cable assemblies ('fuselage cables') attach to the rear of the yoke. Each cable assembly has a short front cable and a long rear cable. All cables go through Teflon tubes. A turnbuckle connects the front and rear cables.
  • Page 689 Flight Controls DA 40 NG AMM AIRCRAFT A. Manual Adjustment You can adjust the position of the rudder pedals. When you pull on the adjuster handle, the latch disengages from the bottom sledge tube. If you pull further, the pedal assembly moves along the sledge tubes towards you.
  • Page 690 Flight Controls DA 40 NG AMM AIRCRAFT Right Rudder Pedal Brake Pedals 'S' Tube for Adjuster Handle Control Cables Brake Reservoir (Co-Pilot only) Brake Master Cylinder Aft Attachment to Floor Panel Tension Springs Left Rudder Pedal Adjuster Return Springs 'S' Tube for...
  • Page 691 Flight Controls DA 40 NG AMM AIRCRAFT Right Rudder Pedal Brake Pedals 'S' Tube for Control Cables Transmission Mechanism Brake Reservoir (Co-Pilot only) Brake Master Cylinder Left Rudder Pedal Aft Attachment to Floor Panel 'S' Tube for Control Cables Front Attachment...
  • Page 692 Flight Controls DA 40 NG AMM AIRCRAFT Bush Left Inboard Cable Spacer Rigging Alternative Version Pin Hole Control Bulkhead Mounting Bracket Fuselage Cables Right Inboard Cable Control Yoke Bulkhead Bush Right Outboard Cable Left Inboard Cable Spacer Pulley Oetiker Clamp...

  • Page 693: Trouble-Shooting

    Flight Controls DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have in the rudder control system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair in the Repair column.
  • Page 694 Flight Controls DA 40 NG AMM AIRCRAFT Rudder Lower Mounting Bracket Rudder Pedestal Spacer Fuselage Cables Bush with Guide Tubes Rudder Stop Bolt Turnbuckles Locking Clamps Fuselage Cables Bush with Guide Tubes Teflon Tube Plastic Spacer Washer Frame Oetiker Clamp...

  • Page 695: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to do test procedures on the rudder control system. They also tell you how to adjust the rudder control system. Refer to Section 55-40 to remove/install the rudder.
  • Page 696 Flight Controls DA 40 NG AMM AIRCRAFT B. Rudder Control Test Procedure Refer to Figure 1. Detail Steps/Work Items Key Items/References Make a copy of the Control Surfaces Adjustment Refer to Section 06-00. Report. Use it to record the measurements.

  • Page 697: Rudder Control System Adjustments

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Rudder Control System Adjustments If you cannot get the correct range of movement of the rudder control system, use this procedure to adjust the system. A. Equipment Item Quantity Part Number Cable tension gauge.
  • Page 698 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Set the rudder pedals to fully left. The rudder must hit the stops at the rudder pedestal. The rudder position must be the distance to the left shown in the Control Surfaces Adjustment Report.

  • Page 699: Remove/Install Rudder Control Cables

    Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (11) Install these items: Refer to Section 25-10. S The pilots’ seats. S The passenger seat. 4. Remove/Install Rudder Control Cables A. Equipment Item Quantity Part Number Cable tension gauge.
  • Page 700 Flight Controls DA 40 NG AMM AIRCRAFT C. Install the Rudder Control Cables (from the Firewall to the Yoke) Detail Steps/Work Items Key Items/References WARNING: ONLY TRAINED AND AUTHORIZED PERSONS SHOULD INSTALL CABLE EYE-ENDS. IF THE EYE-ENDS ARE NOT INSTALLED CORRECTLY, THE RUDDER CONTROLS CAN FAIL.
  • Page 701 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Install the cable to the yoke: S Install the bolt, bush and spacer that attach the cable to the yoke. S Install a washer and self-locking nut. Torque to 6.4 Nm (4.7 lbf.ft.). Use a new self-locking nut.
  • Page 702 Flight Controls DA 40 NG AMM AIRCRAFT D. Remove the Fuselage Rudder Control Cables (from the Yoke to the Rudder) Detail Steps/Work Items Key Items/References Remove these items for access: Refer to Section 25-10. S The pilots’ seats. S The passenger seat.
  • Page 703 Flight Controls DA 40 NG AMM AIRCRAFT E. Install the Fuselage Rudder Control Cables (from the Yoke to the Rudder) Detail Steps/Work Items Key Items/References WARNING: ONLY TRAINED AND AUTHORIZED PERSONS SHOULD INSTALL CABLE EYE-ENDS. IF THE EYE-ENDS ARE NOT INSTALLED CORRECTLY, THE RUDDER CONTROLS CAN FAIL.
  • Page 704 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Install a new eye-end to the rear cable before you Use cables to specification LN9374 or install it in the airplane: ISO 2020 or MIL-DTL-83420. S Inspect the cable eye-end for correct Use Locoloc thimbles and Nico-Press assembly.

  • Page 705: Rudder Control Cable And Yoke Access

    Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (10) Do a test for the correct range of rudder Refer to Paragraph 2. movement. (11) Do an inspection of all the controls that you have adjusted. S If necessary for your Airworthiness Authority, do a second inspection of the controls.
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  • Page 707: Flight Controls - Elevator

    Section 27-30 Flight Controls - Elevator 1. General The DA 40 NG has the usual elevator control system. An elevator attached to the horizontal stabilizer gives longitudinal control. The two control sticks operate the elevator. 2. Description Figure 1 shows the elevator controls in the cockpit. Figure 2 shows the elevator controls in the rear fuselage.
  • Page 708 Flight Controls DA 40 NG AMM AIRCRAFT Front Main Bulkhead Left Stick Idler Lever Rigging Pin Hole Push Rod to Idler Lever Rigging Pin Hole Elevator Lever Torque Tube Assy Control Stick Mounting Block Figure 1: Elevator Control Installation in the Cockpit Page 2 Doc # 6.02.15...

  • Page 709: Operation

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Operation If you move the control stick forward: The torque tube assembly turns. The lever below the torque tube assembly pushes the short push-rod aft. The short push-rod pushes the long push-rod aft.
  • Page 710 Flight Controls DA 40 NG AMM AIRCRAFT Additional Elevator Mass (optional) Balance Weight Elevator Lever Rib Elevator Actuating Lever Large Washer Collar Bush Distance Bush Elevator Push Rod Elevator Bellcrank Rigging Pin Hole Ring Frame 2 Ring Frame 1 Rigging...

  • Page 711: Trouble-Shooting

    Flight Controls DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have in the elevator control system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair in the Repair column.
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  • Page 713: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to do test procedures on the elevator control system. And they tell you how to adjust the elevator control system. Refer to Section 55-20 to remove/install the elevator.
  • Page 714 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Install the rigging pin through the stick mounting Refer to Figure 1. block and the torque tube. Note: Use a ruler or deflection gauge to make all measurements at the elevator control surface.

  • Page 715: Elevator Control System Adjustments

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Elevator Control System Adjustments If you cannot get the correct range of movement of the elevator control system, use this procedure to adjust the system. Gust travel refers to the amount of travel remaining at the control surface with the control stick held against the cockpit stop.
  • Page 716 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References If the elevator does not align with the horizontal Refer to Section 27-00 for the push-rod stabilizer, adjust the vertical push-rod at the rear adjustment procedure. bellcrank. Remove rigging pins from the following: S The stick mounting block.

  • Page 717: Elevator Push-Rod Access

    Flight Controls DA 40 NG AMM AIRCRAFT 4. Elevator Push-Rod Access Elevator Push-Rod Remove/Install Access References Between the control torque tube and Pilots’ seats. Refer to Section 25-10. the idler lever at the front main bulkhead. Between the idler lever at the front Pilots’...
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  • Page 719: Flight Controls - Elevator Trim

    Flight Controls - Elevator Trim 1. General The DA 40 NG has an elevator with a trim tab. The trim tab is mechanically operated. This lets you trim the airplane for different speeds and center-of-gravity positions. A handwheel on the center console controls the elevator trim. An indicator tells the pilot the trim setting.
  • Page 720 Flight Controls DA 40 NG AMM AIRCRAFT Handwheel Right Cover Plate Left Cover Plate Flexible Cable Frame Assembly TRIM HANDWHEEL ASSEMBLY Right Frame Lock Nut Lock Nut Friction Damper Nut Plain Washer Spring Washers Lock Washer Trim Gear Assembly Spring Washers...
  • Page 721 Flight Controls DA 40 NG AMM AIRCRAFT B. Flexible Cable A long flexible cable connects the trim handwheel assembly to the trim tab. The cable goes through holes in the front and rear main bulkheads, the baggage frame and each of the ring frames. It goes up the front face of the front web of the vertical stabilizer and through a slot near the top.
  • Page 722 Flight Controls DA 40 NG AMM AIRCRAFT TrimTab Right Actuating lever Left Actuating lever Friction Damper Friction Clamp Block Flexible Operating Cable Inner Trim Actuator Mounting Bracket Elevator Stop Flexible Operating Cable Outer Figure 2: Trim Tab Actuator Assembly Page 4 Doc # 6.02.15...

  • Page 723: Operation

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Operation When you move the top of the trim handwheel forward, these things happen: The small gear wheel moves the top of the gear segment forward. The gear segment pulls the inner core of the flexible cable forward.
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  • Page 725: Trouble-Shooting

    Flight Controls DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have in the elevator trim control system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair in the Repair column.
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  • Page 727: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to test the elevator trim control system. They also tell you how to adjust the system. Refer to Section 55-20 for data on how to remove and install the elevator and trim tab.

  • Page 728: Elevator Trim Control System Adjustments

    Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Set the trim handwheel to fully NOSE DOWN. Measure the angle of the top surface of the trim Record the angle of the top surface of tab. the trim tab.
  • Page 729 Flight Controls DA 40 NG AMM AIRCRAFT B. Elevator Trim Control Adjustment Procedure Detail Steps/Work Items Key Items/References Remove these items for access: Refer to Section 25-10. S The pilots’ seats. S The center console cover. Put a trestle under the rear fuselage.
  • Page 730 Flight Controls DA 40 NG AMM AIRCRAFT C. Elevator Trim Friction Damper Adjustment Procedure Detail Steps/Work Items Key Items/References Remove the horizontal stabilizer fairing. Refer to Section 55-10. Disconnect the right actuator lever from the friction rod: S Release the spring locking clip from the ball-stud.
  • Page 731 Flight Controls DA 40 NG AMM AIRCRAFT D. Elevator Trim Handwheel Friction Damper Adjustment Procedure Detail Steps/Work Items Key Items/References Remove these items for access: Refer to Section 25-10. S The pilots’ seats. S The center console cover. Loosen the self-locking nut on the handwheel On the right of the mounting frame.
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  • Page 733: Stall Warning System

    Section 27-39 Stall Warning System 1. General The DA 40 NG has a simple mechanical stall warning system. 2. Description and Operation Figure 1 shows the stall warning assy without capillary. Figure 2 shows the stall warning assy with capillary.
  • Page 734 Flight Controls DA 40 NG AMM AIRCRAFT Figure 1: Stall Warning System (Without Capillary) Page 2 Doc # 6.02.15 27-39-00 01 Sep 2017 Rev. 3...
  • Page 735 Flight Controls DA 40 NG AMM AIRCRAFT Figure 2: Stall Warning System (With Capillary) Doc # 6.02.15 Page 3 27-39-00 Rev. 3 01 Sep 2017...
  • Page 736 Flight Controls DA 40 NG AMM AIRCRAFT Figure 3: Stall Warning System (With Capillary and Ball Valve) Page 4 Doc # 6.02.15 27-39-00 01 Sep 2017 Rev. 3...

  • Page 737: Trouble-Shooting

    Flight Controls DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the stall warning system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 739: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove/install the stall warning horn. They also tell you how to drain water from the stall warning system. 2. Remove/Install the Stall Warning Horn (System without Capillary) A.
  • Page 740 Flight Controls DA 40 NG AMM AIRCRAFT B. Install the Stall Warning Horn Assy Detail Steps/Work Items Key Items/References Perform a stall warning horn classification check. Refer to Paragraph 4. Make sure to install a stall warning horn with the same classification.

  • Page 741: Remove/Install A Stall Warning Horn Assy

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Remove/Install a Stall Warning Horn Assy (System with Capillary) A. Remove the Stall Warning Horn Assy Detail Steps/Work Items Key Items/References Remove the instrument panel cover. Refer to Section 25-10. Disconnect the hose from the stall warning horn...
  • Page 742 S Install the cable tie which connects the hose to the stall warning horn assy. Install the instrument panel cover. Refer to Section 25-10. Do a flight check of the stall warning system. Refer to the DA 40 NG Airplane Flight Manual. Page 204 Doc # 6.02.15 27-39-00 01 Sep 2017 Rev.

  • Page 743: Ball Valve)

    Flight Controls DA 40 NG AMM AIRCRAFT 4. Remove/Install a Stall Warning Horn Assy (System with Capillary and Integrated Ball Valve) A. Remove the Stall Warning Horn Assy Detail Steps/Work Items Key Items/References Remove the instrument panel cover. Refer to Section 25-10.
  • Page 744 S Install the cable tie which connects the hose to the stall warning horn assy. Install the instrument panel cover. Refer to Section 25-10. Do a flight check of the stall warning system. Refer to the DA 40 NG Airplane Flight Manual. Page 206 Doc # 6.02.15 27-39-00 01 Sep 2017 Rev.

  • Page 745: Procedure To Remove Water From The Stall Warning System

    Flight Controls DA 40 NG AMM AIRCRAFT 5. Procedure to Remove Water from the Stall Warning System Detail Steps/Work Items Key Items/References Remove the left hand pilot's seat. Refer to Section 25-10. Carefully pull the stall warning hose from the wing root connector.
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  • Page 747: Flight Controls - Flaps

    Flight Controls - Flaps 1. General The DA 40 NG has flaps for landing and take-off. An electric flap actuator moves the flaps. See Section 57-50 for data about the flap structure. A three-position toggle switch controls the flaps. The switch is in the center section or RH section of the instrument panel.
  • Page 748 Flight Controls DA 40 NG AMM AIRCRAFT Rear Closing Rib Torsion Tube Insert Guide Transfer Lever Transfer Pins Push Rod to Right Wing Flap Bushes Torsion Tube Flap Actuator Rear Closing Rib Flap Idler Lever Push Rod to Right Wing...

  • Page 749: Description

    Flight Controls DA 40 NG AMM AIRCRAFT 2. Description Figure 1 shows the flap control system in the fuselage. Figure 2 shows the flap push-rods and bellcranks in the wing. Figure 3 shows the flap actuator installation. A. Flap Actuator An electric actuator operates the flaps.
  • Page 750 Flight Controls DA 40 NG AMM AIRCRAFT Rigging Pin Hole Right Flap Rib Right Flap Right Wing Root Rib Guide Rollers Push Rod from Fuselage Flap Idler Lever in the Fuselage Push Rod from Fuselage Guide Rollers Left Wing Root Rib...
  • Page 751 Flight Controls DA 40 NG AMM AIRCRAFT D. Flap Electrical Control Figure 4 shows the flap electrical control system. The main bus or, if installed, the essential bus supplies power for the flaps. A circuit-breaker protects the circuit (10 A). See Chapter 92 for the wiring diagram.
  • Page 752 Flight Controls DA 40 NG AMM AIRCRAFT Actuator Control Rod Worm-Drive Clamps Circuit Board Actuator Motor Cam Adjusting Nuts Actuator Idler Lever Swivel Block Micro-Switches Micro-Switch Base Plate Bush Base Plate Micro-Switch Mounting Bracket Rear Closing Rib TYPICAL ATTACHMENT OF MICRO-SWITCH...

  • Page 753: Operation

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Operation If you operate the flap selector switch these things happen: The switch energizes the related logic circuit. The logic circuit switches on the related transistors to supply power/ground to the flap motor.
  • Page 754 Flight Controls DA 40 NG AMM AIRCRAFT Flap Selector Switch Flap Position Indicator UP LED Flaps T/O LED LDG LED FLAP CONTROL UNIT IN THE INSTRUMENT PANEL (View Looking Forward) UP Position Open Closed Micro-Switch UP POSITION UP Indication and...

  • Page 755: Trouble-Shooting

    Flight Controls DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have in the flap control system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair in the Repair column.
  • Page 756 Flight Controls DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair Flap circuit-breaker opens Short to ground in the wires to the Do an insulation test between when the flaps have electrical control unit from each wire and ground. Repair moved only a short micro-switch 1.
  • Page 757 Flight Controls DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair No LDG indication when Micro-switch 5 defective. Replace the micro-switch. the flaps are in the LDG Open circuit in the micro-switch 5 Do a continuity test of the position. Flaps will not wiring.
  • Page 758 Flight Controls DA 40 NG AMM AIRCRAFT Trouble Possible Cause Repair T/O LED stays on when Micro-switch 3 defective. Replace the micro-switch. the flaps are not in the T/O position. The other indications operate correctly. Flaps move to LDG when Micro-switch 2 defective.

  • Page 759: Maintenance Practices

    Flight Controls DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove and install the components of the flap control system. They also tell you how to test and adjust the system. See Section 57-50 for data about removing and installing the flaps.
  • Page 760 Flight Controls DA 40 NG AMM AIRCRAFT 2. Remove/Install the Flap Actuator Refer to Figures 1 and 3. A. Remove the Flap Actuator Detail Steps/Work Items Key Items/References If possible, set the flaps to the T/O position. Disconnect the airplane main battery.
  • Page 761 Flight Controls DA 40 NG AMM AIRCRAFT B. Install the Flap Actuator Detail Steps/Work Items Key Items/References Put the flap actuator in position in the fuselage. Install the bolt which attaches the actuator body to At the left rear closing rib.

  • Page 762: Test The Flap Control System

    Flight Controls DA 40 NG AMM AIRCRAFT 3. Test the Flap Control System A. Equipment Item Quantity Part Number Inclinometer. Commercial. Spring balance. Commercial. B. Test the Flap Control System Procedure Detail Steps/Work Items Key Items/References Make a copy of the Control Surfaces Adjustment Refer to Section 06-00.
  • Page 763 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Do steps 3 and 4 for the right flap. Zero the inclinometer to the left flap: S Put the inclinometer on the left flap close to the flap horn.

  • Page 764: Adjust The Flap Control System

    Flight Controls DA 40 NG AMM AIRCRAFT 4. Adjust the Flap Control System If you cannot get the correct range of movement of the flap control system, use this procedure to adjust the system. A. Equipment Item Quantity Part Number Rigging pins.
  • Page 765 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (10) Make sure that both flaps hit the up stops at the Refer to Section 27-00. same time. If necessary, adjust the rod between the bellcrank in the wing and the flap.
  • Page 766 Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (15) Connect the flap actuator: S Hold the flaps hard against the up-stops. S If necessary, adjust the eye-end to align with the idler lever: S Loosen the jam-nut.

  • Page 767: Flap Push-Rod Access

    Flight Controls DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (21) Install these items: S The passenger seat. Refer to Section 25-10. S The flap bellcrank access panels. Refer to Section 53-40. 5. Flap Push-Rod Access Flap Push-Rod...
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  • Page 769 Fuel System DA 40 NG AMM AIRCRAFT CHAPTER 28 FUEL SYSTEM Doc # 6.02.15 Page 1 28-TITLE Rev. 3 01 Sep 2017...
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  • Page 771 Fuel System DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 28 FUEL SYSTEM General ............1 Description .
  • Page 772 DA 40 NG AMM Fuel System AIRCRAFT Section 28-20 Fuel Distribution System General ............1 Description .
  • Page 773 Fuel System DA 40 NG AMM AIRCRAFT Trouble-Shooting General ............101 Maintenance Practices General .
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  • Page 775 For more data on the engine fuel system refer to the AE Operation Manual, latest revision. The DA 40 NG has a fuel tank in each wing. Two different tank versions are provided. The total usable fuel capacity of the fuel system is 28 US gal (106 liter) in case of the standard tank and 39 US gal (148 liter) in case of the long range tank.
  • Page 776 DA 40 NG AMM Fuel System AIRCRAFT Figure 1: Fuel System Schematic Drawing (Standard Tank Configuration) Page 2 Doc # 6.02.15 28-00-00 01 Sep 2017 Rev. 3...

  • Page 777: Fuel System

    Fuel System DA 40 NG AMM AIRCRAFT Figure 2: Fuel System Schematic Drawing (Long Range Tank Configuration) Doc # 6.02.15 Page 3 28-00-00 Rev. 3 01 Sep 2017...

  • Page 778: Description

    2. Description A. Standard Tank Configuration Figure 1 shows the fuel system schematic of the DA 40 NG (standard tank configuration). A tank located inboard in each wing holds the fuel. Each tank has a fuel filler assembly and a vent connection at the outboard end.
  • Page 779 B. Long Range Tank Configuration (if OÄM 40-130 is installed) Figure 2 shows the fuel system schematic of the DA 40 NG (long range tank configuration). The airplane has two fuel tanks. Each tank is made of two fuel chambers: the inboard fuel chamber and the outboard fuel chamber.

  • Page 780: Operation

    DA 40 NG AMM Fuel System AIRCRAFT 3. Operation A. Normal Operation Fuel flows through the finger filter of the left tank to the fuel valve. From the valve it flows through the gascolator. The gascolator functions also as a water separator. From there the fuel flows to the electrically driven fuel pumps and fuel filter to the engine.
  • Page 781 Fuel System DA 40 NG AMM AIRCRAFT D. Shut-Off Valve Function During the usual operation, the shut-off function of the fuel valve is used only to isolate the fuel system when the engine is not operating. In an emergency, the shut-off valve function is used to stop all fuel flow to the engine.
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  • Page 783: Fuel Storage System

    AIRCRAFT Section 28-10 Fuel Storage System 1. General A. Standard Tank Configuration This Section describes the following components of the fuel storage system for the DA 40 NG airplane: Fuel tanks. Fuel filler assembly. Fuel tank vents. Refer to Section 28-00 for a general description of the fuel system and a schematic of the fuel system.
  • Page 784 DA 40 NG AMM Fuel System AIRCRAFT Figure 1: Left Hand Standard Fuel Tank Installation Page 2 Doc # 6.02.15 28-10-00 01 Sep 2017 Rev. 3...
  • Page 785 Fuel System DA 40 NG AMM AIRCRAFT Inboard Mounting Rubber (Chafing Protection) Left Fuel Tank Outboard Mounting Rubber Worm-Drive Clamps Cable Conduit for Flexible Coupling High Fuel Sensor Worm-Drive Clamps Fuel Filler Cap Adapter for High Fuel Sensor Mounting Rubber...

  • Page 786: Fuel Tank Description

    DA 40 NG AMM Fuel System AIRCRAFT 2. Fuel Tank Description A. Standard Tank Description The airplane has two fuel tanks. Each tank has a usable capacity of 14 US gal (53 liter). The tanks are located in the inner part of each wing. Figure 1 shows the left fuel tank assembly. Figure 3 shows the right fuel tank assembly.
  • Page 787 Fuel System DA 40 NG AMM AIRCRAFT B. Long Range Tank Description (if OÄM 40-130 is installed) The airplane has two long range fuel tanks. Each tank has a usable capacity of 19.5 US gal (74 liter). Each wing tank consists of two tank chambers. Figure 2 shows the left long range tank assembly and Figure 4 shows the right long range tank assembly.
  • Page 788 DA 40 NG AMM Fuel System AIRCRAFT Vent Hose with Restrictor Fuel Filler Cap Vent Hoses Bonding Connection Worm-Drive Clamps Flexible Coupling Bonding Connection Worm-Drive Clamps Check Valve (Bleed Type) Bonding Connection Outboard Mounting Rubber (Chafing Protection) Fuel Filler Assembly...
  • Page 789 Fuel System DA 40 NG AMM AIRCRAFT Fuel Filler Cap Vent Hose with Restrictor Mounting Rubber Check Valve Worm-Drive Clamps (Bleed Type) Flexible Coupling Worm-Drive Clamps Right Outboard Chamber Outboard Mounting Rubber (Chafing Protection) Bonding Connection Right Fuel Tank Vent Hoses...

  • Page 790: Fuel Filler Assembly

    DA 40 NG AMM Fuel System AIRCRAFT 3. Fuel Filler Assembly Figures 1 and 3 also show the fuel filler assembly. It is a welded tubular aluminum component, approximately 75 mm (3 in) in diameter. The outboard end has a flange that attaches to the top skin of the wing.

  • Page 791: Trouble-Shooting

    Fuel System DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the possible defects of the fuel storage system. When experiencing trouble detailed in the Trouble column read across to the Possible Cause column, then perform the repair given in the Repair column.
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  • Page 793: Maintenance Practices

    Fuel System DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices describe how to remove/install the fuel tanks. Obey the safety precautions for fuel at all times. WARNING: DO NOT GET FUEL ON YOU. FUEL CAN CAUSE SKIN DISEASE.
  • Page 794 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Disconnect the following electrical connectors: At the inboard end of the tank. S Fuel quantity probe. S Low fuel sensor. S High fuel sensor (left wing only). S Fuel temperature sensor.
  • Page 795 Fuel System DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (10) Gently pull the tank and fuel filler assembly out of Make sure that the tank does not catch the wing through the wing inboard rib. Move the on the wing ribs.

  • Page 796: Assemble/Install The Fuel Tank Assembly

    DA 40 NG AMM Fuel System AIRCRAFT 3. Assemble/Install the Fuel Tank Assembly A. Preparation Detail Steps/Work Items Key Items/References Examine the fuel tank. Look specially for: S Damage to the aluminum skins and welded Use a strong light and a magnifying seams of the tank.
  • Page 797 Fuel System DA 40 NG AMM AIRCRAFT B. Assemble the Tank Detail Steps/Work Items Key Items/References Install the flexible coupling: Refer to Figure 3. S Push the flexible coupling onto the connector Make sure that the coupling is correctly of the fuel filler assembly.
  • Page 798 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Install the connecting link which attaches the tank to the fuel filler assembly: S Move the link into position on the connecting brackets. S Install the two bolts through the link and the connecting brackets.
  • Page 799 Fuel System DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Connect two the vent hoses to the adapters on Near the outboard end of the fuel filler the access panel: assembly. S Push the vent hoses onto the adapters on the access panel.
  • Page 800 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Install the access panel at the wing root rib: S Put the access panel into position on the studs. S If access panel is made from aluminum install Install on 3 bolt from bottom aft corner.
  • Page 801 Fuel System DA 40 NG AMM AIRCRAFT 4. Remove/Disassemble the Long Range Tank Assembly (if OÄM 40-130 is installed) A. Remove the Fuel Tank Assembly Detail Steps/Work Items Key Items/References Remove the wing which has the fuel tank that you Refer to Section 57-10.
  • Page 802 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Disconnect the two vent hoses from the adapters Near the outboard end of the outboard on the access panel: fuel tank chamber. S Remove the access panel from the outer Refer to Section 52-40.
  • Page 803 Fuel System DA 40 NG AMM AIRCRAFT B. Disassemble the Fuel Tank Assembly Detail Steps/Work Items Key Items/References Remove the fuel tank assembly from the wing. Refer to Paragraph 2A. Remove the connecting link that attaches the Refer to Figures 2 and 4.
  • Page 804 DA 40 NG AMM Fuel System AIRCRAFT 5. Assemble/Install the Long Range Tank Assembly (if OÄM 40-130 is installed) A. Preparation Detail Steps/Work Items Key Items/References Examine the fuel tank. Look specially for: S Damage to the skins and welded seams of the Use a strong light and a magnifying tank.
  • Page 805 Fuel System DA 40 NG AMM AIRCRAFT B. Assemble the Tank Detail Steps/Work Items Key Items/References Install the flexible coupling: Refer to Figures 2 and 4. S Push the flexible coupling onto the connector Make sure that the coupling is correctly of the outboard fuel tank chamber.
  • Page 806 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Install the connecting link which attaches the inboard fuel tank chamber to the outboard tank chamber: S Move the link into position on the connecting brackets. S Install the two bolts through the link and the connecting brackets.
  • Page 807 Fuel System DA 40 NG AMM AIRCRAFT C. Install the Tank Assembly Detail Steps/Work Items Key Items/References Move the tank assembly into position in the wing. Make sure that the tank assembly is correctly located. Install the fuel tank: S Make sure that the fuel filler flange in the...
  • Page 808 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Attach the bonding strip to the inboard end of the inboard fuel tank chamber: S Put the bolt up through the bonding tag on the inboard fuel tank chamber.
  • Page 809 Fuel System DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (11) Refuel the airplane. Refer to Section 12-10. Look specially for fuel leaks from the tanks assembly which you have installed. (12) Do an engine ground test. Refer to Section 71-00.
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  • Page 811: Fuel Distribution System

    Fuel Distribution System 1. General This Section describes the fuel distribution system of the DA 40 NG airplane. The fuel distribution system supplies fuel from the fuel tanks to the engine. The following components are part of the fuel distribution system: Flexible fuel hoses.
  • Page 812 DA 40 NG AMM Fuel System AIRCRAFT Fuel Return Line From Aux Tank (RH) Fuel Return Line From Engine Check Valve Fuel Transfer Line From Aux Tank (RH) T-Fitting Fuel Transfer Line to Transfer Pump and Fuel Selector then to Main Tank...

  • Page 813: Description

    AIRCRAFT 2. Description Figure 1 shows the main components of the fuel distribution system for the DA 40 NG. A flexible fuel hose connects the left wing fuel tank to the fuel valve. The fuel valve is located in the center fuselage, below the cockpit floor.
  • Page 814 DA 40 NG AMM Fuel System AIRCRAFT C. Fuel Gascolator and Filter The gascolator connects to the fuel valve and is equipped with a fuel filter and a fuel drain. The filter can be removed for cleaning/replacement. Use the fuel drain to drain the fuel distribution system and to drain fuel to test for fuel contamination.

  • Page 815: Fuel Transfer System Operation

    Fuel System DA 40 NG AMM AIRCRAFT 4. Fuel Transfer System Operation In the usual operation, fuel flows from the left tank, through the fuel valve to the engine. Return fuel from the engine passes through the cooling loop in the right tank and then into the left tank.
  • Page 816 DA 40 NG AMM Fuel System AIRCRAFT Pulsation Damper Element Damper Housing Damper Housing O-Rings Note: Recess on this side O-Rings Pulsating Damper Assy Fuel Supply Line Fuel Return Line Fitting Fuel Filter Cap If installed: Spray Shield Worm Drive Clamp...

  • Page 817: Trouble-Shooting

    Fuel System DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the possible defects of the fuel distribution system. When experiencing trouble detailed in the Trouble column read across to the Possible Cause column, then perform the repair given in the Repair column.
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  • Page 819: Maintenance Practices

    Fuel System DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General This Section describes the Maintenance Practices for the fuel distribution system. The procedures are limited to the removal/installation of the main components of the system. Obey the safety precautions for fuel at all times.
  • Page 820 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Remove the fuel valve and the gascolator: S Remove the bolt and washer which attach the gascolator mounting bracket. S Remove the four bolts and washers which Hold the fuel valve! attach the fuel valve to the fuselage.
  • Page 821 Fuel System DA 40 NG AMM AIRCRAFT B. Install the Fuel Valve and the Gascolator Detail Steps/Work Items Key Items/References Remove the left pilot's seat. Refer to Section 25-10. Move the fuel valve and the gascolator into Make sure that the gascolator mounting position in the fuselage.

  • Page 822: Remove/Install The Gascolator Filter

    DA 40 NG AMM Fuel System AIRCRAFT 3. Remove/Install the Gascolator Filter Obey the safety precautions for fuel at all times. A. Remove the Gascolator Filter Detail Steps/Work Items Key Items/References Set the fuel valve to OFF. Remove the access panel under the fuselage Refer to Section 52-40.
  • Page 823 Fuel System DA 40 NG AMM AIRCRAFT B. Install the Gascolator Filter Detail Steps/Work Items Key Items/References Put the filter into position in the gascolator, tighten filter hand tight. Install a new seal in the filter bowl. Install the filter bowl:...

  • Page 824: Remove/Install The Fuel Filter Body

    DA 40 NG AMM Fuel System AIRCRAFT 4. Remove/Install the Fuel Filter Body Obey the safety precautions for fuel at all times. A. Remove the Fuel Filter Body Detail Steps/Work Items Key Items/References Make sure that the related FUEL SELECTOR In the cockpit.
  • Page 825 Fuel System DA 40 NG AMM AIRCRAFT B. Install the Fuel Filter Body Detail Steps/Work Items Key Items/References Install the screw with the seal washer into the Refer to Figure 5. new filter body. Use Loctite 243 on adapter to fuel filter body connection.

  • Page 826: Remove/Replace/Install The Fuel Pressure Pulsation Damper

    DA 40 NG AMM Fuel System AIRCRAFT 5. Remove/Replace/Install the Fuel Pressure Pulsation Damper (if MÄM 40-468 is installed) Obey the safety precautions for fuel at all times. A. Remove the Fuel Pressure Pulsation Damper Assy Detail Steps/Work Items Key Items/References Set the ENGINE MASTER to OFF.
  • Page 827 Fuel System DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Tighten the fuel pressure pulsation damper Torque 80 ± 4 Nm (59.0 ± 2.9 lbf.ft). housing. Secure the fuel pressure pulsation damper housing with locking wire. C. Install the Fuel Pressure Pulsation Damper Housing Assy...

  • Page 828: Remove/Install The Electrically Driven Fuel Pumps With Bypass Valve

    DA 40 NG AMM Fuel System AIRCRAFT 6. Remove/Install the Electrically Driven Fuel Pumps with Bypass Valve Obey the safety precautions for fuel at all times. A. Remove the Electrically Driven Fuel Pumps with Bypass Valve Detail Steps/Work Items Key Items/References Set the ENGINE MASTER to OFF.
  • Page 829 Fuel System DA 40 NG AMM AIRCRAFT B. Install the Electrically Driven Fuel Pumps with Bypass Valve Detail Steps/Work Items Key Items/References Install the fuel pump assembly and tighten the four worm drive clamps. Install and tighten the two nuts which attach the fuel pump banjo to the support bracket.

  • Page 830: Remove/Install The Fuel Transfer Pump

    DA 40 NG AMM Fuel System AIRCRAFT 7. Remove/Install the Fuel Transfer Pump Obey the safety precautions for fuel at all times. A. Remove the Fuel Transfer Pump Detail Steps/Work Items Key Items/References Defuel the airplane. Refer to Section 12-10.

  • Page 831: Disassemble/Assemble The Fuel Transfer Pump Assembly

    Fuel System DA 40 NG AMM AIRCRAFT 8. Disassemble/Assemble the Fuel Transfer Pump Assembly Obey the safety precautions for fuel at all times. A. Disassemble the Fuel Transfer Pump Assembly Detail Steps/Work Items Key Items/References Loosen jam nuts on 90° fittings and remove Note the installation direction of the fittings from ”in”...
  • Page 832 DA 40 NG AMM Fuel System AIRCRAFT Detail Steps/Work Items Key Items/References Remove one of the top bolts from the pump Remove the lock wire. housing. "Top" means related to the installation in the airplane. (10) Grind housing around the hole where the bolt is To get electrical conductivity.

  • Page 833: Remove/Install The Fuel Cooler

    Fuel System DA 40 NG AMM AIRCRAFT 9. Remove/Install the Fuel Cooler Obey the safety precautions for fuel at all times. A. Remove the Fuel Cooler Detail Steps/Work Items Key Items/References Defuel the airplane. Refer to Section 12-10. Remove the RH main landing gear cover.

  • Page 834: Test The Fuel Valve

    DA 40 NG AMM Fuel System AIRCRAFT 10. Test the Fuel Valve CAUTION: YOU MUST REPLACE THE FUEL VALVE IF THE TEST FAILS. Obey the safety precautions for fuel at all times. Detail Steps/Work Items Key Items/References Remove the cowling.

  • Page 835: Test The Check Valve In The Fuel Return Line

    Fuel System DA 40 NG AMM AIRCRAFT 11. Test the Check Valve in the Fuel Return Line CAUTION: YOU MUST REPLACE THE CHECK VALVE IF THE TEST FAILS. Obey the safety precautions for fuel at all times. Detail Steps/Work Items...
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  • Page 837: Fuel Quantity Indicating

    B. Long Range Tank Configuration (if OÄM 40-130 is installed) In the DA 40 NG long range tank the fuel quantity indication is the same as in the standard tank. The fuel probe is installed in the inboard fuel tank chamber. This fuel probe measures a fuel quantity of maximum 14 US gal (53 liter), which is the maximum quantity of indicated fuel.

  • Page 838: Operation

    DA 40 NG AMM Fuel System AIRCRAFT 3. Operation A. Standard Tank Configuration As the fuel level in the fuel tanks decreases, the area of the fuel probe which is “wetted” with fuel will also decrease. The amount of "wetted" area is converted into an electrical signal which sets the fuel quantity reading at the fuel quantity indicator.
  • Page 839 Fuel System DA 40 NG AMM AIRCRAFT Low Fuel Sensor Left Fuel Tank Fuel Temperature Sensor Fuel Quantity Probe VIEW ON INBOARD END OF LEFT FUEL TANK Figure 1: Fuel Quantity Indication Components in the Left Hand Fuel Tank Doc # 6.02.15...
  • Page 840 DA 40 NG AMM Fuel System AIRCRAFT Temperature Sensor Low Fuel Sensor Right Fuel Tank VIEW ON INBOARD END OF RIGHT FUEL TANK Fuel Quantity Probe Figure 2: Fuel Quantity Indication Components in the Right Hand Fuel Tank Page 4 Doc # 6.02.15...
  • Page 841 Fuel System DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the possible defects of the fuel quantity indicating system. When experiencing trouble detailed in the Trouble column read across to the Possible Cause column, then perform the repair given in the Repair column.
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  • Page 843 Fuel System DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General The Maintenance Practices in this Section describes how to replace a fuel tank probe and a fuel tank sensor. Refer to Section 31-10 for data on removing/installing a fuel quantity indicator.
  • Page 844 DA 40 NG AMM Fuel System AIRCRAFT B. Install a Low Fuel Sensor Detail Steps/Work Items Key Items/References Install the low fuel sensor in the fuel tank: S Apply sealant to the thread of the low fuel Use Loctite 243 or 'seal-lube' or sensor.
  • Page 845 Fuel System DA 40 NG AMM AIRCRAFT 3. Remove/Install the High Fuel Sensor Only the left tank has a high fuel sensor. Obey the safety precautions for fuel at all times. A. Remove the High Fuel Sensor Detail Steps/Work Items Key Items/References Remove the left wing.
  • Page 846 DA 40 NG AMM Fuel System AIRCRAFT 4. Remove/Install a Fuel Quantity Probe Obey the safety precautions for fuel at all times. A. Remove a Fuel Quantity Probe Detail Steps/Work Items Key Items/References Remove the wing where the fuel quantity probe Refer to Section 57-10.
  • Page 847 Fuel System DA 40 NG AMM AIRCRAFT B. Install a Fuel Quantity Probe Detail Steps/Work Items Key Items/References Separate the fuel filler assembly from the fuel Refer to Section 28-10. tank. To gain access to the guide at the outboard end of the fuel tank.
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  • Page 849 Indicating Systems DA 40 NG AMM AIRCRAFT CHAPTER 31 INDICATING SYSTEMS Doc # 6.02.15 Page 1 31-TITLE Rev. 3 01 Sep 2017...
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  • Page 851 Indicating Systems DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 31 INDICATING SYSTEMS General ............1...
  • Page 852 Indicating Systems DA 40 NG AMM AIRCRAFT Section 31-20 Independent Instruments General ............1 Description .
  • Page 853 Indicating Systems DA 40 NG AMM AIRCRAFT Section 31-51 Central Warning System with Conventional Cockpit Installed General ............1 Description and Operation - White Wire Annunciator Panel .
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  • Page 855: Indicating Systems

    This Chapter tells you about the indicating systems installed in the airplane. Refer to these Sections for the related data: Section 31-10. The instrument and control panels for the DA 40 NG with G1000 system installed. Section 31-11. The instrument and control panels for the DA 40 NG with conventional cockpit installed.
  • Page 856 DA 40 NG AMM AIRCRAFT Note: Equipment which is certified for installation in the DA 40 NG is listed in Section 6.5 of the Airplane Flight Manual. Such equipment may be installed in accordance with the Airplane Maintenance Manual. Any equipment which is not listed in Section 6.5 of the Airplane Flight Manual is called "Additional Equipment".

  • Page 857: Instrument And Control Panels With G1000 System Installed

    G1000 System Installed 1. General The DA 40 NG has these instrument and control panels: An instrument panel. The instrument panel is made in several pieces with a shelf. The shelf goes between the panel and the instrument panel frame.
  • Page 858 Indicating Systems DA 40 NG AMM AIRCRAFT 12 17 M anouvering speed: L imitatio ns for G FC 700 Au topi lot Sys te m: =11 1 KIA S (above 1036 up to 1200 kg / above 2284 up to 2646 lb) Do not use AP i f “Alternate S t atic”...

  • Page 859: Instrument Panel Description

    The DA 40 NG has an integrated cockpit system (ICS). The ICS has two large LCD display screens which are located in the instrument panel. These two display screens can digitally display all of the flight, navigation and airplane system data.
  • Page 860 Indicating Systems DA 40 NG AMM AIRCRAFT Top Bracket Rear Bracket Center Bracket Front Bracket Right Side Plate Left Side Plate Figure 2: Engine Control Assembly Structure Page 4 Doc # 6.02.15 31-10-00 01 Sep 2017 Rev. 3...

  • Page 861: Center Console Description

    Indicating Systems DA 40 NG AMM AIRCRAFT 3. Center Console Description The engine control assembly holds the parking brake and heating controls. It also holds the engine power lever. Figure 2 shows the center console structure. Refer to the related Chapters for the data on the controls.
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  • Page 863: Trouble-Shooting

    Indicating Systems DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the control panel in the center console. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 865: Maintenance Practices

    Indicating Systems DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove/install the engine control assembly. See the related Chapter for data about indicators in other systems. 2. Remove/Install the Engine Control Assembly A.
  • Page 866 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install the Engine Control Assembly Detail Steps/Work Items Key Items/References Make sure that there are no loose items, specially in the center console. Move the engine control assembly onto the center console and support it in a position where you can install the control cables.
  • Page 867 Indicating Systems DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References (10) Install the knob on the emergency fuel valve: S Install the mounting plate. S Push the knob onto the fuel valve selector shaft. S Install the cross-head screw which attaches the knob to the shaft.
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  • Page 869: Instrument And Control Panels With Conventional Cockpit Installed

    Conventional Cockpit Installed 1. General The DA 40 NG with the conventional cockpit installed has these instrument and control panels: An instrument panel. The instrument panel is made in one piece with a shelf. The shelf goes between the panel and the firewall.
  • Page 870 Indicating Systems DA 40 NG AMM AIRCRAFT Figure 2: Instrument Panel with Conventional Instrumentation Page 2 Doc # 6.02.15 31-11-00 01 Sep 2017 Rev. 3...
  • Page 871 Indicating Systems DA 40 NG AMM AIRCRAFT Major Instruments and Controls ELECTRIC MASTER key switch ELT control unit FUEL TRANSFER switch Accessory power socket PITOT HEAT switch Airspeed Indicator AVIONICS MASTER switch Attitude Gyro (artificial horizon) ESSENTIAL BUS switch Altimeter...

  • Page 872: Instrument Panel Description

    Indicating Systems DA 40 NG AMM AIRCRAFT 2. Instrument Panel Description A single piece of aluminum alloy makes the instrument panel. The panel has a vertical face with instruments and a horizontal 'shelf' with electrical components. The shelf goes between the firewall and the vertical face of the panel.

  • Page 873: Independent Instruments

    Section 31-20 Independent Instruments 1. General This Section tells you about the digital chronometer which can be installed in the DA 40 NG. Refer to the equipment manufacturers' manuals for more data about the equipment. 2. Description A. Davtron M803 Digital Chronometer Figure 1 shows the Davtron M803 digital chronometer.
  • Page 874 Indicating Systems DA 40 NG AMM AIRCRAFT Figure 1: Davtron M803 Digital Chronometer Page 2 Doc # 6.02.15 31-20-00 01 Sep 2017 Rev. 3...

  • Page 875: Maintenance Practices

    Indicating Systems DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General This Section tells you how to replace the digital chronometer. Refer to the equipment manufacturer's manuals for more data on the digital chronometer. 2. Remove/Install the Digital Chronometer A. Remove the Digital Chronometer...
  • Page 876 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install the Digital Chronometer Detail Steps/Work Items Key Items/References Move the chronometer into its position in the instrument panel. Install the screws which attach the chronometer to the instrument panel. Connect the electrical cable to the rear of the chronometer.

  • Page 877: Central Computers

    PFD and MFD are identically configured to display all of the important flight parameters in the event of display failure. For more detailed data about the ICS refer to the G1000 Cockpit Reference Guide for the DA 40 NG Airplane.
  • Page 878 Indicating Systems DA 40 NG AMM AIRCRAFT Master Configuration Module GMA 1347 Audio Panel Reversionary Reversionary Switch Switch No. 1 No. 2 GDU 10XX ARINC 429 GDU 10XX Primary Multi-Function Flight Display Display ARINC 429 Ethernet Ethernet Ethernet RS-232 Digital COM...

  • Page 879: Description

    Indicating Systems DA 40 NG AMM AIRCRAFT 2. Description Figure 1 shows the schematic diagram for the ICS. The ICS has these main components: A. Primary Flight Display (PFD) Figure 3 shows the PFD. The PFD is a 10.4 in liquid crystal display. Bezels on the left and right side of the PFD have the controls for the ICS.
  • Page 880 Indicating Systems DA 40 NG AMM AIRCRAFT NAV Vol/Sq Garmin Display Unit PU SH NAV Frequency V OL V OL PU SH Transfer EMERG NAV Frequency P USH P USH BARO Selector SD Card Slots Heading Selector P USH P USH...
  • Page 881 Indicating Systems DA 40 NG AMM AIRCRAFT COM knob. This control has a large outer knob and a smaller inner knob. Rotate these knobs to select the COM frequency. Rotate the large outer knob to select the MHz and the inner knob to select the KHz.
  • Page 882 Indicating Systems DA 40 NG AMM AIRCRAFT Nav Frequency Waypoint Status Marker Beacon Com Frequency Window Window Window Annunciation 117.90 112.20 KTYS 136.975 118.000 140% 291% 291% NAV1 PUSH PUSH 108.00 117.95 136.975 118.000 NAV2 EMERG TRAFFIC 6600 PUSH PUSH...
  • Page 883 Indicating Systems DA 40 NG AMM AIRCRAFT The basic flight instruments are: Airspeed Indicator (ASI). The airspeed indicator is on the left side of the display and indicates the airspeed on a rolling number gauge using a moving tape. The airspeed indicator also displays speed ranges for different airplane configurations, airspeed trends and ‘V’...
  • Page 884 Indicating Systems DA 40 NG AMM AIRCRAFT Course Deviation Indicator (CDI). The CDI is a line with an arrowhead that points to the airplane heading on the rotating compass. The line can slide left or right of the center marking to show the deviation of the actual course being flown to the required course.
  • Page 885 Indicating Systems DA 40 NG AMM AIRCRAFT B. Multi-Function Display (MFD) The MFD is a 10.4 in liquid crystal display. Bezels on the left and right side of the MFD have the controls for the ICS. The lower edge of the MFD has ‘softkeys’. The function of the soft keys relates to the on-screen display and if a key has a function related to the current display the display will show the function of the key.
  • Page 886 Indicating Systems DA 40 NG AMM AIRCRAFT Coolant temperature. A pointer above a range bar indicates the coolant temperature. The range bar is color coded, green to show the normal operating range, yellow in the cautionary range and red in the warning range. The pointer moves from left to right to indicate the coolant temperature.
  • Page 887 Indicating Systems DA 40 NG AMM AIRCRAFT Engine gearbox temperature. A pointer above a horizontal range bar shows the gearbox temperature. The range bar is color coded, green in the normal temperature range, yellow in the caution range and then red at the high end of the range. The pointer moves from left to right to show the temperature of the gearbox.
  • Page 888 Indicating Systems DA 40 NG AMM AIRCRAFT Figure 4: MFD Full EIS page Page 12 Doc # 6.02.15 31-40-00 01 Sep 2017 Rev. 3...
  • Page 889 Indicating Systems DA 40 NG AMM AIRCRAFT C. GMA 1347 Audio Control Panel The GMA 1347 audio control panel is located in the airplane instrument panel between the two display screens. The audio control panel integrates the NAV/COM digital audio, intercom system and marker beacon controls.
  • Page 890 Indicating Systems DA 40 NG AMM AIRCRAFT I. GMU 44 Magnetometer The magnetometer senses magnetic field information. Data is sent to the GRS 77/79 ARHS for processing. The magnetometer receives power form the GRS 77/79 and communicates with the GRS 77/79 using RS-485 digital interface. The magnetometer is located in the right outer wing and can accessed through a panel in the lower surface of the wing.

  • Page 891: Trouble-Shooting

    Indicating Systems DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The Garmin ICS has a built-in test and trouble-shooting facility. For more data about troubleshooting the ICS refer to the G1000 System Maintenance Manual. Doc # 6.02.15 Page 101 31-40-00 Rev.
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  • Page 893: Maintenance Practices

    Indicating Systems DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Procedures tell you how to replace the main components of the ICS. They do not tell you how to maintain the components. For data about removing/installing the GMA 1347 audio control unit refer to Section 23-50.
  • Page 894 Indicating Systems DA 40 NG AMM AIRCRAFT The specific DA 40 NG values as to the equipment basic setting are given in the table below: Item Basic Setting Main Lighting - Display. Source ......28 VDC Response Time .
  • Page 895 Indicating Systems DA 40 NG AMM AIRCRAFT Item Basic Setting GMA Configuration S KEYPAD Annunciators Disable COM3: Disable TEL: Disable DME: specific to airplane Disable ADF: specific to airplane Disable AUX: Disable SPEAKER: blank Disable PA: Disable PLAY: blank Disable MUSIC:...

  • Page 896: Remove/Install A Gdu 10Xx Display

    Indicating Systems DA 40 NG AMM AIRCRAFT 2. Remove/Install a GDU 10XX Display A. Remove a GDU 10XX Display Detail Steps/Work Items Key Items/References Make sure that the ELECTRIC MASTER key switch is set to OFF. Set the PFD and MFD circuit-breakers open.
  • Page 897 Indicating Systems DA 40 NG AMM AIRCRAFT In-Line Connector GDU 10XX Display Unit Screw Locking Socket Rivet Figure 5: GDU 10XX Display Unit Installation Doc # 6.02.15 Page 205 31-40-00 Rev. 3 01 Sep 2017...
  • Page 898 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install a GDU 10XX Display Detail Steps/Work Items Key Items/References If necessary, set the PFD and MFD Right side of instrument panel. circuit-breakers open. Install the display unit: S Move the display unit into position at the instrument panel.

  • Page 899: Remove/Install A Gia 63 Integrated Avionics Unit (Iau)

    Indicating Systems DA 40 NG AMM AIRCRAFT 3. Remove/Install a GIA 63 Integrated Avionics Unit (IAU) A. Remove a GIA 63 Integrated Avionics Unit (IAU) Detail Steps/Work Items Key Items/References Make sure that the ELECTRIC MASTER key switch is set to OFF.
  • Page 900 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install a GIA 63 Integrated Avionics Unit (IAU) Detail Steps/Work Items Key Items/References Install the IAU: S Move the GIA IAU into position at the Make sure that the unit is seated mounting and lower the unit into position in correctly.
  • Page 901 Indicating Systems DA 40 NG AMM AIRCRAFT Figure 6: GIA 63 Integrated Avionics Unit (IAU) Installation Doc # 6.02.15 Page 209 31-40-00 Rev. 3 01 Sep 2017...

  • Page 902: Remove/Install The Gtx33/335 R Transponder

    Indicating Systems DA 40 NG AMM AIRCRAFT 4. Remove/Install the GTX33/335 R Transponder A. Remove the GTX33/335 R Transponder Detail Steps/Work Items Key Items/References Make sure that the ELECTRIC MASTER key switch is set to OFF. Remove the lower access panel from the rear Refer to Section 25-50.
  • Page 903 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install the GTX33/335 R Transponder Detail Steps/Work Items Key Items/References Install the GTX33/335 R: S Move the GTX33/335 R into position at the Make sure that the unit is seated mounting and lower the unit into position in correctly.
  • Page 904 Indicating Systems DA 40 NG AMM AIRCRAFT Locking Screw Retainer GTX33 / 335 R Transponder GTX33 / 335 R Mounting Rack Avionics Enclosure Figure 7: GTX33/335 R Transponder Installation Page 212 Doc # 6.02.15 31-40-00 01 Sep 2017 Rev. 3...

  • Page 905: Remove/Install The Grs7X Attitude, Heading And Reference Unit (Ahrs)

    Indicating Systems DA 40 NG AMM AIRCRAFT 5. Remove/Install the GRS7X Attitude, Heading and Reference Unit (AHRS) A. Remove the GRS7X Attitude, Heading and Reference Unit (AHRS) Detail Steps/Work Items Key Items/References Make sure that the ELECTRIC MASTER key switch is set to OFF.
  • Page 906 Indicating Systems DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Do a test for the correct operation of the integrated cockpit system (ICS): S Set the ELECTRIC MASTER key switch to The ICS must power-up and success- fully complete its self-test procedure.
  • Page 907 Indicating Systems DA 40 NG AMM AIRCRAFT GRS77 AHRS Unit Connector Figure 8: GRS77 Attitude, Heading and Reference Unit (AHRS) Installation Doc # 6.02.15 Page 215 31-40-00 Rev. 3 01 Sep 2017...
  • Page 908 Indicating Systems DA 40 NG AMM AIRCRAFT GRS 79 AHRS Unit Connector Mounting Rack Figure 9: GRS79 Attitude, Heading and Reference Unit (AHRS) Installation Page 216 Doc # 6.02.15 31-40-00 01 Sep 2017 Rev. 3...

  • Page 909: Remove/Install The Gdc 7X Air Data Computer (Adc)

    Indicating Systems DA 40 NG AMM AIRCRAFT 6. Remove/Install the GDC 7X Air Data Computer (ADC) A. Remove the GDC 7X Air Data Computer (ADC) Detail Steps/Work Items Key Items/References Disconnect the airplane main battery. Refer to Section 24-31. Remove the instrument panel cover.
  • Page 910 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install the GDC 7X Air Data Computer (ADC) Detail Steps/Work Items Key Items/References Install the GDC 7X: S Move the GDC 7X into position on the mounting rack. S Install the 2 screws that attach the GDC 7X to the mounting rack.

  • Page 911: Remove/Install The Gea 71 Processor

    Indicating Systems DA 40 NG AMM AIRCRAFT 7. Remove/Install the GEA 71 Processor A. Remove the GEA 71 Processor Detail Steps/Work Items Key Items/References Disconnect the airplane main battery. Refer to Section 24-31. Remove the instrument panel cover. Refer to Section 25-10.
  • Page 912 Indicating Systems DA 40 NG AMM AIRCRAFT Garmin GEA 71 Unit Retainer Screw Retainer Mounting Rack Figure 10: GEA 71 Processor Installation Page 220 Doc # 6.02.15 31-40-00 01 Sep 2017 Rev. 3...

  • Page 913: Gmu 44 Magnetometer

    Indicating Systems DA 40 NG AMM AIRCRAFT 8. GMU 44 Magnetometer A. Remove the GMU 44 Magnetometer Detail Steps/Work Items Key Items/References Make sure that the ELECTRIC MASTER key switch is set to OFF. Remove the magnetometer assembly: Refer to Figure 11.
  • Page 914 Indicating Systems DA 40 NG AMM AIRCRAFT B. Install the GMU 44 Magnetometer Detail Steps/Work Items Key Items/References Install the magnetometer assembly: S Move the magnetometer assembly into Pay attention on the dedicated mounting position at the right wing. direction marked by an arrow! S Connect the electrical cables to the At the in-line connector.
  • Page 915 Indicating Systems DA 40 NG AMM AIRCRAFT Figure 11: Magnetometer Assembly Installation Doc # 6.02.15 Page 223 31-40-00 Rev. 3 01 Sep 2017...
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  • Page 917: Central Warning System With Conventional Cockpit Installed

    Conventional Cockpit Installed 1. General The DA 40 NG with the conventional cockpit has warning, caution and status lights combined in one 'White Wire' annunciator panel. Figure 1 shows the annunciator panel. 2. Description and Operation - White Wire Annunciator Panel A.
  • Page 918 Indicating Systems DA 40 NG AMM AIRCRAFT Figure 1: Central Warning System: White Wire Annunciator Panel C. Warning, Caution and Status Lights START. A red warning light shows that the starter solenoid is energized. The warning light receives an electrical current from the starter side of the starter solenoid. The starter warning message shows when the connection between the starter motor and the engine has not been broken.

  • Page 919: Functional Check

    Indicating Systems DA 40 NG AMM AIRCRAFT ALTERNATOR. A red warning light shows alternator failure. The regulator of the alternator operates the ALTERNATOR warning message. ECU A. An amber caution light shows when the ECU A fails. ECU B. An amber caution light shows when the ECU B fails.
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  • Page 921: Trouble-Shooting

    Indicating Systems DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General The table below lists the defects you could have with the central warning system. If you have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do the repair given in the Repair column.
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  • Page 923: Maintenance Practices

    Indicating Systems DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General This Section tells you how to replace the main components of the central warning system. Refer to the equipment manufacturer's manuals for more data on the annunciator panel. Refer to the related Chapter for data on the warning sensors.

  • Page 924: Test The Annunciator Panel

    Indicating Systems DA 40 NG AMM AIRCRAFT 3. Test the Annunciator Panel Detail Steps/Work Items Key Items/References Close front canopy and rear door. Put on a head-set. To hear the aural alert. Set the ELECTRIC MASTER key switch to ON.
  • Page 925 Landing Gear DA 40 NG AMM AIRCRAFT CHAPTER 32 LANDING GEAR Doc # 6.02.15 Page 1 32-TITLE Rev. 3 01 Sep 2017...
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  • Page 927 Landing Gear DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 32 LANDING GEAR General ............1 Description and Operation .
  • Page 928 Landing Gear DA 40 NG AMM AIRCRAFT Maintenance Practices General ............201 Remove/Install the Nose Landing Gear Strut .
  • Page 929 LANDING GEAR 1. General The DA 40 NG has a fixed tricycle landing gear and a castor nose wheel. This Section gives you the general description and operation of the landing gear. See Section 32-10 for Trouble-Shooting and Maintenance Practices for the main gear. See Section 32-20 for Trouble-Shooting and Maintenance Practices for the nose gear.
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  • Page 931 Landing Gear DA 40 NG AMM AIRCRAFT Section 32-10 Main Landing Gear 1. General This Section gives you the data for the main landing gear. It gives you the Trouble-Shooting and Maintenance Practices. Refer to Section 32-40 for data for the main wheels and the brakes.
  • Page 932 Landing Gear DA 40 NG AMM AIRCRAFT Inner Bolt Washer Washer Retaining Bolt Bolt Mounting Block Washer Spring Washers Polyamide Insert Convex Washer Concave Washer Castle Nut Cotter Pin Flexible Insert Retaining Bar Washer Figure 1: Main Landing Gear Strut Mounting Page 2 Doc # 6.02.15...
  • Page 933 Landing Gear DA 40 NG AMM AIRCRAFT Inner Bolt Main Landing Gear Ribs Washer Washer Retaining Bolt Mounting Block Washer Spring Washers Polyamide Insert Convex Washer Concave Washer Washer Castle Nut Cotter Pin Flexible Insert Retaining Bar Washer Bolt Figure 2: Main Landing Gear Strut Mounting (if MÄM 40-574 , OÄM 40-334, or OÄM 40-398 is installed) Doc # 6.02.15...
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  • Page 935 Landing Gear DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General Use the data below to trouble-shoot the main landing gear. WARNING: YOU MUST DO A HARD LANDING CHECK AFTER A HARD LANDING. HARD LANDING CAN CAUSE DAMAGE TO THE STRUCTURE AS WELL AS THE LANDING GEAR.
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  • Page 937 Landing Gear DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove, install and adjust the main landing gear. Refer to the manufacturer for further data. 2. Remove/Install a Main Landing Gear Strut A.
  • Page 938 Landing Gear DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Disconnect the bonding cable from the strut. Remove the 6 bolts, washers and nuts which Refer to Figures 1 and 2. hold the mounting block to the web.
  • Page 939 Landing Gear DA 40 NG AMM AIRCRAFT Main Gear Leg Mounting Plate for Fairing Brake Torque Plate 4 mm Shim (if OÄM 40-398 is installed) 1° Shim (if required) Brake Unit Washer Bolt Axle Axle Nut Figure 3: Main Landing Gear Axle Installation Doc # 6.02.15...
  • Page 940 Landing Gear DA 40 NG AMM AIRCRAFT Main Gear Leg Brake Torque Plate Washer Brake Unit 1° Shim (if required) Split Pin Axle Bolt Axle Nut Figure 4: Main Landing Gear Axle Installation (if OÄM 40-334 is installed) Page 204 Doc # 6.02.15...
  • Page 941 Landing Gear DA 40 NG AMM AIRCRAFT Main Gear Leg Mounting Plate for Fairing Brake Torque Plate 1° Shim (if required) 4 mm Shim Brake Unit Washer Bolt Axle Bush Axle Nut Figure 5: Main Landing Gear Axle Installation (if MÄM 40-574 is installed) Doc # 6.02.15...
  • Page 942 Landing Gear DA 40 NG AMM AIRCRAFT C. Install a Main Landing Gear Strut Detail Steps/Work Items Key Items/References Examine the center section in the area of the Refer to Section 51-10 for GFRP main landing gear mountings. Look specially for inspection procedures.
  • Page 943 Landing Gear DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Install the axle, brake torque-plate, 4 mm Refer to Figures 3, 4 and 5. (0.16 in) shim (if MÄM 40-574 or OÄM 40-398 is Torque: 6.5 Nm (4.8 lbf.ft.).
  • Page 944 Landing Gear DA 40 NG AMM AIRCRAFT 3. Test/Adjust the Main Landing Gear Do this work at the following times: When required by the maintenance checklist (Chapter 05). After a hard landing. After any reinstallation or repair to the main landing gear strut.
  • Page 945 Landing Gear DA 40 NG AMM AIRCRAFT Note: Ensure that the floor is levelled in the work area Wing Root Edge Main Landing Gear Leg Straight Edge Angle Bracket Top View Rear Wheel Track Wheel Track Measurement Measurements Front Wheel Track...
  • Page 946 Landing Gear DA 40 NG AMM AIRCRAFT DA 40 NG Wheel Track Table (valid for DA 40 NG with 6" - Parker rim P/N: 40-414A) ° ° ° 0,03 1,04 2,05 0,06 1,07 2,08 0,09 1,10 2,11 0,12 1,13 2,15...
  • Page 947 Landing Gear DA 40 NG AMM AIRCRAFT B. Procedure Detail Steps/Work Items Key Items/References Make sure that the airplane is at the empty See the Adjustment Report for the weight. airplane. Remove the wheel fairings (if installed): For each wheel.
  • Page 948 Landing Gear DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References If necessary, adjust the wheel track and/or Refer to Chapter 06-00 for limits. camber. Maximum 2° shim per side (camber and toe). See the Illustrated Parts Catalogue for the correct shims.
  • Page 949 2. Description and Operation Figures 1, 2 and 3 show the nose landing gear installation variants. The DA 40 NG has a fixed nose landing gear with a castor wheel. The nose landing gear strut is a welded tubular-steel component.
  • Page 950 Landing Gear DA 40 NG AMM AIRCRAFT Lock Bolt Journal Bearings Elastomer Pack Nose Gear Leg Tubular Strut Nose Wheel Axle Castor Stop Nose Wheel Fork Figure 1: Nose Landing Gear Page 2 Doc # 6.02.15 32-20-00 01 Sep 2017...
  • Page 951 Landing Gear DA 40 NG AMM AIRCRAFT Lock Bolt Elastomer Pack Journal Bearings Nose Gear Leg Tubular Strut Nose Wheel Axle Castor Stop Nose Wheel Fork Figure 2: Nose Landing Gear (if MÄM 40-574 or OÄM 40-334 is installed) Doc # 6.02.15...
  • Page 952 Landing Gear DA 40 NG AMM AIRCRAFT Lock Bolt NLG Damper Journal Bearings Nose Gear Leg Tubular Strut Nose Wheel Axle Castor Stop Nose Wheel Fork Figure 3: Hydraulic Damper Journal Assembly (if OÄM 40-379 is installed) Page 4 Doc # 6.02.15...
  • Page 953 Landing Gear DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General Use the data below to trouble-shoot the nose landing gear. WARNING: YOU MUST DO A HARD LANDING CHECK AFTER A HARD LANDING. HARD LANDINGS CAN CAUSE DAMAGE TO THE STRUCTURE AS WELL AS THE LANDING GEAR.
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  • Page 955: Maintenance Practices

    Landing Gear DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove, install and adjust the nose landing gear. Refer to the manufacturer for further data. 2. Remove/Install the Nose Landing Gear Strut A.
  • Page 956 Landing Gear DA 40 NG AMM AIRCRAFT Elastomer Element Eye End Spacer Plate Washer Number of Elastomer Elements and Spacers: Top End Cap Standard: MÄM 40-574 or OÄM 40-334: 6 MÄM 40-574 and MÄM 40-631 Center Tube (OÄM 40-334 Assembly...
  • Page 957 Landing Gear DA 40 NG AMM AIRCRAFT NLG Damper Bolt Washer Rivet Anchor Nut Bearing Washer Anchor Nut Bearing Rivet Reinforcement Sheet RH Bushing Washer Bolt Reinforcement Sheet LH Washer Bolt Figure 5: Hydraulic Damper (if OÄM 40-379 is installed) Doc # 6.02.15...
  • Page 958 Landing Gear DA 40 NG AMM AIRCRAFT C. Install the Nose Landing Gear Strut Detail Steps/Work Items Key Items/References Preparation: Refer to Figures 1 and 2. S Liberally apply corrosion protection to these Use LPS. items: S The inside of the journal assembly.

  • Page 959: Remove/Install The Elastomer Pack / Hydraulic Damper

    Landing Gear DA 40 NG AMM AIRCRAFT 3. Remove/Install the Elastomer Pack / Hydraulic Damper A. Equipment Item Quantity Part Number Padded trestles. Commercial. Weight and strap. Commercial. B. Remove the Elastomer Pack / Hydraulic Damper Detail Steps/Work Items Key Items/References Use weights to hold the rear fuselage down with Use a strap around the fuselage.
  • Page 960 Landing Gear DA 40 NG AMM AIRCRAFT C. Install the Elastomer Pack / Hydraulic Damper Detail Steps/Work Items Key Items/References If OÄM 40-370 is NOT installed: Install the bearing plates on the lower bearing. Refer to Figure 4. Bearing plates must be installed on journals of trunnion.

  • Page 961: Replace The Elastomer Elements (If Oäm 40-379 Is Not Installed)

    Landing Gear DA 40 NG AMM AIRCRAFT 4. Replace the Elastomer Elements (if OÄM 40-379 is NOT installed) CAUTION: YOU MUST ALWAYS REPLACE CRACKED OR WORN ELASTOMER ELEMENTS. IF YOU DO NOT REPLACE CRACKED OR WORN ELASTOMER ELEMENTS, THE PROPELLER CAN HIT AN OBJECT.
  • Page 962 Landing Gear DA 40 NG AMM AIRCRAFT B. Assemble the Elastomer Pack Detail Steps/Work Items Key Items/References Install the elastomer elements and remaining Refer to Figure 4. parts of elastomer pack. Adjust length between center of the eye end Refer to Figure 4.

  • Page 963: Replace The Center Tube Assembly

    Landing Gear DA 40 NG AMM AIRCRAFT 5. Replace the Center Tube Assembly CAUTION: YOU MUST REPLACE THE CENTER TUBE ASSEMBLY IF THE CENTER TUBE SHOWS SIGNS OF WEAR OR DEFORMATION. IF YOU DO NOT REPLACE THE DEFECTIVE CENTER TUBE, THE ELASTOMER PACK MAY COLLAPSE.
  • Page 964 Landing Gear DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Adjust length between center of the eye end Refer to Figure 4. bearing and center of lower journal bearing Use Molykote DX paste when installing (trunnion) with adjusting nut.

  • Page 965: Adjust The Nose Wheel Steering Friction

    Landing Gear DA 40 NG AMM AIRCRAFT 6. Adjust the Nose Wheel Steering Friction Steering friction prevents nose wheel shimmy. A. Equipment Item Quantity Reference Padded trestle. Commercial. Weight and strap. Commercial. Spring balance. Commercial. B. Procedure Detail Steps/Work Items...

  • Page 966: Nose Wheel Balancing

    Landing Gear DA 40 NG AMM AIRCRAFT 7. Nose Wheel Balancing Always have the nose-wheel balanced before installation. Apply a force of 30 - 50 N (6.75 - 11.25 lb.) in both directions along Pivot Nut the line of the Axle...

  • Page 967: Wheels And Brakes

    Landing Gear DA 40 NG AMM AIRCRAFT Section 32-40 Wheels and Brakes 1. General This Section gives you the data for the main and nose wheels. It also gives you the data for the brake system. And it gives you the Trouble-Shooting and Maintenance Practices.
  • Page 968 Landing Gear DA 40 NG AMM AIRCRAFT Bolt Hub Half Brake Disk Hub Half Distance Washer if OÄM 40-334 is installed Bolt Hub Half Bearing Hub Half Seals Snap Ring Inner Tube Tire Tapered Bearing MAIN WHEEL Inner Tube Tire...
  • Page 969 Landing Gear DA 40 NG AMM AIRCRAFT Max Level 12 mm (0.5 in.) Min Level 25 mm (1 in.) Vented Plug Master Master Fluid Level Cylinders Cylinders Brake Fluid Reservoir Pilot's Pedals Co-Pilot's Pedals LOCK PARKING BRAKE Flexible Hose RELEASE...
  • Page 970 AIRCRAFT C. Brake System Figure 2 shows the brake system schematic diagram. The DA 40 NG has two separate brake systems. The pilot’s and co-pilot’s left toe brake pedals operate the left system. They supply pressure to the left brake caliper. The right toe brake pedals operate the right brake system and supply pressure to the right caliper.
  • Page 971 Landing Gear DA 40 NG AMM AIRCRAFT Figure 3: Brake Master Cylinder and Reservoir Installation Doc # 6.02.15 Page 5 32-40-00 Rev. 3 01 Sep 2017...
  • Page 972 Landing Gear DA 40 NG AMM AIRCRAFT (2) Pilot’s Brake Operation When you press on the pilot’s right brake pedal, these things happen: The connection from the co-pilot’s master cylinder is cut off by the initial movement. (Note: Any hydraulic pressure from the co-pilot’s master cylinder pushes on the back of the piston in the pilot’s master cylinder.
  • Page 973 Landing Gear DA 40 NG AMM AIRCRAFT Figure 4: Wheel Brake Assembly Doc # 6.02.15 Page 7 32-40-00 Rev. 3 01 Sep 2017...
  • Page 974 Landing Gear DA 40 NG AMM AIRCRAFT Back Plate Attaching Bolt Washer Caliper Pressure Plate Back Plates Brake Torque Plate Figure 5: Wheel Brake Assembly (if OÄM 40-334 is installed) Page 8 Doc # 6.02.15 32-40-00 01 Sep 2017 Rev. 3...

  • Page 975: Trouble-Shooting

    Landing Gear DA 40 NG AMM AIRCRAFT Trouble-Shooting 1. General Use the data below to trouble-shoot the wheel and brake system. Complaint Possible Cause Remedy Too much tire wear. Incorrect toe-in. Adjust the toe-in. Refer to Section 32-10. Incorrect inflation pressure.
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  • Page 977: Maintenance Practices

    Landing Gear DA 40 NG AMM AIRCRAFT Maintenance Practices 1. General These Maintenance Practices tell you how to remove/install components. They also give the conditioning procedure for the brake linings. Refer to the manufacturer's data (Cleveland/Parker Hannifin Corporation) for other shop work.
  • Page 978 Landing Gear DA 40 NG AMM AIRCRAFT C. Install a Main Wheel Detail Steps/Work Items Key Items/References Apply a light coating of grease to the axle where Use grease MIL-G-3545. the wheel bearings go. Put the wheel in position on the axle.

  • Page 979: Remove/Install The Nose Wheel

    Landing Gear DA 40 NG AMM AIRCRAFT 3. Remove/Install the Nose Wheel A. Equipment Item Quantity Reference Padded trestle. Commercial. Weight and strap. Commercial. B. Remove the Nose Wheel Detail Steps/Work Items Key Items/References Remove the wheel fairing (if installed): S Remove 6 screws attaching the left half of the fairing to the right half.
  • Page 980 Landing Gear DA 40 NG AMM AIRCRAFT C. Install the Nose Wheel Detail Steps/Work Items Key Items/References Install the axle bolt (if OÄM 40-334 is installed): Refer to Figures 5 and 7. S Make sure the tubular axle is clean and install the axle into the wheel.
  • Page 981 Landing Gear DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Install the wheel fairing (if the wheel fairing was installed): S Put the 2 halves in position. S Install the 2 LH and 2 RH mounting screws. S Install the 6 screws which hold the fairing halves together.
  • Page 982 Landing Gear DA 40 NG AMM AIRCRAFT Wheel Assembly Fork Washer Spacer Bolt Axle Spacer Washer Fork Figure 6: Nose Wheel Assembly (if OÄM 40-334 is NOT installed) Page 206 Doc # 6.02.15 32-40-00 01 Sep 2017 Rev. 3...
  • Page 983 Landing Gear DA 40 NG AMM AIRCRAFT Wheel Assembly Flanged Bush Bolt Spacer Washer Axle Spacer Flanged Bush Washer Fork Figure 7: Nose Wheel Assembly (if OÄM 40-334 is installed) Doc # 6.02.15 Page 207 32-40-00 Rev. 3 01 Sep 2017...

  • Page 984: Remove/Install A Brake Master Cylinder

    Landing Gear DA 40 NG AMM AIRCRAFT 4. Remove/Install a Brake Master Cylinder A. Remove a Brake Master Cylinder Detail Steps/Work Items Key Items/References WARNING: DO NOT GET BRAKE FLUID ON YOU. BRAKE FLUID CAN CAUSE DISEASE. CAUTION: CLEAN UP SPILT BRAKE FLUID IMMEDIATELY. BRAKE FLUID CAN DAMAGE PAINT AND OTHER MATERIAL.
  • Page 985 Landing Gear DA 40 NG AMM AIRCRAFT B. Install a Brake Master Cylinder Detail Steps/Work Items Key Items/References WARNING: DO NOT GET BRAKE FLUID ON YOU. BRAKE FLUID CAN CAUSE DISEASE. CAUTION: CLEAN UP SPILT BRAKE FLUID IMMEDIATELY. BRAKE FLUID CAN DAMAGE PAINT AND OTHER MATERIAL.

  • Page 986: Remove/Install A Brake Cylinder

    Landing Gear DA 40 NG AMM AIRCRAFT 5. Remove/Install a Brake Cylinder A. Remove a Brake Cylinder Detail Steps/Work Items Key Items/References Remove the bolts which hold the back-plate. Refer to Figures 4 and 5. Remove the back-plate. 4 bolts (if OÄM 40-334 is installed) or 2 bolts (otherwise).
  • Page 987 Landing Gear DA 40 NG AMM AIRCRAFT B. Install a Brake Cylinder Detail Steps/Work Items Key Items/References Put the brake cylinder and pressure plate in Use Loctite anti-seize compound 767, position on the torque plate. Loctite 8009 or equivalent on the locating pins.
  • Page 988 Landing Gear DA 40 NG AMM AIRCRAFT Control Bulkhead Attaching Bolt To Right Brake Swivel Fitting Parking Brake Caliper Lever Inlet for Right Brake System To Left Brake Caliper Parking Brake Valve Cable Adjuster Inlet for Left Brake System Control Bulkhead...

  • Page 989: Remove/Install The Parking Brake Valve

    Landing Gear DA 40 NG AMM AIRCRAFT 6. Remove/Install the Parking Brake Valve A. Remove the Parking Brake Valve Detail Steps/Work Items Key Items/References Remove the pilots' seats. Refer to Section 25-10. WARNING: DO NOT GET BRAKE FLUID ON YOU. BRAKE FLUID CAN CAUSE DISEASE.

  • Page 990: Bleed The Brake System

    Landing Gear DA 40 NG AMM AIRCRAFT B. Install the Parking Brake Valve Detail Steps/Work Items Key Items/References Put the parking brake valve in position. At the bottom of the control bulkhead. Refer to Figure 8. Install the 2 nuts, bolts and washers which attach Make sure that the bracket for the the valve.
  • Page 991 Landing Gear DA 40 NG AMM AIRCRAFT 7. Bleed the Brake System A. Equipment Item Quantity Reference Pressure bleed equipment with MIL-PRF-5606H brake Commercial. fluid. Transparent overflow pipe and container. Commercial. B. Bleeding Procedure This procedure bleeds the air from the braking system on one side of the airplane (left or right). If necessary, perform this procedure on both braking systems (left and right).
  • Page 992 Landing Gear DA 40 NG AMM AIRCRAFT Detail Steps/Work Items Key Items/References Operate the pilot’s brake pedals many times to Continue bleeding the system until the remove air from the system. fluid has no bubbles. (10) Operate the co-pilot’s brake pedals many times to Continue bleeding the system until the remove air from the system.

  • Page 993: Condition The Brake Linings

    Landing Gear DA 40 NG AMM AIRCRAFT 8. Condition the Brake Linings The brake linings are a non-asbestos organic material. You must condition new brake linings. Conditioning gives a thin layer of glaze at the friction surface. Usual brake usage keeps the layer of glaze for the life of the brake lining.
  • Page 994 Landing Gear DA 40 NG AMM AIRCRAFT Intentionally left blank Page 218 Doc # 6.02.15 32-40-00 01 Sep 2017 Rev. 3...
  • Page 995 Lights DA 40 NG AMM AIRCRAFT CHAPTER 33 LIGHTS Doc # 6.02.15 Page 1 33-TITLE Rev. 3 01 Sep 2017...
  • Page 996 Lights DA 40 NG AMM AIRCRAFT Intentionally left blank Page 2 Doc # 6.02.15 33-TITLE Rev. 3 01 Sep 2017...
  • Page 997 Lights DA 40 NG AMM AIRCRAFT TABLE OF CONTENTS CHAPTER 33 LIGHTS General ............1 Description .
  • Page 998 Lights DA 40 NG AMM AIRCRAFT Maintenance Practices General ............201 Remove/Install/Check/Adjust the Taxi Light .

  • Page 999: General

    CHAPTER 33 LIGHTS 1. General This Chapter tells you about the cockpit and the exterior lighting of the DA 40 NG. Section 33-10 tells you about the flight compartment lighting and Section 33-40 tells you about the exterior lighting. Note: Equipment which is certified for installation in the DA 40 NG is listed in Section 6.5...
  • Page 1000 Lights DA 40 NG AMM AIRCRAFT Right Wing Tip Light Assy Reading Lights (3 off) Left Wing Tip Light Assy Instrument Panel Flood Light Strip Landing/Taxi Light Assy Figure 1: Flight Compartment and Exterior Lights Page 2 Doc # 6.02.15...

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