G500 PFD/MFD System Instructions for Continued Airworthiness as installed in _____________________________ (Make and Model Airplane) Reg. No.____________ S/N_______________ Dwg. Number: 190-01102-00 Rev. 5 Garmin International, Inc. 1200 E. 151st Street Olathe, Kansas 66062 USA Record of Revision Rev. Date Description of Change 1 2 06/30/09 11/30/09 3 02/08/11 4 08/15/11 5 12/11/12 Initial Release Add replacement instructions for OAT bond strap Update referenced publications.
1. INTRODUCTION................................................................................................................... 3 1.1 Purpose................................................................................................................. 3 1.2 Scope .................................................................................................................... 3 1.3 Document Control ................................................................................................. 3 1.
1. INTRODUCTION 1.1 Purpose This document is designed for use by the installing agency of the Garmin G500 PFD/MFD System as Instructions for Continued Airworthiness in response to Federal Aviation regulation (FAR) Part 23.1529, and Part 23 Appendix G. This ICA includes information required by the operator to adequately maintain the Garmin G500 system installed under Approved Model List (AML) STC. 1.
2. INSTRUCTIONS 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 G500 PFD/MFD System. Applicability: Applies to aircraft altered by installation of the Garmin G500 PFD/MFD System. Definition of Abbreviations: See Section 1.6 Precautions: None Units of measurement: None Referenced publications: Garmin 190-01102-06 Rev.
data on each screen. The function of the soft keys along the bottom of the display is depicted by the text above the key. There are dedicated ENT, CLR, and MENU keys on the MFD side of the unit. Turning the PFD knob adjusts the values for the mode selected by the PFD bezel keys, such as, Heading (HDG), Course (CRS), Altitude (ALT), Vertical Speed (V/S), and Barometric Setting (BARO). The values are shown in a window to the left of the HSI.
2.5 Periodic Maintenance Instructions All G500 system LRUs are designed to detect internal failures. A thorough self-test is executed automatically upon application of power to the units, and built-in tests are continuously executed. Detected errors are indicated on the GDU 620 display via failure annunciations. Operation of the G500 system is not permitted unless an inspection as described in this section has been completed within the preceding 12 calendar months.
2.5.9 Mid Continent Instruments Attitude Indicator Models 4300-4( ), or 4200-( ) with MD420 If a Mid Continent Instruments Attitude Indicator is installed as part of the G500 AML STC, within the preceding 12 calendar months each battery pack must be tested by one of the following means: 1. Manual: a. Disconnect each battery pack from the Attitude Indicator or Battery Module. b. Ensure each battery pack is completely charged (per Section 2.4) and at or near room temperature (20-25°C). c.
2.5.10 Electrical Bonding Test G500 LRU electrical bonding must be tested every 2000 flight hours or ten (10) years, whichever is first. During the test, any cables normally attached to the LRU must be disconnected from the LRU. If measured resistance is greater than applicable values in the following table, bonding must be improved to meet applicable requirements for a new installation in accordance with section 3.8 of the G500 AML STC Installation Manual.
If any work has been done on the aircraft that could affect the system wiring, antenna cable, or any interconnected equipment, verify the G500 system unit power-up self-test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display. Refer to the G500 AML STC Installation Manual (listed under reference documentation in Section 2.1 of this document) for particular LRU removal/installation procedures and special handling precautions. 2.7.
2.13 Additional Instructions None 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 G500 system. If any LRU indicates an internal failure, the unit may be removed and replaced. See the troubleshooting section contained in the G500 AML STC Installation Manual, listed under reference documentation in paragraph 2.1 of this document. 2.
3. APPENDIX A 3.
3.2 Wire Routing – Single-Engine The following diagram depicts the wire routing for the G500 LRUs throughout the aircraft structure for a single-engine aircraft: G500 PFD/MFD System Instructions for Continued Airworthiness 190-01102-00 Rev.
3.3 Wire Routing – Twin-Engine The following diagram depicts the wire routing for the G500 LRUs throughout the aircraft structure for a twin-engine aircraft: G500 PFD/MFD System Instructions for Continued Airworthiness 190-01102-00 Rev.
