Garmin SR02232LA Instruction Manual
Contents
1. Rotorcraft wire routing diagram is contained in Appendix A of this document 2 9 General Procedural Instructions Weight and balance computation may be required after maintenance of the 400W System installation Follow the guidelines in the airframe manufacturer s manual If none are available use the guidelines established in AC 43 13 1B Chapter 10 Section 2 Make appropriate entries in the equipment list indicating items added removed or relocated along with the date accomplished Include your name and certificate number in the rotorcraft records Table 2 identifies the weight of the 400W System equipment Table 3 lists the location of the 400W System equipment as filled out by the installer Table 2 Unit Weight Information aswon iar tn tt GA 36 Weight 0 47 Ibs 0 21 kg GA 37 Weight 0 50 Ibs 0 23 kg Garmin P N 115 00846 00 Doubler Weight Option used as 0 17 Ibs 0 08 kg backing plate for GA 36 or GA 37 GA 36 or GA 37 Fabricated backing plate Installer to Fill in if Applicable GA 35 Fabricated backing plate Installer to Fill in if Applicable Garmin P N 115 00846 10 Doubler Weight Option used as 0 09 Ibs 0 04 k 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 10 of 15 Table 3 Unit Location Information C G Station Installed Location Description inches Part and Model 400W Series Unit GPS Antenna Procedures and data required for wiring maintenance a2. 400W Series Rotorcraft Instructions for Continued Airworthiness as installed in Make and Model Rotorcraft Reg No S N STC SRO2232LA Document Number 190 00356 21 Rev C Garmin Ltd Or its subsidiaries c o Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Record of Revision _ Rev Date Description of Change 10 24 08 Initial Release 1 28 09 Added table for list of interfaced equipment STC number and changed document title 4 24 09 Added STC number and changed revision levels in section 2 1 DN E This page intentionally left blank 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 2 of 15 1 INTRODUCTION EE 4 ti PURPOSE EE 4 E ee E seed ece ede eens 4 lcd DOCUMENT COMUG E 4 1 4 Permission to Use Certain Documents 4 WS IDGTINIMOINS seron A O 4 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 0 cecccceeececeeeeeeaeeeeeneeens 5 CN MPM OCU CON WEE 5 2 2 Description of Alteraton cc cccccccccccceeececeeeceeaeeeeseeeeeeeeeeeseusesseeeeseesesseeeesanes 6 2 3 Control Operating Information ces ccc eecccceeeeeceeeeeeeeeeeseecesseeeesseeeesaeeeetanes 8 24 SERVICING INTORMAL ON NEE 8 2 5 Periodic Maintenance Instruchons 8 2 6 Troubleshooting Information 9 2 7 Removal and Replacement Information cc cece ceccceeeeceeaeeeeeseeceeaeesesseeeesanes 9 KI Leg E 10 2 9 General Procedural Instructions cccccccceeccc
3. Com unit is a 6 A inch wide panel mounted unit with all the interface connections behind the instrument panel The 400W Series units combine a large number of easily acceptable controls to use the color multi function display Nav and Com transceiver GPS WAAS navigator in a single unit The 400W series control and display layout is shown in Figure 1 Photocell for Auto ping Com Freq Graphic Moving Comm Freq Window Map Display and Direct To Key Flip Flop Pleats Navigation Info Window g Range Keys Menu Key Power and Com Volume Squelch SS H l ebe E Clear Key Data K e 1 At y A Cards n ugg 128 300 VRE Zu Tx Wi Enter Key A a AN ae pei EE Functi d Nav Radio ug EZ d LIR vk z unction an Volume i e GK SC E cert Page Number Nav Radio Flip Flop emm p 72 ES ECH Large Knob ok ars HSG UU bitt Large Knob Mior eg wes FA PROD Small Knob Com VLOC EE T A Cursor Press Freq MHZ Terrain Flight to activate Small Knob Phase and Flight Plan Com VLOC GPS Integrity l CDI OBS Key Procedure Key Freq kHz Annunciator Mounting Key Screw Key Message Navigation e Source GPS VLOC or GPS PTK Figure 1 400W Series Control and Display Layout For a list of equipment interfaced to the 400W Series unit as installed in this installation refer to Table 1 below For interfaced system installation configuration refer to the GNS 400W Series Post Installation Checkout Log that is retained as part of th
4. ONS SECTION There are no additional Airworthiness Limitations as defined in 14 CFR 27 Appendix A A27 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 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 14 of 15 APPENDIX A 3 1 Wire Routing The following diagram depicts the wire harness and coax cable routing for the 400W Series unit s and antenna s throughout the rotorcraft structure 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 15 of 15
5. ained in the 400W Series Installation Manual listed under reference documentation in paragraph 2 1 of this document 2 16 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 3 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 17 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 18 Implementation and Record Keeping Modification of a rotorcraft by this Supplemental Type Certificate obligates the rotorcraft operator to include the maintenance information provided by this document in the operator s rotorcraft maintenance manual and or the operator s rotorcraft scheduled maintenance program 3 AIRWORTHINESS LIMITATI
6. ay unit 10 PMI Primary Manufacturing Inspector 11 POI Primary Operations Inspector 12 STC Supplemental Type Certificate 13 TC Type Certification or Type Certificate 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 4 of 15 14 TSO Technical Standard Order 15 BIT Built In Test 16 TCDS Type Certificate Data Sheet 17 N A Not Applicable 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 rotorcraft by installation of the Garmin Models 400W Series GPS WAAS Nav Com Applicability Applies to rotorcraft altered by installation of the Garmin Model 400W Series GPS WAAS Nav Com Definition of Abbreviations see Section 1 5 Precautions None Units of measurement None Referenced publications 190 00357 22 Rev C STC Rotorcraft Installation Supplement for 400W S00W Series or later FAA approved revisions 190 00356 02 Rev G 400W Series Installation Manual 005 C0221 02 Rev 4 400W Series Rotorcraft AML STC Installation Master Data List Retention This document or the information contained within will be included in the rotorcraft s permanent records 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 5 of 15 2 2 Description of Alteration The Garmin Model 400W Series GPS WAAS Nav
7. ceeeeeceeeeeceeeeeseeeeeseeeeeseaeessaeeseaes 10 2 10 Special Inspection Requirements n0nnnnannnennnnnrnnennnsrrnnrnnrsnrrnrnrrenrrnerrrsrrrnen 13 2 11 Application of Protective Treatmentse 13 2 12 Data Relative to GiruchuralFasteners cece ccccccceecceseeeeceeeceseeeeeseeeessueeesenes 13 213 Special OOS EE 13 ZAG ee Wein E E d e a EEN 14 219 OVETNAUL TE le Le EE 14 2 16 IGA Revision and WA RI ele EE 14 AR EE aer 14 2 18 Implementation and Record Keeping noonnnnnnnnnnennnnnnsnnnnnnnnnesnnnnrrnnrrsnrnerrnnern 14 3 AIRWORTHINESS LIMITATIONS GECTION cesses eesseeeeeseeeensees 14 A IR 15 ST Wre ele EE 15 Figure 1 400W Series Control and Display Layout 6 Table 1 Interfaced Equipment to 400W Series Un 7 Tale EREM eege 10 Table 3 Unit kocation Information eege eee E S mi Table 4 400W Series Power Input 12 Table 5 Circuit Breaker Size and Placard ccccccccccecccceeececaeeceeeeeceeaeeceseeecesseeesseeeesaeeesanees 13 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 3 of 15 1 INTRODUCTION 1 1 PURPOSE This document is designed for use by the installing agency of the Garmin Model 400W series GPS WAAS Nav Com as Instructions for Continued Airworthiness in response to Federal Aviation regulation FAR Part 27 1529 Part 27 Appendix A The ICA includes information required by the operator to adequately maintain the Garmin Models 400W series installed und
8. e is displayed the battery should be replaced within 1 to 2 months If the battery is not replaced and becomes totally discharged the 400W Series unit will remain fully operational but the GPS signal acquisition time may be increased This acquisition time can be reduced by entering a new seed position each time the unit is powered on There is no loss of function or accuracy of the 400W Series unit with a dead battery The battery must be replaced by the Garmin factory repair station or factory authorized repair station 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 8 of 15 2 6 Troubleshooting Information If error indications are displayed on the 400W Series unit consult the Troubleshooting section contained in the 400W Series Installation Manual P N 190 00356 02 listed under reference documentation in paragraph 2 1 of this document The 400W Series Post Installation Checkout Log in the rotorcraft permanent records includes the configuration information for the installation See Section 5 in the 400W Series Installation Manual P N 190 00356 02 for a sample Log 2 7 Removal and Replacement Information 2 1 400W Series Unit If the 400W Series unit is removed and reinstalled verify that the 400W Series unit power up self test sequence is successfully completed and no failure messages are annunciated If the 400W Series unit is removed for repair and reinstalled or if the 400W uni
9. e rotorcraft s permanent records 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 6 of 15 Table 1 Interfaced Equipment to 400W Series Unit 400W Series Unit Model 400W Series unit DIN rr CDI HSI Source Selection Annunciator Encoding Altimeter or Blind Encoder Altitude Serializer or Fuel Air Data me ean 400W 500W Series Unit Crossfill 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 7 of 15 2 3 Control Operating Information see the 400W Series Installation Manual P N 190 00356 02 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 troubleshoot the 400W Series unit in accordance with Section 2 6 Troubleshooting Information 2 5 Periodic Maintenance Instructions The 400W Series units are designed to detect internal failure A thorough self test is executed automatically upon application of power to the 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 400W Series unit is not permitted unless an inspection as described in this section has been completed within the preceding 12 calendar months and after a lightning strike or hard landing Conduct a visual inspection look for signs o
10. er Rotorcraft Approved Model List AML STC SRO2232LA 1 2 Scope This document identifies the Instruction for Continued Airworthiness for the modification of the rotorcraft for installation of the Garmin Models 400W series GPS WAAS Nav Com installed under Rotorcraft Approved Model List AML STC SRO02232LA 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 16 for information on how to gain FAA acceptance or approval and how to notify customers of changes 1 4 Permission to Use Certain Documents Permission is granted to any corporation or person applying for approval of a Garmin Model 400W series 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 5 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 9 MFD Multi Function Displ
11. f wear deterioration or damage to wires backshells or connectors of the 400W Series unit and wiring harnesses to ensure 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 4 Inspect related antennas for proper sealing and attachment 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 lamp is rated by the manufacturer as having a usable life of 20 000 hours This life may be more or less than the rated time depending on the operating conditions of the 400W Series unit Over time the backlight lamp 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 lamp requires service 2 5 3 Battery Replacement The 400W series has an internal keep alive battery that will last about 10 years The battery is used for GPS system information Regular planned replacement is not necessary The 400W series will display a low battery message when replacement is required Once the low battery messag
12. ntenna off the rotorcraft and detach the coax from the outside For GA 37 antenna GPS XM combination antenna removal or replacement remove the screws from the outside of the rotorcraft Remove old sealant Lift the antenna off the rotorcraft and detach the coax s from the outside verifying coax s are properly labeled with correct color band Note GPS coax is labeled with a blue band and XM cable with a yellow band For GA 35 GA 36 or GA 37 GPS antenna installation follow GPS WAAS Antenna Installation procedures contained in the STC Rotorcraft Installation Supplement for 400W S00W Series P N 190 00357 22 listed in paragraph 2 1 of this document 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 9 of 15 2 8 Diagrams Refer to the 400W Series Installation Manual P N 190 00356 02 and STC Rotorcraft Installation Supplement for 400W 500W Series P N 190 00357 22 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 H of the 400W Series Installation Manual and Appendix D of the STC Rotorcraft Installation Supplement for 400W 500W Series Refer to the GNS 400W Series Post Installation Checkout Log retained in the rotorcraft permanent records for a list of the interfaced equipment The antenna cables are routed between the 400W Series unit and the antenna with disconnects at each unit A
13. re described in the Cable and Wiring Considerations section in the 400W Series Installation Manual P N 190 00356 02 listed under reference documentation in paragraph 2 1 of this document The electrical load analysis may need update after maintenance in accordance with the guidelines in the airframe manufacturers manual If none are available use the guidelines established in AC 43 13 1B Chapter 11 Use the values in Table 4 for computation 400W Series Rotorcraft 190 00356 21 Rev C Instructions for Continued Airworthiness Page 11 of 15 Table 4 400W Series Power Input 14 VDC 28 VDC Connector sm Man pover zm rooma tan La rooma zen Manpower ze mea zsa some 12a eeng Manpower zm Lu zsa some 12a zem Manpower ze Lu 25a soma 120 Sean Manpower ze Lu 25a soma 120 Circuits should be protected in accordance with the approved data in this document see Table 5 and the guidelines in AC 43 13 1B chapter 11 Section 4 For rotorcraft with multiple power busses it is recommended that for each 400W Series unit all power inputs be connected to the same power bus For power interconnect drawings refer to Appendix H STC Approved Installation Diagrams in the 400W series Installation Manual P N 190 00356 02 listed under reference documentation in paragraph 2 1 of this document 400W Series Rotorcraft 190 00356 21 Rev C Instr
14. t is removed and replaced with a different 400W Series unit then follow Post Installation Configuration amp Checkout Procedures contained in the 400W Series Installation Manual P N 190 00356 02 listed in paragraph 2 1 of this document and verify the 400W unit power up self test sequence is successfully completed and no failure messages are annunciated If any work has been done on the rotorcraft that could affect the system wiring antenna cable or any interconnected equipment verify the 400W Series unit power up self test sequence is successfully completed and no failure messages are annunciated To remove the 400W Series unit from the mounting rack insert a 3 32 inch hex drive tool into the access hole at the bottom of the unit face Rotate the hex tool counterclockwise until the unit is forced out about 3 8 inches and can be freely pulled from the rack The 400W unit is installed in the rack by sliding it straight in until it stops about 1 inch short of the final position Insert the hex drive tool into the access hole at the bottom of the unit face Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly seated in the rack Note There are no special handling requirements for the 400W Series units 2 7 2 GA 35 GPS GA 36 GPS and GA 37 GPS XM Antennas For GA 35 or GA 36 antenna removal or replacement remove the screws from the outside of the rotorcraft Remove old sealant Lift the a
15. uctions for Continued Airworthiness Page 12 of 15 GPS 400W PIN 011 01057 00 10 40 50 GNC 420W PIN 011 01058 00 10 40 50 GNC 420W PIN 011 01058 45 GNC 420AW PIN 011 01059 00 10 40 50 GNS 430W PIN 011 01060 00 10 40 50 GNS 430W PIN 011 01060 45 GNS 430AW PIN 011 01061 00 10 40 50 Table 5 Circuit Breaker Size and Placard Power Input Placard s Main P4001 Main P4001 COM P4002 Main P4001 COM P4002 Main P4001 COM P4002 Main P4001 COM P4002 NAV P4006 Main P4001 COM P4002 NAV P4006 Main P4001 COM P4002 NAV P4006 14 VDC Breaker Size o gt 28 VDC Breaker Size 2 10 Special Inspection Requirements None N A 2 11 Application of Protective Treatments None N A 2 12 Data Relative to Structural Fasteners None N A 2 13 Special Tools No special tools are required for system checkout See 400W Series Installation Manual listed in reference documentation in section 2 1 of this document 400W Series Rotorcraft Instructions for Continued Airworthiness 190 00356 21 Rev C Page 13 of 15 2 14 Additional Instructions None 2 15 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 400W Series unit If the unit indicates an internal failure the unit may be removed and replaced See troubleshooting section cont
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