Garmin R44 Instruction Manual
Contents
1. GDU 1 2 VOLTAGE GDU supply voltage is below 12 Increase the voltage above 12VDC VDC This alert is normal in 14V aircraft that are running on the battery only and should clear once the aircraft engine is started and the alternator generator is carrying the load GEO LIMITS Location is too far north south for GRS 77H magnetic compass GPS 1 2 Communication with GPS1 or GPS2 Ensure GPS 1 2 is turned on lost Verify RS 232 wiring from the GPS to the GDU 620 GPS 1 2 PPS Failure This alert will display if the PPS Ensure GPS 1 2 is turned on signal has not been received in more than 5 sec If the unit is configured for dual GPSs then the side will be specified in the error Verify 1PPS wiring from the GPS to the GDU 620 GSR FAIL GSR has failed Check if GSR power discrete is on and GSR status discrete is off at the same time Verify wiring between the GDU and the GSR Check power and ground wires on GSR 56 HDG FAULT AHRS magnetometer fault has GRS 77H not receiving information from occurred GMU 44 Verify wiring to GMU 44 HDG LOST Heading from the GRS77 GMU 44 Caused by a local magnetic anomaly No is not valid action required lt LRU gt SERVICE Specific LRU should be serviced Return indicated LRU to Garmin for where lt LRU gt denotes specific service LRU MANIFEST GDU has received product data for Ensure the manifest is properly an LRU that should have a manifest e2. at least one GPS has operating in exclusively in no Jinformation acquired a valid position GPS mode If GDU 620 does not have a valid position verify wiring between GDU and GPS receiver and configuration of GDU 620 and GPS receiver If GDU has a valid GPS position verify wiring between GDU and GRS Also verify time mark wiring AHRS1 GPS AHRS 1 not AHRS is not receiving GPS Verify GPS2 power and check the wiring receiving backup GPS information from GPS2 information AHRS1 SRVC AHRS magnetic field model should Update GRS 77H IGRF model current be updated Appears on ground model is with aviation database only AHRS1 TAS AHRS is not receiving true airspeed GDC not powered up Close ADC C B from ADC GDC not receiving input from GTP 59 OAT probe Verify wiring is correct ARINC 429 connection from GDC 74H to GRS 77H is not working Verify wiring is correct AUD NOT AVAIL Audio system not available Contact Garmin Technical Support AUD SYS FAIL Audio system failure Contact Garmin Technical Support CAL LOST Registry reports that it has lost calibration data Contact Garmin Technical Support CNFG MISMATCH GDU 1 2 airframe configurations disagree Applicable only to dual GDU installations GDU in normal mode has received updated crossfill tags for configuration registry entries Restart both GDUs in configuration mode to automatically synchroni
3. close to a large ground power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 2 6 of this ICA Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 16 of 20 Table 2 3 GRS 77H Calibration Criteria Calibrations Required GRS 77H GRS GMU Pitch Roll Magnetic Condition Offset Calibration See Section 5 See Section 5 of the G500H STC of the G500H STC Installation Manual Installation Manual GRS 77H AHRS was removed and or replaced The mounting tray was NOT None Required removed and the mounting tray bolts were NOT loosened GRS 77H AHRS was removed and or replaced The mounting tray WAS removed and or mounting tray bolts WERE loosened GRS 77H AHRS Configuration Module was replaced 2 7 8 GMU 44 Unit 2 7 3 4 Removal 1 Gain access to the GMU 44 magnetometer NOTE Some metal structures of the GMU 44 may become magnetized if closely exposed to A permanent magnets therefore it is recommended to use non magnetic screwdrivers near the GMU 44 to prevent magnetizing any nearby metal structures 2 Unscrew the three screws that hold the GMU 44 to its mounting rack 3 Carefully lift the GMU 44 from the rack 4 Disconnect the wiring harness 2 7 3 2 Installation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Connect the wiring harness
4. stored settings when the UPDT CFG soft key is pressed If the GDU 620 is replaced at the same time as the Configuration Module then the System Setup will need to be performed per Section 5 5 of the G500H Installation Manual 2 7 1 3 Return to Service After removing and reinstalling the GDU 620 per the instructions above a return to service check should be performed 1 Power up the GDU 620 and all interfaced systems in normal mode 2 Verify that there are no red Xs and that no alerts are present If red Xs or alerts are present troubleshoot using Section 2 6 of this ICA 2 7 2 GRS 77H Unit 2 7 2 1 Removal 1 Disconnect the GRS 77H connector NOTE Some metal structures of the GRS 77 may become magnetized if closely exposed to permanent magnets While this will not affect the GRS 77 itself it may slightly affect A nearby magnetic instruments in the area e g whiskey compass Ordinary use of magnetic screwdrivers to tighten GRS 77 fasteners will not cause problems but non magnetic screw drivers are preferred Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 15 of 20 2 Loosen the four Phillips thumbscrews with a screwdriver 3 Gently lift the GRS 77H from the mounting plate if the supports for the mounting plate are removed the GRS 77H must be recalibrated 2 7 2 2 Installation 1 Place the GRS 77H on the mounting plate ensuring the orientation is correct 2 Fas
5. 0 and the circuit breaker is closed Unit intensity turned down Ensure that unit is not in manual intensity control mode with the intensity turned down All expected configuration An Installer Unlock Card is not Insert the Installer Unlock Card pages are not displayed inserted into the GDU 620 P N 010 00769 60 into the bottom slot of the GDU 620 and cycle power The GDC OAT probe type The RS 232 connection to the Ensure that the GDC 74H RS 232 shows up as UNKNOWN GDC 74H is not working connection to the GDU is properly wired and ensure that the GDC 74H circuit breaker is closed When loading software the The software loader card is Insert the loader card in the top slot and LRU software is not being installed in the bottom slot of the cycle power to the GDU displayed on the GDU 620 SOFTWARE UPLOAD page The software loader card contains Repeat the process for making the no information software loader card Configuration errors are The configuration module has not Update the configuration module displayed on power up been updated before the GDU enters normal mode Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 9 of 20 Problem Cause Solin Vertical GPS deviation is not displayed on the GDU 620 For 400W 500W Series units the ARINC 429 vertical deviation labels are not being transmitted Enable Labels on the 400W 500W Series un
6. H HYD PWR Gov START ALT START GAGES e e GPS1 AVIONICS XPDR AUDIO FAN KR BEACON Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 5 of 20 The installed G500H equipment can be accessed as described below the GDU 620 position by removing four glareshield retaining screws GDU 620 FS 30 00 WL 42 5 Access or remove by removing the six screws in the bezel of GRS 77H FS 19 25 WL 30 0 Access or remove by tilting the instrument shroud to its open GMU 44 FS 41 5 WL19 75 Access or remove by lifting the pilots seat bottom GDC 74H FS 39 25 WL 15 75 Access or remove by lifting the co pilots seat bottom Then remove the screws holding the divider plate to the forward half of the co pilots seat box Remove the divider plate to gain access to the GDC 74H bottom of the helicopter 2 2 1 Weight and Balance Information GTP 59 FS 42 5 WL 13 5 Access or remove by removing the center access panel on the Weight and Balance Robinson R44 1 LONGITUDINAL 2 LATERAL 3 ITEM PART NUMBER WEIGHT LB ARM IN MOMENT IN LB ARM IN MOMENT IN LB 1 011 01264 60 GDU 620 Unit Only 6 38 30 00 191 4 15 9 57 GDU 620 Installed connector 7 04 i 211 2 10 56 2 011 00868 20 GRS 77H Unit Only 2 80 53 9 0 0 GRS 77H Install
7. Instructions for Continued Airworthiness for G500H in Robinson R44 Series Rotorcraft Reg No S N STC TBD Dwg Number 190 01190 11 Rev 1 Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Record of Revision Rev Date Description of Change 23 11 11 Initial Release a E x Tto INTRODUGTION 53 n PEE OE e ERR epa 3 Til Uo Em 3 1 2 SCOE actae tc farce edente detect itf bed ovs er P s haee ee Pet ona Ete 3 1 3 DOCUMENT Gontrol scietis tn etta eroe eio ea apo eno Lara ea eer ano dpa ea S a apo apo dean 3 1 4 Permission to Use Certain Documents sse 3 1 5 DORNMMONS oes TE 3 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS senes 4 2 1 IntrOQUClOTr iie EC RA Ee RARE RE RR Ee RR eed 4 2 2 Description of Alteration sesenta 5 2 3 Control Operating Information ssssssssssssseeeneennen nenne 7 2 4 Servicing Information s aan e i aa ea i ia a ii 7 2 5 Periodic Maintenance Instructions esssssssssseeeeeeeee nenne 7 2 6 Troubleshooting Information nennen 9 2 7 Removal and Installation Information sseeenennees 14 2 8 DIagraris iterare et nie gi od re tee odode pa t podre dd 19 2 9 Special Inspection Requirements sssssssssseeeeeeeeeene nenne 19 2 10 Application of Protective Treatments nens 19 2 11 Data Relative to Str
8. L or later revision Garmin 005 W 0227 09 Rev 1 G500H ROBINSON R44 GLARESHIELD HARNESS ASSY REQD or later revision Garmin 190 01 190 00 Rev 2 G500H ROBINSON R44 INSTALLATION DRAWING or later revision Retention This document or the information contained within will be included in the rotorcraft s permanent records 2 2 Description of Alteration This STC upgrades existing avionics for the Robinson R44 series rotorcraft as summarized below The Garmin G500H Flight Display System consists of an instrument panel mounted GDU 620 display and remote mounted LRUs which provide data to the display The GDU 620 provides controls for the G500H system and of a Primary Flight Display and Multifunction Display in the pilot s primary field of view Remote mounted LRUs include one GRS 77H AHRS one GMU 44 Magnetometer one GDC 74H ADC and one GTP 59 OAT probe Rotorcraft modified under this G500H STC are restricted to VFR only To clarify this operation limitation a placard with the text THIS ROTORCRAFT IS APPROVED FOR DAY AND NIGHT VFR OPERATIONS is required to be in the pilot s view All installed G500H equipment is connected to a power bus that receives power as soon as the battery master switch is turned on Separate circuit breakers have been installed in the circuit breaker panel for the GDU 620 PFD GRS 77H GMU 44 AHRS and GDC 74H ADO as circled below e e e e e AUX HORN CLUTC
9. LRU indicates an internal failure the unit may be removed and replaced See the troubleshooting section contained in the G500H 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 submitted to the ACO along with the revised ICA The ACO will obtain AEG acceptance and approve any revision to the Airworthiness Limitations in 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 through any Garmin dealer or from Garmin customer assistance A Garmin Service Bulletin describing ICA revision will be sent to dealers if revision is determined to be significant 2 16 Assistance FAA 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 rotorcraft by this Supplemental Type Certificate obligates the rotorcraft operator to include the maintenance information provided by this document in
10. at the traffic sensor has failed Troubleshoot traffic system TRAFFIC STDBY The traffic information system is in Standby mode while the aircraft is In Air TRK LOST GPS1 TRK lost HSI defaulted to GPS2 TRK 2 7 Removal and Installation Information If any G500H LRUs are removed and reinstalled or a new unit is installed verify that the LRU unit power up self test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display If any work has been done on the rotorcraft that could affect the system wiring or any interconnected equipment verify the G500H system unit power up self test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display Whenever removing or installing units remove power from the LRU by removing aircraft power or opening the LRU circuit breaker 2 7 1 GDU 620 Unit 2 7 4 1 Removal 1 Remove the six mounting screws from the bezel of the GDU 620 2 Pull the GDU 620 far enough out from the instrument panel to access the three rear connectors 3 Disconnect the rear connectors 4 Remove the GDU 620 2 7 1 2 Installation 1 Visually inspect the connectors to ensure that there are no bent or damaged pins Repair any damage 2 Connect the rear connectors ensuring that each slidelock is secured on both sides 3 Setthe GDU 620 into place 4 Install the six mounting screws into the bezel of the GDU 620 Instructions for Co
11. cceptance 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 G500H system 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 ACO Aircraft Certification Office 2 ADC Air Data Computer 3 AEG Aircraft Evaluation Group 4 AHRS Attitude Heading Reference System 5 CFR Code of Federal Regulations FAA Federal Aviation Administration 7 ICA Instructions for Continued Airworthiness MFD Multi Function Display PFD Primary Flight Display 10 PMI Principal Maintenance Inspector 11 STC Supplemental Type Certificate Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 3 of 20 2 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 2 4 Introduction Content Scope Purpose and Arrangement Applicability Definition of Abbreviations Precautions Units of measurement Referenced publications Additional Maintenance Data Instructions for Continued Airworthiness for G500H in Robinson R44 Serie
12. d power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 2 6 of this ICA 2 4 GDC 74H Unit 2 7 4 4 Removal 1 Disconnect the pitot static plumbing from the rear of the unit Reference G500H Installation Manual Section 2 5 3 and 3 2 6 2 Disconnect the single connector 3 Remove the two 2 screws on the mounting plate near the pitot static ports Loosen the other two 2 screws 4 Carefully remove the unit from its mounting location 2 7 4 2 Installation 1 Place the unit in the mounting tray 2 Position the unit and fasten using the four 4 screws 3 Connect the pitot static plumbing Reference G500H Installation Manual Section 2 5 3 and 3 2 6 4 Inspect the connector and pins for damage Repair any damage 5 Connect the connector to the unit ensuring that each jackscrew is secured Original GDC 74H is Reinstalled If the original GDC 74H is re installed then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process New Repaired or Exchange GDC 74H is Installed If a new repaired or exchange GDC 74H unit is installed then software must be loaded to the unit Refer to Section 5 4 2 of the G500H STC Installation Manual for more information GDC 74H Configuration Module is Replaced If the GDC 74H Configuration Module is replaced
13. e artificial changes in airspeed cause disagreement with the other sensor measurements internal to the GRS 77H This sensor disagreement will not occur in the normal conditions of flight Invalidation of heading is possible if the air data tests are conducted indoors due to typical magnetic anomalies even with a good GPS signal Instructions for Continued Airworthiness for G500H in Robinson R44 Series Rotorcraft This is expected behavior and no troubleshooting is required if this occurs To reduce the chances of inducing attitude and heading errors resets while conducting the air data tests ensure that the G500H is receiving good GPS signals This is expected behavior and no troubleshooting is required if this occurs 190 01190 11 Rev 1 Page 10 of 20 2 6 2 G500H Alerts The G500H will display a number of alerts on the GDU 620 MFD These are listed in the following table Table 2 2 GDU 620 Alert Troubleshooting Guide Alert Text Gmse Seen lt LRU gt SERVICE Specific LRU should be serviced Return indicated LRU to Garmin for where lt LRU gt denotes specific service LRU AHRS1 GPS AHRS 1 using AHRS is using the backup GPS Verify GPS1 power and check the wiring backup GPS source information AHRS1 GPS AHRS is not AHRS is not receiving any GPS Verify GPS power and check the wiring receiving any GPS information information AHRS1 GPS AHRS 1 AHRS is not receiving any GPS Ensure that
14. ed with bracket and 19 25 0 0 connector 3 75 72 19 0 0 3 011 00870 10 GMU 44 Unit Only 0 35 14 53 6 13 GMU 44 Installed with bracket and 0 51 ud 2147 E 8 93 connector i 4 011 00882 11 GDC 74H Unit Only 1 70 66 73 19 55 GDC 74H installed with bracketand 5 5 suem p ais E connector Instructions for Continued Airworthiness for G500H in Robinson R44 Series Rotorcraft 190 01190 11 Rev 1 Page 6 of 20 1 A rotorcraft weight and balance is required after installation of the G500H system Refer to installation manual P N 190 01 190 06 for additional information including overall size and center of gravity location of all LRUs 2 The longitudinal arm is measured in terms of the fuselage station FS number 3 The lateral arm is measured in terms of the butt line BL The centerline of the helicopter is BL 0 00 The moment arms to the left side looking forward are negative and the moment arms to the right side are positive 2 3 Control Operating Information See the G500H Pilot s Guide or the 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 Some metal structures of the GRS 77 may become magnetized if closely exposed to permanent magnets While this will not affect the GRS 77 itself it may slightly affect nearby magnetic instruments in the area e g whiskey compass Ordina
15. ess 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 8 of 20 Item Interval Description Procedure Perform an electrical bonding test for each listed LRU 1 Gain access to the LRU see General Arrangement Drawing for LRU location 2 Disconnect all harness connectors from the LRU 3 Measure the resistance between the LRU and a nearby exposed portion of aircraft metallic structure If any resistances are greater than the values below refer to FIBRE GUI T section 3 5 of the Installation Manual 190 01 190 06 for GDU 620 GRS 77H twelve 12 the bonding preparation and the maximum resistance GDC 74H GMU 44 GTP values that must be met 59 rii a For the GDU 620 verify the resistance is less than whichever is or equal to 40 millionms b For the GTP 59 verify the resistance is less than or equal to 5 millionms c Forthe remaining LRUS verify the resistance is less than or equal to 20 milliohms 4 Reconnect all disconnected harness connectors and ensure they are secure first Repeat for each listed LRU 2 6 Troubleshooting Information If error indications are displayed on the GDU 620 display unit consult the Troubleshooting section contained below 2 6 1 G500H Troubleshooting Table 2 1 GDU 620 Troubleshooting Guide Problem Cause Solin Unit does not power up Improper wiring circuit breaker Ensure power is properly wired to the blank screen open GDU 62
16. it ARINC 429 configuration page Unable to control the GPS course when in OBS mode The GPS navigator is not correctly configures as LNAV1 2 or SYS1 2 Configure the ARINC 429 inputs outputs for LNAV1 SYS1 or LNAV2 SYS2 based upon whether the navigator is GPS1 or GPS2 Data is not being received from an ARINC 429 device valid data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page ARINC 429 bus hi and low are swapped Verify wiring Wrong device is connected to port on GDU 620 Use correct ports refer to interconnect details Data is not being received from an ARINC 429 device no data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page On the transmitting LRU the ARINC 429 transmitter speed is not set correctly Set the ARINC 429 transmitter speed to correct speed Wiring is not correct Check for continuity shorts and correct as required Attitude and heading on GDU 620 red X GRS 77H resets during air data ground testing Heading red X during air data ground testing Attitude and heading errors resets are possible if the air data tests are conducted indoors without a good GPS signal With marginal or no GPS signals present sudden changes in airspeed caused by using a pressure tester may result in attitude and heading errors and possibly cause the GRS 77H to reset This occurs because th
17. ntinued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 14 of 20 NOTE The installation configuration settings are stored in the configuration module and will be retained when the GDU 620 is replaced with a new unit User settings such as map orientation preferences are stored internally and will be lost when the GDU 620 is replaced with a new unit Original GDU 620 is Reinstalled If the original GDU 620 is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair process No configuration is required New Repaired or Exchange GDU 620 is Installed If a new repaired or exchange GDU 620 unit is installed then software must be loaded No configuration is required NOTE Upon first power up after installing a new GDU 620 it is normal to see a series of A LOADING messages appear on the screen These messages indicate that the GDU 620 is updating its configuration settings from the configuration module Refer to Section 5 of the G500H STC Installation Manual for the GDU 620 Software Loading procedure 5 4 1 followed by the Manifest Configuration 5 5 6 and the Configuration Module Update 5 5 16 GDU 620 Configuration Module is Replaced If the GDU 620 Configuration Module is replaced the GDU 620 will update the configuration module from its internally
18. ntry but is not in the manifest configured The LRU software P N and version number in the manifest does not match the values being reported by Update the LRU software to match the manifest Update the manifest to match the LRU that LRU software NAV 1 2 No navigation receiver data from Nav 1 or Nav 2 REGISTER GFDS Data services are inoperative Registered the GSR 56 with Garmin Flight register w GFDS Data Services to receive weather data SIMULATOR The simulator mode is active Ensure P6202 36 is not grounded SVT DISABLED Out of Location is beyond region covered available terrain region by terrain database SVT DISABLED Terrain DB A 30 arc second terrain database is Update the Supplemental Data card with resolution too low being used the 9 arc second terrain database Instructions for Continued Airworthiness for G500H in Robinson R44 Series Rotorcraft 190 01190 11 Rev 1 Page 13 of 20 Alert Text Cause Soltin SW MISMATCH GDU software version strings do not Verify the correct SW is loaded match TERRAIN DSP Terrain Airport Terrain or Obstacle Update Reload database database error TRAFFIC FAIL The traffic information system has The GDU 620 is not receiving traffic failed information from the traffic sensor Verify wiring between GDU 620 and traffic sensor The GDU 620 is receiving information from the traffic sensor but the information is indicating th
19. omposite glare shield assembly Garmin PN 011 02759 00 28VDC electrical system or 011 02759 01 14 VDC electrical system for damage Inspect for loose rivets indicated by cracks in composite or aluminum components or paint Contact Garmin customer support for glare shield replacement components 2 Check tightness of instrument panel hinge mounting screws glare shield shear web mounting screws and vibration restraining bracket mounting screws Re torque loose fasteners per Section 1 320 of Robinson Model R44 Maintenance Manual Change 13 October 2006 or later page 1 22 3 Check tightness of mounting screws attaching instrument panel to glare shield Re torque loose fasteners per Section 1 320 of Robinson Model R44 Maintenance Manual Change 13 October 2006 or later page 1 22 GDU 620 GRS 77H GDC 74H GMU 44 GTP 59 100 Hours 12 Calendar Months Conduct a visual inspection look for signs of wear deterioration or damage to wires backshells or connectors on units and their wire harnesses to ensure installation integrity 1 Gain access to LRU see section 2 2 for LRU locations 2 Inspect each unit for security of attachment 3 Inspect all knobs and buttons for legibility 4 Inspect condition of wiring routing and attachment clamping Inspect integrity of shield terminations Inspect for signs of corrosion on equipment and their rack installations oo Instructions for Continued Airworthin
20. robe and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have attached If there is visible sign of damage to the probe then it must be replaced Verify that OAT is displayed on the GDU 620 PFD normally 2 10 Application of Protective Treatments Apply Flat Black Imron 373 P 29950 Polyurthane Enamel from Dupont to the glareshield and instrument panel as required Apply any one of the following corrosion protection to the metal brackets as needed Epoxy Primer Chemical and Solvent Resistant Per MIL P 23377 Alkyd Base One Component Primer Per Federal Specification TT P 1757 Chemical Conversion Coating Per MIL DTL 81706 2 11 Data Relative to Structural Fasteners Refer to the following table for data on the location type and torque values for structural fasteners FASTENER TYPE AND TORQUE Location 6 32 Screw 8 32 Screw 10 32 Screw NUT 5 16 HEX SKIRT see section 2 2 12 15 inch pounds 12 15 inch pounds 22 25 inch pounds 100420 inch pounds Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 19 of 20 2 12 Special Tools For electrical bonding testing a milliohm meter is required 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 G500H system If any
21. ry use of magnetic screwdrivers to tighten GRS 77 fasteners will not cause problems but non magnetic screw drivers are preferred It is also recommended to use non magnetic screwdrivers near the GMU 44 to prevent magnetizing any nearby metal structures In the event of system failure troubleshoot the G500H system in accordance with Section 2 6 Troubleshooting Information 2 5 Periodic Maintenance Instructions Maintenance of the components installed by this STC is on condition except as noted in the following table Item Interval Description Procedure 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 current the unit will issue an alert upon startup indicating the OSVYEEABIRO Prea model has expired The model can be updated by inserting an aviation database card with an updated IGRF model and powering on the system A prompt will direct the user to press ENT to update the model Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 7 of 20 Item Interval Description Procedure Garmin Glareshield Assembly 100 Hours 12 Calendar Months Coincident with upper console 100 hour inspection per Robinson Model R44 Maintenance Manual Change 13 October 2006 or later page 2 16 perform 1 Visual inspection of c
22. s Rotorcraft This document identifies the Instructions for Continued Airworthiness for the modification of the rotorcraft by installation of the Garmin G500H PFD MFD System Applies to Robinson R44 series rotorcraft altered by installation of the Garmin G500H PFD MFD System See Section 1 5 None None Garmin 190 01190 06 Rev 2 G500H INSTALLATION MANUAL FOR ROBINSON R44 SERIES ROTOCRAFT or later revision Garmin 190 01150 02 Rev C G500H PILOT GUIDE or later revision Garmin 005 W0227 00 Rev 1 G500H Robinson R44 MAIN WIRE HARNESS ASSY DWG REQ D or later revision Garmin 005 W0227 01 Rev 1 G500H ROBINSON R44 NAV1 HARNESS ASSY DWG OPTL or later revision Garmin 005 W0227 02 Rev 1 G500H ROBINSON R44 GPS2 HARNESS ASSY DWG OPTL or later revision Garmin 005 W0227 03 Rev 1 G500H ROBINSON R44 NAV2 HARNESS ASSY DWG OPTL or later revision Garmin 005 W0227 04 Rev 1 G500H ROBINSON R44 WX DATALINK HARNESS ASSY DWG OPTL or later revision Garmin 005 W 0227 05 Rev 1 G500H ROBINSON R44 IRIDIUM DATALINK HARNESS ASSY DWG OPTL or later revision Garmin 005 W 0227 06 Rev 1 G500H ROBINSON R44 VIDEO HARNESS ASSY DWG OPTL or later revision 190 01190 11 Rev 1 Page 4 of 20 Garmin 005 W 0227 07 Rev 1 G500H ROBINSON R44 SERIAL ALTITUDE HARNESS ASSY DWG OPTL or later revision Garmin 005 W 0227 08 Rev 1 G500H ROBINSON R44 TRAFFIC HARNESS ASSY DWG OPT
23. ten the unit to the plate using the Phillips thumbscrews Recommended torque is 22 25 inch pounds 3 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 4 Connect the connector to the GRS 77H ensuring that each slidelock is secured on both sides Original GRS 77H is Reinstalled If the original GRS 77H is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Reference Table 2 3 to determine whether recalibration is required New Repaired or Exchange GRS 77H is Installed If a new repaired or exchange GRS 77H unit is installed then software must be loaded per Section 5 4 2 of the G500H STC Installation Manual Reference Table 2 3 to determine whether re calibration is required GRS 77H Configuration Module is Replaced If the GRS 77H Configuration Module is replaced the GRS 77H must be re calibrated Reference Table 2 3 2 7 2 3 Return to Service After removing and reinstalling the GRS 77H the following return to service checks should be performed 1 Power up the G500H system with the GDU 620 in normal mode 2 Verify that the GDU displays valid heading and attitude within approximately one minute Note that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is
24. the GDC 74H must be configured Refer to Section 5 5 12 of the G500H STO Installation Manual 2 7 4 3 Return to Service After removing and reinstalling the GDC 74H the following return to service checks must be performed 1 Power up the G500H system with the GDU 620 in normal mode 2 Verify that the GDU displays valid air data within approximately one minute 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 2 6 of this ICA 4 Perform a leak check of the pitot static system and functional check in accordance with the G500H STO Installation Manual sections 3 2 6 and 5 8 2 Observe the airspeed altitude and vertical speed for proper operation Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 18 of 20 2 8 Diagrams Rotorcraft specific LRU locations and wire routing diagrams are contained in the Garmin Reference Publications listed in Section 2 1 of this document Point to point wiring diagrams are in Appendix D of the G500H STC Installation Manual Refer to the G500H Post Installation Checkout Log retained in the rotorcraft permanent records for a list of the interfaced equipment and port configurations 2 9 Special Inspection Requirements 2 9 1 Post Lightning Strike Inspection In the event of a suspected or actual lightning strike to the aircraft the GTP 59 OAT Probe and its associated installation shall be inspected The p
25. the GDU and the GDL 69 Check power and ground wires on GDL 69 GDL69 CONFIG The GDL 69 configuration With the GDU 620 in configuration mode information stored in the GDL 69 go to the GDL 69 page in the GDL page and the GDU 620 configuration group Verify that the SET and ACTIVE module do not match configuration settings are the same If not use the SET gt ACTV soft key to copy the configuration settings from the GDU 620 into the GDL 69 The GDL 69 configuration was Update the GDL 69 configuration using updated using another LRU the GDU 620 e g the GMX 200 or 400W 500W GDU CONFIG This error appears whenever the Cycle power to the GDU This error GDU is replaced with a GDU that automatically clears on the second power was configured for a different up with a different configuration module installation Error in the configuration of the GDU 620 GDU 1 2 COOLING Specific GDU has poor cooling and Ensure fans on indicated GDU are power usage is being reduced functioning Ensure fans on indicated GDU are not obstructed GDU 1 2 DB ERR Error in specific database where Load the correct databse GDU 1 2 DB denotes specific database GDU KEYSTK GDU KEY key is stuck The GDU has detected the KEY key as stuck where KEY denotes a specific key Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 12 of 20 Alert Text Case Solin
26. the operator s rotorcraft maintenance manual and or the operator s rotorcraft scheduled maintenance program 3 AIRWORTHINESS LIMITATIONS 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 Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 20 of 20
27. to the GMU 44 3 Lower the GMU 44 into the rack and secure the plate with the three Phillips screws Original GMU 44 is Reinstalled If the original GMU 44 was reinstalled then software loading is not required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Recalibration is required only if the mount for the magnetometer was changed If the magnetometer mount was changed refer to Section 5 6 2 of the G500H STC Installation Manual for the GRS 77H GMU 44 Magnetic Calibration New Repaired or Exchange GMU 44 is Installed If a new repaired or exchange GMU 44 unit is installed then software must be loaded and the GRS 77H GMU 44 Magnetic Calibration must be performed Refer to Section 5 of the G500H STC Installation Manual for instructions on software loading 5 4 2 and Magnetic Calibration 5 6 2 Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 17 of 20 Return to Service After removing and reinstalling the GMU 44 the following return to service checks should be performed 1 Power up the G500H system with the GDU 620 in normal mode 2 Verify that the GDU displays valid heading within approximately one minute Note that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large groun
28. uctural Fasteners cccceccecceceeseeeeceeeeeeeeeeeseeeeeeeaesaeeeeseeeaeeas 19 2 12 Special Tools ott oi cene fara eed ie o ev Etui e eet 20 2 13 Additional Instr cl ris an Aa a a i een ein ri ran rk aeu nie ae Y iau a en a 20 214 Overhaul Period Jn tint ati ni n A a 20 2 15 ICA Revision and Distribution essessssssssssseeeeeneene nennen 20 2 16 AssiSlariG8 oiii oi m a e LE e M AO HORT AER He IR dian 20 2 17 Implementation and Record Keeping sss 20 3 AIRWORTHINESS LIMITATIONS sse 20 Instructions for Continued Airworthiness 190 01190 11 Rev 1 for G500H in Robinson R44 Series Rotorcraft Page 2 of 20 1 INTRODUCTION 1 1 Purpose This document is designed for use by the installing agency of the Garmin G500H PFD MFD System as Instructions for Continued Airworthiness in response to Title 14 CFR Part 27 1529 and Part 27 Appendix A This ICA includes information required by the operator to adequately maintain the Garmin G500H system installed under STC TBD 1 2 Scope This document identifies the Instruction for Continued Airworthiness for the modification of the rotorcraft for installation of the Garmin G500H PFD MFD System installed under STC TBD 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 a
29. ze settings CNFG MODULE The configuration module is inoperative Verify wiring to configuration module Replace configuration module DATA LOST Pilot stored data was lost Recheck data and settings Instructions for Continued Airworthiness for G500H in Robinson R44 Series Rotorcraft 190 01190 11 Rev 1 Page 11 of 20 Alert Text DSCRT CONFIG Discrete A discrete output required by an Use the DISCRETE CONFIGURATION output configuration error interfaced system has not been page in the SYS page group to configure configured the discrete outputs to match the installation Verify wiring to the discrete FAN 1 FAIL Fan 1 has reported 0 RPM when it Inspect the GDU fan for an obstruction was powered with a PWM duty Contact Garmin Technical Support cycle higher than or equal to 1096 FAN 2 FAIL Fan 2 has reported 0 RPM when it Inspect the GDU fan for an obstruction was powered with a PWM duty Contact Garmin Technical Support cycle higher than or equal to 1096 GDC CONFIG The GDC configuration information With the GDU 620 in configuration mode stored in the GDC and the GDU 620 go to the GDC page in the GDL page configuration module do not match group Verify that the SET and ACTIVE configuration settings are the same If not use the SET gt ACTV soft key to copy the configuration settings from the GDU 620 into the GDC GDL69 GDL 69 has failed Verify wiring between
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