Diamond Aircraft DA20-A1 Maintenance Manual
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Diamond Aircraft DA20-A1 Maintenance Manual

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AIRCRAFT MAINTENANCE MANUAL
DA20-A1
DOC # DA 201-A1
DIAMOND AIRCRAFT INDUSTRIES INC.
1560 CRUMLIN SIDEROAD, LONDON, ONTARIO
CANADA N5V 1S2
All rights reserved. No part of this manual may be reproduced or copied
in any form or by any means without written permission
of
DIAMOND AIRCRAFT INDUSTRIES INC.
Copyright © 2020 by DIAMOND AIRCRAFT INDUSTRIES INC., London, Ontario
REV 16
Initial Issue: 01 May 94
Revision 16: 06 Jan 21

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Summary of Contents for Diamond Aircraft DA20-A1

  • Page 1 All rights reserved. No part of this manual may be reproduced or copied in any form or by any means without written permission DIAMOND AIRCRAFT INDUSTRIES INC. Copyright © 2020 by DIAMOND AIRCRAFT INDUSTRIES INC., London, Ontario REV 16 Initial Issue: 01 May 94...
  • Page 2 DA20-A1 AIRCRAFT MAINTENANCE MANUAL DIAMOND AIRCRAFT INDUSTRIES INC. 1560 CRUMLIN SIDEROAD London, Ontario, Canada N5V 1S2 http://www.diamondaircraft.com Initial Issue: 01 May 94 DOC # DA 201-A1 06 Jan 21 Rev 16...
  • Page 3 Complete the table below when you have put the revised pages into the AMM. A vertical bar in the left margin shows changes on text pages and illustrations. DAIC: Diamond Aircraft Industries, Inc., Canada Revision Date...
  • Page 4 Record of Revisions DA20-A1 AMM Intentionally Left Blank Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 5 DA20-A1 AMM Highlights HIGHLIGHTS General This revision (Rev 16) is a normal revision cycle of the Aircraft Maintenance Manual (AMM) and the pages that have been revised have a date of 06 Jan 21. Changes of technical material are described below and are indicated in the text pages by revision bars in the margin adjacent to the change.
  • Page 6 Highlights DA20-A1 AMM CH-SE-SU Pages Highlights 05-00-00 1 & 2 Pagination. Section now starts at Page 1. 05-10-00 Removed “and mounted equipment.” Not required. Added airplane life-limited components. 05-20-00 Changed the interval for spark plug replacement. Added engine controls with push pull cables. Added warning.
  • Page 7 DA20-A1 AMM Highlights CH-SE-SU Pages Highlights 12-TITLE Revised the title format. 12-TOC 1 & 2 Revised the TOC format. 12-00-00 1 & 2 Pagination. Section now starts at Page 1. 12-20-00 4 & 5 Reformatted the table. 6 & 7, 8 Pages 6 and 7 new graphics.
  • Page 8 Highlights DA20-A1 AMM CH-SE-SU Pages Highlights 25-TITLE Revised the title format. 25-TOC 1 & 2 Revised the TOC format. 25-00-00 1 & 2 Pagination. Section now starts at Page 1. 25-10-00 Revised para 1.B. to refer the fire extinguisher info to chapter 26.
  • Page 9 DA20-A1 AMM Highlights CH-SE-SU Pages Highlights 31-00-00 Indicated where Figures 1 & 2 can be located. Pagination. 31-10-00 Figure reference revised. 2 & 3 Figures 1 & 2 revised. 32-TITLE Revised the title format. 32-TOC 1 & 2 Revised the TOC format.
  • Page 10 Highlights DA20-A1 AMM CH-SE-SU Pages Highlights 51-10-00 Added to the resin & hardeners. Added Fire Retardant Paint Hensotherm 2 KS to Approved Materials. Replaced Paint N56582/T508 with Paint Steel Guard FM 585. 51-10-00 Pagination. 52-TITLE 1 & 2 New chapter to the manual.
  • Page 11 DA20-A1 AMM Highlights CH-SE-SU Pages Highlights 71-00-00 Changed the warning to a caution. Labeled Figure 2. 71-10-00 Changes to the High Temperature Paint Repair statement. Changed to High Temperature Paint Repair of a Cowling with Steel Guard FM 585. 7 - 10 Added High Temperature Paint Repair of a Cowling with Hensotherm 2 KS.
  • Page 12 Highlights DA20-A1 AMM CH-SE-SU Pages Highlights 79-00-00 Revised the caution. Pagination. Section now starts at Page 1. 79-30-00 Graphic revised for Figure 3. Gave a title to Figure 5. 92-TITLE Revised the title format. 92-TOC 1 & 2 Revised the TOC format.
  • Page 13 DA20-27-07 Rudder Pedal Adjust System (Optional) 21/04/1997 DA20-27-08A Control Surface Hinge Inspection (Alert) 19/01/2001 DA20-27-09 Installation of the Diamond Aircraft flap control module 14/08/2019 unit and microswitch tray (Optional) DA20-28-01 Fuel Cap, Safety chain (Recommended) 26/08/1996 DA20-28-02A Fuel System Indicating and Storage (Alert)
  • Page 14 DA20-61-01 Propeller Pitch Stop (Recommended) 09/03/1996 DA20-72-01 Inspection, Coolant Bottle (Recommended) 06/03/1997 DA20-72-02 DA20-A1 - Evans NPG+ Coolant (Mandatory) 22/08/2006 DA20-72-03 Use of 50/50 Glycol Coolant types to comply with 23/07/2009 EASA AD 2007-0155 (Optional) DA20-72-04A Change of measurement from CHT to Coolant...
  • Page 15 Defective Oil Filter (Alert) 28/11/1997 DA20-79-05 DA20 A1 - Oil Line Retrofit - F3 Engine 13/06/2014 (Recommended) DA20-79-06A Inspection of Oil Tank Cover (Alert) 02/05/2000 DA20-79-07 Oil Quantity Placard DA20-A1/DA20-100 (Mandatory) 18/09/2003 DA201-A1 Page 3 06 Jan 21 Rev 16...
  • Page 16 DA20-A1 AMM List of SBs Service Bulletin Revision Incorporated Title of SB / Description Number Number DA20-79-08 Introduction of a new Oil Pressure Indicator 17/12/2012 (Mandatory) DA20-92-04 Installation of Photo Luminescent Placards (Optional) 27/05/2013 DA20-92-05 Operation Limitations (Mandatory) 27/05/2013 Page 4...
  • Page 17 DA20-A1 AMM List of TRs LIST OF TEMPORARY REVISIONS NOTE: All Temporary Revisions have been incorporated into the manual at Revision 16. There are no outstanding Temporary Revisions at this time. Temporary Revision Number Date Issued Date Inserted Inserted By...
  • Page 18 List of TRs DA20-A1 AMM Intentionally Left Blank Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 19 DA20-A1 AMM List of Effective Pages LIST OF EFFECTIVE PAGES General The List of Effective Pages (LOEP) uses the following abbreviations: TOC = Table of Contents ROR = Record of Revisions SB = Service Bulletin TR = Temporary Revisions All Chapters have a Title page.
  • Page 20 List of Effective Pages DA20-A1 AMM Front Matter Page Revision Date MASTER-TOC 06 Jan 21 MASTER-TOC 06 Jan 21 MASTER-TOC 06 Jan 21 LOEP Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 21 DA20-A1 AMM List of Effective Pages CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 01-TITLE 06 Jan 21 03-00-00 06 Jan 21 01-TITLE 20 Apr 10 03-00-00 06 Jan 21 01-TOC 06 Jan 21 03-00-00 06 Jan 21 01-TOC 06 Jan 21...
  • Page 22 List of Effective Pages DA20-A1 AMM CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 05-20-00 06 Jan 21 05-20-00 06 Jan 21 05-20-00 06 Jan 21 05-30-00 20 Apr 10 05-20-00 06 Jan 21 05-30-00 20 Apr 10 05-20-00 06 Jan 21...
  • Page 23 DA20-A1 AMM List of Effective Pages CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 08-TITLE 06 Jan 21 10-20-00 20 Apr 10 08-TITLE 20 Apr 10 10-30-00 20 Apr 10 08-TOC 06 Jan 21 10-30-00 20 Apr 10 08-TOC 06 Jan 21...
  • Page 24 List of Effective Pages DA20-A1 AMM CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 12-10-00 20 Apr 10 20-00-00 06 Jan 21 12-10-00 20 Apr 10 21-TITLE 06 Jan 21 12-20-00 20 Apr 10 21-TITLE 20 Apr 10 12-20-00 20 Apr 10...
  • Page 25 DA20-A1 AMM List of Effective Pages CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 24-00-00 06 Jan 21 25-00-00 06 Jan 21 24-00-00 06 Jan 21 25-10-00 06 Jan 21 24-00-00 06 Jan 21 25-10-00 20 Apr 10 24-00-00 06 Jan 21...
  • Page 26 List of Effective Pages DA20-A1 AMM CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 27-10-00 20 Apr 10 27-40-00 06 Jan 21 27-10-00 20 Apr 10 27-40-00 06 Jan 21 27-11-00 20 Apr 10 27-40-00 06 Jan 21 27-11-00 20 Apr 10...
  • Page 27 DA20-A1 AMM List of Effective Pages CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 28-20-00 06 Jan 21 32-10-00 06 Jan 21 28-20-00 06 Jan 21 32-10-00 20 Apr 10 28-40-00 06 Jan 21 32-10-00 04 Jan 11 28-40-00 06 Jan 21...
  • Page 28 List of Effective Pages DA20-A1 AMM CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 32-40-00 06 Jan 21 34-10-00 20 Apr 10 32-40-00 06 Jan 21 34-10-00 20 Apr 10 32-40-00 20 Apr 10 34-10-00 20 Apr 10 32-40-00 20 Apr 10...
  • Page 29 DA20-A1 AMM List of Effective Pages CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 51-10-00 18 Jun 12 53-00-00 06 Jan 21 51-10-00 18 Jun 12 53-10-00 20 Apr 10 51-10-00 18 Jun 12 53-10-00 20 Apr 10 51-10-00 20 Apr 10...
  • Page 30 List of Effective Pages DA20-A1 AMM CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 57-TITLE 06 Jan 21 71-TITLE 20 Apr 10 57-TITLE 20 Apr 10 71-TOC 06 Jan 21 57-TOC 06 Jan 21 71-TOC 06 Jan 21 57-TOC 06 Jan 21...
  • Page 31 DA20-A1 AMM List of Effective Pages CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 71-20-00 20 Apr 10 76-10-00 06 Jan 21 71-20-00 20 Apr 10 77-TITLE 06 Jan 21 71-60-00 20 Apr 10 77-TITLE 20 Apr 10 71-60-00 20 Apr 10...
  • Page 32 List of Effective Pages DA20-A1 AMM CH-SE-SU Page Revision Date CH-SE-SU Page Revision Date 79-30-00 20 Apr 10 92-30-00 06 Jan 21 79-30-00 06 Jan 21 92-30-00 06 Jan 21 79-30-00 18 Jun 12 92-30-00 06 Jan 21 79-30-00 06 Jan 21...

  • Page 33: Table Of Contents

    DA20-A1 AMM Master TOC TABLE OF CONTENTS CH-SE-SU Subject INTRODUCTION............01-00-00 ORGANIZATION AND HANDLING OF THE MANUAL.
  • Page 34 Master TOC DA20-A1 AMM TABLE OF CONTENTS Subject CH-SE-SU PARKING, MOORING, STORAGE AND RETURN TO SERVICE ....10-00-003 PARKING ............10-10-00 MOORING .
  • Page 35 DA20-A1 AMM Master TOC TABLE OF CONTENTS CH-SE-SU Subject EQUIPMENT/FURNISHING ..........25-00-00 FLIGHT COMPARTMENT .
  • Page 36 Master TOC DA20-A1 AMM TABLE OF CONTENTS Subject CH-SE-SU WHEELS AND BRAKES ..........32-40-00 LIGHTS .
  • Page 37 DA20-A1 AMM Master TOC TABLE OF CONTENTS CH-SE-SU Subject WINGS ..............57-00-00 WING STRUCTURE.
  • Page 38 Master TOC DA20-A1 AMM Intentionally Left Blank MASTER-TOC DA201-A1 Page 6 Rev 16 06 Jan 21...

  • Page 39: Introduction

    DA20-A1 AMM Introduction CHAPTER 01 INTRODUCTION 01-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
  • Page 40 Introduction DA20-A1 AMM Intentionally Left Blank 01-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 41 DA20-A1 AMM Introduction TABLE OF CONTENTS Subject CH-SE-SU Page INTRODUCTION........... . . 01-00-00 ..1 General.
  • Page 42 Introduction DA20-A1 AMM Intentionally Left Blank 01-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...

  • Page 43: Introduction

    The purpose of this Aircraft Maintenance Manual (AMM) is to furnish the maintenance personnel with all data required to maintain the DA20-A1 aircraft. It is comprised of a detailed description of systems, troubleshooting and correction, removal and installation, as well as maintenance information.

  • Page 44: Warning, Cautions And Notes

    Introduction DA20-A1 AMM Warning, Cautions and Notes Obey all the usual safety precautions and maintenance instructions when doing maintenance. This AMM also contains warnings, cautions and notes before applicable instructions: WARNING: A WARNING TELLS THE PERSON DOING THE MAINTENANCE THAT INJURY OR DEATH IS POSSIBLE IF THEY DO NOT FOLLOW THE INSTRUCTIONS.

  • Page 45: Contents (Peculiarities)

    MAIN GROUP 05, ENGINE These chapters contain information pertaining to only the parts manufactured by Diamond Aircraft. Only the most important aspects, regarding the maintenance of the Rotax 912 A3 and F3 engine are mentioned in this chapter. For further maintenance information, the engine manufacturer’s manuals should be consulted.

  • Page 46: Arrangement Of Chapters

    Introduction DA20-A1 AMM Arrangement of Chapters STRUCTURE Chapter Section Unit Example: (Flight Controls) (Rudder) (Pedal assy) This type of chapter structure, in three groups, provides a clear and understandable organization of the Maintenance Manual and facilitates easy integration of any new or revised pages.
  • Page 47 Introduction DA20-A1 AMM Order of Pages PAGES PRECEDING THE ACTUAL MANUAL Pages Cover Page 1 and 2 Record of Revisions 1 and 2 Revision Highlights 1 thru xx List of Service Bulletins 1 thru xx List of Temporary Revisions 1 and 2...
  • Page 48 Introduction DA20-A1 AMM Intentionally Left Blank 01-00-00 Page 6 DA201-A1 06 Jan 21 Rev 16...
  • Page 49 Organization and Handling of the Manual DA20-A1 AMM CHAPTER 02 ORGANIZATION AND HANDLING OF THE MANUAL 02-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 50 Organization and Handling of the Manual DA20-A1 AMM Intentionally Left Blank 02-TITLE DA201-A1 Page 2 20 Apr 10 Rev 13...
  • Page 51 Organization and DA20-A1 AMM Handling of the Manual TABLE OF CONTENTS Subject CH-SE-SU Page ORGANIZATION AND HANDLING OF THE MANUAL..... . . 02-00-00 ..1 General.
  • Page 52 Organization and Handling of the Manual DA20-A1 AMM Intentionally Left Blank 02-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...

  • Page 53: Organization And Handling Of The Manual

    Organization and DA20-A1 AMM Handling of the Manual ORGANIZATION AND HANDLING OF THE MANUAL General To search for information regarding a specific system of the airplane, the manual user should refer to the Table of Contents for the correct chapter number.

  • Page 54: Record Of Revisions

    “RECOMMENDED” or “OPTIONAL”, depending on the subject of the bulletin. List of Applicable Publications Diamond Aircraft publishes a List of Applicable Publications (LOAP) on a quarterly basis. The LOAP lists applicable supporting documentation which is produced by Diamond Aircraft, Rotax, and Hoffmann Propellers.

  • Page 55: Abbreviations

    Organization and DA20-A1 AMM Handling of the Manual Abbreviations Where appropriate, abbreviations are used that are in accordance with applicable regulations and standard industry practice.. ACL: Anti-Collision Light A.M.E: Aircraft Maintenance Engineer A&P: Airframe and Powerplant Mechanic FRP: Fiber Reinforced Plastic...
  • Page 56 Organization and Handling of the Manual DA20-A1 AMM Intentionally Left Blank 02-00-00 Page 4 DA201-A1 06 Jan 21 Rev 16...

  • Page 57: General Description Of The Aircraft

    General Description of the Aircraft DA20-A1 AMM CHAPTER 03 GENERAL DESCRIPTION OF THE AIRCRAFT 03-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
  • Page 58 General Description of the Aircraft DA20-A1 AMM Intentionally Left Blank 03-TITLE Page 2 DA201-A1 Rev 13 20 Apr 10...
  • Page 59 DA20-A1 AMM General Description of the Aircraft TABLE OF CONTENTS Subject CH-SE-SU Page GENERAL DESCRIPTION OF THE AIRCRAFT ......03-00-00 ..1 General.
  • Page 60 General Description of the Aircraft DA20-A1 AMM Intentionally Left Blank 03-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 61 "Utility" airworthiness category airplane. Description The DA20-A1 may be operated under DAY-VFR conditions. The single engine, two-seat, low wing airplane consists of a self supporting wing structure and a T-tail. The latest state-of-the-art fiber composite production techniques were used in the manufacturing of the DA20-A1.
  • Page 62 General Description of the Aircraft DA20-A1 AMM Figure 1 - Three View Drawing of the DA20-A1 03-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 63 DA20-A1 AMM General Description of the Aircraft Figure 2a - Access Holes and Other Openings 03-00-00 Page 3 DA201-A1 06 Jan 21 Rev 16...
  • Page 64 General Description of the Aircraft DA20-A1 AMM Figure 2b - Access Holes and Other Openings 03-00-00 Page 4 DA201-A1 06 Jan 21 Rev 16...
  • Page 65 DA20-A1 AMM General Description of the Aircraft Figure 3 - Stiffeners and Bulkheads 03-00-00 Page 5 DA201-A1 06 Jan 21 Rev 16...
  • Page 66 B bulkhead below the floor of the baggage compartment. Vendor Documentation The following table lists suppliers of vendor systems and equipment installed in the DA20-A1. It will be helpful when detailed information on the respective systems and equipment is to be obtained.
  • Page 67 DA20-A1 AMM General Description of the Aircraft Available Manuals: Operation and Maintenance Manual, Doc. No. E540 Overhaul Manual, Doc. No. E569 Propeller Governor: A210786 Woodward Supplier: 5125-35th St. Rockford, Il 61125 Phone No.: 815 624-2499 Fax No.: 815 874-9598 Main Wheel Brakes: Cleveland 30-9...
  • Page 68 General Description of the Aircraft DA20-A1 AMM Intentionally Left Blank 03-00-00 Page 8 DA201-A1 06 Jan 21 Rev 16...

  • Page 69: Airworthiness Limitations

    DA20-A1 AMM Airworthiness Limitations CHAPTER 04 AIRWORTHINESS LIMITATIONS 04-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
  • Page 70 Airworthiness Limitations DA20-A1 AMM Intentionally Left Blank 04-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 71 DA20-A1 AMM Airworthiness Limitations TABLE OF CONTENTS Subject CH-SE-SU Page AIRWORTHINESS LIMITATIONS ........04-00-00 ..1 General.
  • Page 72 Airworthiness Limitations DA20-A1 AMM Intentionally Left Blank 04-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 73 March 14, 2023...
  • Page 74 Airworthiness Limitations DA20-A1 AMM Intentionally Left Blank 04-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 75 DA20-A1 AMM Airworthiness Limitations General It is the responsibility of the operator to ensure that time limits or operating limitations for equipment described within this chapter are not exceeded. 04-00-00 DA201-A1 Page 3 06 Jan 21 Rev 16...
  • Page 76 Airworthiness Limitations DA20-A1 AMM Intentionally Left Blank 04-00-00 Page 4 DA201-A1 06 Jan 21 Rev 16...

  • Page 77: Limited Time Parts

    DA20-A1 AMM Airworthiness Limitations LIMITED TIME PARTS General The items listed below are life limited items which must be removed from service at the replacement times shown, and discarded (scrapped). Component Replacement Time Flexible Rubber brake lines 8 years (not flexible Stainless Steel Braided lines)
  • Page 78 DA20-A1 AMM Airworthiness Limitations Intentionally Left Blank 04-10-00 Page 2 DA201-A1 Rev 13 20 Apr 10...

  • Page 79: Paint Finish

    Airworthiness Limitations DA20-A1 AMM PAINT FINISH General To ensure that the temperature of the composite structure is kept below 129 °F (54 °C), the outer surface of the aircraft must be painted white, except for the areas of registration marks, placards and minor trim, as specified by the type certificate holder.
  • Page 80 Airworthiness Limitations DA20-A1 AMM Intentionally Left Blank 04-20-00 Page 2 DA201-A1 Rev 13 20 Apr 10...
  • Page 81 DA20-A1 AMM Time Limits and Maintenance Checks CHAPTER 05 TIME LIMITS AND MAINTENANCE CHECKS 05-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
  • Page 82 Time Limits and Maintenance Checks DA20-A1 AMM Intentionally Left Blank 05-TITLE Page 2 DA201-A1 Rev 13 20 Apr 10...
  • Page 83 DA20-A1 AMM Time Limits and Maintenance Checks TABLE OF CONTENTS Subject CH-SE-SU Page TIME LIMITS AND MAINTENANCE CHECKS ......05-00-00 ..1 General.
  • Page 84 Time Limits and Maintenance Checks DA20-A1 AMM Intentionally Left Blank 05-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...

  • Page 85: Time Limits And Maintenance Checks

    Time Limits and Maintenance Checks TIME LIMITS AND MAINTENANCE CHECKS General During the design of the DA20-A1 maintainability of the equipment was one of the prime considerations. Chapters 04 and 05 should be used by the maintenance personnel as reference in the execution of proper maintenance and inspections.
  • Page 86 Time Limits and Maintenance Checks DA20-A1 AMM Intentionally Left Blank 05-00-00 Page 2 DA201-A1 Rev 16 06 Jan 21...

  • Page 87: Time Limits

    Time Limits and Maintenance Checks DA20-A1 AMM TIME LIMITS Time Limits for Equipment Component Specified Time Between Overhaul Engine Rotax 912 A3 or F3 600 hours or 10 years, whichever comes first ** 1000 hours or 10 years, whichever comes first **...
  • Page 88 Time Limits and Maintenance Checks DA20-A1 AMM AIRPLANE LIFE-LIMITED COMPONENTS Airplane Life-Limited Components COMPONENT REPLACEMENT TIME Hours Calendar Time Amerex 337TS fire extinguisher 12 yrs ± 90 days 05-10-00 DA201-A1 Page 2 06 Jan 21 Rev 16...

  • Page 89: Scheduled Maintenance Checks

    Time Limits and Maintenance Checks DA20-A1 AMM SCHEDULED MAINTENANCE CHECKS General The tasks contained in this sub-chapter include the requirements for performing daily checks, regular inspections, and annual inspections. Daily checks are done before the first flight of the day and are described in the Flight Manual.
  • Page 90 Time Limits and Maintenance Checks DA20-A1 AMM MAINTENANCE PRACTICES INSPECTION CHECKLIST DA20-A1 General Enter the applicable data in the blocks below: Table 1 Aircraft S/N: ___________________ Registration: ______________ Engine Hours, TTSN/ Date: ___________________ ______________ TSMOH: Aircraft Operating Scope: ___________________ ______________...
  • Page 91 Time Limits and Maintenance Checks DA20-A1 AMM Initial Test Run Refer to Aircraft Flight Manual, Chapter 4, and Rotax 912 Maintenance Manual, Chapter 12. Table 2 Interval (Flight Hours) Inspection Items 1000 Initials Run engine until oil temperature reaches 40 °C (100°F).
  • Page 92 Time Limits and Maintenance Checks DA20-A1 AMM Table 3 Interval (Flight Hours) Inspection Items 1000 Initials Oil filter; replace and inspect. Refer to Rotax 912 Maintenance Manual, Chapter 12. Perform compression test. Refer to Rotax 912 Maintenance Manual, Chapter 12. (Engine warm, throttle open).
  • Page 93 Time Limits and Maintenance Checks DA20-A1 AMM Table 3 Interval (Flight Hours) Inspection Items 1000 Initials 10. Perform a detailed examination of the exhaust system. Look especially for cracks and heat damage. Some disassembly may be required to gain proper access to areas being inspected.
  • Page 94 Time Limits and Maintenance Checks DA20-A1 AMM Table 3 Interval (Flight Hours) Inspection Items 1000 Initials 20. Check torque of nut on engine mount to firewall bolts. Refer to Chapter 20-00, section 4. 21. Reduction gear; Gearbox friction. Refer to Rotax 912 Maintenance Manual, Chapter 12.
  • Page 95 Time Limits and Maintenance Checks DA20-A1 AMM Table 3 Interval (Flight Hours) Inspection Items 1000 Initials Operating fluids used: (Type and quantity) Oil: ______________________________________ Coolant: ____________________________________ Misc: ______________________________________ Parts Replaced: ____________________________________ ____________________________________ ____________________________________ Remarks: 05-20-00 DA201-A1 Page 7 06 Jan 21...
  • Page 96 Time Limits and Maintenance Checks DA20-A1 AMM Propeller Table 4 Interval (Flight Hours) Inspection Items 1000 Initials Remove spinner; check spinner and spinner mount for cracks, dents, and run-out. Blades; check for radial play, maximum: 1º check for bladeshake Clean propeller and hub.
  • Page 97 Time Limits and Maintenance Checks DA20-A1 AMM Cabin Table 5 Interval (Flight Hours) Inspection Items 1000 Initials Canopy: - Check for defects; - Check bond of canopy to frame for signs of separation. - Check locking mechanism for proper operation; make sure unlatching force lies between 58-80 N (13-18 lbf).
  • Page 98 Time Limits and Maintenance Checks DA20-A1 AMM Table 5 Interval (Flight Hours) Inspection Items 1000 Initials 12. Navigation and Landing lights: - Check for proper operation. 13. Compass; check for proper operation. 14. Verify compliance with FAA AD 93-05-06 Reference ACS / Gerdes Service Bulletin, SB92-01-ACS, ignition switch lubrication/inspection.
  • Page 99 Time Limits and Maintenance Checks DA20-A1 AMM Table 6 Interval (Flight Hours) Inspection Items 1000 Initials Flaps and flap control mechanism in fuselage; check for proper connection and proper safetying, through bottom access panels. Flaps; check pre-tension and adjust if required.
  • Page 100 Time Limits and Maintenance Checks DA20-A1 AMM Table 6 Interval (Flight Hours) Inspection Items 1000 Initials 16. Remove floor plate from baggage compartment and remove seat shell; Landing gear mounting; check for secure attachment and proper safetying. Rudder control cables, rudder bellcrank (in B-bulkhead) and aileron and flap control system parts;...
  • Page 101 Time Limits and Maintenance Checks DA20-A1 AMM Table 6 Interval (Flight Hours) Inspection Items 1000 Initials 23. Drain and vent bores in wings, fuselage, and control surfaces; check 24. Remove aileron push rods; check for chafing. 25. B-bolts; check for axial play. Refer to Maintenance Manual, Chapter 57.
  • Page 102 Time Limits and Maintenance Checks DA20-A1 AMM Table 7 Interval (Flight Hours) Inspection Items 1000 Initials Examine the nose landing gear shock absorber assembly as follows: Inspect for damage, corrosion or cracks Inspect rubber dampers for deterioration, cracks or damage Inspect for proper attachment and loose components.
  • Page 103 Time Limits and Maintenance Checks DA20-A1 AMM Table 7 Interval (Flight Hours) Inspection Items 1000 Initials 18. Visually examine the NLG strut condition. Look especially for distortion, corrosion and condition of the paint. 19. Visually examine the NLG strut upper journal assembly lock bolt.
  • Page 104 Time Limits and Maintenance Checks DA20-A1 AMM General Table 8 Interval (Flight Hours) Inspection Items 1000 Initials Pitot-static system; check for leaks and cleanliness. Drain any water which may have accumulated in the Pitot static system. Lubricate in accordance with Lubrication Schedule in Chapter 12-20.
  • Page 105 Time Limits and Maintenance Checks DA20-A1 AMM Maintenance Report Complete a copy of the Maintenance Report after all of the applicable maintenance tasks in the Maintenance Checklist have been initialled. DA20-A1 Aircraft Serial Number: Registration Number: Check: __________________ (50 hr., 100 hr., 200 hr., 1000 hr., 6000 hr.) REMARKS: The aircraft is airworthy with respect to its maintenance condition.
  • Page 106 Time Limits and Maintenance Checks DA20-A1 AMM Maintenance Check Flight Report NOTE: The maintenance check flight must be done in accordance with the applicable national regulations. MAINTENANCE CHECK FLIGHT DA20-A1 (See Maintenance Checklist for Applicability) Page 1 of 2 Registration:...
  • Page 107 Time Limits and Maintenance Checks DA20-A1 AMM MAINTENANCE CHECK FLIGHT DA20-A1 (See Maintenance Checklist for Applicability) Page 2 of 2 Findings Functional Check, Flight Behavior Taxiing behavior, take-off behavior Airspeed indicator Vertical speed indicator Compass Behavior during climb Cylinder head temperature...
  • Page 108 Time Limits and Maintenance Checks DA20-A1 AMM 6000 Hour Inspection All inspection items listed in Tables 3.1-3.6 must be performed within 6000 hours of flight time and every 6000 hours thereafter. The inspection must be performed in conjunction with the coincident 1000 hour inspection.
  • Page 109 Defect Limits for Composites Diamond Aircraft has established defect limits for inspection of composite airframe components; refer to Chapter 51-10 for this information.
  • Page 110 Time Limits and Maintenance Checks DA20-A1 AMM 6000 HOUR INSPECTION CHECKLIST DA20-A1 S/N: ________________________________ Registration: ________________________ Airplane Date: ________________________________ Operating Hours:________________________ File completed Inspection Checklist and Findings Report in the Airplane Maintenance Log. NOTE: Where the inspection method indicated in the following tables is followed by the symbol ”(T)”, perform a tap test, if visual inspection reveals evidence of possible...
  • Page 111 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.1 Left Wing Must be performed in conjunction with coincident 1000 hr inspection. Inspection Inspection Items Initials Method Left Upper and Lower Wing Skins Check for delamination, cracks, dents, scratches Check condition of paint (chips, scratches, UV damage)
  • Page 112 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.2 Right Wing Must be performed in conjunction with coincident 1000 hr inspection. Inspection Inspection Items Initials Method Right Wing Root Ribs (in front and behind spar) Bonding with the skins V (T)
  • Page 113 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.2 Right Wing Must be performed in conjunction with coincident 1000 hr inspection. Inspection Inspection Items Initials Method Check for damage to core or disbond between skin and core V (T) Leading edge bond (disbonds, cracks above or below overlap seam)
  • Page 114 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.3 Fuselage Must be performed in conjunction with coincident 1000 hr inspection. Inspection Inspection Items Initials Method Fuselage Skin, including Vertical Stabilizer Check for delamination, cracks, dents, scratches Check condition of paint (chips, scratches, UV damage, condition of...
  • Page 115 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.3 Fuselage Must be performed in conjunction with coincident 1000 hr inspection. Inspection Inspection Items Initials Method Main landing gear and A-bolt attachment brackets (cracks or corrosion of bracket, disbond from or delamination in surrounding...
  • Page 116 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.4 Horizontal Must be performed in conjunction with coincident 1000 hr inspection. Stabilizer Inspection Inspection Items Initials Method HS Skins Check for delamination, cracks, dents, scratches V (T) Check condition of paint (chips, scratches, UV damage)
  • Page 117 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.5 Control Must be performed in conjunction with coincident 1000 hr inspection. Surfaces Inspection Inspection Items Initials Method Ailerons Check for delamination, cracks, dents, scratches V (T) Check condition of paint (chips, scratches, UV damage)
  • Page 118 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.5 Control Must be performed in conjunction with coincident 1000 hr inspection. Surfaces Inspection Inspection Items Initials Method Elevator and Anti-Servo Tab Check skins for delamination, cracks, dents, scratches Check condition of paint (chips, scratches, UV damage)
  • Page 119 Time Limits and Maintenance Checks DA20-A1 AMM Table 3.6 Landing Gear Must be performed in conjunction with coincident 1000 hr inspection. Inspection Inspection Items Initials Method Main Landing Gear Check MLG strut condition (distortion, corrosion, condition of paint) Remove main wheels from axles and check condition of axle (cracks,...
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  • Page 121: General Inspections

    Time Limits and Maintenance Checks DA20-A1 AMM GENERAL INSPECTIONS General Preflight as well as post flight inspections are part of the general inspection procedure. In general these inspections are performed on a daily base. This inspection is described in the Flight Manual and in general is performed by the pilot.
  • Page 122 Time Limits and Maintenance Checks DA20-A1 AMM (4) To check that the fuel shut off valve is operating properly, switch electric fuel pump ON, fuel pressure warning light should remain illuminated. (5) Turn fuel shut off valve to OPEN position, fuel pressure warning light should turn OFF.

  • Page 123: Unscheduled Inspections

    Time Limits and Maintenance Checks DA20-A1 AMM UNSCHEDULED INSPECTIONS General Unscheduled inspections are only performed in the event that during flight operation of the airplane incidents occur which are not part of a normal flight operation, and which could have caused a defect or interfere with the airworthiness of the airplane.
  • Page 124 Time Limits and Maintenance Checks DA20-A1 AMM Furthermore wings and stabilizers must be inspected on the leading edge, in the vicinity of the wing spar, around the connecting points to the fuselage, and especially in the area of the mounting fittings.
  • Page 125 Time Limits and Maintenance Checks DA20-A1 AMM Tail Impact Damage Inspection continued: Figure 1 - Tail Impact Damage Inspection 05-40-00 Page 3 DA201-A1 20 Apr 10 Rev 13...
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  • Page 127: Dimensions And Areas

    DA20-A1 AMM Dimensions and Areas CHAPTER 06 DIMENSIONS AND AREAS 06-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 129 DA20-A1 AMM Dimensions and Areas TABLE OF CONTENTS Subject CH-SE-SU Page DIMENSIONS AND AREAS ..........06-00-00 ..1 General.
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  • Page 131: Dimensions And Areas

    DA20-A1 AMM Dimensions and Areas DIMENSIONS AND AREAS General Most dimensions in this chapter are metric. The spans are measured parallel to their respective datum plane if not indicated otherwise. Unit Conversions Units/Abbreviations Conversion Factor Length Meter [m] [mm] / 25.4 = [in] Millimeter [mm] [cm] / 2.54 = [in]...

  • Page 132: Adjustment Values For Control Surfaces And Trim

    Adjustment Values for Control Surfaces and Trim ADJUSTMENT REPORT (Refer to Figures 1 and 2). All adjustment values are recorded in the adjustment Report before a DA20-A1 is delivered. The completed report is part of the Airplane Maintenance Log. When the adjustment values are checked, the report should be used to determine whether any deviations from the recorded measurements have occurred.
  • Page 133 Dimensions and Areas DA20-A1 AMM Diamond Aircraft DA20 S/N: __________________ Date: _________________ INSP.: _______________ ITEM DEFLECTION WEIGHT STATIC MOMENTS BEFORE BALANCING AFTER BALANCING MOMENT TRAILING EDGE BALANCE LIMITS ACTUAL LIMITS ACTUAL WEIGHT LIMITS ACTUAL WEIGHT LIMITS ACTUAL (degrees) (degrees) (kg)
  • Page 134 Dimensions and Areas DA20-A1 AMM ITEM LIMITS ACTUAL ITEM LIMITS ACTUAL HORIZONTAL FLAP PRELOAD LEFT 3.0 to 5.0 1.5° ± 0.5° STABILIZER (kg) RIGHT (kg) degrees INCIDENCE MAIN LANDING 1° to 6° DIHEDRAL LEFT 2.90 TO 330* (0º to 2º...

  • Page 135: Control Surface Gaps

    DA20-A1 AMM Dimensions and Areas Control Surface Gaps The gaps between control surfaces and wings/fins must be at least 3 mm (0.12 in) wide. Weight And Static Moments Of Control Surfaces WARNING: IF YOU REPAINT (OR DO REPAIRS) TO THE CONTROL SURFACES, MAKE SURE THAT THE WEIGHTS AND STATIC MOMENTS OF THE CONTROL SURFACES ARE NOT MORE THAN THE VALUES IN THE ADJUSTMENT REPORT.
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  • Page 137: Lifting And Shoring

    DA20-A1 AMM Lifting and Shoring CHAPTER 07 LIFTING AND SHORING 07-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 139 DA20-A1 AMM Lifting and Shoring TABLE OF CONTENTS Subject CH-SE-SU Page LIFTING AND SHORING ..........07-00-00 ..1 General.
  • Page 140 Lifting and Shoring DA20-A1 AMM Intentionally Left Blank 07-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 141 Lifting and Shoring LIFTING AND SHORING General The DA20-A1 is a very light airplane and does not have any crane attachment points. Belts are used to lift the airplane. The wings and horizontal stabilizer are removed and carried by hand.
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  • Page 143: Lifting

    Lifting and Shoring DA20-A1 AMM LIFTING General No lifting equipment is required for installation and removal of the wings and elevator unit. Belts are used to lift the fuselage. The forward belt should be placed in front of the steps, the rearward belt should be placed in front of the tail fin.
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  • Page 145: Jacking

    Lifting and Shoring DA20-A1 AMM JACKING General Two jacking points are located at the bottom of the fuselage's root ribs. The rear is supported, using the proper support seat, by the third jack in front of the vertical stabilizer. Refer to Figure 1.
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  • Page 147: Leveling And Weighing

    DA20-A1 AMM Leveling and Weighing CHAPTER 08 LEVELING AND WEIGHING 08-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 149 DA20-A1 AMM Leveling and Weighing TABLE OF CONTENTS Subject CH-SE-SU Page LEVELING AND WEIGHING ......... . . 08-00-00 ..1 General.
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  • Page 151 Empty weight and corresponding center of gravity and useful load must be recorded in the Weighing Report (see DA20-A1 Flight Manual). Leveling Prior to weighing the airplane axes must be aligned horizontally and vertically by leveling the airplane.
  • Page 152 Leveling and Weighing DA20-A1 AMM To determine the empty weight and the empty weight CG position, the airplane is to be positioned in the above mentioned pre-weighing condition, with the nose gear and each main gear on a scale. Ensure the aircraft is level longitudinally as illustrated on the weighing report (see Figure 1).
  • Page 153 DA20-A1 AMM Leveling and Weighing Figure 1 - Weighing Report Support Gross Tare Net Mass Lever Arm [lbs] ([kg]) [lbs] ([kg]) [lbs] ([kg]) [in] ([m]) Nose Main Left Main Right Empty Weight W = __________lbs (kg) Empty Weight Moment = _____________in lbs (m kg)
  • Page 154 Leveling and Weighing DA20-A1 AMM Permissible Empty Weight C.G. Range The empty weight center of gravity must be within the limits listed in the table below. Max rearward empty Max forward empty Empty Weight weight CG position weight CG position...

  • Page 155: Towing And Taxiing

    DA20-A1 AMM Towing and Taxiing CHAPTER 09 TOWING AND TAXIING 09-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 157 Towing and Taxiing DA20-A1 AMM TABLE OF CONTENTS Subject CH-SE-SU Page TOWING AND TAXIING ..........09-00-00 ..1 General.
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  • Page 159 Equipment and Accessories The DA20-A1 is towed using a tow bar that is part of the standard equipment, and attached to the nose wheel. One person is capable of moving the airplane on a smooth, level surface using this equipment.
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  • Page 161: Towing

    Towing Procedure Towing without tow vehicle Normally the DA20-A1 is moved manually using the tow bar. The following procedure should be followed: (1) Attach the tow bar to the nose wheel strut and close. (2) Release parking brake.
  • Page 162 AIRCRAFT BACKWARDS, PUSH THE TAIL DOWN TO RAISE THE NOSE WHEEL OFF THE GROUND AND HANDLE AS PER “C” BELOW. Moving without Tow Bar The airplane may be moved without using the tow bar. The DA20-A1 may be pushed at the wing-tips and at the wing-fuselage connection. CAUTION:...

  • Page 163: Taxiing

    DA20-A1 AMM TAXIING General The DA20-A1 is controlled with toe operated brakes during taxiing. In order to achieve very tight turning radii, the brake may be applied to individual wheels. NOTE: The airplane may only be taxied by authorized personnel.
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  • Page 165 DA20-A1 AMM Parking and Mooring CHAPTER 10 PARKING AND MOORING 10-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 167 DA20-A1 AMM Parking and Mooring TABLE OF CONTENTS Subject CH-SE-SU Page PARKING, MOORING, STORAGE AND RETURN TO SERVICE....10-00-00 ..1 General.
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  • Page 169: Parking, Mooring, Storage And Return To Service

    PARKING, MOORING, STORAGE AND RETURN TO SERVICE General To avoid possible damage to the airplane, the DA20-A1 should always be parked or moored while not in use. The pilot and maintenance personnel should thoroughly familiarize themselves with the procedures described in Chapters 10-10 and 10-20.
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  • Page 171: Parking

    DA20-A1 AMM Parking and Mooring PARKING General The following parking procedures must be followed to protect the airplane when it is parked outside. The scope of the procedure depends on the parking time and weather conditions. Short Term Parking If the airplane is parked for a short period of time, the following procedure should be followed: (1) Taxi or tow airplane to its parking position (2) Align airplane into the wind.
  • Page 172 Parking and Mooring DA20-A1 AMM NOTE: Failure to install the flight control lock whenever the aircraft is parked may result in control system damage, due to gusts or turbulence from other aircraft. (1) Trim aircraft to zero (0) degrees. (2) Pull the left rudder pedals fully aft and check they are locked in position.

  • Page 173: Mooring

    Parking and Mooring DA20-A1 AMM MOORING General Whenever the airplane is parked outside for extended periods of time, it should be moored. Unexpected strong gusts or heavy winds can cause severe damage to an airplane that is not moored. Mooring The airplane has three mooring points;...
  • Page 174 Parking and Mooring DA20-A1 AMM Figure 1 - Location of Mooring Points on the Airplane 10-20-00 DA201-A1 Page 2 20 Apr 10 Rev 13...

  • Page 175: Parking Duration

    DA20-A1 AMM Parking and Mooring PARKING DURATION Parking Over 30 Days For parking over 30 days the following maintenance work is required: Engine Preservation and De Preservation See Operator's Manual for the Rotax engine. Fuel Supply The fuel tank must be filled completely. Check for water in the tank each week.
  • Page 176 Parking and Mooring DA20-A1 AMM Loose Equipment Collect all loose equipment and store. Electronic Equipment No special procedure required. Airplane Ventilation Vent the airplane thoroughly before parking. Parking and Mooring See Chapter 10 20. 10-30-00 DA201-A1 Page 2 20 Apr 10...

  • Page 177: Required Placards

    DA20-A1 AMM Required Placards CHAPTER 11 REQUIRED PLACARDS 11-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 179 DA20-A1 AMM Required Placards TABLE OF CONTENTS Subject CH-SE-SU Page REQUIRED PLACARDS ..........11-00-00 ..1 General.
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  • Page 181 DA20-A1 AMM Required Placards REQUIRED PLACARDS General Placards are used for identification and indication purposes. They describe the function, operation, and operating limitations of the various systems and equipment. This chapter describes the location of the placards on the interior and exterior surfaces of the airplane.
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  • Page 183: Location Of Placards

    DA20-A1 AMM Required Placards LOCATION OF PLACARDS General In addition to the fire proof identification plate, the following placards are installed: On the instrument panel next to airspeed indicator NOTE: Ensure correct applicability of placard, depending on national limitations This airplane is classified as a very light airplane approved for VFR only, in non-icing conditions.
  • Page 184 Required Placards DA20-A1 AMM On the instrumentpanel under the airspeed indicator Next to the Swiches On the Flap Control CRUISE On the Dimming Switch Next to the Dimming Potentiometer for trim display, flap control and GPS (if installed) for cabin and fuel shut off valve light...
  • Page 185 DA20-A1 AMM Required Placards On the instrument panel next to the individual circuit breakers CHT/OIL PRESS OIL TEMP COM/NAV FUEL QTY COM/NAV COM/NAV FUEL PUMP LANDING LIGHT * Depending on aircraft specific avionic equipment TAXI LIGHT configuration INTERNAL AVIONICS AVIONICS...
  • Page 186 Required Placards DA20-A1 AMM On top of the instrument panel under the compass Around Trim Display on top of the instrument panel On top the instrument panel within pilot’s direct line of vision On DME channeling switch on the RH side of the...
  • Page 187 DA20-A1 AMM Required Placards Und r the instrument panel next to the individual knobs On the centre consol between throttle and propeller On the side of the throttle quadrant next to levers tension adjustment knob Next to trim switch on the centre console...
  • Page 188 Required Placards DA20-A1 AMM Next to canopy release handles Inside Left (partially coloured red) Inside Right (partially coloured red) Outside Left Outside Right Canopy Locked Position Placard inside LH UNLOCKED LOCKED (Green Background) (Red Background) Canopy Locked Position Placard inside RH...
  • Page 189 DA20-A1 AMM Required Placards On the LH side of baggage compartment On the brake fluid reservoirs (rudder pedals) On underside of lid of oil access hole cover (colored red) On oil filler cap On coolant equalizing reservoir On coolant dispatcher vessel...
  • Page 190 Required Placards DA20-A1 AMM On fuselage upper skin behind cockpit (only if ELT is installed), colored yellow On fuselage underside (belly), by left wing Under each wing and tail skid plate Around Stall Warning Hole in left wing On Nose Landing Gear Strut...

  • Page 191: Servicing

    DA20-A1 AMM Servicing CHAPTER 12 SERVICING 12-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 193 DA20-A1 AMM Servicing TABLE OF CONTENTS Subject CH-SE-SU Page SERVICING ............12-00-00 ..1 General.
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  • Page 195 DA20-A1 AMM Servicing SERVICING General This chapter describes the servicing tasks which are performed on the ground. Servicing on the ground in general includes replenishing and the periodic lubrication of component groups. Other tasks which are performed during ground services are also described in this chapter.
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  • Page 197: Replenishing

    Fuel System Refueling Fuel for the DA20-A1 is supplied from a fuselage mounted fuel tank with a capacity of 20.1 US gal (76 liters). The aluminum welded fuel tank is located between the spar bridge - and B-bulkhead below the baggage compartment floor.
  • Page 198 RECENT ISSUE). The engine installed in the DA20-A1 is equipped with a dry sump pressure lubrication system with a capacity of 3.4 liters (3.6 US quarts), including oil in oil filter. The filler cap of the oil tank is located on the right hand side of the engine behind cylinder No.
  • Page 199 Remove reservoir filler caps to add fluid. In the event that the fluid level is found to be low, the reason for loss of brake fluid must be determined. Only brake fluid meeting the MIL H 5606A specification should be used. Tires The DA20-A1 landing gear is equipped with tires of the size Main Landing Gear 5.00-5 Nose Landing Gear 5.00-4...
  • Page 200 Servicing DA20-A1 AMM The tire pressure on the main landing gear wheels is 33 psi (227 kPa), on the nose wheel 26 psi, (179 kPa). To reduce any damage to the tires due to landing shocks or stones with sharp edges and to increase the life time of the tires, the tire pressure should be checked at regular intervals.
  • Page 201 Servicing DA20-A1 AMM After the first top up, close the pressure cup and let the engine run for approximately 3 minutes at increased idle speed. Then fill up dispatcher vessel completely as described above. The maximum coolant quantity is 2.5 liters (2.6 US quarts).
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  • Page 203: Scheduled Servicing

    This chapter describes the procedures for lubricating those areas which require lubricating and identifies the items which must not be lubricated. The DA20-A1 is equipped with sealed roller bearings with lifetime lubrication, as well as with friction bearings (Teflon bushings). Lubrication of points requiring service are shown in table 2.2.
  • Page 204 Servicing DA20-A1 AMM Lubrication Schedule Location Type of Lubricant Interval See Figure 1 and 2 (Hours) (1), (2) • Brake Pedal Pivot • Rudder Cable S-tubes • Flap Actuator Extension Rod • Upper Rudder Pivot Bearing • 1000 Upper NLG Pivots (Left and Right) •...
  • Page 205 DA20-A1 AMM Servicing NOTES: (1) Lubrication at indicated interval or at every disassembly or assembly. (2) More frequent lubrication is required in severe climates and operating conditions. (3) Many aircraft were assembled at the factory with Mastinox 6856K (yellow in colour) in lieu of TYPE 5 corrosion inhibitor in the nose gear transverse tube area only.
  • Page 206 Servicing DA20-A1 AMM Specification Product Manufacturer TYPE 1 MIL-G-3545 (obsolete) AeroShell Grease 5 Shell Canada Products Limited P O Box 100 Station M Calgary, Alberta, T2P 2H5 Canada Shell Oil Co P O Box 2463, One Shell Plaza Houston, TX 77001, USA...
  • Page 207 DA20-A1 AMM Servicing Specification Product Manufacturer TYPE 4 VV-P-236 (petrolatum) Royco 1 Royal Lubricants Co Inc. River Road East Hanover, NJ 07936, USA DC 4 Dow Corning S Saginaw Rd Midland, MI 48641, USA TYPE 5 MIL-C-16173 (grade 2) LPS 3...
  • Page 208 Servicing DA20-A1 AMM Figure 2.1 12-20-00 DA201-A1 Page 6 06 Jan 21 Rev 16...
  • Page 209 DA20-A1 AMM Servicing Figure 2.2 12-20-00 Page 7 DA201-A1 06 Jan 21 Rev 16...
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  • Page 211: Unscheduled Servicing

    For cleaning the Plexiglas canopy, in principal the same rules should be applied as for the outside surface of the DA20-A1. The cleaning should be performed using plenty of water, and with only clean sponges and chamois. Even the smallest dust particle can cause scratch marks.
  • Page 212 Servicing DA20-A1 AMM Snow and Ice Removal After snow has collected on the airplane it should be removed as soon as possible to prevent melted water from refreezing on the surface, or in any gaps. CAUTION: DO NOT USE SHARP OBJECTS TO REMOVE SNOW OR ICE.

  • Page 213: Standard Practices - Airframe

    DA20-A1 AMM Standard Practices - Airframe CHAPTER 20 STANDARD PRACTICES - AIR FRAME 20-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 215 DA20-A1 AMM Standard Practices - Airframe TABLE OF CONTENTS Subject CH-SE-SU Page STANDARD PRACTICES - AIRFRAME ........20-00-00 ..1 General.
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  • Page 217: General

    Bolt and Nut Types Used in the Aircraft The bolts used in the DA20-A1 are of AN, MS and DIN specifications which can be identified by the markings located on the head of the bolts and by the surface treatment.

  • Page 218: Standard Torques For Screwed Connections

    Standard Practices - Airframe DA20-A1 AMM Standard Torques for Screwed Connections Obey the safety precautions for the torque procedures that follow: (1) Do not put lubricant or anti−seize compounds on the threaded fasteners unless it is specified. (2) Do not remove the lubricant or corrosion−preventive compound that is applied by the manufacturer.
  • Page 219 Standard Practices - Airframe DA20-A1 AMM Standard Torque Values These tables show the maximum permissible torque values for bolts and nuts in accordance with AN specifications. Use the listed torque values for all bolts/nuts/screws which meet the specifications unless they are in the list of special torque values in Para 8.

  • Page 220: Standard Torques For Fittings

    Standard Practices - Airframe DA20-A1 AMM DIN Specifications Metric Thread Torque (lbf-ft) Torque (Nm) 11.8 16.0 23.6 32.0 44.4 60.0 Standard Torques for Fittings These tables show the standard torque values for fittings. Steel Fittings Torque Size Torque (lbf-ft) Decanewton metre (daNm) 7.89 - 9.95...

  • Page 221: Standard Torques For Hose Clamps

    Standard Practices - Airframe DA20-A1 AMM Standard Torques for Hose Clamps The standard torques are valid for standard worm drive hose clamps, if not otherwise stated in the referring design data. If other hose clamps are required and the referring design data doesn’t state tightening torques, instructions of the hose-clamp manufacturer apply.

  • Page 222: Special Torques

    Standard Practices - Airframe DA20-A1 AMM Special Torques Part Torque (Nm) Torque (lbf-ft) Propeller flange nuts 80 - 90 59.8 - 67.3 Spark plugs 14.8 Bolts attaching the engine mount to the firewall 25.8 height of spring washers +0.01mm Nose wheel fork assembly +0.5 mm...

  • Page 223: Measuring Torque Details

    Standard Practices - Airframe DA20-A1 AMM Measuring Torque Details CAUTION: SELF LOCKING NUTS MUST BE REPLACED WITH NEW ITEMS AFTER REMOVAL IN THE EVENT THAT THE FRICTION TORQUE HAS DIMINISHED. Where self locking nuts are used, the torque value of the safetying mechanism (friction or brake torque) must be added to the value in the table.
  • Page 224 Standard Practices - Airframe DA20-A1 AMM (2) If you identify the fastener assembly with a stripe, do it as follows: (a) To identify a bolt assembly with the head shown, apply a continuous straight stripe of lacquer across the head of the bolt.
  • Page 225 Standard Practices - Airframe DA20-A1 AMM Apply a continuous Apply a continuous Apply a continuous straight stripe across straight stripe across straight stripe across the head of the bolt. the head of the nut and the head of the screw...

  • Page 226: Torque Conversion Graphs

    Standard Practices - Airframe DA20-A1 AMM Torque Conversion Graphs Use graph 1 for conversion of torque values (Nm - lbf-ft) and use graph 2 for conversion of (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 227 Standard Practices - Airframe DA20-A1 AMM Find the Nm value on the horizontal axis. Move vertically to the solid black diagonal line. Then move horizontally to the vertical axis. Read the value in lbf.in. Example: To convert 4.4 Nm to lbf.in., find 4.4 Nm on the horizontal axis (see the dashed line). Follow the dashed line vertically to the solid black diagonal line.
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  • Page 229: Environmental Systems

    DA20-A1 AMM Environmental Systems CHAPTER 21 ENVIRONMENTAL SYSTEMS 21-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 231 DA20-A1 AMM Environmental Systems TABLE OF CONTENTS Subject CH-SE-SU Page ENVIRONMENTAL SYSTEMS......... . 21-00-00 ..1 General.
  • Page 232 Environmental Systems DA20-A1 AMM Intentionally Left Blank 21-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 233 ENVIRONMENTAL SYSTEMS General The heating and ventilation system installed in the DA20-A1 permits the independent supply of cold and warm air as well as the supply of warm air to the floor and the canopy. Control of the heating system is accomplished using the cabin heat knob, located in the center console below the instrument panel.
  • Page 234 DA20-A1 AMM Environmental Systems Intentionally Left Blank 21-00-00 DA201-A1 Page 2 06 Jan 21 Rev 16...

  • Page 235: Distribution

    ENVIRONMENTAL DA20-A1 AMM DISTRIBUTION Functional Description Heating System and Canopy Defroster (Refer to Figure 1) During flight, ram air is directed to the heat exchanger through an air hose installed behind the radiator. After passing the heat exchanger, the warm air is directed by an air hose to the heat valve assembly, which is mounted to the lower half of the firewall.
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  • Page 237: Heating

    Environmental Systems DA20-A1 AMM HEATING Heat Exchanger Removal (1) Remove the engine cowlings. (2) Loosen hose clamps of air intake and cabin heat hose and remove both hoses from the upper half of the heat exchanger. (3) Remove the carburetor heat hose in a similar manner.
  • Page 238 Environmental Systems DA20-A1 AMM Intentionally Left Blank 21-40-00 Page 2 DA201-A1 20 Apr 10 Rev 13...

  • Page 239: Communications

    DA20-A1 AMM Communications CHAPTER 23 COMMUNICATIONS 23-TITLE Page 1 DA201-A1 06 Jan 21 Rev 16...
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  • Page 241 DA20-A1 AMM Communications TABLE OF CONTENTS Subject CH-SE-SU Page COMMUNICATIONS ..........23-00-00 ..1 General.
  • Page 242 Communications DA20-A1 AMM Intentionally Left Blank 23-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 243 DA20-A1 AMM Communications COMMUNICATIONS General The VHF radio system is used for communication between airplane and ground station, and between airplanes. It operates in the frequency band between 118.000 to 136.975 MHz, and has a channel separation of 25 kHz in simplex operation mode.
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  • Page 245: Speech Communication Bendix/King Kx125

    SPEECH COMMUNICATION BENDIX/KING KX125 General Refer to figure 2. The KX125 radio system is part of the NAV/COMM system used in the DA20-A1. The COMM frequency range of 118.000 MHz to 136.975 MHz includes 760 channels. The memory can store one frequency.
  • Page 246 Communications DA20-A1 AMM Legend COMM transfer switch COMM frequency indicator Active COMM frequency Transmit mode indicator COMM volume, ON/OFF rotational switch, test/squelch control switch COMM frequency selector buttons Unit lock LCD contrast adjustment System Description For overview of communication system, refer to figure 3.
  • Page 247 DA20-A1 AMM Communications (2) Frequency Selection The required frequency is selected by rotating of the COMM frequency selection buttons, where the outer button is the MHz control. With the inner knob, the frequency can be adjusted in steps of 50 kHz (pushed position) or 25 kHz (pulled position).
  • Page 248 Communications DA20-A1 AMM Troubleshooting The following table contains procedures for general troubleshooting on the radio and intercom system. For the corresponding wiring diagrams refer to Chapter 92 of the Maintenance Manual. COMPLAINT POSSIBLE CAUSE REMEDY Unable to transmit or receive, LCD...
  • Page 249 DA20-A1 AMM Communications Maintenance Information General The Bendix/King KX125 radio unit requires no regular maintenance. Removal and Installation of the Radio Unit The KX125 is held in its place by a retaining claw which can be turned with a hexagon socket screw and catches in the rack.
  • Page 250 Communications DA20-A1 AMM Intentionally Left Blank 23-10-00 Page 6 DA201-A1 20 Apr 10 Rev 13...

  • Page 251: Electrical Power

    DA20-A1 AMM Electrical Power CHAPTER 24 ELECTRICAL POWER 24-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 252 Electrical Power DA20-A1 AMM Intentionally Left Blank 24-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 253 DA20-A1 AMM Electrical Power TABLE OF CONTENTS Subject CH-SE-SU Page ELECTRICAL POWER..........24-00-00 ..1 General.
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  • Page 255: General

    ELECTRICAL POWER General The DA20-A1 is equipped with a 14 Volt direct current (DC) electrical system, refer to Figure 1. A generator with a self-contained rectifier and regulator is mounted on the engine, supplies DC power to the electrical system.
  • Page 256 Electrical Power DA20-A1 AMM Figure 1 - DA20-A1 Electrical System - Simplified Schematic 24-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 257: Description

    Ground Stud Terminal Strip Figure 2 - DA20-A1 Electrical System - Components in Engine Compartment Description Battery The lead acid battery is located in the engine compartment, it supplies power to the starter and is also used as an emergency electrical supply when the engine is not running.
  • Page 258 Electrical Power DA20-A1 AMM Starting Relay The starting relay connects the output of the battery relay with the starter motor. The starter can only be operated with the master switch ON, and with the battery relay closed. Generator Warning Light The generator warning indicator is illuminated in the event of a generator failure.

  • Page 259: Troubleshooting

    DA20-A1 AMM Electrical Power Troubleshooting The following table lists defects as they could appear in the electrical system, and their correction. Detailed troubleshooting tables are presented in the respective chapters. The wiring diagrams are located in Chapter 92. COMPLAINT POSSIBLE CAUSE REMEDY Starter motor inoperative;...

  • Page 260: Maintenance Information

    Electrical Power DA20-A1 AMM Maintenance Information CAUTION: GENERAL SAFETY PRACTICES SHOULD OBSERVED DURING MAINTENANCE PERFORMED ON THE ELECTRICAL SYSTEM, AS WELL AS SAFETY INSTRUCTIONS DESCRIBED IN THE FOLLOWING CHAPTERS. CAUTION: THE BATTERY SHOULD BE DISCONNECTED FOR EXTENSIVE MAINTENANCE OPERATIONS. AFTER COMPLETION OF MAINTENANCE TASKS, AND BEFORE...

  • Page 261: Dc Generation

    DA20-A1 AMM Electrical Power DC GENERATION General The DC generation system has the following components: Component Identification GO2430-03 Generator OV2430-01 Over-voltage Control Relay OV2430-02 Over-voltage Sensor GO2430-01 Generator Warning Light GO2430-02 Generator Circuit-breaker GC2430-01 Generator Control Circuit-breaker VM2430-01 Voltmeter AM2430-01...
  • Page 262 DA20-A1 AMM Electrical Power Figure 3 - DA20 Generator System - Simplified Schematic Diagram 24-30-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 263: Description

    DA20-A1 AMM Electrical Power Description A 40 amp generator is mounted on the forward left side of the engine. It is mounted on the engine and is belt driven from the propeller hub. The voltage is generated in coils which are arranged in a tangential direction and whose windings are crossed by the magnetic flux lines of the rotor magnet.

  • Page 264: Troubleshooting

    DA20-A1 AMM Electrical Power Troubleshooting The following table lists defects as they could appear on the generator system, and their correction. The wiring diagrams are located in Chapter 92. COMPLAINT POSSIBLE CAUSE REMEDY No power supplied by generator with Generator...
  • Page 265 DA20-A1 AMM Electrical Power (d) Supporting generator, cut lock wire and remove M10 bolt (1) (paying specific attention to location of spacer) from upper generator mounting bracket (2). (e) Remove generator. (2) Installation (a) For installation, reverse the sequence. (b) Refer to Chapter 20 for generator belt tension and bolt torque specification.

  • Page 266: Maintenance Information

    DA20-A1 AMM Electrical Power Overvoltage Control Relay (1) Removal (a) Set the generator master switch to OFF position. (b) Remove upper engine cowling. (c) Remove connector from overvoltage control relay. (d) Remove the front mounting screws on the overvoltage control relay; remove relay.

  • Page 267: Battery System

    Electrical Power BATTERY SYSTEM General The DA20-A1 is equipped with a 12 volt, 20 amp/hrs lead acid battery, which is located in the engine compartment. The battery is charged by the generator and charging system. Venting of the battery cells is accomplished through a silicon hose which directs the gas generated by the charging process in a downward direction to the exterior of the airplane.

  • Page 268: Troubleshooting

    DA20-A1 AMM Electrical Power Troubleshooting The following table lists defects as they could appear on the generator system, and their correction. The wiring diagrams are located in Chapter 92 of the maintenance manual. COMPLAINT POSSIBLE CAUSE REMEDY Battery can not be connected to the...
  • Page 269 DA20-A1 AMM Electrical Power Maintenance Information The battery has an inspection interval of 50 flight hours or 30 days, whichever comes first. At this inspection interval, the fluid level should be checked (level should be approximately at or between the max/min indicators), as well as the charge condition using a hydrometer.

  • Page 270: Removal And Installation

    DA20-A1 AMM Electrical Power Removal and Installation CAUTION: ALWAYS DISCONNECT NEGATIVE TERMINAL FIRST, WHEN DISCONNECTING THE BATTERY. CAUTION: FOR RECONNECTING THE BATTERY, ALWAYS CONNECT THE NEGATIVE TERMINAL (-), LAST. Battery (1) Removal (a) Set the battery master switch to the OFF position.
  • Page 271 DA20-A1 AMM Electrical Power (2) Installation (a) For installation, reverse the sequence. NOTE: To ensure correct polarization of the diode, refer to Chapter 92 for the wiring diagram. Ammeter (1) Removal (a) Set the battery master switch to the OFF position.

  • Page 272: Cleaning

    DA20-A1 AMM Electrical Power Cleaning In the event that acid has leaked from the battery, the battery must be removed from the airplane and rinsed with water. Also the battery trough should also be cleaned and rinsed with water. Any acid residue should be neutralized with natrium carbonate solution and rinsed with plenty of water.

  • Page 273: Electric Load Distribution

    All switches are located on the bottom left side of the instrument panel. Description The DA20-A1's electrical power is distributed via an electrical bus. The avionics master relay is also part of the distribution system and it is connected to the bus by the avionics master switch.
  • Page 274 Electrical Power DA20-A1 AMM Figure 6 - Electrical Load Power Distribution - Simplified Schematic 24-50-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 275: Troubleshooting

    DA20-A1 AMM Electrical Power Troubleshooting The following table lists defects as they could appear on the generator system, and their correction. The wiring diagrams are located in Chapter 92 of the maintenance manual. COMPLAINT POSSIBLE CAUSE REMEDY Radio unit and navigational...

  • Page 276: Maintenance Information

    Electrical Power DA20-A1 AMM Maintenance Information WARNING: TO AVOID BURNS OR FIRE DURING MAINTENANCE TASKS PERFORMED IN THE ENGINE COMPARTMENT, NEAR THE BATTERY, OR DIRECTLY ON THE ELECTRICAL SYSTEM (REPLACING OF COMPONENTS, OR WORKING ON THE CABLING), CAUTION SHOULD ALWAYS BE TAKEN. DISCONNECT THE NEGATIVE (-) BATTERY TERMINAL TO AVOID ANY SHORT CIRCUITS.
  • Page 277 DA20-A1 AMM Equipment/Furnishings CHAPTER 25 EQUIPMENT/FURNISHINGS 25-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 279 DA20-A1 AMM Equipment/Furnishings TABLE OF CONTENTS Subject CH-SE-SU Page EQUIPMENT/FURNISHING ..........25-00-00 ..1 General.
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  • Page 281: Equipment/Furnishing

    DA20-A1 AMM Equipment/Furnishings EQUIPMENT/FURNISHING General The cabin equipment is subdivided into the two (2) pilot seats, cabin lining, equipment components, and baggage compartment. A description of the individual component groups and equipment can be found in the respective chapters. 25-00-00...
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  • Page 283: Flight Compartment

    Refer to Chapter 26 for more information on the fire extinguisher. Emergency Locator Transmitter The DA20-A1 can be equipped with an Emergency Locator Transmitter. The ELT is installed in a compartment designed for the ELT and located in the B-bulkhead, behind the right seat. The ELT transmits a signal automatically after a crash on the emergency frequencies of 121.5 and 243.0...
  • Page 284 Equipment/Furnishings DA20-A1 AMM (1) ELT Functional Test Set receiver of the radio unit to frequency 121.5 MHz. Operate ELT manually, check that a signal can be heard. Switch off ELT. NOTE: The functional test should only be performed within the first five (5) minutes following each full hour to prevent false alarm situations.
  • Page 285 Equipment/Furnishings DA20-A1 AMM Removal and Installation (1) Removal (a) Loosen wing nuts, remove cover. (b) Slide unit from mounting, disconnect antenna. (2) Installation (a) For installation reverse the sequence. Instrument Panel Cover (1) Removal (a) Remove screws around instrument panel cover.
  • Page 286 Equipment/Furnishings DA20-A1 AMM Seat Belts (1) Removal (a) Remove baggage shelf. (b) Remove shoulder harness by removing accompanying hardware. (c) Remove seat shells. (d) Remove lap belts with central lock by feeding belts through mountings. (e) Remove lap belts without central lock by loosening mounting screw and pulling belts from the attachment.

  • Page 287: Baggage Compartment

    Equipment/Furnishings DA20-A1 AMM BAGGAGE COMPARTMENT General The baggage compartment is used for storage of small baggage and equipment. It is located within the cabin and is within reach of both seats. The baggage compartment has flame resistant floor covering and is approved for loads of up to 20 kg (44 lbs). The baggage restraining device supplied with the aircraft must be used to secure the baggage.
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  • Page 289 DA20-A1 AMM Fire Protection CHAPTER 26 FIRE PROTECTION 26-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 291 DA20-A1 AMM Fire Protection TABLE OF CONTENTS Subject CH-SE-SU Page FIRE PROTECTION ..........26-00-00 ..1 General.
  • Page 292 Fire Protection DA20-A1 AMM Intentionally Left Blank 26-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 293 Fire Protection FIRE PROTECTION General This Chapter tells you only about the fire extinguisher installed in the DA20-A1 aircraft. See the fire extinguisher manufacturer's manual for more data about the extinguisher. NOTE: Equipment which is certified for installation in the DA20-A1 aircraft is listed in Section 6.5 of the Airplane Flight Manual.
  • Page 294 DA20-A1 AMM Fire Protection MODEL 337TS Amerex Manufacturer UL Rating 2B:C Agent Capacity 0.87 kg (1.92 lb.) Filled Weight 1.44 kg (3.17 lb.) Height 285.75 mm (11.25 in.) Width 101.6 mm (4 in.) Depth 82.6 mm (3.25 in.) Discharge Time...
  • Page 295 DA20-A1 AMM Fire Protection Fire Extinguisher NOTE: Installation is not exactly as illustrated. Baggage Compartment Floor Mounting Bracket Figure 1 - Fire Extinguisher Installation 26-00-00 DA201-A1 Page 3 06 Jan 21 Rev 16...
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  • Page 297: Flight Controls

    DA20-A1 AMM Flight Controls CHAPTER 27 FLIGHT CONTROLS 27-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 298 Flight Controls DA20-A1 AMM Intentionally Left Blank 27-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 299 DA20-A1 AMM Flight Controls TABLE OF CONTENTS Subject CH-SE-SU Page FLIGHT CONTROLS ..........27-00-00 ..1 General.
  • Page 300 Flight Controls DA20-A1 AMM TABLE OF CONTENTS Subject CH-SE-SU Page RUDDER CONTROLS IN FUSELAGE ........27-20-20 ..1 General .
  • Page 301 Ailerons and elevator are deflected with the control stick via push rods. The rudder is deflected with the rudder pedals via control cables. The DA20-A1 is equipped with an electric elevator trim system. The trim switch mounted on the center console is used to actuate an electric motor which trims the elevator.
  • Page 302 DA20-A1 AMM Flight Controls Figure 1 - Control Surface Hinge Components 27-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 303: Ailerons Control Systems

    The aileron mass balance is attached to the outboard end of the aileron. Description Refer to Figure 1. The DA20-A1 can be operated from either seat. A roll control movement is transmitted from the control sticks to the ailerons through the following parts: Control sticks...
  • Page 304 Flight Controls DA20-A1 AMM Figure 1 - Aileron Control System Troubleshooting The following table lists defects as they could appear in the aileron control system and their correction. COMPLAINT POSSIBLE CAUSE REMEDY Interference Unclean or defective bearings Replace Aircraft moves about...
  • Page 305 DA20-A1 AMM Flight Controls Removal and Installation Refer to Figure 1. Control Sticks Refer to Sub Chapter 27-11. Aileron Push Rods Connected to Control Sticks (1) Removal (a) Remove mounting bolts from the rod end bearings of the respective push rod.
  • Page 306 Flight Controls DA20-A1 AMM (b) Move push rod in rearward direction until forward end can be lifted through the opening in the center console. (c) Extract push rod in forward direction. (2) Installation (a) For installation, reverse the sequence. Bellcrank attached to the Aft Control Push Rods Baggage compartment floor and fuel tank must be removed.
  • Page 307 DA20-A1 AMM Flight Controls Aileron Bellcrank in Wing (1) Removal (a) Open the inspection hole on the wing bottom side. (b) Remove the mounting bolts of the push rods. (c) Remove the mounting bolt of the bellcrank bearing. (d) Remove the bellcrank.
  • Page 308 Flight Controls DA20-A1 AMM (d) Apply Loctite 222 to the pins; refer to Figure 2a and 2b. It is important that the Loctite not contact the pin or hinge area where the bushing is installed. Apply the Loctite 222 to the pin after sliding it part way through the hinge as shown in Figure 2b.
  • Page 309 Adjustment Refer to Figure 1. The DA20-A1 is an airplane with excellent aerodynamic characteristics; any improper adjustment of the ailerons may have a negative effect on the roll stability. After a repair of the aileron control system, a check of the system to verify the correct aileron deflections given in Sub-Chapter 06-00 must be carried out.
  • Page 310 Flight Controls DA20-A1 AMM Fine Adjustment The requirements for roll stability and a properly trimmed longitudinal axis must be met in all flight conditions. The following modifications can be made to achieve correct adjustment: Adjusting the fixed trim tab. Adjusting the wing flaps.

  • Page 311: Main Column

    DA20-A1 AMM Flight Controls MAIN COLUMN General The main column is located under the seats. It consists of the two control sticks and a torque tube for the transmission of the elevator and aileron control inputs. Description The ailerons and the elevator are actuated by means of the control sticks.
  • Page 312 Flight Controls DA20-A1 AMM Adjustment Control Sticks The control sticks must be centered for initial adjustment. The stops, located on the control stick, must be adjusted so that the surface deflections conform to the nominal values given in the Adjustment Report (refer to Sub Chapter 06-00).

  • Page 313: Rudder Control System

    Description Refer to Figure 3A and 3B. The DA20-A1 is equipped with dual control rudder pedals. Any movement of the pedal is transmitted to the rudder through control cables and guide rollers. Both pedal assemblies can be adjusted. Figure 3a shows the location of the T-Grip adjustment on aircraft serial number 10300 and below.
  • Page 314 DA20-A1 AMM Flight Controls Aircraft serial #300 and below Figure 3A 27-20-00 Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 315 DA20-A1 AMM Flight Controls Aircraft serial #301 and Above and aircraft with service bulletin DA20-27-07 incorporated. Figure 3B 27-20-00 DA201-A1 Page 3 20 Apr 10 Rev 13...
  • Page 316 DA20-A1 AMM Flight Controls Troubleshooting The following table lists defects as they could appear in the rudder control system and their correction. COMPLAINT POSSIBLE CAUSE REMEDY Interference Unclean or defective bearings Replace or clean bearings Aircraft moves about its axis...

  • Page 317: Rudder Pedal Assembly

    Flight Controls RUDDER PEDAL ASSEMBLY General The DA20-A1 includes complete pedal assemblies on both sides as standard equipment. Refer to Figure 4. These are mounted on the floor group. In addition to the pedals, each assembly consists of an adjustment mechanism and brake cylinders for the left and right wheel brakes. After loosening the...
  • Page 318 Flight Controls DA20-A1 AMM Figure 4A On Aircraft serial number 10301 and above and aircraft with Service Bulletin DA20-27-07 incorporated. Removal and Installation Pedal Assembly It is recommended to remove the complete pedal assembly. (1) Removal (a) Disconnect the control cables from the firewall.

  • Page 319: Rudder Controls In Fuselage

    DA20-A1 AMM Flight Controls RUDDER CONTROLS IN FUSELAGE General Rudder control inputs are transmitted through control cables within the fuselage. Four pulleys under the seats and the rudder lever under the B-bulkhead guide the cables through the fuselage structure. Description Refer to Figure 3a or 3b.
  • Page 320 DA20-A1 AMM Flight Controls Adjustment Refer to Figure 3a or 3b. After a repair of the rudder control system a check of the system to verify the correct rudder deflections given in Sub-Chapter 06-00 must be carried out. To adjust the system, the multi-hole fittings on the firewall, the control cable turnbuckles, and the stop bolts (see Sub-Chapter 27-20-30) in the rudder lower mounting plate must be adjusted.

  • Page 321: Rudder

    RUDDER General The DA20-A1 is equipped with a conventional rudder which allows control of the airplane about its vertical axis. A fixed trim tab on the rudder allows fine adjustment of the yaw angle. The forward center section of the rudder contains a mass balance.
  • Page 322 Flight Controls DA20-A1 AMM Figure 4.1 - Rudder Stop Bolts 27-20-30 Page 2 DA201-A1 20 Apr 10 Rev 13...

  • Page 323: Elevator Control System

    DA20-A1 AMM Flight Controls ELEVATOR CONTROL SYSTEM General The elevator control system provides control of the airplane about its pitch axis. It consists of the control sticks, the elevator torque tube assembly, push rods, and the elevator. The elevator is equipped with an electrically activated trim assembly.
  • Page 324 Flight Controls DA20-A1 AMM Troubleshooting The following table lists defects as they could appear in the elevator control system, and their correction. COMPLAINT POSSIBLE CAUSE REMEDY Interference Unclean or defective bearings Replace or clean bearings Excessive play Bearing or bolt worn...
  • Page 325 DA20-A1 AMM Flight Controls Item (6): Elevator Push Rod in Vertical Stabilizer Rudder must be removed. Refer to Sub Chapter 27-30-30. (1) Removal Refer to Figure 5.1 (a) Disconnect elevator push rod from lower bellcrank (1). (b) Disconnect horizontal stabilizer mounting bolts. (2).
  • Page 326 Flight Controls DA20-A1 AMM Figure 5.1 - Elevator Structure 27-30-00 Page 4 DA201-A1 18 Jun 12 Rev 15...
  • Page 327 DA20-A1 AMM Flight Controls Figure 5.2 - Elevator Pushrod in Vertical Stabilizer Elevator (1) Removal (a) Disconnect the elevator push-rod from the elevator horn. (b) Remove the cotters pins. (c) Remove the pins from the hinges. (d) Remove the elevator.
  • Page 328 Flight Controls DA20-A1 AMM (2) Installation (a) Clean the hinges. (b) If a crack or corrosion is suspected on the any of the control surface hinge components, it is recommended that the paint be removed locally for further inspection. Replace damaged components.
  • Page 329 DA20-A1 AMM Flight Controls (e) Rotate the pin several times once it has been installed to evenly distribute the Loctite. Push the head of the pin up against the hinge. Orient the cotter pinhole so that the cotter pins can easily be installed once the Loctite has cured.
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  • Page 331: Elevator Trim System

    Description Refer to Figure 6. The elevator trim system used in the DA20-A1 is electrically operated. A rocker switch mounted in the center console controls an electric actuator which is connected to the vertical elevator push pull rod via a spring mount assembly. Depressing the rocker switch causes the actuator to increase the pre-load in the spring assembly and trim the elevator.
  • Page 332 Flight Controls DA20-A1 AMM Figure 6 - Elevator Trim System 27-40-00 Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 333 DA20-A1 AMM Flight Controls Actuator Cotter Pin Snubber Washer Clevis Pin Actuator Cotter Pin Washer Mounting Bracket Motor Wiring Harness Washer Clevis Pin Figure 7 - Elevator Trim Actuator and Actuator Motor 27-40-00 DA201-A1 Page 3 06 Jan 21 Rev 16...
  • Page 334 Flight Controls DA20-A1 AMM Troubleshooting The following table lists defects as they could appear in the elevator trim system, and their correction. COMPLAINT POSSIBLE CAUSE REMEDY Trim system inoperative Defective circuit breaker Replace On-board voltage too low Check battery and alternator...
  • Page 335 DA20-A1 AMM Flight Controls Removal and Installation Rocker Switch (1) Removal (a) Using access hole in center console, squeeze retaining clips on rocker switch and pull upwards slightly. (b) Disconnect wiring harness. (c) Remove switch. (2) Installation (a) For installation, reverse the sequence.
  • Page 336 Flight Controls DA20-A1 AMM Spring Mount Assembly (Refer to Figure 6) (1) Removal (a) Remove the rudder. Refer to Sub-Chapter 27-30-30. (b) Disconnect elevator pushrod from lower bellcrank. (c) Remove rod end bearing from elevator push pull rod. (d) Remove the upper and lower roll pins from the spring mount assembly.
  • Page 337 DA20-A1 AMM Flight Controls Adjustment The trim system used on the DA20-A1 is designed to be maintenance free and therefore is non- adjustable. The following check can be used to verify the trim system is properly adjusted: With the trim indicator in the neutral position, the elevator and anti-servo tabs must be aligned with the trailing edge of the horizontal stabilizer.
  • Page 338 Flight Controls DA20-A1 AMM Intentionally Left Blank 27-40-00 Page 8 DA201-A1 06 Jan 21 Rev 16...

  • Page 339: Wing - Flaps

    Flight Controls WING - FLAPS General The DA20-A1 is equipped with electrically operated wing flaps. The flaps are operated by means of a 3 position toggle switch located in the center section of the instrument panel. The flap position indicator is located next to the flap toggle switch. It has LED's for the CRUISE, T/O, and LDG positions.
  • Page 340 Flight Controls DA20-A1 AMM Figure 8A - Wing Flaps Troubleshooting The following table lists defects as they could appear in the flap system, and their correction. For aircraft serial number 10039 and above and aircraft with service bulletin DA20-27-01 (formerly SB95-05) incorporated additional troubleshooting is identified by indicating the service bulletin number in the table e.g.
  • Page 341 DA20-A1 AMM Flight Controls COMPLAINT POSSIBLE CAUSE REMEDY Flaps moving too slowly or at Defective flap motor Replace motor the wrong speed Binding actuator Check actuator for binding at guide grom- met. Defective current limiter (DA20-27-01) Check current limiter No or incorrect position...
  • Page 342 Flight Controls DA20-A1 AMM (c) On two part hinges there are two different ways that the cotter pin, pin and hinge are assembled. Install the flap. Refer to figure 8b and 8c. Reinstall all of the pins with the head of the pin against the aircraft side hinge part as shown in figure 8c. On three part hinges the pin can be installed as it was removed.
  • Page 343 DA20-A1 AMM Flight Controls NOTE: To ease cotter pin installation, bend the cotter pin at a right angle about 1/3 of the way from the bottom. Use needle nose pliers to insert the pin into the hole. Use a 90 degree pick to hold the top of the cotter pin while grabbing the bottom of the pin (sticking out through the hole) with the needle nose pliers.
  • Page 344 Flight Controls DA20-A1 AMM Push-Rod The wing must be removed (refer to Chapter 57). (1) Removal (a) Disconnect push-rod from bellcrank in wing. (b) Remove rod end bearing from push-rod. (c) Remove push-rod from wing. (2) Installation (a) For installation, reverse the sequence.
  • Page 345 DA20-A1 AMM Flight Controls Figure 9 - Flap Actuator 27-50-00 DA201-A1 Page 7 20 Apr 10 Rev 13...
  • Page 346 Flight Controls DA20-A1 AMM Current Limiter Refer to Figure 10. For aircraft serial number 10039 and above and aircraft with service bulletin DA20-27-01 (formerly SB95-05) incorporated. (1) Removal (a) Remove the left seat shell. (b) Disconnect the wires from the terminal block to the flap motor.
  • Page 347 Flight Controls DA20-A1 AMM Figure 10 27-50-00 DA201-A1 Page 9 18 Jun 12 Rev 15...
  • Page 348 Flight Controls DA20-A1 AMM Adjustment After a repair of the flap system, a check of the system to verify the correct flap travel given in Sub- Chapter 06-00 must be carried out. The end positions of the flaps are adjusted with limit switches. Refer to Drawing No 20-2400-00-00 in Chapter 92 and to Figure 11.
  • Page 349 DA20-A1 AMM Flight Controls With the flap control switch in UP position, adjust pockets to 17 degrees with the limit stop switches. Install stop, adjust to 1 to 2 mm (0.04 to 0.08 in.) free play in the UP and LDG positions.
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  • Page 351: Fuel

    DA20-A1 AMM Fuel CHAPTER 28 FUEL 28-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 352 Fuel DA20-A1 AMM Intentionally Left Blank 28-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 353 DA20-A1 AMM Fuel TABLE OF CONTENTS Subject CH-SE-SU Page FUEL............. . 28-00-00 ..1 General.
  • Page 354 Fuel DA20-A1 AMM Intentionally Left Blank 28-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 355 FUEL General The fuel system of the DA20-A1 consists of an aluminum fuel tank with a capacity of 20.1 US gal (76 liters) a fuel shut off valve, an electrical and a mechanical fuel pump, the carburetors, ball valve, a check valve (912 A3 equipped aircraft only) and the fuel lines.
  • Page 356 Fuel DA20-A1 AMM Figure 1 - Fuel System (S/N 10002 through 10092) 28-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 357 Fuel DA20-A1 AMM Figure 2 - Fuel System (S/N 10093 and subsequent and aircraft serial number 10002 to 10092 with service bulletin DA20-73-01 or DA20-73-03 incorporated) 28-00-00 DA201-A1 Page 3 06 Jan 21 Rev 16...
  • Page 358 Fuel DA20-A1 AMM Fuel Shut Off Valve And Check Valve Inspection This inspection is used to verify the proper operation of both the fuel shut off valve and the check valve (located in the fuel return line). Turn fuel shut off valve to CLOSED position.

  • Page 359: Storage (Tank)

    STORAGE (TANK) General Fuel in the DA20-A1 is supplied from a fuselage mounted tank. The welded aluminum fuel tank is located between the spar bridge and the B-bulkhead beneath the baggage compartment. The fuel filler cap is located on the left hand side behind the canopy and is connected to the fuel tank via a Military Specification hose.
  • Page 360 Fuel DA20-A1 AMM Removal and Installation of the Fuel Tank WARNING: EXTINGUISH ANY SOURCE OF HEAT OR OPEN FLAME, BEFORE WORKING ON FUEL SYSTEM. Removal (a) Drain the tank completely using the drain valve; disconnect fuel feed line. (b) Remove the baggage compartment floor.

  • Page 361: Distribution

    DA20-A1 AMM Fuel DISTRIBUTION General Refer to Figure 1 or Figure 2 as applicable. The fuel distribution system consists of an electrical and a mechanical fuel pump, fuel filters, the fuel shut off valve, and a fuel pump switch. The fuel lines are made out of shielded Teflon hoses with screw type connectors.
  • Page 362 Fuel DA20-A1 AMM Mechanical Fuel Pump The mechanical fuel pump is a diaphragm type pump driven directly by the engine. With the engine running, the pump sucks fuel via the electric fuel pump to deliver it to the carburetors with a pressure of approximately 0.15 to 0.4 bar (2.2 to 5.8 psi).
  • Page 363 DA20-A1 AMM Fuel Removal and Installation Fuel Shut-Off Valve (1) Removal Prior to removal, the fuel tank must be drained. (a) Remove the hand hole cover on the right side of the center console. (b) Disconnect both the hose lines.
  • Page 364 Fuel DA20-A1 AMM Check the disk magnet (5) for metal particles. (g) Reassemble the filter and cap (3 and 4). (h) Install the hose connector (2). Slide on the locking ring (1). Secure the cap using locking wire (6). (k) Secure the locking ring against movement by wrapping locking wire around three times.

  • Page 365: Indicating

    DA20-A1 AMM Fuel INDICATING General A submerged tube sensor is installed in the top side of the fuel tank from which the fuel level is electrically sensed. This signal is sent to the fuel quantity indicator. The airplane is also equipped with a fuel pressure sensor which illuminates a warning light, located in the instrument panel, when the fuel pressure is low.
  • Page 366 Fuel DA20-A1 AMM Removal and Installation Fuel Pressure Sensor The fuel pressure sensor and fuel distribution manifold are supplied as one unit. Fuel Quantity Sensor Refer to Figure 4. (1) Removal (a) Remove baggage compartment floor. (b) Disconnect electrical connectors.
  • Page 367 DA20-A1 AMM Fuel Calibration After replacement of the fuel quantity sensor or indicator, or as required by the checklist in Sub-Chapter 05-20 the gauge has to be checked for accurate indication. The fuel quantity indicator is calibrated as follows: (a) Drain tank completely.
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  • Page 369: Indicating/Recording Systems

    DA20-A1 AMM Indicating Systems CHAPTER 31 INDICATING/RECORDING SYSTEMS 31-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 371 DA20-A1 AMM Indicating Systems TABLE OF CONTENTS Subject CH-SE-SU Page INDICATING/RECORDING SYSTEMS ........31-00-00 ..1 General.
  • Page 372 Indicating Systems DA20-A1 AMM Intentionally Left Blank 31-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 373 Indicating Systems DA20-A1 AMM INDICATING/RECORDING SYSTEMS General In Chapter 31-10-00, Figure 1 illustrates the location of each instrument in the Cockpit on aircraft serial numbers 10002 to 10020 and Figure 2 illustrates the location of each instrument on panels installed in aircraft serial number 10021 and subsequent and aircraft with service bulletin DA20-33-01 incorporated.
  • Page 374 Indicating Systems DA20-A1 AMM Intentionally Left Blank 31-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 375: Instrument Panel

    DA20-A1 AMM Indicating Systems INSTRUMENT PANEL General The instrument panel is divided into five (5) sections: the LH, RH and center section, the instrument panel cover, and the panel on the center console. Description Refer to Figure 1 and Figure 2.
  • Page 376 Indicating Systems DA20-A1 AMM Figure 1 - Instrument Panel Effective for Serial # 10002 through 10020 without compliance to Service Bulletin DA20-33-01 (Formerly SB95-01). 31-10-00 Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 377 DA20-A1 AMM Indicating Systems Item Description Item Description Item Description Item Description 1. Outside Air Temp. Ind. 16. Landing Light Switch 31. Intercom 44. I-Panel Light Switch 2. Not Used 17. Taxi Light Switch 32. Manifold Pressure 45. Map Light Switch 3.
  • Page 378 Indicating Systems DA20-A1 AMM Removal and Installation The DA20-A1 was designed with accessibility of the equipment in mind. Consequently, the instruments are easy to reach after removal of the instrument panel cover. Removal (a) Remove the engine cowlings. (b) Disconnect the instrument wiring at terminal strip.

  • Page 379: Landing Gear

    DA20-A1 AMM Landing Gear CHAPTER 32 LANDING GEAR 32-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 380 Landing Gear DA20-A1 AMM Intentionally Left Blank 32-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 381 DA20-A1 AMM Landing Gear TABLE OF CONTENTS Subject CH-SE-SU Page LANDING GEAR ........... . 32-00-00 ..1 General.
  • Page 382 Landing Gear DA20-A1 AMM Intentionally Left Blank 32-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 383 LANDING GEAR General The DA20-A1 is equipped with a fixed tricycle landing gear, including a castering nose wheel. The two main landing gear struts are connected to the spar bridge using two mounting brackets each. The nose gear is attached to the engine mount and to the bottom side of the fuselage. Shock absorbing is achieved with an elastomer package located between engine mount and steel leg.
  • Page 384 Landing Gear DA20-A1 AMM Intentionally Left Blank 32-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 385: Main Landing Gear

    The struts absorb the landing shocks and are made of quenched and tempered steel. Brake disks are installed on the aluminum wheels. The disk brakes of the DA20-A1 are part of the standard equipment. Description Refer to Figure 1.
  • Page 386 Landing Gear DA20-A1 AMM SECTION A - A Flight Direction DETAIL X Outer Bracket Strut UHMW Inserts SECTION B - B DETAIL X Flight Direction Strut Spring Washers Figure 1 - Landing Gear Strut Removal and Installation Main Landing Gear Refer to Figure 2.
  • Page 387 DA20-A1 AMM Landing Gear (d) Remove the wheel axle nut and remove the caliper. (e) Remove the wheel. Remove the brake line from the strut. (g) Remove the axle from the strut by removing the four attachment bolts. (h) Remove the nut and the bolt at the inner mounting bracket.
  • Page 388 At each 1000 hours inspection, or after each hard landing as well as after any repair on the strut or the spar bridge, the wheel alignment has to be checked. For this, the DA20-A1 is placed onto slide sheets and alignment checked at empty weight against the data in the Adjustment Report (refer to Chapter 06).
  • Page 389 Landing Gear DA20-A1 AMM MAIN LANDING GEAR Effective for aircraft serial number 10235 and all subsequent aircraft General This Section gives you the data for the main landing gear. It gives you the trouble-shooting and maintenance practices. See Chapter 32-40 for data for the main wheels and the brakes.
  • Page 390 Landing Gear DA20-A1 AMM Figure 3A - Aluminum Main Landing Gear 32-10-00 Page 6 DA201-A1 06 Jan 21 Rev 16...
  • Page 391 DA20-A1 AMM Landing Gear Troubleshooting Use the data below to trouble-shoot the main 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.
  • Page 392 DA20-A1 AMM Landing Gear Remove the nut and bolt at the inner attachment bracket Remove the nuts which hold the retaining bar to the outer mounting bracket. (k) Remove the strut. Installation (a) Examine the spar bridge in the area of the main gear mountings. Look specially for damage to the GFRP structure.
  • Page 393 Landing Gear DA20-A1 AMM (n) Install the wheel fairing: Install the outer bolt. Install 2 screws on the inner side. (o) Lower the aircraft with the jacks. (p) Do a test for correct adjustment of the landing gear. Adjustment Do this work at the following times: At each 1000 hour check.
  • Page 394 Landing Gear DA20-A1 AMM Figure 3B - Measure Toe-In and Camber 32-10-00 Page 10 DA201-A1 20 Apr 10 Rev 13...

  • Page 395: Nose Landing Gear

    NOSE LANDING GEAR General The DA20-A1 is equipped with a fixed nose landing gear with a castoring wheel. On its rear mount, the leg is attached to the fuselage bottom using a special fitting. The forward mount is attached to the engine mount using a shock absorber assembly.
  • Page 396 Landing Gear DA20-A1 AMM Attachment To Engine Mount Shock Absorber Assembly Journal Assembly Bearing Stainless Steel Bush in Fuselage Fairing Attachment Screws Pivot Stop Pivot Nut Figure 4 - Nose Landing Gear 32-20-00 Page 2 DA201-A1 18 Jun 12 Rev 15...
  • Page 397 DA20-A1 AMM Landing Gear Removal and Installation Nose Landing Gear Strut (1) Removal (a) Jack the aircraft. Refer to Chapter 07-20-00. (b) Remove the engine cowling. Refer to Chapter 71-10-00. (c) Disconnect the shock absorber assembly from the nose landing gear strut as follows: Remove and discard the rivets.
  • Page 398 Landing Gear DA20-A1 AMM Put the NLG strut into position on the aircraft from below. Slide out the large pivot from the journal to engage the bearings in the fuselage. NOTE: No lateral free play is allowed. Drill a 2 mm (+/- 0.015 mm) hole in the large pivot through the pilot hole in the strut journal (one side only).
  • Page 399 DA20-A1 AMM Landing Gear Install the shock absorber assembly to the nose landing gear strut as follows: Refer to Figure 6. Apply a light corrosion protection on strut pins and clip retainers. Use Mastinox (6856K). Clean off any excess corrosion protection.
  • Page 400 Landing Gear DA20-A1 AMM (d) Install the thrust plate, stop plate and spacer. (e) Install the belleville springs and washers. Make sure that the belleville springs are installed with the open side facing up. Install the castellated nut. (g) Apply corrosion protection to the nut and the washers only on the stud end of the NLG strut axle.
  • Page 401 DA20-A1 AMM Landing Gear (2) Installation Refer to Figure 6. WARNING: USE PROPER PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN HANDLING CORROSION PROTECTION AND GREASE. THESE CHEMICALS CAN IRRITATE OR CAUSE DAMAGE TO THE SKIN WHEN CONTACTED. (a) Install the shock absorber assembly to the nose landing gear strut as follows: Apply a light corrosion protection on strut pins and clip retainers.
  • Page 402 Landing Gear DA20-A1 AMM (c) Remove the washer, rubber damper and the retainer. (d) Replace the defective elements. (2) Installation Refer to Figures 6. (a) Assemble the shock absorber assembly in the reverse order removed. (b) Install the retainer, rubber damper and washer.
  • Page 403 DA20-A1 AMM Landing Gear Engine Mounting Frame Lock Wire Rubber Dampers (x10) Spacers (x9) Journal Assembly Spring Pin Rivet Lock Bolt Stud Bearing Stainless Steel Bush in Fuselage Rivet Shock Absorber Retainer Rubber Damper Retainer Clip Washer Adjusting Nut Strut Pins 245 mm (9.65 IN)
  • Page 404 Landing Gear DA20-A1 AMM Self Locking Nut Washer Washer Bolt Pivot View A View A Journal Assembly View A 50°±1° Lock Bolt Hole Centerline NLG Strut Tube Figure 7a - Lock Bolt Hole - Center line Position 32-20-00 Page 10...
  • Page 405 DA20-A1 AMM Landing Gear Pivot Bushing Stop Bolt Assembly Pivot Bushing NLG Fork Assembly Thrust Washer Stop Plate Spacer Belleville Springs Washer Light Washer (Optional) Castellate Nut Cotter Pin Figure 7b - NLG Fork Assembly 32-20-00 DA201-A1 Page 11 18 Jun 12...
  • Page 406 Landing Gear DA20-A1 AMM Adjustment Nose Wheel Steering Friction Refer to Figure 7c. Steering friction prevents nose wheel shimmy and is adjusted with the nose-wheel fork pivot nut. (1) Jack the aircraft. Refer to Chapter 07-20-00. (2) Remove the nose-wheel fairing.
  • Page 407 DA20-A1 AMM Landing Gear Apply a force of 6.75 to 11.25lbs (30 to 50N) in both directions along the Line of the Axle with wheel lifted from the ground. Pivot Nut Pivot Stop Figure 7c - Adjust the Nose Wheel Steering Friction...
  • Page 408 Landing Gear DA20-A1 AMM Figure 7d - Allowable Free Play in NLG 32-20-00 Page 14 DA201-A1 18 Jun 12 Rev 15...

  • Page 409: Wheels And Brakes

    The parking brake of the DA20-A1 is standard equipment. The parking brake valve is located on the left hand aft side of the firewall for aircraft S/N 10002 to 10287 and is operated via a bowden cable. The parking brake valve is located under the right seat shell for aircraft S/N 10288 and subsequent (and aircraft with service bulletin DA20-32-01 incorporated) and is operated via a bowden cable.
  • Page 410 Landing Gear DA20-A1 AMM Figure 8 - Brake System Schematic 32-40-00 Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 411 DA20-A1 AMM Landing Gear Troubleshooting The following table lists defects as they could appear on the wheels and brakes, and their correction. COMPLAINT POSSIBLE CAUSE REMEDY Excessive tire wear Track adjusted improperly Adjust (see Chapter 32-10). Excessive axial play of wheel...
  • Page 412 Landing Gear DA20-A1 AMM (2) Installation (a) For installation reverse the sequence. Figure 9 - Main Wheel (3) Main Wheel Disassembly CAUTION: PRIOR TO DISASSEMBLY OF THE WHEEL THE TIRE MUST BE COMPLETELY DEFLATED BY REMOVING THE VALVE INSERT. (a) Remove the bolts on the rim.
  • Page 413 DA20-A1 AMM Landing Gear Nose Wheel (1) Removal (a) Remove the six allen screws securing the fairing halves to each other. (b) Remove the LH and RH fairing mounting screw. (c) Remove the fairing. (d) Unload the nose wheel. (e) Remove the M10 nut and the bolt (serving as axle) and remove the nose wheel.
  • Page 414 Landing Gear DA20-A1 AMM (2) Installation (a) For installation reverse the sequence. Master Brake Cylinders Brake Lines Figure 10 - Master Brake Cylinders Caliper NOTE: After maintenance tasks which involved opening or disconnecting of the brake line system, the brake system should be bled and checked for proper operation.
  • Page 415 DA20-A1 AMM Landing Gear Figure 11 - Caliper Disc Brake Brake disks should be replaced when their thickness is less than 4.242 mm (0.167 in). (1) Removal (a) Remove the wheel and the caliper. (b) Disassemble the wheel. (c) Remove the brake disk.
  • Page 416 Landing Gear DA20-A1 AMM Brake Linings Brake linings should be replaced when their thickness is less than 3 mm (0.12 in). (1) Removal (a) Remove the back pressure plate from the caliper. (b) Remove the pressure plate from the caliper.
  • Page 417 DA20-A1 AMM Landing Gear Parking Brake Valve Mounting Bolts Bowden Cable Figure 12 - Parking Brake Valve Parking Brake Valve Effective Aircraft Serial # 10288 and subsequent and aircraft with that have Service Bulletin DA20-32-01 incorporated. Remove the Parking Brake Valve.
  • Page 418 Landing Gear DA20-A1 AMM 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. (c) Disconnect the four brake pipes from the parking brake valve. Put the caps on the connections.
  • Page 419 DA20-A1 AMM Landing Gear Figure 12A - Parking Brake Valve Installation under Right Seat 32-40-00 DA201-A1 Page 11 20 Apr 10 Rev 13...
  • Page 420 Landing Gear DA20-A1 AMM Bleeding of Brake System Bleeding of the brake system requires a pressure pump which pumps brake fluid into the brake line system. (a) Remove the brake fluid reservoir cap and remove brake fluid down to approximately 1/3 of the normal level.
  • Page 421 Landing Gear Adjustment The brakes installed on the DA20-A1 are self adjusting. After installation of the calipers or after the brake line replacement, make sure that the wheels turn freely. If a wheel does not turn freely, the cause must be investigated and corrected.
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  • Page 423: Lights

    DA20-A1 AMM Lights CHAPTER 33 LIGHTS 33-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 425 DA20-A1 AMM Lights TABLE OF CONTENTS Subject CH-SE-SU Page INTERIOR ............33-10-00 ..1 General.
  • Page 426 Lights DA20-A1 AMM Intentionally Left Blank 33-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...

  • Page 427: Interior

    (b) Instrument Panel Lighting Description The internal lighting of the DA20-A1 is provided by a lighting module located aft of the Pilot's head and on the center line of the aircraft. Included in this module are two panel illumination lights and one map light.
  • Page 428 Lights DA20-A1 AMM Removal and Installation Lighting Module (1) Removal (a) Switch off the battery master switch. (b) Remove the nuts fastening the module to the fuselage. (c) Disconnect the wiring harness. (2) Installation (a) Connect the wire harness to the light assembly. Observe the connector numbering codes.
  • Page 429 DA20-A1 AMM Lights Figure 1 - Light Alignment 33-10-00 DA201-A1 Page 3 06 Jan 21 Rev 16...
  • Page 430 Lights DA20-A1 AMM Intentionally Left Blank 33-10-00 Page 4 DA201-A1 06 Jan 21 Rev 16...

  • Page 431: Exterior

    DA20-A1 AMM Lights EXTERIOR General The DA20-A1 can be equipped with the following exterior lighting: (a) Anti Collision Lights (ACL) (b) Position Lights (c) Navigation light (d) Taxiing Light. Description The anti collision and position lights are combined in one unit and are located at each wing tip. The anti collision strobe light power supply is installed under the pilots seat.
  • Page 432 Lights DA20-A1 AMM COMPLAINT POSSIBLE CAUSE REMEDY Both ACL’s inoperative. Defective switch Replace Defective breaker Replace Defective wiring in the forward Repair cockpit area Defective power supply Replace Left ACL inoperative Defective power supply Replace Defective ACL lamp Replace Defective wiring...
  • Page 433 DA20-A1 AMM Lights Removal and Installation WARNING: THE POWER SUPPLIES OF THE ANTI COLLISION STROBE LIGHTS GENERATE HIGH VOLTAGE WHICH IS CONNECTED DIRECTLY TO THE STROBE LIGHTS. PRIOR TO PERFORMING ANY MAINTENANCE ON THE WIRING OR ON THE LIGHT ITSELF, A MINIMUM OF FIVE (5) MINUTES WAITING TIME MUST BE...
  • Page 434 Lights DA20-A1 AMM ACL Power Supply (1) Removal (a) Remove the pilot's seat. (b) Disconnect the wiring harness. (c) Remove the four nuts securing the power supply to the fuselage. (2) Installation (a) For installation reverse the sequence. Navigation light (1) Removal (a) Remove the screws securing the light cover to the wing.

  • Page 435: Navigation And Pitot Static

    DA20-A1 AMM Navigation and Pitot Static CHAPTER 34 NAVIGATION AND PITOT STATIC 34-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 436 Navigation and Pitot Static DA20-A1 AMM Intentionally Left Blank 34-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 437 DA20-A1 AMM Navigation and Pitot Static TABLE OF CONTENTS Subject CH-SE-SU Page NAVIGATION AND PITOT STATIC ........34-00-00 ..1 General.
  • Page 438 Navigation and Pitot Static DA20-A1 AMM Intentionally Left Blank 34-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 439 DA20-A1 AMM Navigation and Pitot Static NAVIGATION AND PITOT STATIC General The navigation systems include the instruments that operate on dynamic and static pressure, and electrically powered gyros. They include the airspeed, altitude, attitude, and direction indicators. The equipment supplied with dynamic and static pressure includes the altimeter, airspeed indicator, and vertical speed indicator.
  • Page 440 Navigation and Pitot Static DA20-A1 AMM Intentionally Left Blank 34-00-00 Page 2 DA201-A1 06 Jan 21 Rev 16...

  • Page 441: Pitot Static

    DA20-A1 AMM Navigation and Pitot Static PITOT STATIC General The Pitot static system is used to measure and deliver dynamic and static pressure to the airspeed indicator, altimeter, and vertical speed indicator. Refer to Figure 1. Figure 1 - Pitot Static System Schematic...
  • Page 442 Pitot Head/Lines Refer to Figure 2. The Pitot head of the DA20-A1 is designed to measure pitot and static pressure. The Pitot head is located below the left wing. Lines running through the left wing and the fuselage connect the Pitot head to the instruments.
  • Page 443 DA20-A1 AMM Navigation and Pitot Static Figure 3 - Water Sump Type Drain System Altimeter The altimeter measures the change in atmospheric pressure using aneroid chambers. The changes in pressure correspond to changes in altitude. A special mechanism converts the movement of the aneroid chambers into deflections of the pointers.
  • Page 444 Outside Air Temperature Indicator The DA20-A1 can be equipped with an outside air temperature indicator. The temperature sensor is located in the left NACA type air inlet. The system operates on onboard power.
  • Page 445 DA20-A1 AMM Navigation and Pitot Static Maintenance Information With the exception of the drain system the Pitot and static system is maintenance free. The Pitot head should be covered when the airplane is parked outside. After working on the Pitot static system, it must be checked in accordance with the table below.
  • Page 446 Navigation and Pitot Static DA20-A1 AMM Pitot Static Test Airspeed Indicator Leakage : At 150 kts max. loss off pressure 10 kts/min. Indication Error : At 150 kts max. tolerance = 4.5 kts. At 45 kts max. tolerance = 1.5 kts.

  • Page 447: Stall Warning System

    DA20-A1 AMM Navigation and Pitot Static STALL WARNING SYSTEM Description The airplane is equipped with a stall warning system as part of the standard equipment. The sensor works pneumatically and is located in the left wing. The stall warning system should warn the pilot acoustically using a horn, shortly before reaching the maximum angle of attack.
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  • Page 449: Attitude And Direction

    DA20-A1 AMM Navigation and Pitot Static ATTITUDE AND DIRECTION General This section describes the equipment indicating attitude and flight direction. All equipment is gyro driven, with the exception of the magnetic compass. Description Magnetic Compass The magnetic compass indicates the heading of the airplane relative to magnetic north. It is installed at the top of the instrument panel.
  • Page 450 DA20-A1 AMM Navigation and Pitot Static Attitude Gyro The attitude gyro shows the airplane's attitude in relation to the earth's surface. Any movement about the pitch axis and the roll axis is displayed. The attitude gyro consists of an electrically powered, gimbal mounted gyro. The gyro axis is perpendicular to the earth's surface.
  • Page 451 DA20-A1 AMM Navigation and Pitot Static Removal and Installation Magnetic Compass (1) Removal (a) Remove bolts and nuts from support. (b) Remove compass from support. (2) Installation (a) For installation reverse the sequence. NOTE: Only brass or other non magnetic bolts and nuts may be used to attach the compass.
  • Page 452 DA20-A1 AMM Navigation and Pitot Static (e) Check friction of movable indicator by approaching the instrument with a small magnet. The indicator must move freely in the display plane. Start engine and switch radio ON. (g) Align the airplane with magnetic north and equalize deviations with compensation magnets.

  • Page 453: Position Determining Systems

    DA20-A1 AMM Navigation and Pitot Static POSITION DETERMINING SYSTEMS General The factory installed navigation system of the DA20-A1 includes the following systems. Refer to Figure 4. Figure 4 - VHF NAV Equipment Positions 34-50-00 DA201-A1 Page 1 20 Apr 10...
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  • Page 455 DA20-A1 AMM Structures CHAPTER 51 STRUCTURES 51-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 457 DA20-A1 AMM Structures TABLE OF CONTENTS Subject CH-SE-SU Page STANDARD PRACTICES - STRUCTURES ....... 51-00-00 ..1 General.
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  • Page 459: Standard Practices - Structures

    The DA20-A1 is a low wing airplane in full composite construction. The fuselage consists of a self supporting glass fiber skin in semi monocoque construction with bulkheads and stiffeners. The single engine cantilever type monoplane is equipped with a T tail. The DA20-A1 has a fixed tricycle landing gear with trailing nose wheel.

  • Page 460: Inspection Techniques

    Structures DA20-A1 AMM Fuselage skin bulkheads & stiffeners rudder fin rudder Horizontal Stabilizer horizontal stabilizer elevator Inspection Techniques There are different methods of inspecting a damaged composite area. The following gives the procedures for inspecting a damaged Fiber Reinforced Plastic (FRP) area.
  • Page 461 DA20-A1 AMM Structures Coin Tap Test Damage to the laminate can be detected by tapping a coin on the laminate. The sound of tapping will change its frequency as you move over the damaged area in relation to the sound of other areas of corresponding thickness.
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  • Page 463: Repair Of Composite Parts

    DA20-A1 AMM Structures REPAIR OF COMPOSITE PARTS Approved Material, Suppliers Resin and Hardner Supplier: Scheufler, D-70327 Stuttgart Resin: L160 (100 parts by weight) Hardener: H163 (28 parts by weight) Resin: L285 (100 parts by weight) Hardener: H286 (40 parts by weight)
  • Page 464 Structures DA20-A1 AMM Product Part Number/Description Manufacturer Supplier PVC Rigid Foam H060 Divinycell Divinycell Stochem 106 Summerlea Road Aerosil Aerosil 200 Brampton, ON, L6T 4X3, Canada Ashland Chemical Canada Microbaloons 10515 Rue Notre-Dame Motreal, PQ H1B 2V1 Quarry Hill Foundry Supplies...

  • Page 465: Damage Classifications

    DA20-A1 AMM Structures Product Part Number/Description Manufacturer Supplier Paint Steel Guard FM 585 Clear Coat 432-0303 Hardener N39/1327 (use for clear coat only) PRC-Desoto International Fire Retardant Hein-Sass-Weg 29 Desothane HS Buffable PPG Aerospace Paint D-21129 Hamburg- Clear Coat 9008B900D...

  • Page 466: Defect Limits For Composites

    Defect Limits for Composites Diamond Aircraft has established defect limits for inspection of composite airframe components. Defects meeting these limits are not expected to propagate significantly beyond these limits prior to the next scheduled inspection.

  • Page 467: Fuselage Layup

    DA20-A1 AMM Structures Delamination and disbond from core: No delamination or disbond from core greater than 15 mm in diameter. No 2 delaminations or disbonds from core larger than 10 mm diameter within 100 mm of each other. No delaminations or disbonds from core in the following critical areas:...
  • Page 468 Structures DA20-A1 AMM ITEM DESCRIPTION PART NO./SUPPLIER DIMENSIONS (mm) Core, Fuselage 20-5360-04-01 Core, Cabin Lower-RH 20-5360-04-02 Core, Cabin Upper-RH 20-5360-04-03 Core, Cabin Lower-LH 20-5360-03-02 Core, Cabin Upper-LH 20-5360-03-03 Interglas 1 x 92145 0 Interglas 1 x 92125 ± 45 Interglas 1 x 92125 ±...
  • Page 469 DA20-A1 AMM Structures Figure 1 - Fuselage Layup 51-10-00 DA201-A1 Page 7 18 Jun 12 Rev 15...
  • Page 470 Structures DA20-A1 AMM Figure 2 - Fuselage Layup 51-10-00 Page 8 DA201-A1 18 Jun 12 Rev 15...
  • Page 471 DA20-A1 AMM Structures Figure 3 - Fuselage Layup 51-10-00 DA201-A1 Page 9 18 Jun 12 Rev 15...
  • Page 472 Structures DA20-A1 AMM Figure 4 - Fuselage Layup 51-10-00 Page 10 DA201-A1 18 Jun 12 Rev 15...
  • Page 473 DA20-A1 AMM Structures Figure 5 - Fuselage Layup 51-10-00 DA201-A1 Page 11 18 Jun 12 Rev 15...

  • Page 474: Gfrp Repair

    Structures DA20-A1 AMM GFRP Repair When the airplane is damaged, proceed as follows: Carefully visually inspect the surface and damaged area, then classify the damage as per section two of this subchapter. Often other parts are affected as well. Occasionally the crack continues invisibly under the surface.

  • Page 475: Sandwich Repair

    DA20-A1 AMM Structures Sandwich Repair Minor Surface Damage The laminate may have unbonded from the rigid foam around the area of a crack. The affected area is determined by tap testing. Remove the loose laminate using a sanding disk, a sanding block, or a sharp knife.

  • Page 476: Laminate Repair

    Structures DA20-A1 AMM After the laminate is pre hardened at room temperature and has been chamfered, the protruding rigid foam is sanded down so it is flush with the exterior contour. The repair area must then be cleaned as follows: (a) Remove sanding dust with vacuum and avoid the use of pressurized air.

  • Page 477: Spar Repair

    DA20-A1 AMM Structures After initial hardening at room temperature, the damaged area must be cured in accordance with the prescribed temperature cycle (15 hrs. at 60 °C / 140 °F). After the area is completely hardened, it may be sanded and painted.
  • Page 478 Structures DA20-A1 AMM Painting When the laminate in the repair area is hardened and cured, sand the area with number 80 sanding paper to remove the major unevenness. Smaller unevenness are primed. Then use number 150 or 320 sanding paper to create a uniform rough surface. Clear the repair area from dust, parting compounds, and other foreign substances.

  • Page 479: Repair Of Metal Parts

    DA20-A1 AMM Structures REPAIR OF METAL PARTS General Steel Fittings Repairs of metal fittings should only be performed after consulting the manufacturer. If welding is required, it must be performed with a TIG (Tungsten Inert Gas) welder, 1.7734.2 (for 1.7734.4) and 1.7324.0 (for St 35 BK or combinations of 1.7734.4 and St 35 BK) must be used as welding additives.
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  • Page 481 Doors DA20-A1 AMM CHAPTER 52 DOORS 52-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 483 DA20-A1 AMM Doors TABLE OF CONTENTS Subject CH-SE-SU Page CANOPY............52-00-00 ..1 General.
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  • Page 485: Canopy

    General Refer to Figure 1. The DA20-A1 is equipped with a single piece lifting canopy with a frame fabricated of glass fiber laminate and rovings. To provide a generous all around view, an acrylic glass window is installed. It is held by screws and a bonding.

  • Page 486: Maintenance Information

    Doors DA20-A1 AMM Troubleshooting The following table lists defects as they could appear on the canopy system, and their correction. COMPLAINT POSSIBLE CAUSE REMEDY Canopy jams Misaligned locking shoes or Realign locking rod Emergency window is hard to Unclean or defective guides...

  • Page 487: Remove/Install The Canopy

    DA20-A1 AMM Doors Remove/Install the Canopy CAUTION: TWO PEOPLE WILL BE NEEDED TO REMOVE/INSTALL THE CANOPY. THE CANOPY WILL BE DAMAGED IF YOU DROP IT. Remove the Canopy Detail Steps/Work Items Key Items/References Open the canopy. Remove the screw located on the upper guide Hold the canopy.

  • Page 488: Remove/Install The Emergency Windows

    Doors DA20-A1 AMM Remove/Install the Emergency Windows Remove the Emergency Window Detail Steps/Work Items Key Items/References Remove the upper window guide. Lift window from the lower window guide. Install the Emergency Window Detail Steps/Work Items Key Items/References Place the window to the lower window guide.

  • Page 489: The Canopy Latch Force Test

    DA20-A1 AMM Doors The Canopy Unlatch Force Test Refer to Figure 2. NOTE: Do the test of the locking mechanism when the canopy and/or canopy components which can affect the adjustment are removed or installed Equipment Item Quantity Part Number...
  • Page 490 Doors DA20-A1 AMM Detail Steps/Work Items Key Items/References Install the aft locking pin on the LH side. Repeat Steps 5 through 10 for the RH side. Make sure that the Emergency Lever is in the closed position during this operation...

  • Page 491: Door Warning Annunciation Check

    If required, do rework per Repair Instruction R20-56-006 (latest revision). NOTE: Contact Diamond Aircraft Industries, Customer Support for the latest revision of Repair Instruction R20-56-006. Repeat Steps 2 and 3 for the RH side. Turn the Master Switch (GEN/BAT) to OFF.
  • Page 492 Doors DA20-A1 AMM Figure 2 - Canopy Locking Mechanism 52-00-00 Page 8 DA201-A1 06 Jan 21 Rev 16...

  • Page 493: Fuselage

    DA20-A1 AMM Fuselage CHAPTER 53 FUSELAGE 53-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 495 DA20-A1 AMM Fuselage TABLE OF CONTENTS Subject CH-SE-SU Page FUSELAGE............53-00-00 ..1 General.
  • Page 496 Fuselage DA20-A1 AMM Intentionally Left Blank 53-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 497 FUSELAGE General The DA20-A1 fuselage is of semi-monocoque construction. The self supporting GFRP-fuselage is reinforced with bulkheads and stiffeners. The number of orientation of the layers corresponds to the loads in the individual sections. Therefore the fuselage skin has different thickness and fiber orientations.
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  • Page 499: Main Frame

    The bulkheads and stiffeners are of different shape. They are fabricated from glass fiber laminate. Firewall The firewall of the DA20-A1 separates the engine compartment from the rest of the fuselage. It is fabricated from glass fiber laminate. For fire protection, the front side of the firewall is covered with heat resistant protective texture as well as with stainless sheet steel.
  • Page 500 Fuselage DA20-A1 AMM Aft Control Bulkhead The aft control bulkhead is bonded to the fuselage lower skin and the spar bridge. The aft control bulkhead is fabricated of glass fiber laminate. In its center area it is formed into a U-profile, where further fittings and bellcranks for the aileron and wing flap controls are attached.
  • Page 501 DA20-A1 AMM Fuselage Paint Application Procedure for the Aircraft Belly The following maintenance practices describe how to do a high temperature paint repair of the area underside of the aircraft flight compartment, aft of the engine. High Temperature Paint Repair of the Fuselage - with Steel Guard FM 585...
  • Page 502 Fuselage DA20-A1 AMM Detail Steps/Work Items Key Items/References Prepare the area(s) of the fuselage for the For approved materials and suppliers, refer application of the high temperature paint, as to Chapter 51-00. follows: - If dirt or grease is present, wash the area with clean carbon tetrachloride or acetone.
  • Page 503 DA20-A1 AMM Fuselage Detail Steps/Work Items Key Items/References Apply the first coat of fire resistant paint with a For approved materials and suppliers, refer splatter spray gun, a brush or a roller to a to Chapter 51-00. minimum thickness of 0.010 in (250 microns).
  • Page 504 Fuselage DA20-A1 AMM Detail Steps/Work Items Key Items/References Apply the two cross coats to achieve the Film thickness: required thickness. For the first coat: 25 microns For the second coat: 35 microns. Total thickness: 60 microns (0.002 in or 2.3 mil)
  • Page 505 DA20-A1 AMM Fuselage High Temperature Paint Repair of the Fuselage - with Hensotherm 2 KS Detail Steps/Work Items Key Items/References Remove the cowling. Refer to the AMM, Section 71-10. Carefully examine the fuselage and identify the At each step of the repair, complete all area(s) that require(s) repair.
  • Page 506 Fuselage DA20-A1 AMM Detail Steps/Work Items Key Items/References Prepare the area(s) of the fuselage for the For approved materials and suppliers, refer application of the high temperature paint, as to Chapter 51-00. follows: - If dirt or grease is present, wash the area with clean carbon tetrachloride or acetone.
  • Page 507 DA20-A1 AMM Fuselage Detail Steps/Work Items Key Items/References Mix the paint by agitating before use. For approved materials and suppliers, refer to Chapter 51-00. Apply the first coat of paint with a splatter spray Make sure that the painting is done in a gun (preferred), brush, or roller to a weight of dust free area.
  • Page 508 Fuselage DA20-A1 AMM Detail Steps/Work Items Key Items/References Let the top coat dry, in a dust free area. The following drying times refer to a normal climate of 23 ºC and 50% humidity: - Full cure: 24 hours. NOTE: A minimum of 48 hrs cure is recommended before flying.

  • Page 509: Inspection Holes

    INSPECTION HOLES General The DA20-A1 fuselage has four inspection holes. Their covers are fitted to the surface of the fuselage and are installed either with self-tapping screw or quick lock fasteners. The openings enable visual inspection and access to components and connections.
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  • Page 511: Stabilizers

    DA20-A1 AMM Stabilizers CHAPTER 55 STABILIZERS 55-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 513 DA20-A1 AMM Stabilizers TABLE OF CONTENTS Subject CH-SE-SU Page STABILIZERS............55-00-00 ..1 General.
  • Page 514 Stabilizers DA20-A1 AMM Intentionally Left Blank 55-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 515 STABILIZERS General The tail plane of the DA20-A1 consists of the horizontal stabilizer, elevator including Anti Servo Tab, vertical stabilizer, and rudder. This chapter describes only the horizontal stabilizer, elevator and rudder. The structural design is described in this chapter, while Chapter 27 describes removal and installation of the control surfaces.
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  • Page 517: Horizontal Stabilizer

    DA20-A1 AMM Stabilizers HORIZONTAL STABILIZER General Attached to the horizontal stabilizer is the elevator with the Anti Servo Tab located in the middle. Description The horizontal stabilizer is attached to the lower tail fin rib with a metal fitting and four bolts. A second mounting point is located near the leading edge of the horizontal stabilizer.
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  • Page 519: Elevator

    DA20-A1 AMM Stabilizers ELEVATOR General The elevator control system provides control of the aircraft's pitch axis. For maintenance information, refer to sub-chapter 27-30. This chapter describes only the elevator structure. Description The half shells of the elevator are constructed using PVC rigid foam, which is sandwiched between layers of GFRP.
  • Page 520 DA20-A1 AMM Stabilizers Install the Elevator Detail Steps/Work Items Key Items/References Put the elevator in position on the horizontal Use 2 persons. stabilizer. Install the five hinge bolts. There are two bolts outboard at each side and one center bolt through the control horn.
  • Page 521 DA20-A1 AMM Stabilizers Figure 1 - Elevator Structure 55-20-00 DA201-A1 Page 3 18 Jun 12 Rev 15...
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  • Page 523: Rudder

    DA20-A1 AMM Stabilizers RUDDER General The conventionally designed DA20-A1 rudder allows flight control of the airplane about the vertical axis. For maintenance information, refer to Chapter 27-20-30. This chapter describes only the rudder structure. Description The symmetrical half shells of the rudder are manufactured of PVC rigid foam covered on both sides.
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  • Page 525: Wings

    DA20-A1 AMM Wings CHAPTER 57 WINGS 57-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 526 Wings DA20-A1 AMM Intentionally Left Blank 57-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 527 DA20-A1 AMM Wings TABLE OF CONTENTS Subject CH-SE-SU Page WINGS ............57-00-00 ..1 General.
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  • Page 529 WINGS General The wing assembly of the DA20-A1 is a low wing monoplane design, and consists of two cantilever wings with ailerons and wing flaps. The wings are of semi monocoque sandwich construction. For removal and installation of the wing flaps refer to Chapter 27. The structure is described in this chapter.
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  • Page 531: Wing Structure

    Wings WING STRUCTURE General The DA20-A1 is a low wing monoplane design, using conventional ailerons and wing flaps. Description The cantilever wings of the DA20-A1 are of semi monocoque sandwich construction. An I-spar with caps constructed of carbon fiber is the base of the wing construction. The spar stumps reach to the middle of the fuselage.
  • Page 532 Wings DA20-A1 AMM (e) Extract main bolt. Carefully remove the wing from the spar bridge, observing and disconnecting the electrical harness located at the root for the lights installed at the wing tips. When removing the left wing, observe and disconnect the Pitot, static, and stall warning system lines.
  • Page 533 DA20-A1 AMM Wings Figure 2 - Properly Secured Bolt 57-10-00 DA201-A1 Page 3 20 Apr 10 Rev 13...
  • Page 534 Wings DA20-A1 AMM Figure 3 - Properly Secured Main Bolts 57-10-00 Page 4 DA201-A1 20 Apr 10 Rev 13...
  • Page 535 DA20-A1 AMM Wings Bolt Play Radial Play The wing connection bolts are not sensitive to axial or radial play. However, values given in the table below should not be exceeded. A-bolt in spherical bearing 0.08 mm 0.003" B-bolt in spherical bearing 0.08 mm...
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  • Page 537: Wing Flaps

    DA20-A1 AMM Wings WING FLAPS General The DA20-A1 is equipped with electrically operated wing flaps which are attached to the wings with hinges. This sub-chapter only describes the structure. For removal and installation refer to Chapter 27 50. Description The wing flaps are of semi monocoque sandwich construction consisting of PVC rigid foam and glass and carbon fiber layers.
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  • Page 539: Ailerons

    AILERONS General The DA20-A1 is equipped with one aileron on each wing, operated by push rods. This sub-chapter only describes the structure and the removal and installation of the ailerons. For a systems description as well as for removal and installation procedures of the aileron controls refer to Chapter 27 10.
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  • Page 541: Propeller

    DA20-A1 AMM Propeller CHAPTER 61 PROPELLER 61-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 542 Propeller DA20-A1 AMM Intentionally Left Blank 61-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 543 DA20-A1 AMM Propeller TABLE OF CONTENTS Subject CH-SE-SU Page PROPELLER ............61-00-00 ..1 General.
  • Page 544 Propeller DA20-A1 AMM Intentionally Left Blank 61-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 545 PROPELLER General The HO-V352F Hoffmann Propeller is used for the DA20-A1. It has a hydraulic infinitely variable pitch adjustment controlled by a propeller governor. When the desired propeller speed is preselected, the governor automatically keeps the speed at a constant value, regardless of manifold pressure and airspeed.
  • Page 546 Propeller DA20-A1 AMM Spinner Assembly The spinner assembly consists of a spinner mount and a spinner dome, which are connected with screws. The spinner dome is supported in front of the propeller by a guide plate. Troubleshooting NOTE: Any maintenance performed on the propeller, MUST be performed in accordance to the propeller manufacturers documentation.
  • Page 547 DA20-A1 AMM Propeller COMPLAINT POSSIBLE CAUSE REMEDY Surging RPM Wrong speeder spring in the Check governor designation governor with Airplane Type Certification Data Sheet. Speeder spring in the governor Periods of surging with low too weak amplitude are acceptable. If governor does not stabilize then repair.
  • Page 548 Propeller DA20-A1 AMM COMPLAINT POSSIBLE CAUSE REMEDY Pitch change extremely Clogged oil lines between Clean lines. sluggish after movement of governor and propeller propeller speed control lever NOTE: This kind of malfunction and/or RPM changes with does not appear abruptly. The...
  • Page 549 DA20-A1 AMM Propeller Installation Procedure NOTE: Propeller installation may only be carried out by authorized personnel and must be checked immediately after completion. Any maintenance must be performed in accordance with the propeller manufacturer's documentation. (a) Clean the propeller and engine flange with suitable cleaning agent. The torque is transmitted through friction;...
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  • Page 551: Power Plant

    DA20-A1 AMM Power Plant CHAPTER 71 POWER PLANT (ENGINE) 71-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 552 Power Plant DA20-A1 AMM Intentionally Left Blank 71-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 553 DA20-A1 AMM Power Plant TABLE OF CONTENTS Subject CH-SE-SU Page POWER PLANT ........... . . 71-00-00 ..1 General.
  • Page 554 Power Plant DA20-A1 AMM Intentionally Left Blank 71-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 555 POWER PLANT General Refer to Figure 1. This chapter describes the engine installed in the DA20-A1, its external units, removal and installation, as well as troubleshooting procedures. For maintenance or overhaul of the engine refer to the engine manufacturer's documentation. For operation refer to the Operator's Manual.
  • Page 556 DA20-A1 AMM Description The engine installed in the DA20-A1 is a ROTAX 912 A3 (S/N 10002through 10092) or 912 F3 (S/N 10093 and subsequent and aircraft with Service Bulletin DA20-73-01 incorporated) with a take-off performance of 80 hp at 5800 RPM. (engine speed). The engine installed in the DA20/100-A1 is a ROTAX 912 S3 with a take-off performance of 100 hp at 5800 RPM (engine speed).
  • Page 557 DA20-A1 AMM Power Plant Engine Specifications RPMs are propeller speeds, crankshaft speeds in parentheses. ROTAX Model A3 and F3. ITEM DATA Take off performance 59.6 kW (80 hp) Take off RPM 2550 RPM (5800 RPM) Max. continuous power 56 kW (78 hp)
  • Page 558 Power Plant DA20-A1 AMM RPMs are propeller speeds, crankshaft speeds in parentheses. ROTAX Model S3. ITEM DATA Take off performance 73.5 kW (100 hp) Take off RPM 2385 RPM (5800 RPM) Max. continuous power 69 kW (92 hp) Idle RPM minimum, DA20/100...
  • Page 559 DA20-A1 AMM Power Plant Starter The starter is attached to the engine and is located on the right hand side, at the rear of the engine. The starter pinion is pushed forward during the start phase to engage into the ring gear. With the engine running, the starter pinion is retracted by centrifugal force.
  • Page 560 Power Plant DA20-A1 AMM Spark plugs The approved spark plug for A3 and F3 model is type is NGK 12 DCPR7E. The approved spark plug for the S3 model is type NGK 12. DCPR8E. Troubleshooting The following table lists defects as they could appear on the engine, and their correction.
  • Page 561 DA20-A1 AMM Power Plant COMPLAINT POSSIBLE CAUSE REMEDY Engine does not start Internal engine damage Inspect magnetic plugs and oil (continued) filter for metal particles; in case of presence, repair engine. refer to the engine manufacturer’s documentation. Engine idles unsteadily after...
  • Page 562 Power Plant DA20-A1 AMM COMPLAINT POSSIBLE CAUSE REMEDY Engine runs too hot, oil Defective bearings If there are metal particles on temperature exceeds 140 °C the magnetic engine plugs or in (continued) oil filter, overhaul engine. Refer to the engine manufacturer’s documentation.
  • Page 563 DA20-A1 AMM Power Plant COMPLAINT POSSIBLE CAUSE REMEDY Post ignition Idle speed too high Adjust to 950 RPM Defective ignition switch Check ground connections, overhaul switch Overheated engine Allow engine to cool off at 950 Excessive oil consumption Worn, broken, or improperly...
  • Page 564 Power Plant DA20-A1 AMM Removal and Installation Engine (1) Removal NOTE: In many cases it is better to remove the engine together with the engine mount from the firewall. The following is a description of such task. WARNING: BEFORE REMOVING THE ENGINE, DISCONNECT THE BATTERY AND...
  • Page 565 DA20-A1 AMM Power Plant (2) Installation (a) For installation reverse the sequence. (b) Prime lubrication system, follow Rotax Service Instruction SI-912-005. CAUTION: TO PREVENT ENGINE DAMAGE, BEFORE THE INITIAL STARTING OF THE ENGINE, ENSURE THE OIL RADIATOR AND OIL LINES ARE FILLED WITH THE APPROPRIATE GRADE OF MOTOR OIL.
  • Page 566 Power Plant DA20-A1 AMM Reduction Gear Checks (1) Backlash The propeller can be turned easily by hand by approximately 30°. While turning there should not be any abnormal noises or resistance. (2) GEARBOX FRICTION CHECK (Refer to Figure 2) To be performed every 100 hrs. There should be a friction of 15 to 45 Nm (130 in.lbs to 400 in.lbs) within the range of the backlash, which should be checked using a spring scale...
  • Page 567 DA20-A1 AMM Power Plant (3) Overload Clutch The overload clutch should only be checked if there is suspicion of clutch malfunction. The overload clutch is adjusted to a torque of 400 to 500 Nm (295 to 369 lbs.ft.) by the manufacturer.
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  • Page 569: Cowling

    COWLING General The DA20-A1 aircraft has two cowlings. It has a top cowling and a bottom cowling. The two halves attach to the airframe with camlock fasteners. The top cowling has a left and a right air intake. It also has an inspection panel to give you access to the engine oil dipstick.
  • Page 570 Power Plant DA20-A1 AMM Install the Cowlings Detail Steps/Work Items Key Items/References Inspect the cowlings for damage. Look especially for damage to the camlock fasteners Put the bottom cowling in position on the bottom of the aircraft. - Lock the camlock fasteners.
  • Page 571 DA20-A1 AMM Power Plant High Temperature Paint Repair of a Cowling - with Steel Guard FM 585 NOTE: An equivalent procedure can be used to repair damage in the area underside of the aircraft flight compartment, aft of the engine. This area is a fixed part of the aircraft structure.
  • Page 572 Power Plant DA20-A1 AMM Detail Steps/Work Items Key Items/References Prepare the area(s) of the cowling for the For approved materials and suppliers, refer application of the high temperature paint, as to Chapter 51-00. follows: - If dirt or grease is present, wash the area with clean carbon tetrachloride or acetone.
  • Page 573 DA20-A1 AMM Power Plant Detail Steps/Work Items Key Items/References Apply the first coat of fire resistant paint with a For approved materials and suppliers, refer splatter spray gun, a brush or a roller to a to Chapter 51-00. minimum thickness of 0.010 in (250 microns).
  • Page 574 Power Plant DA20-A1 AMM Detail Steps/Work Items Key Items/References Allow it to dry for 30 to 45 minutes and apply the second coat. Apply the two cross coats to achieve the Film thickness: required thickness. For the first coat: 25 microns For the second coat: 35 microns.
  • Page 575 DA20-A1 AMM Power Plant High Temperature Paint Repair of a Cowling - with Hensotherm 2 KS NOTE: An equivalent procedure can be used to repair damage in the area underside of the aircraft flight compartment, aft of the engine. This area is a fixed part of the aircraft structure.
  • Page 576 Power Plant DA20-A1 AMM Detail Steps/Work Items Key Items/References Prepare the area(s) of the cowling for the For approved materials and suppliers, refer application of the high temperature paint, as to Chapter 51-00. follows: - If dirt or grease is present, wash the area with clean carbon tetrachloride or acetone.
  • Page 577 DA20-A1 AMM Power Plant Detail Steps/Work Items Key Items/References Mix the paint by agitating before use. For approved materials and suppliers, refer to Chapter 51-00. Apply the first coat of paint with a splatter spray Make sure that the painting is done in a gun (preferred), brush, or roller to a weight of dust free area.
  • Page 578 Power Plant DA20-A1 AMM Detail Steps/Work Items Key Items/References Let the top coat dry, in a dust free area. The following drying times refer to a normal climate of 23 ºC and 50% humidity: - Full cure: 24 hours. NOTE: A minimum of 48 hrs cure is recommended before flying.

  • Page 579: Mounts

    DA20-A1 AMM Power Plant MOUNTS General Refer to Figure 3. The engine is mounted to the airframe via the engine mount and the shock mounts. The engine mount consists of a welded steel bar frame which is mounted to the firewall using bolts and self locking nuts.
  • Page 580 DA20-A1 AMM Power Plant Figure 3 - Engine Mount 71-20-00 Page 2 DA201-A1 20 Apr 10 Rev 13...

  • Page 581: Air Intakes And Guides

    DA20-A1 AMM Power Plant AIR INTAKES AND GUIDES General A ram air guide made of GFRP is installed on the engine to ensure optimal engine cooling. Description The air guide is designed to follow the contours of the engine block and cylinders. The exact fitting makes attachment screws unnecessary.
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  • Page 583: Engine Cooling

    DA20-A1 AMM Engine Cooling CHAPTER 75 ENGINE COOLING 75-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 585 DA20-A1 AMM Engine Cooling TABLE OF CONTENTS Subject CH-SE-SU Page ENGINE COOLING........... 75-10-00 ..1 General.
  • Page 586 Engine Cooling DA20-A1 AMM Intentionally Left Blank 75-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...

  • Page 587: Engine Cooling

    DA20-A1 AMM Engine Cooling ENGINE COOLING General The engine cooling is performed using two different systems. Ram air guided by a duct is used to cool the cylinders, while the cylinder heads are liquid cooled. The cylinder head cooling system consists of a coolant pump, radiator, dispatcher vessel, and an equalizing reservoir.
  • Page 588 Engine Cooling DA20-A1 AMM Dispatcher Vessel Figure 2 - Dispatcher Vessel Equalizing Reservoir Clamps Figure 3 - Equalizing Reservoir 75-10-00 Page 2 DA201-A1 06 Jan 21 Rev 16...
  • Page 589 DA20-A1 AMM Engine Cooling Replenishing For replenishing, refer to Sub-Chapter 12-10. Removal and Installation Dispatcher Vessel Refer to Figure 2. (1) Removal (a) Remove all hoses connected to dispatch vessel. (b) Remove dispatcher vessel. (2) Installation (a) For installation, reverse the sequence.
  • Page 590 Engine Cooling DA20-A1 AMM Equalizing Reservoir Refer to Figure 3. (1) Removal (a) Remove all hoses connected to reservoir. (b) Remove clamps securing reservoir, and remove. (2) Installation (a) For installation, reverse the sequence. Water Pump (1) Removal and Installation Refer to Engine Manufacturers documentation.

  • Page 591: Engine Controls

    DA20-A1 AMM Engine Controls CHAPTER 76 ENGINE CONTROLS 76-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 593 DA20-A1 AMM Engine Controls TABLE OF CONTENTS Subject CH-SE-SU Page ENGINE CONTROLS ..........76-10-00 ..1 General.
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  • Page 595: Engine Controls

    Engine Controls DA20-A1 AMM ENGINE CONTROLS General The engine is controlled with: throttle and the choke control levers carburetor heat lever and propeller speed control lever. Bowden cables are used for the transmission of control movements. The bowden cables are sealed with a fire resistant compound as they pass through the firewall.
  • Page 596 This lever defines the control point by means of a slide valve. Refer to figure 5. Throttle Quadrant Friction Control In the DA20-A1, the lever motion for throttle and propeller speed can be arrested by turning the black knob on the left hand side of the center console in a clockwise direction. The arresting is performed by clamping the friction washers installed on the lever axis.
  • Page 597 Engine Controls DA20-A1 AMM Removal and Installation, Adjustment Throttle Control Bowden Cables Effective for aircraft serial # 10002 to 10300 (1) Removal (a) Remove engine cowlings. Refer to Sub Chapter 71-10 (b) Remove instrument panel cover. Refer to sub-Chapter 31-10 (c) Disconnect bowden cable clamps on carburetors.
  • Page 598 Engine Controls DA20-A1 AMM Figure 1a (2) Installation (a) Insert the new inner cables from the throttle quadrant end. (b) Tighten the throttle cable retaining hardware until the cable eyelets do not rotate independently of each other. Back off the nut by 3/4 of a turn. The Cable eyelets should rotate freely and independently of each other.
  • Page 599 Engine Controls DA20-A1 AMM Figure 1b (g) Move the throttle arm on the carburetor to the idle stop (it may be easier to remove the spring on the throttle arm). While gently pulling the inner throttle cable forward and holding the throttle lever to idle stop, tighten the throttle arm swivel. Lubricate the swivel with Aeroshell Grease 5.
  • Page 600 Engine Controls DA20-A1 AMM Figure 1c (3) Adjustment Refer to Figure 2a and Figure 2b. To perform the initial idle speed adjustment, the idle speed adjustment screws must be turned back until the throttle valves have reached their limit position within the carburetors. Then the adjustment screws should be turned clockwise until a clearance of 0.004 in (0.1 mm) has been...
  • Page 601 Engine Controls DA20-A1 AMM Choke Control Bowden Cable Idle Adjustment Lock Nuts Idle Adjustment Screw Throttle Lever Throttle Control Bowden Cable Figure 2a - Throttle Valve Adjustment Items 76-10-00 DA201-A1 Page 7 06 Jan 21 Rev 16...
  • Page 602 Engine Controls DA20-A1 AMM Idle Adjustment Screw Throttle Lever 0.004 ”(0.1 mm) Figure 2b - Throttle Valve Adjustment Item Choke Bowden Cables (1) Removal (a) Remove engine cowling. (b) Remove instrument panel cover. (c) Disconnect bowden cables from carburetors. (d) Disconnect bowden cables from parallel guide on center console.
  • Page 603 Engine Controls DA20-A1 AMM Carburetor Heat Bowden Cable (1) Removal (a) Remove engine cowling. (b) Disconnect bowden cable from flap actuating lever on air distribution box. Refer to Figure 3. (c) Remove instrument panel cover. (d) Disconnect bowden cable from carburetor heat knob.
  • Page 604 Engine Controls DA20-A1 AMM Propeller Speed Control Bowden Cable (1) Removal (a) Remove engine cowling. (b) Disconnect bowden cable from propeller governor. (c) Loosen mounting hardware of throttle quadrant on the center console, and remove RH rotary knob. (d) Remove throttle quadrant from center console in upward direction.
  • Page 605 Engine Controls DA20-A1 AMM Lever Figure 4 - Lever on Propeller Governor Throttle Quadrant Friction Control (1) Removal (a) Remove rotary knob on RH side of center console. (b) Remove washer springs and replace if required. (2) Installation (a) For installation reverse the sequence.
  • Page 606 Engine Controls DA20-A1 AMM Throttle Lever Propeller Speed Control Lever Friction Control knob Figure 5 - Throttle Quadrant 76-10-00 Page 12 DA201-A1 06 Jan 21 Rev 16...

  • Page 607: Engine Indicating

    DA20-A1 AMM Engine Indicating CHAPTER 77 ENGINE INDICATING 77-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 608 Engine Indicating DA20-A1 AMM Intentionally Left Blank 77-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 609 DA20-A1 AMM Engine Indicating TABLE OF CONTENTS Subject CH-SE-SU Page ENGINE INDICATING ..........77-00-00 ..1 General.
  • Page 610 Engine Indicating DA20-A1 AMM Intentionally Left Blank 77-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 611 Refer to Figures 1 and 2, in 31-10-00 for the locations of the instruments. Description RPM Indicator In the DA20-A1 the RPM indication is done by a mechanical system. The RPM indicated on the cockpit instrument is that of the propeller and NOT that of the engine. Fuel Pressure Warning Light The fuel pressure warning light is located in the center section of the instrument panel, and is activated by a pressure sensor located on the firewall.
  • Page 612 Engine Indicating DA20-A1 AMM Troubleshooting The following table lists defects as they could appear on the engine indicating system, and their correction. COMPLAINT POSSIBLE CAUSE REMEDY No RPM indication Defective flexible shaft Replace Defective RPM indicator Replace Incorrect RPM indication...
  • Page 613 DA20-A1 AMM Engine Indicating Removal and Installation NOTE: In order to gain access to the instruments, the instrument panel cover must first be removed. RPM Indicator (1) Removal (a) Disconnect flexible shaft from rear of instrument. (b) Remove nuts from mounting bracket.
  • Page 614 Engine Indicating DA20-A1 AMM Oil Temperature Indicator (1) Removal (a) Pull off connectors from rear of instrument. (b) Remove nuts from mounting bracket. (c) Remove instrument from panel. (2) Installation (a) For installation reverse the sequence. Cylinder Head Temperature Indicator (1) Removal (a) Pull off connectors from rear of instrument.

  • Page 615: Exhaust

    DA20-A1 AMM Exhaust CHAPTER 78 EXHAUST 78-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 617 DA20-A1 AMM Exhaust TABLE OF CONTENTS Subject CH-SE-SU Page EXHAUST ............78-00-00 ..1 General.
  • Page 618 Exhaust DA20-A1 AMM Intentionally Left Blank 78-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 619 DA20-A1 AMM Exhaust EXHAUST General Each of the engine cylinders is equipped with its own exhaust pipe leading to the underside of the engine, where they are attached to the muffler. To enable heat expansion of the exhaust system, the connections between muffler and pipes are movable and secured with two springs each.
  • Page 620 Exhaust DA20-A1 AMM Description Refer to Figure 1, Exhaust System and to Chapter 21-00-00, Figure 1 - Heating and Defrosting System. The exhaust pipes are fabricated of welded high-grade steel. They run from the cylinders to the underside of the engine where they are connected to the muffler. A heat exchanger surrounds the muffler.
  • Page 621 DA20-A1 AMM Exhaust Removal and Installation of the Exhaust System The following maintenance practices describe how to remove and install the exhaust system. WARNING: MAKE SURE THAT THE EXHAUST SYSTEM IS COOL BEFORE YOU DO WORK ON THE SYSTEM. THE EXHAUST SYSTEM CAN BE HOT. THIS MAY CAUSE INJURY.
  • Page 622 Double check all connections and clearances to ensure adequate clearance against rub from pipes to nearby components Perform an Engine Run-up Refer to DA20-A1 Airplane Flight Manual. - Do an exhaust system leak check. Install the cowlings. Refer to Chapter 71-10.
  • Page 623 DA20-A1 AMM Exhaust Inspection of Exhaust System The exhaust system should be inspected for leaks every 100 hours. The weld seams are especially susceptible to cracks through which dangerous carbon monoxide can enter the cabin. If there is suspicion of leakage, the cabin should be checked for contamination using a gas-detector apparatus.
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  • Page 625: Oil Systems

    DA20-A1 AMM CHAPTER 79 OIL SYSTEMS 79-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
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  • Page 627 DA20-A1 AMM TABLE OF CONTENTS Subject CH-SE-SU Page OIL SYSTEMS ............79-00-00 ..1 General.
  • Page 628 DA20-A1 AMM Intentionally Left Blank 79-TOC DA201-A1 Page 2 Rev 16 06 Jan 21...
  • Page 629 This chapter describes the lubrication system which is located outside of the engine. The DA20-A1 is equipped with an oil radiator attached to the engine mount on the right hand engine side and connected to the engine with oil lines. An opening in the lower engine cowling supplies ram air to the oil radiator.
  • Page 630 DA20-A1 AMM LEGEND 1. Oil Pump 6. Oil Feed Line 2. Oil Filter 7. Oil Radiator 3. Oil Temp. Sensor 8. Oil Return Line 4. Oil Tank 9. Oil Pressure Sensor 5. Oil Tank Venting Figure 1 - Oil Circuit...

  • Page 631: Oil Radiator

    DA20-A1 AMM OIL RADIATOR General The oil radiator is located on the lower right side of the engine, attached to the engine mount. The oil radiator has two threaded connection sleeves to which the oil lines are attached. The sleeves are also used to secure the radiator to the engine mount.
  • Page 632 DA20-A1 AMM Radiator Figure 2 - Oil Radiator (2) Installation (a) For installation reverse the sequence. NOTE: Use new locking plates. NOTE: In the event that the engine has to be disassembled due to metal particles detected during an oil filter change, the oil radiator must be flushed or replaced.

  • Page 633: Indicating

    DA20-A1 AMM INDICATING General The DA20-A1 is equipped with an oil pressure and an oil temperature sensor for monitoring the lubrication system. The oil temperature sensor is attached next to the oil filter, while the oil pressure sensor is located opposite of the oil filter.
  • Page 634 DA20-A1 AMM Removal and Installation Oil Temperature Sensor (1) Removal (a) Disconnect wiring. (b) Remove sensor using suitable tool. (2) Installation (a) For installation reverse the sequence. When installing a new seal, the sensor is to be turned until the torque increases perceptibly, and then by another 135° (3/8 revolutions).
  • Page 635 DA20-A1 AMM Oil Pressure Sensor Effective for aircraft serial number 10002 to 10144. (1) Removal (a) Disconnect wiring. (b) Remove sensor. (2) Installation (a) For installation reverse the sequence. When installing the sensor, a suitable sealing compound must be used (e.g. Crane pac Plastic Lead Seal No. 2).
  • Page 636 DA20-A1 AMM Oil Pressure Sensor Effective for aircraft serial number 10145 and subsequent and aircraft with service bulletin DA20-79-01 incorporated. (1) Removal Refer to Figure 5. (a) Disconnect wiring. (b) Remove the sensor. (2) Installation (a) Install the sensor. Use thread locker Loctite 592 or Sealube. Apply to male threads, keep holes clear.
  • Page 637 DA20-A1 AMM (3) Testing The oil pressure sensor changes its resistance with increase of pressure. It can be checked using the following table. Pressure Pressure Resistance [bar] [psi] 52 ± 4 88 ± 4 124 ± 5 155 ± 5 In the event that the sensor fails to reach these values, it must be replaced.
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  • Page 639: Wiring Diagrams

    Wiring Diagrams DA20-A1 AMM CHAPTER 92 WIRING DIAGRAMS 92-TITLE DA201-A1 Page 1 06 Jan 21 Rev 16...
  • Page 640 Wiring Diagrams DA20-A1 AMM Intentionally Left Blank 92-TITLE Page 2 DA201-A1 20 Apr 10 Rev 13...
  • Page 641 Wiring Diagrams DA20-A1 AMM TABLE OF CONTENTS PAGE 92-00-00 - WIRING DIAGRAMS General ........................... 3 List of Wiring Diagrams/Schematics ..................3 92-10-00 - SYSTEM WIRING DIAGRAMS/SCHEMATICS Electrical System - Sheet 1....................1 Electrical System - Sheet 2....................2 Electrical System - Sheet 3....................3 Electrical System - Sheet 4....................
  • Page 642 Wiring Diagrams DA20-A1 AMM PAGE NAV/COM - KX 125 .........................8 NAV/COM - KX 155 .........................9 GPS/COM - KLX 135A ......................10 NAV/COM - KX 155 .......................11 KX 125 - Package 01......................12 Intercom..........................13 Intercom - PM 501 with KX 125 .....................14 Audio Panel - KA 134 (with ADF) ..................15 Intercom - PM 501 with KLX 135A..................16...
  • Page 643 Wiring Diagrams DA20-A1 AMM WIRING DIAGRAMS General This Subject describes the Wiring Diagram/Schematic for each system installed on the DA20-A1 aircraft. The Wiring Diagrams/Schematics use the ATA Chapter/Section/Subject numbering system. List of Wiring Diagrams/Schematics. No. of CH-SE-SU Title Drawing No.
  • Page 644 Wiring Diagrams DA20-A1 AMM No. of CH-SE-SU Title Drawing No. Rev. # Sheets 92-30-00 AUDIO PANEL, KA 134 20-2350-02-00 92-30-00 INTERCOM, PM501 - With KLX 135A 20-2350-04-00 92-30-00 INTERCOM, PM2000 20-2350-06-00 92-30-00 AUDIO PANEL, KA 134 20-2350-08-00 92-30-00 AUDIO PANEL, KMA 24...
  • Page 645 DA20-A1 AMM Wiring Diagrams TB2400-05 24321A8N GS2400-03 ROTAX ENGINE ELECTRICAL MOUNTING PLATE 24321A8N GC2430-02 SS8010-03 24300A8 80102A4 24324A20N 24301A20N 24301A20N TB2400-03 80100A20 80100A20 24323A18N 24321A18 74300A20 74300A20 74301A20 VM2430-01 24302A20 TB2400-01 BB2430-02 24300A8 24308A8 24311A8 BB2430-01 AM2430-01 74301A20 80101A20 GRD.
  • Page 646 DA20-A1 AMM Wiring Diagrams J3340-01 SL3340-01 J3340-02 2 3 4 5 6 7 8 9 10 11 10 9 8 7 6 5 4 3 2 1 STROBE POWER SUPPLY P3340-09 P3340-07 33402A18Wh 33404A18Wh 33404A18bk 33402A18bk 33404A18rd 33416B14N 33402A18rd P2400-03...
  • Page 647 DA20-A1 AMM Wiring Diagrams J3310-01 P3310-01 INTERNAL LIGHT 33104A20 33101A20 TB2400-03 MAIN BUS #1 33111A20N TAXI/MAP 33109A20 CP3410-01 REF. SHT.1 33107A20 COMPASS R3310-01 33108A20N 33120A22 TB2400-03 33121A22N P3310-04 J3310-04 TRIM TB2400-05 DISPLAY R3310-02 P/N 20-2720-40-00 SPL1 LED1 33112A20 P2750-01 NIGHT...
  • Page 648 DA20-A1 AMM Wiring Diagrams Braided cable A600-PG-14 AILERON BELLCRANK 33423A14N J3340-02 P3340-02 WHITE P3340-05 J3340-05 GREEN 33416C14N 33405C14 33404C14N 33404B18rd 33404B18bk STROBE 33404B18wh CONDUIT NL3340-02 P3340-06 J3340-06 Effectivity SCHEMATIC SHEET ELECTRICAL SYSTEM 20-2400-01-00 92-10-00 Page 4 DA201-A1 06 Jan 21...
  • Page 649 DA20-A1 AMM Wiring Diagrams P3340-11 J3340-11 TAXI LIGHT TL3340-01 PITOT/STATIC PORT AILERON BELLCRANK J3340-10 P3340-10 LANDING LIGHT LL3340-01 Braided cable A600-PR-14 33422A14N J3340-01 P3340-01 WHITE 33410C16 33414C16N 33412C16 P3340-03 J3340-03 33415C16N 33417C14N 33400C14 33401C14N 33402B18rd 33402B18bk STROBE 33402B18wh CONDUIT NL3340-01...
  • Page 650 DA20-A1 AMM Wiring Diagrams WIRE CONNECTION L/H WIRE CONNECTION R/H (Ref.) (Ref.) J2400-04 J2400-05 23125B18 23500B22 23112B22WH DATA JACK MARKER 23126B18 23112B22BL 23141B18 23112B22OR IS2350-02 COM/NAV 1 23142B18 23100B18 23111B22WH COM/GPS 2 23101B18 23111B22BL 34500B22 23127B18N 23157B22 23511B22N 34755B22 23110B22N...
  • Page 651 DA20-A1 AMM Wiring Diagrams TB2400-05 ELECTRICAL MOUNTING PLATE 1A FUSE 24321A8N GS2400-03 TB2400-01 ROTAX ENGINE 80102A4 24321A8N GC2430-02 24300A8 SS8010-03 BB2430-02 24324A20N 24301A20N 24301A20N TB2400-03 80100A20 80100A20 24323A18N 24321A18 74300A20 74300A20 74301A20 VM2430-01 24302A20 24300A8 24308A8 24311A8 BB2430-01 AM2430-01 74301A20 80101A20 GRD.
  • Page 652 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET HOURMETER 20-2400-07-02 92-10-00 Page 8 DA201-A1 06 Jan 21 Rev 16...
  • Page 653 DA20-A1 AMM Wiring Diagrams Effectivity ELECTRICAL SYSTEM SCHEMATIC SHEET ALL - With SB Installed Advanced Starting System 20-9274-00-00 with Service Bulletin DA20-74-01 Installed 92-10-00 Page 9 DA201-A1 06 Jan 21 Rev 16...
  • Page 654 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET CABIN VENTILATION 20-2121-04-00 (OPTIONAL) 92-10-00 DA201-A1 Page 10 06 Jan 21 Rev 16...
  • Page 655 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET TRIM DISPLAY 20-2720-10-00 92-10-00 DA201-A1 Page 11 06 Jan 21 Rev 16...
  • Page 656 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET GPS/COM - KLX 135 20-2310-00-00 92-30-00 Page 1 DA201-A1 06 Jan 21 Rev 16...
  • Page 657 DA20-A1 AMM Wiring Diagrams IS2350-02 P2350-51 #1 NAV/COM 12 13 KX 125 P2310-11 (TOP PLUG) SPEAKER OUT HI 23113A22 23113A22 SPEAKER OUT LO REFERENCE PHONE OUT HI 23122A22 23122A22 AUDIO PHONE OUT LO 23123A22 INTERCOM MIC HI 23124A22 DRAWING AUX AUDIO IN...
  • Page 658 DA20-A1 AMM Wiring Diagrams KX 125 P2310-11 (TOP PLUG) SPEAKER OUT HI 34804A22bl SPEAKER OUT LO 34804A22wh REFERENCE PHONE OUT HI 23137A22wh AUDIO PHONE OUT LO 23137A22bl INTERCOM MIC HI 23138A22wh DRAWING AUX AUDIO IN 23138A22bl AUX AUDIO LO NAV AUDIO LO...
  • Page 659 DA20-A1 AMM Wiring Diagrams COM#1 TB2400-06 KLX 135A INTERNAL LIGHT P2310-02 34734A22 NC2310-02 (TOP PLUG) S3450-01 AVIONIC BUS LIGHTING LO 33104A20 28VDC/LIGHTING GND R3450-01 REF. 14VDC LIGHTING 34735A22 34736A22 A/C GND BRIGHT A/C GND A/C GND A/C GND 23110A22N 34509A22...
  • Page 660 DA20-A1 AMM Wiring Diagrams P2350-51 IS2350-02 12 13 KX 155 P2310-50 (TOP PLUG) SPEAKER OUT HI 23130A22 23130A22 SPEAKER OUT LO NAV AUDIO HI 34530A22 NAV AUDIO LO 34531A22 COMM AUDIO HI 23131A22 COMM AUDIO LO 23132A22 SUMMED AUDIO OUT...
  • Page 661 DA20-A1 AMM Wiring Diagrams TB2400-06 KX 155 IS 2350-01 PM 501 TOP PLUG P2310-50 P2350-01 23511A20N ICS BREAKER 23500A20 12 V DC SPEAKER HI 23113A22 23511A20N SPEAKER LO 23122A22 COM PHONE DME AUDIO HI 34757B22 34757A22WH REF. DME AUDIO 23123A22...
  • Page 662 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET VHF TRANSCEIVER 20-2310-06-00 AR 4201 92-30-00 DA201-A1 Page 7 06 Jan 21 Rev 16...
  • Page 663 DA20-A1 AMM Wiring Diagrams KX 125 P2310-11 (TOP PLUG) SPEAKER OUT HI 34804A22bl REFERENCE SPEAKER OUT LO 34804A22wh PHONE OUT HI 23137A22wh AUDIO PHONE OUT LO 23137A22bl INTERCOM MIC HI 23138A22wh DRAWING AUX AUDIO IN 23138A22bl AUX AUDIO LO NAV AUDIO LO...
  • Page 664 DA20-A1 AMM Wiring Diagrams 23177A22wh KX 155 23137A22bl REFERENCE 34533A22wh P2310-50 AUDIO 34533A22bl DRAWING (TOP PLUG) 23138A22wh A/C GND 23135A20N 23138A22bl G/S + UP 34530A22wh G/S + DOWN 34530A22bl G/S + FLAG 34531A22 G/S - FLAG 34532A22 P2310-51 (BOTTOM PLUG)
  • Page 665 DA20-A1 AMM Wiring Diagrams KLX 135A P2310-02 (TOP PLUG) LIGHTING LO 28VDC/LIGHTING GRN 14VDC LIGHTING 34735A22 A/C GND 23110A22N A/C GND A/C GND A/C GND 34509A22 34509A22 34508A22 34508A22 34507A22 34507A22 34506A22 34506A22 REFERENCE 34505A22 34505A22 TRANSPONDER 34504A22 34504A22 SYSTEM...
  • Page 666 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET NAV/COM, KX 155 20-2310-10-00 92-30-00 DA201-A1 Page 11 06 Jan 21 Rev 16...
  • Page 667 DA20-A1 AMM Wiring Diagrams PM501 P2350-01 23500A22 12 V DC POWER 23511A22N 23108A22 COM PHONE #1 NAV/COM 23109A22wh MIC AUDIO HI KX 125 23109A22Bl COM MIC KEY 23502A22 11 PILOT MIC HI P2310-11 23503A22 PILOT MIC HI (TOP PLUG) 23504A22...
  • Page 668 DA20-A1 AMM Wiring Diagrams AA 80 IS 2350-01 12 V DC 23500A20 23511A20N TB2400-05 KLX 135 P2310-01 COM PHONE 4 SPEAKER Hi COM MIC AUDIO 4 SPEAKER Lo COM MIC KEY 23502A22 PILOT MIC KEY 23503A22 PILOT MIC hi PHONES Hi...
  • Page 669 DA20-A1 AMM Wiring Diagrams PM 501 IS 2350-01 ICS BREAKER 12 V DC 23500A20 KX 125 TOP PLUG 23511A20N 15 GND TB2400-06 P2310-01 23122A22 COM PHONE 4 SPEAKER Hi 23113A22 23123A22 COM MIC AUDIO 4 SPEAKER Lo 23124A22 PILOT MIC KEY...
  • Page 670 DA20-A1 AMM Wiring Diagrams KA 134 P2350-02 23137A22bl COMM 1 AUDIO 23137A22wh 23137A22wh NAV 1 AUDIO 34804A22wh 34804A22wh REFERENCE 34804A22bl 34804A22bl COMM #1 COMM 1 MIC AUDIO 23138A22wh 23138A22wh COMM 1 KEY 23138A22bl 23138A22bl ADF AUDIO 34570A22 34570A22 ADF REFERENCE...
  • Page 671 DA20-A1 AMM Wiring Diagrams IS 2350-01 PM 501 ICS BREAKER 12 V DC 23500A20 KLX 135A BOTTOM PLUG TB2400-06 23511A20N 15 GND P2310-01 23122A22 COM PHONE 4 SPEAKER Hi 23113A22 23123A22 COM MIC AUDIO 4 SPEAKER Lo 23124A22 PILOT MIC KEY...
  • Page 672 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET INTERCOM, PM 2000 20-2350-06-00 92-30-00 DA201-A1 Page 17 06 Jan 21 Rev 16...
  • Page 673 DA20-A1 AMM Wiring Diagrams KA 134 P2350-02 23137A22bl COMM 1 AUDIO 23137A22wh 23137A22wh NAV 1 AUDIO 34804A22wh 34804A22wh REFERENCE 34804A22bl 34804A22bl COMM #1 COMM 1 MIC AUDIO 23138A22wh 23138A22wh COMM 1 KEY 23138A22bl 23138A22bl 23104A22 23105A22 REFERENCE 23104A22 23106A22wh COMM #2...
  • Page 674 DA20-A1 AMM Wiring Diagrams 23137A22wh 23137A22bl 34533A22wh COMM#1 34533A22wh KMA 24 23138A22wh 23138A22bl P2350-02 HEADPHONE PWR. 23125A18 MARKER/SPEAKER PWR. 23126A18 COMM 1 PHONE HI 23137A22wh 23137A22bl 23104A22 NAV 1 PHONE HI 34533A22wh 23105A22 COMM#2 34533A22bl 23106A22wh COMM 1 MIC HI...
  • Page 675 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET AUDIO PANEL - KMA 24 20-2350-10-00 92-30-00 DA201-A1 Page 20 06 Jan 21 Rev 16...
  • Page 676 DA20-A1 AMM Wiring Diagrams ATC BREAKER 34500A22 TR3450-03 34522A22 KT 76A AVIONIC BUS SSD120 P3450-01 P3450-04 13.75VDC 34500A22 34522A22 13.75VDC GROUND 34525A22N 34523A22N GND. GROUND TB2400-06 TB2400-06 34526A22 34526A22 A2 K 34527A22 34527A22 34528A22 34528A22 34529A22 34529A22 34517A22 34517A22 34518A22...
  • Page 677 DA20-A1 AMM Wiring Diagrams 34501A22 34502A22 34503A22 REFERENCE 34504A22 34505A22 GPS SYSTEM 34506A22 IF USED. 34507A22 34508A22 34509A22 TR3450-03 34500A22 AVIONIC BUS 34522A22 KT 76A SSD120 P3450-01 P3450-04 13.75VDC 34500A22 DIMMER 34522A22 13.75VDC GROUND 34525A22N 34523A22N GND. GROUND TB2400-06 TB2400-06...
  • Page 678 DA20-A1 AMM Wiring Diagrams KR87 KI227 P3450-24 P3450-22 14VDC 34561A22 ADF DC SIN HI 34562A22 34562A22 ADF DC COS HI 34563A22 34563A22 +4.5V ADF REF. 34564A22 34564A22 34571A22N A/C GROUND TB2400-06 AUDIO HI 34570A22 REF. AUDIO PANEL KA44B SEE DETAIL...
  • Page 679 DA20-A1 AMM Wiring Diagrams KLN 35A P3450-06 GPS BREAKER AVIONIC BUS A/C POWER 23157A22 A/C POWER A/C POWER A/C GROUND 23158A22N A/C GROUND S3450-01 TB2400-05 INTERNAL R3450-01 LIGHT 14 V LIGHTING 34735A22 34736A22 34734A22 MAIN BUS #1 28 V LIGHTING/GROUND...
  • Page 680 DA20-A1 AMM Wiring Diagrams ATC BREAKER 34500A22 TR3450-03 34522A22 KT 76A AVIONIC BUS SSD120 P3450-01 P3450-04 13.75VDC 34500A22 34522A22 13.75VDC GROUND 34525A22N 34523A22N GND. GROUND TB2400-06 TB2400-06 34526A22 34526A22 A2 K 34527A22 34527A22 34528A22 34528A22 34529A22 34529A22 34517A22 34517A22 34518A22...
  • Page 681 DA20-A1 AMM Wiring Diagrams KX155 TB2400-06 23140A18N KN 64 (BOTTOM PLUG) P3450-18 P2310-51 23140A18N DME COMMON 34750A22 RNAV/CHAN REQ 34751A22 CLOCK BUS 34752A22 DATA BUS 34753A22 AUDIO HI 34757A22wh AUDIO LO 34757A22bl 34757A22wh REF. AUDIO GROUND 34759A22N 34757A22bl A/C GROUND...
  • Page 682 DA20-A1 AMM Wiring Diagrams Effectivity SCHEMATIC SHEET TRANSPONDER - ATC 2000 20-3450-07-00 92-30-00 DA201-A1 Page 27 06 Jan 21 Rev 16...
  • Page 683 DA20-A1 AMM Wiring Diagrams KLN 35A P3450-06 P2400-04 A/C POWER 23157A22 23157A22 A/C POWER A/C GROUND 23158A22N A/C GROUND 14 V LIGHTING 34735A22 28 V LIGHTING/GROUND 34509A22 34508A22 34507A22 34506A22 REFERENCE XPDR 34505A22 SYSTEM 34504A22 P2400-05 34503A22 34502A22 34501A22 23158A22N...
  • Page 684 DA20-A1 AMM Wiring Diagrams P2400-04 34500A22 34501A22 34502A22 34503A22 REFERENCE 34504A22 34505A22 GPS SYSTEM 34506A22 IF USED. 34507A22 34508A22 34509A22 KT 76A P3450-01 13.75VDC 34500A22 DIMMER P2400-05 GROUND 34525A22N GROUND DIMMER GND 34525A22N 34526A22 34526A22 A2 K 34527A22 34527A22 34528A22...
  • Page 685 DA20-A1 AMM Wiring Diagrams P3470-01 J100 GPS BREAKER CB3470-01 34731A22 A/C POWER 34708A22N P3470-03 TB2400-06 GPS ANNTENA 34714A58 J3470-05 P3470-05 J3470-05 Effectivity SCHEMATIC SHEET GPS 150 20-3470-00-00 92-30-00 DA201-A1 Page 30 06 Jan 21 Rev 16...

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