Garmin Part 23 AML STC Airplane Flight Manual Supplement
Contents
1. LRU Aluminum included in foil tape 8 ae LRU this isad ior Description of Location installation grounding GDU 620 1 M Yes N A GRS 77 1 M Yes O Yes O No GDC 74 1 M Yes O Yes ONo GMU 44 1 Yes N A GTP 59 1 Yes N A GAD 43 43e O Yes ONo O Yes O No MCI 4300 4 O Yes O No N A MCI 4200 O Yes O No N A MCI MD420 O Yes O No N A GDU 620 2 dual installations O Yes O No N A only GRS 77 2 dual installations Q Yes U No N A only GDC 74A 2 dual installations Q Yes O No N A only GMU 44 2 dual installations O Yes U No N A only GTP 59 2 dual installations Q Yes U No N A only G500 PFD MFD System Instructions for Continued Airworthiness 190 01102 00 Rev 5 Page 11 of 13 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 ee e G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 12 of 13 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 JX SR l i SE G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 13 of 132. G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 5 of 13 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 Conduct a visual inspection look for signs of wear deterioration or damage to wires switches backshells connectors overbraid bonding straps or foil of the G500 system LRUs and wiring harnesses to ensure installation integrity 1 Inspect all units for security of attachment including visual inspection of brackets and other supporting structure attaching all units to the airframe 2 Inspect all switches knobs and buttons for legibility 3 Visually inspect each unit s wiring for chafing or wear at each termination 4 Visually check for any signs of corrosion 2 5 1 Transient Voltage Suppressors non metallic aircraft only The GDU 620 1 GRS 77 1 GDC 74 1 and GAD 43 if installed will have a TVS located at each LRU The electronic Mid Continent Instrument standby Attitude Indicator if installed will have a TVS located at the indicator and at the attitude indicator
3. Non Metallic Aircraft GDU 620 Display Unit 40 MQ to instrument panel 40 40 mO to instrument reng to instrument 40 mO to instrument reng GRS 77 Attitude Heading 20 mQ to aircraft ground 20 mQ to instrument panel Reference System AHRS plane GMU 44 Magnetometer 20 mQ to aircraft ground No bond check required since plane the GMU is required to be isolated from it s mounting location Verify that there is sufficient clearance around the installation per section 2 5 11 5 3 of the G500 AML STC Installation Manual GDC 74 Air Data Computer 20 mQ to aircraft ground 20 mQ to instrument panel plane GTP 59 OAT Probe 5 mQ to aircraft skin No bond check required since the GTP is required to be isolated from it s mounting location Verify that there is sufficient clearance around the installation per section 2 5 11 7 2 of the G500 AML STC Installation Manual GAD 43 43e Adapter 20 mQ to aircraft ground 20 mQ to instrument panel plane Note there are no applicable bonding requirements for the Mid Continent Instruments Attitude Indicator Models 4300 4 or 4200 with MD420 2 6 Troubleshooting Information If error indications are displayed on the GDU 620 display unit and or the optional Mid Continent Instruments standby attitude indicator consult the Troubleshooting section contained in the G500 AML STC Installation Manual The G500 System Post Installation Checkout Log in
4. highlight available fields The system starts in normal mode when power is applied to the LRUs After completing the self test the database confirmation page is displayed Invalid or expired databases are displayed in yellow Press ENT to proceed to normal mode Normal mode consists of a Primary Flight Display PFD on one screen and a Multifunction Display MFD on the other screen The AHRS alignment should complete within one minute and attitude should be displayed on the PFD System alerts are accessible via an ALERTS softkey at the lower right of the MFD During normal system operation with all aircraft systems and avionics powered there should not be any red Xs or system alerts on the GDU 620 To enter into Configuration Mode verify that the GDU 620 is off and an Installer Unlock Card is inserted in the SD card slot of the GDU 620 Apply power to the GDU 620 while holding the ENT key Release the ENT key when INITIALIZING SYSTEM appears in the upper left corner of the display Refer to the G500 AML STC Installation Manual for further configuration instructions 2 4 Servicing Information In the event of system failure troubleshoot the G500 system in accordance with Section 2 6 Troubleshooting Information If the Mid Continent Instruments 4300 4XX Electric Attitude Indicator or MD420 battery pack is installed the battery or batteries may be charged by one of the following methods 1 Keep the battery or batteries plugged int
5. locations and wire routing diagram are contained in Appendix A of this document Refer to the G500 AML STC Series Installation Manual listed under reference documentation in Section 2 1 of this document for drawings applicable to this installation Point to point wiring diagrams are in Appendix F of the G500 AML STC Installation Manual Refer to the G500 Post Installation Checkout Log retained in the aircraft permanent records for a list of the interfaced equipment and port configurations 2 9 Special Inspection Requirements After a suspected lightning strike the following actions must be performed e Inspect the GTP 59 OAT for signs of lightning damage Check the self sealing washer P N 212 00026 00 used on the probe tip outside of the aircraft for any evidence of melting or lack of seal Replace washer if damaged If there is evidence of lightning strike to the OAT or any lightning damage replace the GTP 59 OAT e Non metallic aircraft must have all Transient Voltage Suppressors replaced in accordance with section 8 3 1 of the G500 AML STC Installation Manual e Tube and fabric aircraft must replace the OAT bond strap if installed in accordance with section 8 3 3 of the G500 AML STC Installation Manual e Aircraft with a GMU mounted in the wingtip of metallic aircraft with non metallic wingtip covers must inspect the magnetometer installation in accordance with section 8 4 1 of the G500 AML STC Installation Manual e Aircraft with
6. submitted to the ACO or ODA along with the revised ICA The ACO or ODA will obtain AEG acceptance and approve any revision to the Airworthiness Limitations in Section 1 4 After FAA acceptance approval Garmin will release the revised ICA for customer use and provide any required notification of the revision The latest revision of this document will be available on the Garmin website www garmin com A Garmin Service Bulletin describing ICA revision will be sent to dealers if revision is determined to be significant 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 Garmin customer assistance may be contacted during normal business hours via telephone 913 397 8200 or email from the Garmin web site at www 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 G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 10 of 13 3 APPENDIX A 3 1 LRU Locations The following table describes the locations of the G500 LRUs
7. 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 06 30 09 Initial Release 11 30 09 Add replacement instructions for OAT bond strap Update referenced publications Clarified periodic maintenance 3 02 08 11 instructions Foil check annual Added new special inspection requirements and periodic bonding test 4 08 15 11 Remove FAA Approved language Update IM rev Add additional instructions for Mid Continent standby attitude indicator installations 5 12 11 12 Added information regarding GAD 43e Added additional Control Operating Information and deleted Pilote Guide reference Incorporated GDC 74 testing procedural information from Installation Manual Revised lightning strike inspection WEE EES en 1 INTRODUC TON E 3 A PUROS EE 3 T2 le EE 3 Li Document Control 0c textes Aaa heh titi teed 3 1 4 Airworthiness Limitations Section cccceccceeeeeeeeeeceeeeeeeaeeeeeeeseeeeeseaeeeeeaeeeeneeees 3 1 5 Permission to Use Certain Documents 3 TGs leegen E T 3 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS nsiiieeeeeeeeeeereesrresrresrrssrrssrnenns 4 2A AATROGUGTION 2 fies TAEA PA Sen tedepenvtdado S E anes cpeesteaduarnaeds EET 4 2 2 Description of Alteraton eeeseceee
8. an ARINC 708 weather radar interfaced to the GDU 620 must inspect the overbraid to the weather radar in accordance with section 8 4 2 of the G500 AML STC Installation Manual If the Mid Continent Standby Attitude Indicator if installed has not been operated for more than 3 months charge each battery pack using one of the methods described in Section 2 4 2 10 Application of Protective Treatments None N A 2 11 Data Relative to Structural Fasteners Data relative to structural fasteners such as type torque and installation requirements can be found in Section 3 of the G500 AML STC Installation Manual 2 12 Special Tools For electrical bonding testing a milli ohm meter is required No special tools are required for system checkout See G500 AML STC Installation Manual listed in reference documentation in Section 2 1 of this document G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 9 of 13 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 15 ICA Revision and Distribution To revise this ICA a letter must be
9. attery may be permanently damaged if it is left in a discharged state Recharge a discharged battery as soon as possible and maintain with a float charge for maximum battery life Within the preceding 12 calendar months proper operation of the attitude instrument must be verified with the following procedure 1 Apply aircraft power to the unit and verify that the invalid flag is removed from view and the STBY PWR indicator is not illuminated 2 Remove aircraft power from the unit and verify that the invalid flag is not visible and the STBY PWR indicator is flashing 3 Press the STBY PWR button and verify that the invalid flag is not visible and the STBY PWR indicator is not flashing 4 Press the STBY PWR button a second time and verify that the invalid flag is displayed Otherwise maintenance of the Mid Continent Instruments attitude indicator is on condition only G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 7 of 13 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 Metallic Aircraft
10. d 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 Scope This document identifies the Instruction for Continued Airworthiness for the modification of the aircraft for installation of the Garmin G500 PFD MFD System installed under Approved Model List AML STC 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 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 48 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 G500 system to use and reference appropriate STC documents to accomplish the Instructions for Continued Airworthiness an
11. d 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 ADC Air Data Computer 4 AEG Aircraft Evaluation Group AHRS Attitude Heading Reference System CFR Code of Federal Regulations FAA Federal Aviation Administration ICA Instructions for Continued Airworthiness 9 MFD Multi Function Display 0 PFD Primary Flight Display 1 PMI Primary Manufacturing Inspector 2 STC Supplemental Type Certificate 13 TSO Technical Standard Order 14 TVS Transient Voltage Suppressor G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 3 of 13 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 7 G500 AML STC Installation Manual or later revision
12. ennececeenneeeeeenaeeeeeeaaeeeeseaaeeeseeaaeeeeseaeeeenenaes 4 2 3 Control Operating Information ccccceeeeeeeeeeeeeeceeeeecaeeeseaeseeeeeeeeeeseaeeseeeeeaes 4 2 4 Servicing Information ss EE 5 2 5 Periodic Maintenance Instruchons 6 2 6 Troubleshooting Information 0 00 eee eeeeeceeeeeeeeeeeenneeeeeeaeeeeeeaeeeeeeaeeeesenaeeeeneaaes 8 2 7 Removal and Replacement Information ec ceeeeceeeeenneeeeeenneeeeeeaeeeeeenaeeeeneaaes 8 E KR EE 9 2 9 Special Inspection Requirements esseesseesseesseeesetesrettnrstnnstnnstnnsennntnnennssnnsenn 9 2 10 Application of Protective Treatments A 9 2 11 Data Relative to Structural Fasteners cccccecseeeeeeeeeceeeeeeeseeeeeeeeeeseaeeneeeteaes 9 2712 Special Keel EE 9 2 13 Additional INStrUCtiONS arias EA ET AARE E EA 10 2 14 e EIB e WEE 10 2 15 ICA Revision and Distribution ccccccceeeceeeeeeeeeeeceeeeecaeeeeaaeseeeeeseeeesaeeseaeeteaes 10 2 16 ASSISTANCE EE 10 2 17 Implementation and Record Keeping ssesssssesssssrssssrnssssrrssrsrnnsrinnsstrnnnsrnnnnsnnnns 10 Ho Pees ER EN Dr eege Eege 11 Sil E ME te ait Anite aie ieee SA i Ws 11 3 2 Wire Routing Single Engine ceccceeeseceeseeceeeeceeeeeeeaeeeeaaeseeeeeseeeessaeeseeeeeaes 12 23 Wire Routing TWIN ENngine nesgo e aE a E T 13 G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 2 of 13 1 INTRODUCTION 1 1 Purpose This document is designe
13. is on condition only G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 6 of 13 2 5 9 Mid Continent Instruments Attitude Indicator Models 4300 4 or 4200 1 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 Connect each battery to a load of 90 ohms rated for 10 watts for 60 minutes while monitoring the battery voltage level i If the battery voltage is at or above 15 0 volts while under load at the end of the 60 minute test the battery may be recharged immediately in accordance with Section 2 4 and re installed in the aircraft ii If the battery voltage is below 15 0 volts while under load at the end of the 60 minute test the battery must be replaced 2 Automatic a Use the Mid Continent Instruments Battery Charger Tester P N 36029 to test the battery i If the time required for discharge is 60 minutes or greater the battery may be recharged immediately in accordance with Section 2 4 and re installed in the aircraft ii If the time required for discharge is less than 60 minutes the battery must be replaced V ARNING The b
14. ly powered from multiple circuit breakers then the circuit breakers will be suffixed with the letters A and B i e AHRS 1A and AHRS 1B The GDU 620 has a PFD and MFD display and front panel controls for performing all normal and configuration operations Knobs at the lower left and right corners are used for selecting and entering G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 4 of 13 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 Pressing the PFD knob reverts to the default value of the selected mode The Small Inner MFD Knob selects a specific page within a page group Pressing the small MFD knob turns the selection cursor ON and OFF When the cursor is ON data may be entered in the applicable window by turning the small and large MFD knobs In this case the large MFD knob moves the cursor on the page and the small MFD knob selects individual characters or values for the highlighted cursor location The Large Outer MFD Knob selects the MFD page group When the cursor is ON the large MFD knob moves the cursor to
15. o the Attitude Indicator or Battery Module Apply power to the aircraft and run the unit overnight approx 15 hours at the rated voltage 2 Float Charging Disconnect the battery or batteries from the indicator or module Connect the battery or batteries to a constant voltage source battery plug pin 1 red wire positive of 20 4 to 20 6 VDC continuously Float charging may take 24 hours or longer to charge a battery pack 3 Routine Charging Disconnect the battery or batteries from the indicator or module Connect the battery or batteries to a constant voltage source battery plug pin 1 red wire positive of 21 6 to 22 1 VDC with a current limit of 0 1 ampere maximum When the charging current drops to approximately 5mA the battery is fully charged and should be disconnected Leaving 21 6 to 22 1 VDC charge voltage on the battery for an extended time will degrade its life If continuous maintenance of the charge is desired refer to step 2 Float Charging V ARNING Battery out gassing and a rotten egg odor may occur due to prolonged high rate overcharging and may result in battery damage The battery assembly must be replaced if out gassing has occurred 4 The Mid Continent Instruments Battery Charger Tester P N 36029 may be used This Battery Charger Tester will apply an initial charge per step 3 above and then automatically switch to maintain a float charge per step 2 above indefinitely after initial charging is complete
16. power bus These components must be tested every 24 calendar months in accordance with section 8 3 1 of the G500 AML STC Installation Manual 2 5 2 Aluminum Foil Tape non metallic aircraft only Any aluminum foil tape used in the G500 installation see section 3 1 of this document must be inspected every 12 calendar months in accordance with section 8 3 2 of the G500 AML STC Installation Manual 2 5 3 GDU 620 Display Unit Maintenance of the GDU 620 is on condition only 2 5 4 GRS 77 Attitude Heading Reference System AHRS The GRS 77 utilizes an Earth magnetic field model which is updated once every five years as part of the Aviation Database maintained by the owner operator If the magnetic model is not up to date the unit will issue an alert upon startup indicating the model has expired The model can be updated in accordance with the database update section of the G500 AML STC Installation Manual Otherwise maintenance of the GRS 77 is on condition only 2 5 5 GMU 44 Magnetometer Maintenance of the GMU 44 is on condition only 2 5 6 GDC 74 Air Data Computer Test according to 14 CFR 91 411 When testing in accordance with 14 CFR Part 43 Appendix E it is not necessary to perform sections b 1 iv Friction or b 1 vi Barometric Scale Error 2 5 7 GTP 59 OAT Probe Maintenance of the OAT Probe is on condition only 2 5 8 GAD 43 48e Adapter Maintenance of the GAD 43 43 e
17. s Retention This document or the information contained within will be included in the aircrafts permanent records 2 2 Description of Alteration The Garmin G500 PFD MFD System is a combination of Garmin LRUs designed to provide both a PFD and MFD in the primary field of view The system consists of a GDU 620 display GRS 77 AHRS GDC 74 ADC GMU 44 magnetometer and GTP 59 outside air temperature probe This modification may also include a Garmin GAD 43 Adapter and or Mid Continent Instruments attitude indicator models 4300 4 or 4200 with MD420 Installation of the Garmin G500 system specific for the aircraft installation is documented in the G500 AML STC Installation Manual 2 3 Control Operating Information The GDU 620 GRS 77 GMU 44 and GDC 74 are powered by an electrical bus which is normally energized with battery generator or external power applied to the aircraft The GAD 43 48 e is typically powered by an avionics bus which is normally controlled by the avionics bus power switch The LRUs do not have individual power switches and are powered when the bus is energized and the circuit breakers are closed The following circuit breakers provide power to the individual LRUs PFD GDU 620 AHRS GRS 77 1 and GMU 44 1 e ADC GDC 74 GAD GAD 43 43e In a dual G600 installation the PFD AHRS and ADC circuit breakers are suffixed with the numbers 1 and 2 i e AHRS 1 and AHRS 2 If an LRU is optional
18. the aircraft permanent records includes the configuration information for the installation See Section 5 in the G500 System Installation Manual for a sample Log 2 7 Removal and Replacement Information If any G500 LRUs are removed and reinstalled verify that the LRU unit power up self test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display See the unit replacement procedure in Section 3 of the G500 AML STC Installation Manual Perform any additional procedures that are required for each LRU as specified in the following subsections G500 PFD MFD System 190 01102 00 Rev 5 Instructions for Continued Airworthiness Page 8 of 13 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 1 GAD 48e Adapter Replacement If the GAD 43e is used with an analog navigation receiver the GAD 43e calibration specified in 5 5 11 3 of the G500 AML STC Installation Manual must be performed whenever the GAD 43e and or the analog navigation receiver is replaced 2 8 Diagrams Aircraft specific LRU
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