Garmin SA01692SE Instruction Manual
Contents
1. units and built in test is continuously executed Detected errors are indicated on the equipment via failure annunciations and maintenance is on condition Operation of the GMX 200 is not permitted unless an inspection as described in this section has been completed within the preceding 12 calendar months Conduct a visual inspection on the unit and its wire harness to insure continued installation integrity 1 Inspect the unit for security of attachment 2 Inspect all knobs and buttons for legibility 3 Inspect condition of wiring routing and attachment clamping 2 5 1 Cleaning the Front Panel The front bezel keypad and display can be cleaned with a soft cotton cloth dampened with clean water DO NOT use any chemical cleaning agents Care should be taken to avoid scratching the surface of the display 2 5 2 Display Backlight The display backlight is rated by the manufacturer as having a usable life of 50 000 hours This life may be more or less than the rated time depending on the operation conditions of the GMX 200 unit Over time the backlight may dim and the display may not perform as well in direct sunlight conditions The user must determine by observation when the display brightness is not suitable for its intended use Contact the Garmin factory repair station when the backlight requires service 2 5 3 Altitude Encoder In this VFR non essential system it is recommended that any interfaced pressure altitude source be cal2. CA for customer use and provide any required notification of the revision The latest revision of this document will be available on the Garmin website garmin com A Garmin Service Letter describing ICA revision will be sent to dealers and GMX 200 owners of record if revision is determined to be significant GMX 200 P N 190 00607 00 Rev A Instructions for Continued Airworthiness Page 6 of 7 2 16 Assistance Flight Standards Inspectors or the certificate holder s PMI have the required resources to respond to questions regarding this ICA In addition the customer may refer questions regarding this equipment and its installation to the manufacturer Garmin AT Garmin AT customer assistance may be contacted during normal business hours via telephone 800 525 6726 or email from the Garmin web site at support salem garmin com 2 17 Implementation and Record Keeping Modification of an aircraft by this Supplemental Type Certificate obligates the aircraft operator to include the maintenance information provided by this document in the operator s aircraft maintenance manual and or the operator s aircraft scheduled maintenance program GMX 200 P N 190 00607 00 Rev A Instructions for Continued Airworthiness Page 7 of 7
3. CTIONS FOR CONTINUED AIRWORTHINESS 2 1 Introduction Content Scope Purpose and Arrangement This document identifies the Instructions for Continued Airworthiness for the modification of the aircraft by installation of the Garmin GMX 200 Applicability Applies to aircraft altered by installation of the Garmin GMX 200 Definition of Abbreviations See Section 1 6 Precautions None Units of measurement None Referenced publications 190 00607 04 Rev B GMX 200 Installation Manual or later FAA approved revisions 005 C0315 00 Rev A GMX 200 STC Master Data List Retention This document or the information contained within will be retained in the aircrafts permanent records 2 2 Description of Alteration Installation of the Garmin GMX 200 and other system interfaces The GMX 200 consists of a LCD display keypads keyboard and rotary knob 2 3 Control Operating Information See the GMX 200 Installation Manual listed under the reference documentation in paragraph 2 1 of this document for system operation and self test information 2 4 Servicing Information None In the event of system failure return the unit to the manufacturer or an approved Garmin repair station GMX 200 P N 190 00607 00 Rev A Instructions for Continued Airworthiness Page 4 of 7 2 5 Periodic Maintenance Instructions The GMX 200 is designed to detect internal failure A thorough self test is executed automatically upon application of power to the
4. GMX 200 Instructions for Continued Airworthiness FAA STC Project No ST9731SE A Document Number 190 00607 00 Rev A Garmin Ltd Or its subsidiaries c o Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Confidential This drawing and the specifications contained herein are the property of Garmin Ltd or its subsidiaries and may not be reproduced or used in whole or in part as the basis for manufacture or sale of products without written permission Record of Revision Rev Date Description of Change 6 02 06 Initial Release 6 19 06 Production Release ell 1 INTRODUCTION EE 3 le Tale ee eege teas 3 le 3 1 3 Document Controls TEE 3 1 4 Airworthiness Limitations Gechon 3 1 5 Permission to Use Certain Documents 3 LP ADSNAIIONS sisese ree R EATS EEEE eE ERE EEA ENSE EEKEREN EROR 3 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ieeeeseesnesrressrnesrnssrnssrrssrrssns 4 Zl lu tg elteren DT 4 2 2 Description of Alieraton nenn 4 2 3 Control Operating Information cecceeecececeeeeeeeeceeeeeeeaeeeeeaeseeeeeeeeeeesaeeseeeeeeaas 4 2 4 Servicing Information 4 2 5 Periodic Maintenance Instruchons 5 2 6 Troubleshooting Information cccccscceeceeceeeeeeeeeeeeeeeeseaeeesaaeseeeeeeeeeeessaeeeeeeeeeas 5 2 7 Removal and Replacement Information ssseessessseeseeesrnesrnesrnsssnnnsnnsrnssrnssrnsens 5 ER WE RI e LE EEN 6 2 9 Special Inspection Requirements ess
5. Installation Manual 2 9 Special Inspection Requirements None N A 2 10 Application of Protective Treatments None N A 2 11 Data Relative to Structural Fasteners None N A 2 12 Special Tools No special tools are required for system checkout See GMX 200 Installation Manual listed in reference documentation in section 2 1 of this document 2 13 Additional Instructions for Aircraft Operating under FAR 121 135 1 Aircraft Electrical Loads Perform aircraft electrical system load analysis See GMX 200 Installation Manual listed in reference documentation in section 2 1 of this document Methods of balancing flight controls N A Special Repair Methods applicable to the airplane See certificate holder s General Maintenance Manual for instructions 2 14 Overhaul Period The system does not require overhaul at a specific time period Power on self test and continuous BIT will monitor the health of the GMX 200 unit If the unit indicates an internal failure the unit may be removed and replaced See troubleshooting section contained in the GMX 200 Installation Manual listed under reference documentation in paragraph 2 1 of this document 2 15 ICA Revision and Distribution To revise this ICA a letter must be submitted to the ACO along with the revised ICA The ACO will obtain AEG acceptance and approve any revision to the Airworthiness Limitations Section 1 4 After FAA acceptance approval Garmin will release the revised I
6. eeseseeeessrssrssiissrssrissrinssrnssrnssrnssrnnsren 6 2 10 Application of Protective Treatment ccccccecsseceeeeeceeeeeeeeeeeeseeseeeeeeteaeeeeeeeeaes 6 2 11 Data Relative to Structural Fasteners ccccceeeseeceeeeeceeeeeeaeeeeeeeeeeeeseaeeeeeeeeaes 6 2 125 SPO Clalll Kee EE 6 2 13 Additional Instructions for Aircraft Operating under FAR 121 135 6 2 14 Overhaul Period 6 2 15 ICA Revision and Dietrbuton sssini te niena atgan aetna ea arrai eekan ade kaTa ida 6 216 EE ue ET 7 2 17 Implementation and Record Keeping ssssssssssesssrresssnnessnrnnsrnnnnssnnnnnennnnnsnnnnnnnennee 7 GMX 200 P N 190 00607 00 Rev A Instructions for Continued Airworthiness Page 2 of 7 1 INTRODUCTION 1 1 PURPOSE This document is designed for use by the installing agency of the Garmin GMX 200 as Instructions for Continued Airworthiness in response to Federal Aviation regulation FAR Part 23 1529 and Part 23 Appendix G They include information required by the operator to adequately maintain the Garmin GMX 200 1 2 Scope This document identifies the Instruction for Continued Airworthiness for modification of the aircraft for installation of the Garmin GMX 200 1 3 Document Control This document shall be released archived and controlled in accordance with the Garmin document control system When this document is revised refer to Section 2 15 for information on how to gain FAA acceptance or approval and how to notify customers
7. ibrated every 24 months Refer to the manufacturer s installation and calibration manual 2 6 Troubleshooting Information If error indications are displayed on the GMX 200 unit consult the Troubleshooting section contained in the GMX 200 Installation Manual listed under reference documentation in paragraph 2 1 of this document The GMX 200 Post Installation Checkout Log in the aircraft permanent records includes the configuration information for the installation See Table 5 3 in the GMX 200 Installation Manual for a sample Log 2 7 Removal and Replacement Information If the GMX 200 unit is removed and reinstalled verify that the unit power up self test sequence is successfully completed and no failure messages are annunciated If the GMX 200 unit is removed for repair and reinstalled or if the unit is removed and replaced with a different unit then follow Post Installation Configuration amp Checkout Procedures procedures contained in the GMX 200 Installation Manual listed in paragraph 2 1 of this document and verify the unit power up self test sequence is successfully completed and no failure messages are annunciated GMX 200 P N 190 00607 00 Rev A Instructions for Continued Airworthiness Page 5 of 7 2 8 Diagrams Refer to the GMX 200 Installation Manual listed under reference documentation in section 2 1 of this document for drawings applicable to this installation Wiring diagrams are in Appendix E of the GMX 200
8. of changes 1 4 Airworthiness Limitations Section There are no additional Airworthiness Limitations as defined in 14 CFR 23 Appendix G G23 4 that result from this modification The Airworthiness Limitations section is FAA approved and specifies maintenance required under 43 16 and 91 403 of the Federal Aviation Regulations unless an alternative program has been FAA approved 1 5 Permission to Use Certain Documents Permission is granted to any corporation or person applying for approval of a Garmin GMX 200 to use and reference appropriate STC documents to accomplish the Instructions for Continued Airworthiness and show compliance with STC engineering data This permission does not construe suitability of the documents It is the responsibility of the applicant to determine the suitability of the documents for the ICA 1 6 Definitions The following terminology is used within this document 1 AC Advisory Circular 2 ACO Aircraft Certification Office 3 AEG Aircraft Evaluation Group 4 CFR Code of Federal Regulations 5 DER Designated Engineering Representative 6 FAA Federal Aviation Administration 7 IAW In Accordance With 8 ICA Instructions for Continued Airworthiness GMX 200 P N 190 00607 00 Rev A Instructions for Continued Airworthiness Page 3 of 7 i MFD Multi Function Display unit 10 PMI Primary Manufacturing Inspector 11 POI Primary Operations Inspector 12 STC Supplemental Type GEI AE 2 INSTRU
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