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Garmin B4 Instruction Manual

1. POST MOD 07 3850 3587 ee 140L CONSOLE TERMINAL STRIP 58 ISTING 11K733E cF20 ZONE 702 1LK745E MEET A 1LK694E 20 AWG 81 428V INDICATOR 1 1 A EXISTING OR PRE MOD 07 3850 1491 1 zav Ps 12 dakK294EL 2 A EFIS TB ZONE C2 OUTPUT DAY NIGHT rt 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 74 of 82 DETAIL F AIR GROUND STATUS OPTION FOR A C ALL BEFORE MOD 3514 PANE A EFIS TB BA 1 024 m M G B P i FN AA VEU OR FOR A C ALL POST MOD 3514 ENS ON m oA N 1EMTE n E Zio Mc etr VEU OR FOR ALL POST MOD 3514 WITH POST MOD 07 3850 4 ALPHA WARNING PANEL EXISTING Ax sess 3 EFIS we r M G B P AN 4 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 75 of 82 EMERGENCY SWITCH PRE MOD 0 5850 INSTRUMENT PANEL YELLOW So
2. 30 Section 12 00 00 Servicing Maintenance Practices 11 30 Section 12 10 00 Return to Service Practices u 31 Section 12 20 00 Calibration Requirements 32 20 2 2 kaa 33 Section 20 00 00 Standard Practices ax RR eR ECKE 33 Section 20 10 00 Torques Maintenance 34 Section 20 30 00 Painting Maintenance Practices sess 38 Section 20 40 00 Corrosion Control Maintenance 39 Section 20 90 00 Dye Penetrant Inspection 2 42 CHAPTER 31 c 43 Section 31 00 00 8 43 CHAPTER 68 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 2 of 82 Section 98 00 00 Wiring Diagrams and Pitot Static System 68 Section 98 10 00 Wiring Dlagrams cure ie tse 69 Section 98 20 00 Pitot Static System Schematic 1 82 Inst
3. EMERGENCY SW A 2 NLT15A22 LIMIT ANNUNCIATOR PRE MOD 07 3587 INSTRUMENT PANEL ee MCN zas S 4 ANLTI2A20 2 A 150L PATE PANEL EXISTING 1501 A 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 76 of 82 Jr EI aze Jw 43 0985 0 1504 s oE NY MS XONZOMNG PS MOTTA Ww RE 4 a JIDSNOO 1091 9 e swa SIG os E T 5 HOVI SN vc di 3 SIGSNOD 70 1 L 1 smo 13 4 TOULNOD ONINAIG w u ji SSGSHV SNISIXS Ny avzu n 9 4 86 81 5133 1 TIAN ONISHI E e M ev s 98 7 amp T 29 y E aw z e iar as x lt ES 3105405 1071 r E NOLVIONCINNV SNIGNV 1 TANVd LNANNYLSNI ONILHOIT LNIWNAYLSNI 16 TWOldAL Page 77 of 82 190 01527 15 Rev 1 98 10 00 for the Garmin G500H Installation in Eurocopter EC130 Instructions for Continued Airworthiness 00 TI
4. GDU 620R PFD MFD o AWI ARINC 429 IN4 A ARINC 429 IN 4 B ARINC 429 IN6 A NAV 2 ARINC 429 IN 6 B NAV 1 5 232 OUT 5 OR RS 232 5 2 5 252 GND 5 AUDIO OUT HI AUDIO OUT LO AUDIO INHIBIT IN AUDIO ACTIVE OUT ETHERNET IN 2A ETHERNET IN 2B ETHERNET OUT 2A ETHERNET OUT 2B A TRAFFIC TAS TEST TIS TAS STANDBY ARINC 429 IN 7 A L ARINC 429 IN 7 B SERIAL A ALTITUDE RS 232 OUT 8 RS 232 GND 8 GSR RMT PWR ON 5 232 IN 6 RS 232 OUT 6 RS 232 GND 6 AX GSR 56 GSR STATUS IN ETHERNET IN 1A ETHERNET IN 1B ETHERNET OUT 1A ETHERNET OUT 1B GDL69 A COMPOSITE VIDEO IN 1 COMPOSITE VIDEO RTN A COMPOSITE VIDEO IN 2 AIR GROUND STATUS FIS TI gt 2 gt m gt rr EE HAR ERE 7 5 nioj gt gt gt gt amp W ON gt 7 _ r C rea A AN Tw J 1 AD A e B _ J AA N A A REF k i Si pu H rw J MAR a1 y EE TA HEJ 8 A fe D AN N P 1 WE PTE A Q lt im HER A Y AXE C 4 m z gt c gt HHH AH HRA UA m njoj 98 10 00 Instructions for Continued Airw
5. Short Open End Adapter TORQUE ADAPTFR WRENCH HANDGRIP CENTERLINE PREDETERMINED Set Screw Adapter me TxL FORMULA LE aY gt EXAMPLE WITH AS PLUS DIMENSION 135x10 1350 T 135 LB IN Y 10415 115 117 39 Y UNKNOWN Hose Clamp Adapter L 10 0 IN 1 5 IN Y 447 LB IN T ACTUAL DESIRED TORQUE Y APPARENT INDICATED TORQUE L EFFECTIVE LENGTH LEVER E EFFECTIVE LENGTH OF EXTENSION Open End Wrench TORQUE WRENCH Adapter WRENCH HANDGRIP DRIVE CENTERLINE CENTERLINE ADAPTER PREDETERMINED 7 16 Flare Nut Wrench Adapter TxL FORMULA ce Y EXAMPLE WITH E AS MINUS DIMENSION A q T 435 LB IN Ys T 1350 158 2 UNKNOWN Spanner Wrench L 10 0 IN Adapter E 1 5 IN Y 159 LB IN Figure 20 01 20 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 35 of 82 2 Torque Wrenches Warning Do not exceed maximum allowable torque value Overstressing of fastener may result Standard hardware torque values are given in the following tables 20 01 through table 20 03 Table 20 01 gives recommended torque values for fine thread fasteners shear and tension applications Table 20 02 gives recommended torque values for coarse thread fasteners shear and tension applications Table 20 03 gives recommended torque values for phillips head Screws Table 20 01 Recommended Torque Values for Fine
6. TT I 735 Trichloroethane MIL T 81533 Nylon Scouring Pad 3M Scotchbrite 63 3M 240 Grit Sandpaper Commercial B20 Grit Sandpaper Commercial 240 Grit Aluminum Oxide Abrasive Cloth Commercial Sealant MIL S 8802 Adhesive transfer tape 950 2 70 0060 3057 4 3M 31 00 00 190 01527 15 Rev 1 Page 61 of 82 4 Troubleshooting guide If error indications are displayed on the GDU 620 display unit consult the Troubleshooting section contained in Table 31 11 The G500H will display a number of alerts the GDU 620 These are listed in the Table 31 12 Table 31 11 GDU 620 Troubleshooting Guide Unit does not power up blank screen Improper wiring circuit breaker open Ensure power is properly wired to the GDU 620 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 pages are not displayed An Installer Unlock Card is not inserted into the GDU 620 Insert the Installer Unlock Card P N 010 00769 60 into the bottom slot of the GDU 620 and cycle power The GDC OAT probe type shows up as UNKNOWN The RS 232 connection to the GDC 74H is not working Ensure that the GDC 74H RS 232 connection to the GDU is properly wired and ensure that the GDC 74H circuit breaker is closed When loading software the LRU software is not bein
7. 0 0 1 1 16 M81714 67 18 7 BLOCK RAIL 2025 a 1 14 53320 20 7313515 m m 1 11 011 00871 00 44 CONNECTOR KIT 1 110 01 016 8 0 44 MAGNETOMETER Po E i 111 00459 00 GRS 77H INSTALLATION RACK 1 1 7 JOr 0869 01 ers 77H CONNECTOR KT 1 9 01 01656 00 GDU 620 CONNECTOR KIT 1 114 01 0078 0 16 59 OATPROE En 1 3 SOFTWARE P N 006 1071 21 GDU 620 SOFTWARE VERSION 4 01 01 024 50 GU 620 ppp J aa 1 1 SOFTWARE P N 006 B0223 H1 GRS_77H_AHRS SOFTWARE VERSION 3 51 1 1 SOFTWARE P N 006 80223 HO GRS 77H AHRS SOFTWARE VERSION 3 50 011 00868 20 GRS_77H_AHRS GARMIN 01 PART NUMBER DESCRIPTION MANUFACTURER 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 70 of 82 NOTES 1 UNSHIELDED WIRE IS 22759 16 UNSHIELDED HIGH TEMP WIRE IS 22759 8 TWISTED SHIELDED WIRES ARE M27500 xx TGxT14 INDICATES AWG X NUMBER OF CONDUCTORS SUFFIX OF EACH WIRE NUMBER INDICATES WIRE AWG 2 WIRE LEGEND NEW EXISTING 3 ALL WRES ARE 22 AWG EXCEPT WHERE NOTED OTHERWSE ALL SPLICES ARE TO MIL S 81824 1 X 4 GROUND DESIGNATIONS SHIELD BLOCK GROUND AIRFRAME GROUND THE LENGTH OF SHIELD GROUNDS MUST NOT EX
8. 82 2 Connect the rear connectors ensuring that each slidelock is secured on both sides 3 Set the GDU 620 into place 4 Install the six mounting screws into the bezel of the GDU 620 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 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 5 and the Configuration Module Update 5 5 12 GDU 620 Configuration Module is Replaced If the GDU 620 Configuration Module is replac
9. GROUNDS TO THE CONNECTOR BACKSHELL THE SHIELD LEADS MUST BE LESS THAN 3 INCHES DO NOT DAISY CHAIN SEE DETAIL D FOR ALTERNATIVE CONNECTION OPTIONS A FOR FURTHER WIRING INFORMATION REFER TO TYPICAL STANDBY INTRUMENT LIGHTING PAGE 5 OF 8 A FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC130 WIRING DIAGRAM MANUAL REMOVE EXISTING 2 5 AMP CIRCUIT BREAKER LABELED HSI AND REPLACE WITH ITEM 29 OF THE PARTS LIST RELABLE CIRCUIT BREAKER EFIS AS SHOWN REFERENCE EC 130 WIRING DIAGRAM MANUAL CHAPTER 34 A USE THE EXISTING 2 5 AMP FUSE LABELED HSI FOR EFIS FAN RELABEL HSI FUSE HOLDER AS SHOWN REFERENCE 130 WRING DIAGRAM MANUAL CHAPTER 34 RADAR ALTIMETER INTERFACE REQUIRES 500 INSTALLATION WITH 02 SOFTWARE P6203 PIN 45 MUST BE CONFIGURED FOR RADAR ALTIMETER PUSH TO TEST FUNCTIONALITY SEE GDU 620 INSTALLATION MANUAL FOR CONFIGURATION PROCEDURES A DE PIN WIRE 1LMSSF AT THE 150L P1 AND 140L CONSOLE CAP AND STOW WRE AS SHOWN FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC 130 WDM RIGHT HAND LIGHT 53 45 01 AND LEFT HAND LIGHT 35 43 02 ORDER ITEM 25 OF BOM ONLY FOR AIRCFRAFT WITH PRE MOD 07 3587 INSTALLATION OF THE LIMIT ANNUNCIATOR WILL REQUIRE ORDERING A QTY OF 1 PART NO 18 200 QUICK CONNECT PLUG AND AS REQUIRED MIL C 39029 22 192 CONTACT SOCKETS FOR FUTHER WIRING INFORMATION REFERENCE EUROCOPTER 150 WDM HYDRAULIC DOUBLE 29 11 REMOVE WIRE 1DH7E AT 150L P1 PIN 13 AND ROUTE
10. IS NOT INCLUDED IN THE INSTALLATION ALL WIRES ARE NOT REQUIRED FOR EVERY TRAFFIC SYSTEM ONLY CONNECT THOSE WIRES REQUIRED BY THE INSTALLATION REFER TO THE G500H INSTALLATION MANUAL APPENDIX E SERIAL ALTITUDE OUT IS OPTIONAL DO NOT CONNECT IF NOT REQUIRED FOR THE INSTALLATION 5 232 DATA IS SHADIN ALTITUDE 9600 BAUD POST MOD 07 3245 FOR 31 32 ALPHA PANEL AND 07 3540 FOR 16 ALPHA PANEL INTRODUCE BREAKER PANEL IN REPLACEMENT OF FUSES PANEL REFER TO GARMIN DRAWING 190 01527 11 CIRCUIT BREAKER INSTALLATION EUROCOPTER EC130 FOR LOCATION OF EFIS MASTER CIRCUIT BREAKER LABEL CIRCUIT BREAKER AS SHOWN THE GDL 69 69A IS AN OPTIONAL CONNECTION DO NOT CONNECT IF INCLUDED IN THE INSTALLATION THE GSR 56 IS AN OPTIONAL CONNECTION DO NOT CONNECT IF NOT INCLUDED IN THE INSTALLATION USE ONLY AIRCRAFT GRADE CATEGORY 5 ETHERNET CABLE SUCH AS P N 392404 FROM ELECTRONIC CABLE SPECIALIST OR P N 10424 FROM PIC WIRE AND CABLE THE GDU 620 MUST BE CONFIGURED FOR THE CORRECT LIGHTING BUS VOLTAGE 28 VDC AND THE PHOTOCELL MUST BE CONFIGURED FOR PROPER AUTO DIM WHEN THE LIGHTING BUS IS TURNED OFF FOR CONFIGURATION AND PROGRAMMING INSTRUCTIONS REFER TO THE GARMIN G500H ROTORCRAFT STC INSTALLATION MANUAL 190 01150 06 REVISION 2 OR LATER FAA APPROVED REVISION FOR THE EC 130 B4 STC FOR PROGRAMMING DISPLAYED AIRSPEED MARKINGS ON GDU 620 PFD MFD REFER TO GARMIN DRAWING 190 01527 14 CONFIGURATION G500H INSTAL
11. Post Lightning Strike Inspection that must be performed the event of a suspected or actual lightning strike to the aircraft The Post Lightning Strike Inspection requirements are specified in Table 5 05 5 Definitions and Acronyms The following is short descriptions of words and terms used in the procedures for the required scheduled inspections Examine Look carefully to find the condition of the component Find how that condition is related to a specific standard e Condition The state of an item or component compared to a known standard e Standard A specified rule or measure that is used to find the condition of a component Damage Physical deterioration of a component e Inspection A procedure that includes checking inspecting and examining a system or component e Scheduled Inspection An inspection procedure that must occur at a specified calendar interval or at specified operational time intervals Scheduled Inspections are required to help ensure the rotorcraft stays airworthy e Maintenance The servicing and or repair of a rotorcraft a system or a component that keeps it serviceable e Security Term used for inspection of hardware and components to make sure they are properly attached and tightened Acronyms FOV Field of View ICA Instructions for Continued Airworthiness PFD Primary Flight Display MFD Multifunction Display VOM Volt Ohm Meter GDC Garmin Data Computer GRS Gar
12. Shear Tension Fractional decimal Recommended Maximum Recommended Maximum in Ib m in Ib N m in Ib N m in Ib N m 8 32 7 9 12 12 15 20 0 1640 32 0 79 1 02 1 36 1 36 1 69 2 26 10 24 12 15 21 20 25 35 0 1900 24 1 36 1 69 2 37 2 25 2 82 3 95 74 20 25 30 45 40 50 75 0 2500 20 2 82 3 38 5 08 4 51 5 64 8 47 5 16 18 48 55 100 80 90 160 0 3125 18 5 42 6 21 11 29 9 03 10 16 18 07 3 8 16 95 100 170 160 185 275 0 3750 16 10 73 11 29 19 20 18 07 20 89 31 06 7 16 14 140 155 280 235 255 475 0 4375 14 15 81 17 50 31 62 26 54 28 8 53 65 15 13 240 290 520 400 480 880 0 5000 13 27 11 32 75 58 73 45 18 54 22 99 40 9 16 12 300 420 650 500 700 1 100 0 5625 12 33 88 47 44 73 42 56 48 79 07 124 25 5 8 11 420 540 900 700 900 1 500 0 6250 11 47 44 60 99 101 66 79 07 101 66 169 44 54 10 700 950 1 500 1 150 1 600 2 500 0 7500 10 79 07 107 31 169 44 129 90 180 73 282 40 7 8 9 1 300 1 800 2 700 2 200 3 000 4 600 0 8750 9 146 84 203 32 474 43 248 51 338 88 519 61 1 8 2 200 3 000 4 500 3 700 5 000 7 600 1 0000 8 248 51 338 88 508 32 417 95 564 80 858 49 1 1 8 8 3 300 4 000 7 200 5 500 6 500 12 000 1 1250 8 372 76 451 84 813 31 621 28 734 24 1355 5 1 1 4 8 4 000 5 000 10 000 6 500 8 000 16 000 1 2500 8 451 84 564 80 1129 6 734 24 903 68 1807 4 N m Table 20 03 Recommended Torque Values for Phillips Head Fasteners Thread
13. TO THE LIMIT ANNUNCIATOR IN THE INSTRUMENT PANEL IF WIRE 1DH7E DOES NOT REACH THE LIMIT ANNUNCIATOR BOM ITEM 25 SPLICE WRE 1DH7E TO NEW WIRE AS SHOWN N POST MOD 07 3850 WRE 1LK694E AT 150L P1 PIN AND SPLICE TO NEW WIRE AT THE INSTRUMENT PANEL AS AHOWN PRE MOD 07 3850 SPLICE NEW WIRE TO EXISTING 3LK294E 1491 P2 PIN 12 AS SHOWN CONNECT NEW WIRE TO 149L P2 PIN 14 AS SHOWN FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC130 WIRING DIAGRAM MANUAL 525 INDICATOR WITH NAV2 SWITCHING POST MOD 07 3850 DE PIN WIRE 1RS2356E MUNI dr AS SHOWN CONSOLE BREAKER PANEL X4 PIN 5 CAP AND STOW WIRE 1RS2356E A FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC130 WIRING DIAGRAM MANUAL 525 INDICATOR WTH NAVI NAV2 SWITCHING POST MOD 07 3245 DE PIN WIRE 1RS867E THE 31 ALPHA 32 CONSOLE BREAKER PANEL X4 5 CAP AND STOW WIRE 1RS867E NEAR X4 AS SHOWN FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC130 WIRING DIAGRAM MANUAL 525 INDICATOR WITH NAVI NAV2 SWITCHING PRE MOD 07 3245 DE PIN 1RSB67E THE 31 ALPHA 32 CONSOLE BREAKER PANEL 31ALP B PIN 14 AND STOW WIRE 1RSB867E NEAR 31ALP B AS SHOWN VAN COOLING FAN AND ASSOCIATED COMPONENTS ARE OPTIONAL IF THE COOLING FAN OPTION IS NOT UTILIZED REDUCE PARTS ORDERED FOR THE INSTALLATION ACCORDINGLY WIRE 1LK301E AT THE 1401 CONSOLE CAP AND STOW WIRE AS SHOWN FOR FURTHER WIRIN
14. such as a hangar wall or if the magnetometer is close to a large ground power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 31 00 00 Troubleshooting b GDC74H 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 31 00 00 Troubleshooting 4 Drain pitot static system reference table 5 01 90 Day Inspection 5 Perform a leak check of the pitot static system and observe the airspeed altitude and vertical speed for proper operation c GRS 77H 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 close to a large ground power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Section 31 00 00 Troubleshooting d GDU 620 1 Power up the G500H system with the GDU 620 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 31 00 00 Troubleshooting 12 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin
15. the G50OH 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 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 43 of 82 a GMU 44 Magnetometer i Removal 1 Access the GMU 44 magnetometer reference Section 6 00 00 Dimensions and Access 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 ii Installation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Connectthe wiring harness to the GMU 44 3 Lowerthe 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 r
16. the aircraft Figure 6 04 Figure 6 04 Access Methods i Removal 1 Uncscrew the Center lower belly access panel 2 Disconnect the retaining straps that prevent the panel from falling to the floor 3 If aftermarket items are attached to the Center lower belly panel it may be necessary to remove or disconnect them in order to remove the lower belly panel Consult the manufacturers Installation and Removal instructions for proper removal of items ii Installation 1 Re install aftermarket items Consult the manufacturers Installation and Removal instructions for proper installation of items 2 Connect the retaining strap that was disconnected to gain access to the air data computer 3 Close the Center lower belly access panel and attach screws Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 22 of 82 Terminal Block Installation Terminal Block is located underneath the cabin floor between station 1703 and 1766 on the left side of the aircraft Figure 6 05 Terminal Block Figure 6 05 Access Methods i Removal 1 Un latch the Center lower belly access panel Disconnect the retaining straps that prevent the panel from falling to the floor If
17. 00 Airworthiness Limitations There are no additional Airworthiness Limitations as defined in 14 CFR Part 27 Appendix A A27 4 that result from this modification The Airworthiness Limitations section is FAA approved and specifies inspections and other maintenance required under 14 CFR 43 16 and 91 403 of the Federal Aviation Regulations unless an alternative program has been FAA approved 04 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 5 of 82 CHAPTER 5 Section 05 00 00 Continued Airworthiness Inspections 1 General This chapter contains time limit intervals for the Component Overhaul Schedule and Scheduled Inspections for the G500H Installation This chapter is to be added to the approved scheduled inspection for the rotorcraft 2 Component Overhaul Schedule 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 LRU indicates an internal failure the unit may be removed and replaced 3 Scheduled Inspections Overview The G500H Installation requires a 90 Day Inspection that must be performed 90 days after installation and then afterwards within 90 days of the last GSOOH Installation 90 day inspection The 90 Day Inspection requirements are specified in Table 5 01 The G500H Installation requires an Annual Inspection that must be performed within 1
18. 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 20 of 82 GRS 77H AHRS GRS 77H is located underneath the cabin floor between station 2249 and 2737 on the left side of the aircraft Figure 6 03 GDC 77H Figure 6 03 Access Methods i Removal 1 Un screw the Center lower belly access panel 2 Disconnect the retaining straps that prevent the panel from falling to the floor 3 If aftermarket items are attached to the Center lower belly panel it may be necessary to remove or disconnect them in order to remove the lower belly panel Consult the manufacturers Installation and Removal instructions for proper removal of items ii Installation 1 Re install aftermarket items if removed to gain access to the AHRS Consult the manufacturers Installation and Removal instructions for proper installation of items 2 Connectthe retaining strap that was disconnected to gain access to the AHRS 3 Close the Center lower belly access panel and attach screws Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 21 of 82 Shelf Installation The shelf installation is located underneath the cabin floor between station 2249 and 2737 on the left side of
19. 1 115 01812 00 DOUBLER GARMIN 2 1 011 00978 00 GTP 59 OAT PROBE GARMIN 3 8 MS20470AD4 3 RIVET 4 A R MIL S 8802 SEALING COMPOUND EXISTING OAT PROBE INSTALLATION TYP 2 PLACES REF EXISTING ROTORCRAFT STRUCTURE 0 032 IN THICK AUG1 T4 8X 0 098 EXISTING BELLY PANEL TO MATCH RIVET HOLES IN ITEM 2 DRILL 00 332 THROUGH EXISTING BELLY PANEL TO MATCH OAT PROBE HOLE IN ITEM 2 REF 212 00026 00 WASHER PART OF 011 00978 00 GTP S9OAT PROBE SUB ASSEMBLY EE REF 210 00055 00 NUT PART OF 011 00978 00 GTP 59 OAT PROBE SUB ASSEMBLY Figure 31 06 GTP 59 OAT PROBE INSTALLATON EXPLODED VIEW Reference Table 31 06 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 55 of 82 Table 31 07 Parts List for Figures 31 07 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 011 03096 01 INSTRUMENT PANEL ASSEMBLY GARMIN 2 011 01264 50 GDU 620 PFD MFD GARMIN 3 233 40024 00 DIMMING CONTROL PANEL GARMIN 4 REF EXISTING GNS 430 GARMIN 5 REF EXISTING NR TACHOMETER EUROCOPTER 6 REF 350A67 0159 20 2 IN EYEBROW LIGHT EUROCOPTER 7t REF 350A62118800 EMERGENCY BATTERY SWITCH EUROCOPTER 8 REF EXISTING 3 IN AIRSPEED EUROCOPTER REF EXISTING 3 IN ALTIMETER EUROCOPTER 10 REF B19030MD05 V E M D THALES 11 REF 704447723072 ANNUNCIATOR PANEL COMTRONIC
20. 12 4 71450B23 LED POST LIGHT WHELEN 13 1 LED 40 17 HE EOFVP ANNUNCIATOR FAN VIVISUN 14 1 LED 40 17 HE EOG3T ANNUNCIATOR LDG TAXI VIVISUN 15 1 LED 40 17 HE EOFYH ANNUNCIATOR LIMIT VIVISUN 16 2 521042106 NUT 17 3 MS33737 16C INSTRUMENT NUT 18 8 MS35214 29 SCREW 19 7 MS35214 31 SCREW 20 6 MS35214 44 SCREW 21 6 NAS1149DN832H WASHER Reference Table 31 08 and Figure 31 08 Alt P N for the Emergency Switch Overlay that comes with item 24 is 4332 28 15 NC Vendor Aero Dynamix Inc Item 7 is only required if the Emergency Switch is installed in the instrument panel 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter 130 190 01527 15 Rev 1 Page 56 of 82 eS es es Instructions for Continued Airworthiness CS eg PO H in iH n Figure 31 07 INSTRUMENT PANEL INSTALLATION Reference Table 31 07 31 00 00 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 57 of 82 Table 31 08 Parts List for Figure 31 08 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 115 01818 01 INSTRUMENT PANEL GARMIN 2 1 161 03095 01 LABEL GARMIN 3 4 521061 08 NUTPLATE 4 6 MS21069 08 NUTPLATE 5 6 521071 06 NUTPLATE 6 2 521075 08 NUTPLATE 7 36 MS20426AD3 4 RIVET 31 00 00 Instructions for Continued Airworthiness for the
21. 31 Section 31 00 00 Instruments 1 Description and Operation 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 GDU 620 provides controls for the 500 system and a PFD and in the pilot s primary field of view The remote mounted LRUs include one GRS 77H AHRS one GMU 44 Magnetometer one GDC 74H ADC and one GTP 59 OAT probe The G500H system depends on electrical power to function The Garmin Display Unit GDU Attitude and Heading Reference System AHRS and Air Data Computer ADC are connected to the aircraft main bus The major components of the G500H are circuit breaker protected with push pull type circuit breakers available to the pilot These breakers are located in the pedestal circuit breaker panel 30 a and are labeled as shown in Table 31 01 Table 31 01 Circuit Breakers Label Unit Controlled PFD Garmin Display Unit PFD MFD GDU 620 AHRS Attitude and Heading Reference System GRS 77H ADC Air Data Computer GDC 74H 2 Removal and Installation If 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
22. 5 Rev 1 Page 48 of 82 Figure 31 01 GMU 44 MAGNETOMETER INSTALLATION EXPLODED VIEW Reference Table 31 01 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 49 of 82 Table 31 02 Part Lists for Figures 31 02 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 115 01815 00 FWD GUSSET SUPPORT GARMIN BRACKET 2 1 115 01816 00 AFT GUSSET SUPPORT GARMIN BRACKET 3 1 115 01817 00 SHELF GARMIN 4 8 AN3 3A BOLT 5 8 AN3 4A BOLT 6 16 MS20426AD3 3 RIVET 7 8 MS21042L3 NUT 8 16 MS21075L3N NUT 9 24 NAS1149D0332K WASHER 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190 01527 15 Rev 1 Page 50 of 82 Figure 31 02 SHELF INSTALLATION EXPLODED VIEW Reference Table 31 02 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 51 of 82 Table 31 03 Parts List for Figure 31 03 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 011 00882 11 GDC 74H ADC GARMIN 2 4 AN525 10R7 SCREW 3 4 MS21075L3N NUTPLATE 4 8 MS20426AD3 3 RIVET REF EXISTING ROTORCRAFT STRUCTURE 8X TRUE 0 201 MATCH DRILL TO ITEM 1 8X 20 0987 THRU gt 20 179 100 Figure 31 03 GDC 74H INSTALLATION EXP
23. 780 BL 756 7 190 01527 04 GDC 74H 1 92 Ibs STA 2615 WL 2744 BL 731 9 190 01527 05 GRS 77H AHRS 3 46 Ibs STA 2565 WL 2747 BL 817 9 190 01527 01 Instrument Panel 47 80 Ibs STA 872 WL 2066 BL 0 0 190 01527 06 Terminal Block 0 47 Ibs STA 1766 WL 2600 BL 592 3 190 01527 12 Cooling Fan 0 70 Ibs STA 427 WL 2491 BL 0 0 8 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190 01527 15 Rev 1 Page 27 of 82 CHAPTER 11 Section 11 00 00 Placards and Markings 1 Placards and Decals Shelf Installation The Shelf Installation requires one 1 placard that is mounted to the upper surface of the Shelf in plain view The placard will read MAX LOAD 30185 Instrument Panel Installation When NAV 2 is not displayed on the GDU 620 the Instrument Panel Installation requires one 1 placard that is mounted to the top of the pedestal just below the Instrument Panel in plain view NAV 2 NOT DISPLAYED EFIS Master Circuit Breaker Installation The EFIS Master Circuit Breaker Installation requires one 1 placard that is mounted to the left side of the pedestal with a 50 in diameter hole cut out in the middle so the circuit breaker can stick through the placard EFIS 11 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 28 of 82 E F LS Circuit Breaker Installation Circuit Breaker Installation requir
24. C130 Page 38 of 82 Section 20 40 00 Corrosion Control Maintenance Practices 1 Corrosion Control The G500H mounting components are fabricated primarily of aluminum All components should be inspected regularly for any signs of corrosion The following procedures should be used for removing corrosion and treating affected areas 2 Corrosion Removal Remove corrosion by either chemical or mechanical means a Paint Removal Chemical Caution Do not use chemical paint stripper on composite materials Chemical paint strippers can cause composite components to debond and or loose adhesion of the epoxy matrix 1 Mask all non metallic surfaces in area to be stripped as well as areas where solution may get entrapped Warning Paint stripper can cause burns and irritation when it contacts skin proper gloves should be worn Vapors are harmful and caustic to eyes Goggles must be worn for eye protection Paint stripper is poisonous Vapors are harmful to life or health work should be performed with proper ventilation and or respirators should be worn while working with paint stripper 2 Using a fiber brush apply sufficient paint stripper Turco 5873 to cover area of removal Note If paint stripper evaporates quickly or works slowly cover area with plastic sheet 3 Allow paint remover to remain on surface for a time sufficient to cause wrinkling and lifting of paint about 10 30 minutes 4 Using non metallic scraper or a
25. CEED 3 INCHES 5 ROUTE AND TIE WIRES ALONG EXISTING ROTORCRAFT WIRE HARNESS FOLLOWING GUIDELINES SPECIFIED IN SECTION 20 02001 411 CABLE BINDING METHODS OF EUROCOPTER STANDARD PRACTICES MANUAL o RG 179 IS MIL C 17 094G A REFER TO GARMIN DRAWING 190 01527 11 CIRCUIT BREAKER INSTALLATION EUROCOPTER 130 SEE DETAIL A FOR TERMINAL BLOCK CONFIGURATION OF ITEM 15 SEE DETAIL C FOR TERMINAL BLOCK CONFIGURATION OF ITEM 20 SEE DETAIL E FOR TERMINAL BLOCK CONFIGURATION OF ITEM 28 GPS 2 IS AN OPTIONAL CONNECTION DO NOT CONNECT IF ONLY ONE GPS IS USED IN THE INSTALLATION THE NAV 1 AND NAV 2 CONNECTIONS MAY BOTH BE ARINC 429 OR ONE ARINC 429 AND ONE RS232 CONNECTION CONNECTIONS MUST ONLY MADE AUTHORIZED UNITS REFER TO THE 6500 INSTALLATION MANUAL FOR ACCEPTABLE NAV UNITS AND CONNECTIONS THE 2 CONNECTION IS OPTIONAL DO NOT CONNECT IF ONLY ONE NAV IS USED IN THE INSTALLATION THE 5 252 5 INPUTS MAY CONFIGURED AS NAV 1 OR 2 BOTH THE 500 INSTALLATION MANUAL FOR CONFIGURATION ON F THE TERRIAN FEATURE IN THE GDU 620 IS ENABLED THE AUDIO INPUT OF THE AUDIO PANEL MUST UNSWTCHED AND UNMUTED IF THE AUDIO PANEL DOES NOT HAVE AN AVAILABLE UNSWITCHED INPUT AND THE GDU 620 AUDIO MUST BE COMBINED WITH OTHER AUDIO REFER TO THE GSOOH INSTALLATION MANUAL APPENDIX E TRAFFIC SYSTEM IS OPTIONAL DO NOT CONNECT IF A TRAFFIC SYSTEM
26. CTV soft key to copy the configuration settings from the GDU 620 into the GDL 69 Update the GDL 69 configuration using the GDU 620 Cycle power to the GDU This error automatically clears on the second power up with a different configuration module GDU 1 2 COOLING Specific GDU has poor cooling and power usage is being reduced Ensure fans on indicated GDU are functioning Ensure fans on indicated GDU are not obstructed GDU 1 2 DB ERR Error in specific database where GDU 1 2 DB denotes specific database Verify the correct card is installed reload the DB on the card GDU 1 2 VOLTAGE GDU supply voltage is below 12 VDC Increase the voltage above 12VDC GEO LIMITS Location is too far north south for GRS 77H magnetic compass GPS 1 2 FAIL No GPS1 or GPS2 data is available Ensure GPS 1 2 is turned on Verify RS 232 wiring from the GPS to the GDU 620 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190 01527 15 Rev 1 Page 65 of 82 Alert Text Solution GPS 1 2 PPS Failure This alert will be set if the PPS 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 Ensure GPS 1 2 is turned on Verify 1PPS wiring from the GPS to the GDU 620 GPS2 FPL USED The GPS1 has failed and GPS2 is config
27. G INFORMATION REFERENCE EUROCOPTER EC 130 WDM LIGHTING INST PANEL AND CONSOLE POST POST MOD 07 3587 CHAPTER 33 FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC 130 WDM LANDING LIGHT 33 43 48 REFERENCE GARMIN DRAWING 190 01527 14 CONFIGURATION G500H INSTALLATION EUROCOPTER EC130 FOR INFORMATION ON DIFFERENT SOFTWARE CONFIGURATIONS THE 02 SOFTWARE 15 OPTIONAL BUT MUST BE INSTALLED FOR THE FOLLOWING OPTIONAL SYSTEM INTERFACES TO FUNCTION ARINC 429 RADAR ALTIMETER 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 72 of 82 DETAIL DETAIL DETAIL EFIS POWER OPTION POST MOD 07 3245 16 ALPHA PANEL 32 ALPHA CIRCUIT BREAKER N jaj d A AGA MASTER Eaj et 1 EFSOBA12 4208 75 11 FANPi e ejl a 2 rsss KAI AER uw 1 ue OR PRE MOD 07 3245 18 ALPHA PANEL 31 32 ALPHA FUSE PANEL Za EFIS BUS 22 i N 185867 J ens FAN bos 2 d ss 2 5 k Lx 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 73 of 82 DETAIL D INSTRUMENT DIMMING OPTIONS K
28. G500H Installation in Eurocopter EC130 Page 31 of 82 Section 12 20 00 Calibration Requirements Condition GRS 77H AHRS was removed and or replaced The mounting tray was NOT removed and the mounting tray bolts were NOT loosened Calibrations Required GRS 77H Pitch Roll Offset See Section 5 of the G500H STC Installation Manual GRS GMU Magnetic Calibration See Section 5 of the G500H STC Installation Manual None Required Engine Run up Vibration Test See Section 5 of the G500H STC Installation Manual 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 12 20 00 190 01527 15 Rev 1 Page 32 of 82 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter 130 CHAPTER 20 Section 20 00 00 Standard Practices This chapter contains maintenance information and procedures that are common standard practices used on the G500H installation Information contained in this chapter is standard torque charts and application procedures corrosion prevention painting mechanical fastener sealing and dye penetrant inspection techniques 20 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 33 of 82 Section 20 10 00 Torques Maintenance Practices 1 Torque Wrenches a Torqu
29. Garmin G500H Installation in Eurocopter EC130 190 01527 15 Rev 1 Page 58 of 82 Figure 31 08 INSTRUMENT PANEL ASSEMBLY Reference Table 31 08 31 00 00 190 01527 15 Rev 1 Instructions for Continued Airworthiness Page 59 of 82 for the Garmin G500H Installation in Eurocopter EC130 Table 31 09 Parts List for Figure 31 09 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 013 00103 00 COOLING FAN GARMIN 2 6 MS20426AD3 3 RIVET 3 3 MS21059L06 NUTPLATE 4 3 MS35206 236 SCREW 5 3 NAS43DD1 20 SPACER 6 3 MB 3A CABLE TIE MOUNT TYTON 7 7 TI8L O TYWRAP TYTON 8 A R 5700 1 COOLING HOSE EDMO Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter 130 Figure 31 09 COOLING FAN INSTALLATION OPTIONAL Reference Table 31 09 31 00 00 190 01527 15 Rev 1 Page 60 of 82 Table 31 10 List of Consumable Materials DESCRIPTION P N VENDOR SPECIFICATION THREAD LOCK 242 LOCTITE ADHESIVE 1300L 3M Cleaning cloth Low Lint Commercial 52 MIL PRF 680 TYP II Mineral Spirits Cleaning Solvent OR ASTM D235 Alodine Alodine 1200 Alodine Iridite 14 2 Paint Stripper Turco 5873 Polyamide Paint Primer Dye Penetrant Kit Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 cetone ASTM D329 Isopropyl Alcohol
30. Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Dwg Number 190 01527 15 Rev 1 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 Rev Date Description of Change 04 22 2014 Initial release Note Document was RSG P N 16E08310001 Rev E Table of Contents ef ugly EE 4 Section 01 00 00 Met 4 CHAPTER EET 5 Section 04 00 00 Airworthiness Limitations 5 CHAPTER d m 6 Section 05 00 00 Continued Airworthiness Inspections 222 6 Section 05 20 10 Continued Airworthiness Scheduled Inspections 9 Section 05 20 20 Continued Airworthiness Special Inspections 2 17 CHAPTER 6 EET 19 Section 06 00 00 Dimensions and Access 19 CHAPTER Mp 27 Section 8 00 00 Weight and Balance Information 27 CHAPTER WA Em 28 Section 11 00 00 Placards and Markings 28 CHAPTER 12
31. LATION EUROCOPTER EC13 AA SEE DETAIL B FOR ALTERNATIVE CONNECTIONS A COMPOSITE VIDEO IS AN OPTIONAL CONNECTION DO NOT CONNECT IF NOT INCLUDED INSTALLATION VIDEO COAX MUST BE RUN SEPARATE AND NOT INCLUDED IN AIRCRAFT WIRE BUNDLES CONNECTIONS MUST ONLY BE MADE TO APPROVED GPS WAAS UNITS REFER TO THE G500H INSTALLATION MANUAL FOR ACCEPTABLE GPS UNITS AND CONNECTIONS FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC 130 WDM LIGHTING AND INST PANEL AND CONSOLE 35 10 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 71 of 82 A FOR AR AROUND STATUS REFER TO DETAIL F FOR THE APPROPRIATE MOD OPTION THE GDU 620 6201 PIN 7 BE CONNECTED TO MAIN GEAR BOX PRESSURE SO THAT WHEN ON GROUND A GROUND SIGNAL IS PRESENT AT PIN 7 SPLICE WIRE GDU36A22 NEAR THE 4 ALPHA WARNING PANEL P1 AS SHOWN CONFIGURATION MODULES ARE MOUNTED THE BACKSHELL OF THE P6202 P771 AND P741 CONNECTORS CONFIGURATION MODULE HARNESS USES 28 AWG WIRES CONTACTS SUPPLIED WITH CONFIGURATION MODULE MUST BE USED FOR CONNECTING CONFIGURATION MODULE HARNESS TO P6202 771 OR 741 FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER EC130 WIRING DIAGRAM MANUAL CHAPTER 24 A DE PIN WIRE 1LK745E 140L TERMINAL STRIP TERMINAL 5B AND STOW WIRE 140L TERMINAL STRIP LOCATE SPLICE INSIDE OF THE CONNECTOR BACKSHELL AT GDU 620 GRS 77H_AND GDC 74H CONNECT SHIELD
32. LER UNLOCK CARD 1 1 48 010 00844 0 77 500 DOWNLOAD SW SD CARD GARMIN 4 amp EED 0 ee as DELETED 271 1 1 4 4 Dusz2 12120 CONNECTOR RECEPTACLE EUROCOPTER TERMINAL CRIMP MALE j ESE KEE 03 06 2004 06 2024 uc 00 998 39 01 BRIDGE LIGHTING WHITE 1 1138 35046705207 SUPPORT S EUROCOPTER 5 5 37 7084402 oR 71450623 LED POST LIGHT 2 2 3 5279817 7 CLAMP BACKSHELL a PART NUMBER DESCRIPTION MANUFACTURER a 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 69 of 82 1f 1 15120249 D SUBPLUG 1 1 31 233 40024 00 DMMNG conor pane GARMIN 1 1 30 350462180 7 EMERGENCY SWITCH OVERLAY EUROCOPTER BREAKER 1 AMP 1 1 28 mB1714 60 20 02 TERMNAL Brok L C CAR AR 27 00 2 02 1 CONTACT socket 000 2 2 26 18 200 connecT Prue AX t 1 25 1 1 24 LED 40 17 HE EOGST ANNUNCIATOR LDG TAX L 1 1 23 1 0 40 1 ANNUNCIATOR EFIS FAN FAIL VIVISUNT 1 1 22 015 010 0 CT COOLING FAN 1 1 GARMN 21 in to A O ferna Bok AR AR 18 6 179 17 90 75 OHM COAX J _ 0
33. LODED VIEW Reference Table 31 03 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 52 of 82 Table 31 04 Parts List for Figure 31 04 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 011 00868 20 GRS 77H AHRS GARMIN 2 1 115 00459 00 GRS 77 MOUNT RACK GARMIN 3 5 AN525 10R7 SCREW 4 5 MS21075L3N NUTPLATE 5 10 MS20426AD3 3 RIVET REF EXISTING ROTORCRAFT STRUCTURE Figure 31 04 GRS 77H INSTALLATION EXPLODED VIEW Reference Table 31 04 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 53 of 82 Table 31 05 Part List for Figure 31 05 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 M81714 67 18 RAIL 2 2 M81714 60 22 05 TERMINAL BLOCK 3 1 AN525 10R7 SCREW 4 1 MS21042L3 NUT 5 2 NAS1149F0332P WASHER MATCH DRILL 0 233 THRU EXISTING WEB TO ITEM 1 TYP 2 PLCS L REF EXISTING WEB 0 050 IN THICK 6061 T6 ALUMINUM Figure 31 05 TERMINAL BLOCK INSTALLATION EXPLODED VIEW Reference Table 31 05 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 54 of 82 Table 31 06 Parts List for Figure 31 06 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1
34. NGON INCO GND 31000 2 gio e aze VL N 82 3NDYN LNO W2128012N0VN ino 252 54 8i Sa Su vi M S9Y SU WOT TINON INOJ 317009 INCO QN9 FINGON Wd 9uHNOO 7 OND M30d LIVEOUIV 98 10 00 Page 78 of 82 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Instructions for Continued Airworthiness A GDU 620R PFD MFD GRS 77H AHRS a Y 5 Ye V 48Y 49Y CEY YN pm ARINC 429 IN 1 ARINC 429 IN 1 B ARINC 429 DUT 1 A ARINC 429 DUT 1 B RS 232 IN 1 RS 232 OUT 1 RS 232 GND 1 GPS 1 RS 232 OUT GPS 1 RS 232 IN SIGNAL GND RS 232 OUT 4 RS 232 GND 4 GPS 2 RS 232 IN SIGNAL GND A GDC 74H ADC ARINC 429 DUT 1A ARINC 429 ARINC 429 IN 2 A ARINC 429 IN 2 B RS 252 2 RS 232 OUT 2 RS 232 GND 2 RS 232 DUT 1 RS e3e IN 1 RS 232 GND 1 RS 232 IN 3 RS 252 GND 3 TIME MARK IN 1 A TIME MARK IN 1 B ARINC 429 IN ARINC 429 IN 3 B ARINC 429 OUT 1 A ARINC 429 OUT 1 B RS 232 IN 4 TIME MARK IN 2 A TIME MARK IN 2 B ARINC 429 INS A ARINC 429 IN 5 B 98 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 79 of 82
35. Size Recommended in lb m Fractional decimal 20 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 37 of 82 Section 20 30 00 Painting Maintenance Practices The following procedures should be used to touch up paint flaking scratches nicks and gouges Warning Cleaning solvents and epoxy primer are flammable Cleaning solvents epoxy primer and alodine can cause burns and irritation when skin is contacted Vapors are harmful and caustic to eyes Goggles must be worn for eye protection Cleaning solvents and alodine are poisonous Vapors are harmful to life or health work should be performed with proper ventilation and or respirators should be worn while working with Cleaning solvents epoxy primer and alodine 1 Paint Touch Up of Small Areas Use the following procedures to touch up paint of small sanded areas and Nicks Scratches Gouges Etc that do not go through paint and primer to bare metal a Wipe surface clean with trichloroethane MIL T 81533 or equivalent cleaning solvent and wipe dry immediately b Apply coat of epoxy polymide primer MIL P 23377F or equivalent to match original Feather primer coating onto surrounding color coat Allow primer to air dry for 30 minutes c Apply topcoat to match original finish 20 30 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter E
36. Thread Fasteners Thread Size Ser Fractional decimal Recommended Maximum Recommended Maximum is m 0 1640 36 0 79 1 02 1 36 1 36 1 69 2 26 10 32 12 15 25 20 25 40 14 28 30 40 60 50 70 100 0 2500 28 3 38 4 51 6 77 5 64 7 90 11 29 5 16 24 60 85 140 100 140 225 0 3125 24 6 77 9 60 15 81 11 29 15 81 25 41 3 8 24 95 110 240 160 190 390 0 3750 24 10 73 12 42 27 11 18 07 21 46 44 05 7 16 20 270 300 500 450 500 840 0 4375 20 30 49 33 88 56 48 50 83 56 48 94 88 55 20 290 410 660 480 690 1 100 0 5625 18 54 22 67 77 108 44 90 36 112 96 180 73 5 8 18 660 780 1 400 1 100 1 300 2 400 54 16 1 300 1 500 3 000 2 300 2 500 5 000 0 7500 16 146 84 169 44 338 88 259 80 282 40 564 80 7 8 14 1 500 1 800 4 200 2 500 3 000 7 000 0 8750 14 169 44 203 32 474 43 282 40 338 88 790 72 1 12 2 200 3 300 6 000 3 700 5 500 10 000 1 0000 12 248 51 372 76 677 76 417 95 621 28 1129 6 1 1 8 12 3 000 4 200 9 000 5 000 7 000 15 000 1 1250 12 338 88 474 43 1016 6 564 80 790 72 1694 4 1 1 4 12 5 400 6 600 15 000 9 000 11 000 25 000 1 2500 12 609 98 745 53 1694 4 1016 6 1242 6 2824 0 20 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 36 of 82 Table 20 02 Recommended Torque Values for Coarse Thread Fasteners Thread Size
37. accordance with Section 20 10 00 Torques Maintenance Practices 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 13 of 82 Table 5 03 5 Year Inspection Registration No Helicopter Total Hours 5 Year Scheduled Inspection The 5 Year Inspection shall be accomplished at least at an interval of once every 5 years of elapsed calendar time Initial each item after accomplishing the inspection Record all findings and attach a copy of findings to this inspection form After correction of all findings make maintenance record entry 5 Year Pre inspection fees 1 1 Review Airworthiness Directives 5 Year Inspection ee GRS 77H AHRS 1 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 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 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 14 of 82 Table 5 04 10 Year 2000 Flight Hour Inspection Registration No Helicopter Total Hours 10 Year 2000 Flight Hour Schedu
38. aftermarket items are attached to the Center lower belly panel it may be necessary to remove or disconnect them in order to remove the lower belly panel Consult the manufacturers Installation and Removal instructions for proper removal of items ii Installation 1 Re install aftermarket items if removed to gain access to the terminal block Consult the manufacturers Installation and Removal instructions for proper installation of items 2 Connect the retaining strap that was disconnected to gain access to the terminal block 3 Close the Center lower belly access panel and latch it Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 23 of 82 f GTP 59 OAT Probe Installation The GTP 59 OAT Probe is located on the existing belly panel between station 2205 and 2269 Figure 6 06 Figure 6 06 Access Methods i Removal 1 Un latch the Center lower belly access panel 2 Disconnect the retaining straps that prevent the panel from falling to the floor 3 If other aftermarket items are attached to the Center lower belly panel it may be necessary to remove or disconnect them in order to remove the lower belly panel Consult the manufacturers Installation and Removal instructions for
39. al magnetic anomalies even with a good GPS signal 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 63 of 82 Table 31 12 GDU 620 Alert Troubleshooting Guide 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 at least one GPS has acquired a valid position If GDU 620 does not have a valid position verify wiring between GDU and GPS receiver and configuration of GDU 620 and GPS receiver operating in exclusively in no information GPS mode 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 model is with aviation database be updated Appears on ground 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
40. and caustic to eyes Goggles must be worn for eye protection Vapors are harmful to life or health work should be performed with proper ventilation and or respirators should be worn while working with Solvents Solvent cleaners are flammable Use the following steps to perform dye penetrant inspection 1 Using cleaning solvent trichloroethane MIL T 81533 clean area to be inspected Note Parts to be inspected must be dry and heated to at least 70 F 21 1 C but not over 130 F 54 4 C Note Manufacturers instructions on Dye Penetrant Kit take precedence over the following instructions 2 Apply penetrant from dye penetrant kit MIL 25135 by brushing spraying or by dipping Allow to stand for a minimum of 2 minutes 3 Remove excess penetrant with remover available with dye penetrant kit or by cleaning with plain water Allow part to dry 4 Apply a light even layer of developer from dye penetrant kit by brushing spraying or by dipping When dipping avoid excess quantity 5 Penetrant which has penetrated into cracks or other openings in the surface of the part will be drawn out by the developer resulting in a bright red indication 6 If part is serviceable or repairable clean part free of penetrant and developer with trichloroethane MIL T 81533 cleaning solvent 20 90 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 42 of 82 CHAPTER
41. ardless of hours of operation Inspection Table 5 01 the requirements of the 90 day inspection b 1 Year Annual Inspection The 1 year annual inspection is required to be performed every 1 year period of calendar elapsed time regardless of hours of operation Inspection Table 5 02 the requirements of the 1 year annual inspection c 5 Year Inspection The 5 year inspection is required to be performed every 5 year period of calendar elapsed time regardless of hours of operation Inspection Table 5 03 the requirements of the 5 year inspection d 10 Year 2000 Flight Hours The 10 year 2000 Flight Hour inspection is required to be performed at a 10 year period of calendar elapsed time or at 2000 flight hours of operation whichever occurs first Inspection Table 5 04 specifies the requirements of the 10 year 2000 flight hour inspection 3 Tools and Special Tools for Scheduled Inspection Although not necessarily considered special tools the adjustable ball swivel mirror and bright flashlight and or drop light are standard requirements for doing inspections These items should be used freely and frequently to enhance inspection quality and help ensure 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 9 of 82 discrepancies not missed It is important to have adequate lighting for all phases of the inspection The special tools necessary fo
42. brasive pads 3M scotchbrite 63 scrub area to further loosen paint 5 Re apply paint stripper Turco 5873 as necessary in areas where paint remains tightly adherent 6 Wash and scrub surface with demineralized water and alkaline cleaner to neutralize paint stripper 7 Remove masking materials and any residual paint or stripper 20 40 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 39 of 82 8 Rinse with demineralized water b Paint Removal Mechanical Caution Do not sand into or expose composite fibers Do not remove more material than necessary Do not use aluminum oxide abrasive materials on epoxy graphite materials Use abrasive flap wheel abrasive disk abrasive paper or plastic media blast to remove paint c Corrosion Removal Note Aircraft shall be electrically grounded during corrosion removal operations When removing exterior corrosion from electronic boxes the unit case shall be electrically grounded during the complete operation 1 Corrosion shall be removed by the mildest method possible a Hand scrub with dry non metallic brush pad 3M scotchbrite 63 cellulose nylon scouring pad b Use abrasive cloth Aluminum oxide 240 grit Caution Do not use on epoxy graphite materials c Use 320 grit sandpaper d Glass bead blast e Use 240 grit abrasive wheel Note On high strength steel do not use power tools ot
43. ct hardware Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice GDC 74H ADC Installation 1 Access GDC 74H reference Section 6 00 00 Dimensions and Access Inspect GDC 74H and mount for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices 2 Inspect unit for security of attachment Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice 3 Conduct visual inspection of wires backshells and connectors looking for signs of wear deterioration or damage Replace as required 4 Inspect harness connections in back of unit Secure any loose connections and support unsecure wiring harness with additional clamping and or tie rap supports if required 5 Inspect Pitot Static System for damage Replace parts as needed Complete the 90 Day Inspection found in Table 5 01 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 12 of 82 GTP 59 OAT Probe Installation 1 Access GTP 59 OAT Probe reference Section 6 00 00 Dimensions and Access Inspect GTP 59 OAT and mount for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Co
44. e Wrench Accuracy Torque wrenches must be of good quality and calibrated at least once a year Any torque wrench that has been dropped or abused should be calibrated to ensure continued accuracy b Application of Torque Wrench Loads 1 Be sure the bolt and nut and the surface they bear on are clean and dry unless otherwise specified by the manufacturer 2 Run the nut down to near contact with the washer or bearing surface and check the friction drag torque required to turn the nut Add the friction drag torque to the desired torque to arrive at the final torque to be registered on the torque wrench indicator 3 Whenever possible apply the torque to the nut instead of the bolt This will reduce rotation of the bolt in the hole and reduce wear 4 Apply a smooth even pull when applying torque pressure 5 If special adapters are used which will change the effective length of the torque wrench the final torque indication or wrench setting must be adjusted accordingly To determine the torque wrench setting or indication with adapter installed reference Figure 20 01 20 10 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 34 of 82 WHEN USING TORQUE WRENCH ADAPTER WHICH CHANGES THE DISTANCE FROM THE TORQUE WRENCH DRIVE TO THE ADAPTER DRIVE APPLY THE FOLLOWING FORMULAS TO OBTAIN THE CORRECTED TORQUE READING
45. ed the GDU 620 will update the configuration module from its internally 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 STC Installation Manual e Cooling Fan if option is installed i Removal 1 Disconnect the hoses from the cooling fan 2 Remove the three screws mounting the cooling fan to the pedestal 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 47 of 82 3 Disconnect the connectors 4 Remove the cooling fan ii Installation 1 Connect the connectors 2 Setthe cooling fan into place 3 Install the three mounting screws into the cooling fan 3 Illustrated Parts List This section contains information on parts for the G500H Flight Display System for use in ordering replacements if necessary Table 31 01 Parts List for Figure 31 01 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 115 01814 00 DOUBLER GARMIN 2 8 MS20470AD4 3 RIVET 3 6 MS20426AD5 5 RIVET 4 3 211 60037 08 SCREW GARMIN 5 A R MIL S 8802 SEALING COMPOUND 6 1 011 00870 10 GMU 44 MAGNETOMETER GARMIN 7 1 115 00481 10 INSTALL RACK GARMIN Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 31 00 00 190 01527 1
46. eleted 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 4 of the G500H STC Installation Manual for more information GDC 74H Configuration Module is Replaced If the GDC 74H Configuration Module is replaced the GDC 74H must be configured Refer to Section 5 5 8 of the G500H STC Installation Manual iii Return to Service After removing and reinstalling the GDC 74H the return to service checks must be performed reference Section 12 00 00 Return to Service Check C GRS 77H AHRS i Removal 1 Disconnect the GRS 77H connector 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 ii Installation 1 Place the GRS 77H on the mounting plate ensuring the orientation is correct 2 Fasten the unit to the plate using the Phillips thumbscrews Recommended torque is 22 25 inch pounds 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 45 of 82 3 Visually inspect the connectors to ensure there 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 Rei
47. emoved or disconnected to remove the instrument panel Consult the manufacturers Installation and Removal instructions for proper installation of items 2 Re install screw on front of instrument panel Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 25 of 82 h Cooling Fan Installation If option is installed The Cooling Fan is located on the forward side of the flight control pedestal Figure 6 08 Cooling Access Methods i Unlatch and open door to enter cabin ii Access forward side of the flight control pedestal Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 26 of 82 CHAPTER 8 Section 8 00 00 Weight Balance Information Installation Description Weight CG Location 190 01527 07 GTP 59 OAT Probe 0 08 Ibs STA 2208 WL 2547 BL 7 2 190 01527 02 GMU 44 Magnetometer 3 49 Ibs STA 6783 WL 2066 BL 0 0 190 01527 03 LH Shelf 2 00 Ibs STA 2463 WL 2
48. epaired 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 3 and Magnetic Calibration 5 6 2 ii Return to Service After removing and reinstalling the GMU 44 the following return to service checks should be performed reference Section 12 00 10 Return to Service Checks b GDC 74H Air Data Computer i Removal 1 Access the GDC 74H reference Section 6 00 00 Dimensions and Access 2 Disconnect the pitot static plumbing from the rear of the unit 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 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 44 of 82 4 Carefully remove the unit from its mounting location ii Installation Position the unit and fasten using the four 4 screws Connect the pitot static plumbing Inspect the connector and pins for damage Repair any damage a Wey 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 d
49. es one 1 placard that is mounted to the top of the lower pedestal with three 50 in diameter hole cut outs in the middle so the circuit breakers can stick through the placard 2 Decal and Placard Application a Wipe the surface area with isopropyl alcohol or acetone to thoroughly clean before applying the decal or placard Allow cleaned area to dry Separate backing from adhesive side of decal and apply to cleaned dry surface Roll out all wrinkles b Mask around edges where practical do not put tape on decal surface with masking tape Seal edges of placard or decal with 3M 3950 Edge Sealer Remove any masking tape after 1 2 minutes 11 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 29 of 82 12 Section 12 00 00 Servicing Maintenance Practices This chapter includes Return to Service Practices and Calibration Practices to be used with the G500H Flight Display System Installation 12 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 30 of 82 Section 12 10 00 Return to Service Practices 1 General a GMU 44 Magnetometer 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
50. g displayed on the SOFTWARE UPLOAD page Configuration errors are displayed on power up before the GDU enters normal mode The software loader card is installed in the bottom slot of the GDU 620 Insert the loader card in the top slot and cycle power to the GDU The software loader card contains no information The configuration module has not been updated Repeat the process for making the software loader card Update the configuration module For 400W 500W Series units the ARINC 429 vertical deviation labels are not being transmitted Enable Labels on the 400W 500W Series unit ARINC 429 configuration page Vertical GPS deviation is not displayed on the GDU 620 Unable to control the GPS course when in OBS mode The GPS navigator is not correctly Configure the ARINC 429 inputs outputs for LNAV1 SYS1 or LNAV2 SYS2 based upon whether the navigator is GPS1 or GPS2 Verify wiring configures as LNAV1 2 or SYS1 2 ARINC 429 bus hi and low are swapped Data is not being received from an ARINC 429 device 31 00 00 190 01527 15 Rev 1 Page 62 of 82 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 Gu valid data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page Data is not being received from an ARINC 429 device no data is being received on t
51. ghtning Strike Inspection that must be performed in the event of a suspected or actual lightning strike to the aircraft The Post Lightning Strike Inspection requirements are specified in Table 5 05 3 Tools and Special Tools for Special Inspections Although not necessarily considered special tools the adjustable ball swivel mirror and bright flashlight and or drop light are standard requirements for doing inspections These items should be used freely and frequently to enhance inspection quality and help ensure discrepancies are not missed It is important to have adequate lighting for all phases of the inspection The special tools necessary for the G500H inspection are listed as follows a Milliohm meter for electrical bonding testing 05 20 20 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 17 of 82 Table 5 05 Post Lightning Strike Inspection Registration No Helicopter Total Hours Post Lightning Strike Inspection e The Post Lightning Strike Inspection shall be accomplished in the event of a suspected or actual lightning strike to the aircraft e Initial each item after accomplishing the inspection e Record all findings and attach a copy of findings to this inspection form e After correction of all findings make maintenance record entry Post Lightning Strike Pre inspection 1 Review Airworthiness Directives Post Lightning Strike Inspecti
52. he 429 input port as shown on the GDU 620 PORT MONITORING page Attitude and heading on GDU 620 red X GRS 77H resets during air data ground testing Heading red X during air data ground testing Wrong device is connected to Use correct ports refer to interconnect port on GDU 620 details On the transmitting LRU the Set the ARINC 429 transmitter speed to ARINC 429 transmitter speed is correct speed not set correctly Wiring is not correct Check for continuity shorts and correct as required Attitude and heading This is expected behavior and no errors resets are possible if the troubleshooting is required if this occurs air data tests are conducted To reduce the chances of inducing indoors without a good GPS attitude and heading errors resets while signal With marginal or no GPS conducting the air data tests ensure that signals present sudden changes the G500H is receiving good GPS signals 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 the 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 This is expected behavior and no if the air data tests are conducted troubleshooting is required if this occurs indoors due to typic
53. her than a flap brush or mandrel with abrasive mat overheating and notching may occur 2 Ensure all active corrosion and corrosion products have been removed 3 Using 320 grit sandpaper blend edges of paint if applicable surrounding repair area to create a smooth transition Vacuum area thoroughly to remove all contaminates 4 Apply aluminum surface treatment if applicable Ref Item 4 Below 5 Touch up primer and paint to match original 3 Mechanical Defects Nicks Scratches Gouges Etc a Determine if damage is through the paint If not touch up the paint Ref Section 20 30 00 20 40 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 40 of 82 b If damage is through the paint surface prepare area for paint touch up using following methods Note On high strength steel do not use power tools other than a flap brush or mandrel with abrasive mat overheating and notching may occur 1 Remove defect using flap wheel abrasive disk abrasive paper or plastic media blast 2 Using 320 grit sandpaper blend edges of paint surrounding repair area to create a smooth transition 3 Apply aluminum surface treatment if applicable Ref Item 4 Below 4 Touch up primer and paint to match original 4 Aluminum Alloy Surface Touch Up Treatment Note If there is any question of whether or not the protective coating is removed surface t
54. led Inspection The 10 Year 2000 Flight Hour Inspection shall be accomplished at least at an interval of once every 10 years of elapsed calendar time or 2000 Flight Hours whichever occurs first Initial each item after accomplishing the inspection Record all findings and attach a copy of findings to this inspection form After correction of all findings make maintenance record entry 10 Year 2000 Flight Hour Pre inspection Requirement 1 Review Airworthiness Directives 10 Year 2000 Flight Hour Inspection Requirement GRS 77H AHRS 1 Access GRS 77H Reference Section 6 00 00 Dimensions and Access and disconnect all harness connectors 2 Measure the resistance between the GRS 77H and a nearby exposed portion of aircraft metallic structure Verify that the resistance is less than or equal to 20 milliohms If greater must be restored to the value specified in the G500H STC Installation Manual 3 Reconnect all disconnected harness connectors and ensure they are secure 4 Access GDU 620 Reference Section 6 00 00 Dimensions and Access and disconnect all harness connectors 5 Measure the resistance between the GDU 620 and a nearby exposed portion of aircraft metallic structure Verify that the resistance is less than or equal to 40 milliohms If greater must be restored to the value specified in the G500H STC Installation Manual 6 Reconnect all disconnected harness connectors and ensure they are secure 05 20 10 Instructio
55. min Reference System GMU Garmin Magnetometer Unit GDU Garmin Display Unit 05 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 7 of 82 GTP ADC STC AHRS Outside Air Temperature Garmin Temperature Probe Air Data Computer Supplemental Type Certificate Attitude Heading Reference System 05 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter 130 190 01527 15 Rev 1 Page 8 of 82 Section 05 20 10 Continued Airworthiness Scheduled Inspections 1 General This section contains requirements for scheduled inspections Also included is a list of special tools required to perform the scheduled inspections If any part of the installation appears to be functioning improperly consult the troubleshooting guide If a major component is damaged or continues to malfunction the component in question should be returned to the manufacturer for replacement 2 Scheduled Inspection Program G500H Installation requires scheduled inspections in order to maintain continued airworthiness Every effort should be made to perform the inspections with the aircraft placed in clean well lit environment There are four different scheduled inspections required for the G500H Installation a 90 Day Inspection The 90 day inspection is required to be performed every 90 day period of calendar elapsed time reg
56. ns for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 15 of 82 GDC 74H ADC 7 Access GDC 74H Reference Section 6 00 00 Dimensions and Access and disconnect all harness connectors 8 Measure the resistance between the GDC 74H and a nearby exposed portion of aircraft metallic structure Verify that the resistance is less than or equal to 20 milliohms If greater must be restored to the value specified in the G500H STC Installation Manual 9 Reconnect all disconnected harness connectors and ensure they are secure 10 Access GMU 44 Reference Section 6 00 00 Dimensions and Access and disconnect all harness connectors 11 Measure the resistance between the GMU 44 and a nearby exposed portion of aircraft aN metallic structure Verify that the resistance is less than or equal to 20 milliohms If greater must be restored to the value specified in the G500H STC Installation Manual 12 Reconnect all disconnected harness connectors and ensure they are secure 13 Access GTP 59 Reference Section 6 00 00 Dimensions and Access and disconnect all harness connectors 14 Measure the resistance between the GTP 59 and a nearby exposed portion of aircraft metallic structure Verify that the resistance is less than or equal to 5 milliohms If greater must be restored to the value specified in the G500H STC Installation Manual 15 Reconnect all disconnected harness connectors and ens
57. nstalled 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 Section 12 20 00 Calibration Requirements 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 Section 12 20 00 Calibration Requirements 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 Section 12 10 20 Calibration Requirements iii Return to Service After removing and reinstalling the GRS 77H the return to service check should be performed Reference Section 12 00 10 d GDU 620 MFD i 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 Disconnect the rear connectors 4 Remove the GDU 620 ii Installation 1 Visually inspect the connectors to ensure that there are no bent or damaged pins Repair any damage 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 46 of
58. ntrol Maintenance Practices 2 Inspect harness connections in back of unit Secure any loose connections and support unsecure wiring harness with additional clamping and or tie rap supports if required 3 Inspect unit for security of attachment Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice Terminal Block Installation 1 Access Terminal Block Installation reference Section 6 00 00 Dimensions and Access Inspect installation for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices 2 Inspect unit for security of attachment Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice Cooling Fan Installation If option is installed 1 Access Cooling Fan Installation reference Section 6 00 00 Dimensions and Access Inspect installation for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices 2 Inspect cooling fan hoses for physical damage and security Repair or replace any damaged hoses Replace any damaged or missing Tywraps 3 Inspect unit for security of attachment Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in
59. on GTP 59 OAT Probe Installation 1 Access the GTP 59 OAT Probe Installation Reference Section 6 00 00 Dimensions and Access 2 Inspect the probe and the doubler P N 115 01812 00 for signs of structural damage If there are visible signs of damage replace the parts as needed Post Lightning Strike Post Inspection fern 22222 Ld 1 Verify that the OAT is displayed on the GDU 620 PFD normally 05 20 20 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 18 of 82 CHAPTER 6 Section 06 00 00 Dimensions and Access 1 Access Methods For removal and installation of specific components reference Section 31 00 00 Instruments Removal and Replacement a GMU 44 Magnetometer Magnetometer is located in the tail boom between TB 868 and 1578 Figure 6 01 Figure 6 01 Access Methods i Removal 1 Un latch and open the battery door on the left side of the aircraft 2 Ifa battery is installed it may be necessary to remove the battery to gain access to the magnetometer Consult the manufacturers Installation and removal instructions for proper removal of unit ii Installation 1 Re install battery if removed to gain access to the magnetometer Consult the manufacturers Installation and Removal instructions for proper installation of unit 2 Close the battery access door and latch it Caution Use of power tools during removal or installati
60. on of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 19 of 82 b GDC 74H Air Data Computer GDC 74H is located underneath the cabin floor between station 2249 and 2737 on the left side of the aircraft Figure 6 02 GDC 74H Figure 6 02 Access Methods i Removal 1 Un latch the Center lower belly access panel 2 Disconnect the retaining straps that prevent the panel from falling to the floor 3 If aftermarket items are attached to the Center lower belly panel it may be necessary to remove or disconnect them in order to remove the lower belly panel Consult the manufacturers Installation and Removal instructions for proper removal of items ii Installation 1 Re install aftermarket items if removed to gain access to the air data computer Consult the manufacturers Installation and Removal instructions for proper installation of items 2 Connect the retaining strap that was disconnected to gain access to the air data computer 3 Close the Center lower belly access panel and latch it Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190
61. or signs of wear deterioration or damage Replace as required 3 Inspect harness connections in back of unit Secure any loose connections and support unsecure wiring harness with additional clamping and or tie rap supports if required 4 Inspect unit for security of attachment Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice GMU 44 Magnetometer Installation 1 Access GMU 44 reference Section 6 00 00 Dimensions and Access Inspect GMU 44 and mount for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices 2 Conduct visual inspection of wires backshells and connectors looking for signs of wear deterioration or damage Replace as required 3 Inspect hardware Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice 4 Inspect harness connections in back of unit Secure any loose connections and support unsecure wiring harness with additional clamping and or tie rap supports if required Shelf Installation 1 Access Shelf Installation reference Section 6 00 00 Dimensions and Access Inspect for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices 2 Inspe
62. orthiness for the Garmin G500H Installation in Eurocopter EC130 Y is 2 gt 190 01527 15 Rev 1 Page 80 of 82 RAD ALT ARINC 429 IN 8 A ARINC 429 IN 8 B RAD ALT PUSH TEST 98 10 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 N A A 190 01527 15 Rev 1 Page 81 of 82 Section 98 20 00 Pitot Static System Schematic INSTRUMENT PANEL gt Ex S N REF STATIC TUBE REF STATIC TUBE DRAIN PITOT TUBE EN3628 050 LOCKWIRE ASNA 4246 007 01 TUBE 355A76607323 UNION TEE 3 33844 NUT 1 23024 58 LABEL STATIC 2 23024 57 LABEL PITOT BELL HELICOPTER 9 8 7 6 5 4 3 2 EUROCOPTER UNION DUCT UNION DUCT EUROCOPTER 120 3005 01 H341 78 4D 39 2 FITTING MALE CONNECTOR ITEM PART NUMBER DESCRIPTION MANUFACTURER ALT P N 12059 UNION VENDOR RENAISSANCE MACHINE 98 20 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 82 of 82
63. proper removal of items ii Installation 1 Re install any other aftermarket items if removed to gain access to the GTP59 OAT Probe Consult the manufacturers Installation and Removal instructions for proper installation of items 2 Connectthe retaining strap that was disconnected to gain access to the GTP59 OAT Probe 3 Close the Center lower belly access panel and latch it Caution Use of power tools during removal or installation of panels and attaching hardware may damage nut plates or deform holes in composite doors covers panels and fairings 06 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 24 of 82 g GDU 620 Installation The GDU 620 is located in the left hand side of the instrument panel Reference Section 31 00 00 Instruments Figures 31 08 through 31 11 for specific location based on installation configuration T aaoooaaag 4OCOOOOOOM l E 7 o lt Figure 6 07 Access Methods i Removal 1 Un screw the screws on the front of the instrument panel 2 For items that are attached to the instrument panel it may be necessary to remove or disconnect them in order to remove the instrument panel Consult the manufacturers Installation and Removal instructions for proper removal of items ii Installation 1 Re install items if r
64. r the G500H inspection are listed as follows a Milliohm meter for electrical bonding testing Table 5 01 90 Day Inspection Registration No Helicopter Total Hours 90 Day Scheduled Inspection The 90 Day Inspection shall be accomplished at least at an interval of once every 90 days of elapsed calendar time Initial each item after accomplishing the inspection Record all findings and attach a copy of findings to this inspection form After correction of all findings make maintenance record entry 90 Day Pre inspection 1 Access GDC 74H reference Section 6 00 00 Dimensions and Access Drain the pitot static system by removing the safety wire nut and plug 2 Re install the plug nut and safety wire 3 Reference Section 12 10 00 Return to Service Practices for the GDC 74H ENN 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 10 of 82 Table 5 02 1 year Annual Inspection Registration No Helicopter Total Hours 1 Year Annual Scheduled Inspection e The 1 Year inspection shall be accomplished at least at an interval of once every year of elapsed calendar time e Initial each item after accomplishing the inspection e Record all findings and attach a copy of findings to this inspection form After correction of all findings make maintenance record entry 1 year Annual Pre inspection Requirement Initial 1 Revie
65. reatment shall be applied Warning Alodine and solvents can cause burns and irritation when it contacts skin proper gloves should be worn Vapors are harmful and caustic to eyes Goggles must be worn for eye protection Alodine is poisonous Vapors are harmful to life or health work should be performed with proper ventilation and or respirators should be worn while working with Solvents and alodine Solvent cleaners are flammable a Scuff surface using 3M scotchbrite 63 cellulose nylon scouring pad b Wipe exposed surface with isopropyl alcohol or aliphatic naphtha Allow area to air dry for 10 minutes Do not touch or otherwise contaminate surface after solvent wipe c Apply Alodine 1200 or equivalent with cotton swap non metallic brush or by dipping Maintain moist surface for 1 3 minutes with repeated application Surface will become amber or brown in color d Irrigate surface with demineralized or distilled water to remove surface treatment chemical Allow to air dry for approximately 1 hour e Ifthere are any surface without color change repeat procedure f Apply paint touch up as required Ref Section 20 30 00 20 40 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 41 of 82 Section 20 90 00 Dye Penetrant Inspection Methods Warning solvents can cause burns and irritation when it contacts skin proper gloves should be worn Vapors are harmful
66. rocopter 130 190 01527 15 Rev 1 Page 66 of 82 Alert Text Case TRAFFIC FAIL The traffic information system has failed The GDU 620 is not receiving traffic 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 that the traffic sensor has failed Troubleshoot traffic system TRK LOST GPS1 TRK lost HSI defaulted to GPS2 TRK TRK TRAFFIC Heading Lost Traffic is now based on track See HDG errors GDU 620 is not receiving radar altimeter data 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter 130 Verify wiring between GDU 620 and Radar Altimeter sensor 190 01527 15 Rev 1 Page 67 of 82 CHAPTER 98 Section 98 00 00 Wiring Diagrams and Pitot Static System Schematics This chapter includes the Wiring Diagrams and Pitot Static System Schematics for the GSOOH Flight Display System 98 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 68 of 82 Section 98 10 00 Wiring Diagrams OPTIONS 01 G500H WITHOUT RADAR ALTIMETER 02 G500H WITH RADAR ALTIMETER ee one or eo AR 53 SWT316 3 16 TEFLON SPIRAL WRAP DALLAS aviones AVIONICS 1 1 52 12883 5 1 RELAY SOCKET HH Er EE 49 010 00769 60 GDU INSTAL
67. ructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 3 of 82 CHAPTER 1 Section 01 00 00 Introduction These are accepted Instructions for Continued Airworthiness for modifications performed in accordance with Eurocopter EC130 B4 Garmin G500H Flight Display System Installation STC All references to the G500H in this document will refer to the Garmin G500H Flight Display System Installation and other related components specified in these Instructions for Continued Airworthiness ICA A STC permission letter and Instructions for Continued Airworthiness ICA should be supplied to the owner operator of the STC at the time of completion Subsequent accepted changes to the ICA will be distributed to owners and operators of the STC This Instructions for Continued Airworthiness is intended to supplement the Model EC130 B4 rotorcraft maintenance manuals provided by Eurocopter The information procedures requirements and limitations contained in this Instructions for Continued Airworthiness for this type design change supersedes the information procedures requirements and limitations contained in the rotorcraft s maintenance manual when the type design change is installed on the Type Certificate Holder s rotorcraft 01 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 4 of 82 4 Section 04 00
68. ure they are secure 4 PostInspection Maintenance Practices After completion of the 1 Year Annual Inspection 5 Year Inspection and 10 Year 2000 Flight Hour Inspection and all discrepancies found have been corrected the Return to Service Practices Reference Section 12 00 00 Return to Service Practices should be accomplished in preparation for returning the rotorcraft to service 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 16 of 82 Section 05 20 20 Continued Airworthiness Special Inspections 1 General This section contains requirements for special inspections Also included is a list of special tools required to perform the scheduled inspections If any part of the installation appears to be functioning improperly consult the troubleshooting guide If a major component is damaged or continues to malfunction the component in question should be returned to the manufacturer for replacement 2 Special Inspection Program Conditions may arise from incidents or accidents that may warrant additional inspection requirements A Special Inspection is required if the aircraft is involved in a hard landing or is subjected to total immersion in water If either of these conditions occurs the G500H Installation must be inspected using the same procedures called out in the Annual Inspection Procedures in Table 5 02 G500H Installation has Post Li
69. ured and operating HDG FAULT AHRS magnetometer fault has occurred GRS 77H not receiving information from GMU 44 Verify wiring to GMU 44 HDG LOST Heading from the GRS77 GMU 44 is not valid Caused by a local magnetic anomaly No action required lt LRU gt SERVICE MANIFEST Specific LRU should be serviced where lt LRU gt denotes specific LRU GDU has received product data for an LRU that should have a manifest entry but is not in the manifest The LRU software P N and version number in the manifest does not match the values being reported by that LRU Return indicated LRU to Garmin for service Ensure the manifest is properly configured Update the LRU software to match the manifest Update the manifest to match the LRU software NAV1 FAIL No navigation receiver 1 data NAV2 FAIL No navigation receiver 2 data SIMULATOR The simulator mode is active Ensure P6202 36 is not grounded SVT DISABLED Out of available terrain region Location is beyond region covered by terrain database SVT DISABLED Terrain DB resolution too low SW MISMATCH A 30 arc second terrain database is being used GDU software version strings do not match Update the Supplemental Data card with the 9 arc second terrain database Verify the correct SW is loaded 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eu
70. w Airworthiness Directives 1 year Annual Inspection Requirement GDU 620 1 Locate GDU 620 reference Section 6 00 00 Access and Dimension Inspect all knobs and buttons for legibility 2 Inspect instrument panel for damage corrosion and security If damaged replace damaged or cracked Instrument panel Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices Tighten any loose hardware to values listed in Section 20 10 00 3 Inspect unit for security of attachment Replace the damaged or corroded hardware Replace any missing hardware Torque all screws in accordance with Section 20 10 00 Torques Maintenance Practice 4 Conduct visual inspection of wires backshells and connectors looking for signs of wear deterioration or damage Replace as required 5 Inspect harness connections in back of unit Secure any loose connections and support unsecure wiring harness with additional clamping and or tie rap supports if required GRS 77H AHRS 1 Access GRS 77H reference Section 6 00 00 Dimensions and Access Inspect AHRS and mount for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20 40 00 Corrosion Control Maintenance Practices 05 20 10 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 11 of 82 2 Conduct visual inspection of wires backshells and connectors looking f
71. working Verify wiring is correct CAL LOST Registry reports that it has lost Contact Garmin Technical Support calibration data CNFG MODULE The configuration module is Verify wiring to configuration module inoperative Replace configuration module DATA LOST Pilot stored data was lost Recheck data and settings 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 31 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter 130 Page 64 of 82 Alert Text cause 2 GDL69 CONFIG GDU CONFIG Fan 2 has reported 0 RPM when it was powered with a PWM duty cycle higher than or equal to 10 The GDL 69 configuration information stored in the GDL 69 and the GDU 620 configuration module do not match The GDL 69 configuration was updated using another LRU e g the GMX 200 or 400W 500W This error appears whenever the GDU is replaced with a GDU that was configured for a different installation Error in the configuration of the GDU 620 Inspect the GDU fan for an obstruction Contact Garmin Technical Support With the GDU 620 in configuration mode go to the GDL 69 page in the GDL page group Verify that the SET and ACTIVE configuration settings are the same If not use the SET gt A
72. year 12 months of initial installation and then afterwards within 1 year 12 months of the last G500H Installation annual inspection The annual inspection requirements are specified in Table 5 02 The G500H Installation requires a 5 Year Inspection that must be performed within 60 months of initial installation and then afterwards within 60 months of the last G500H Installation inspection The 5 Year Inspection requirements are specified in Table 5 03 The G500H Installation requires a 10 Year 2000 Flight Hours Inspection that must be performed within 120 months or 2000 flight hours whichever occurs first of initial installation and then afterwards within 120 months or 2000 flight hours whichever occurs first of the last GSOOH Installation 10 year 2000 flight inspections The 10 Year 2000 Flight Hour Inspection requirements are specified in Table 5 04 4 Special Inspection Practices Conditions may arise from incidents or accidents that may warrant additional inspection requirements A Special Inspection is required if the aircraft is involved in a hard landing or is subjected to total immersion in water If either of these conditions occurs the G500H Installation must be inspected using the same procedures called out in the Annual Inspection Procedures in Table 5 02 05 00 00 Instructions for Continued Airworthiness 190 01527 15 Rev 1 for the Garmin G500H Installation in Eurocopter EC130 Page 6 of 82 G500H Installation has

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