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 1 04/22/2014 Initial release.
Table of Contents CHAPTER 1 .................................................................................................................................. 4 Section 01-00-00 Introduction ......................................................................................................... 4 CHAPTER 4 .................................................................................................................................. 5 Section 04-00-00 Airworthiness Limitations ...........................
Section 98-00-00 Wiring Diagrams and Pitot-Static System Schematics ....................................... 68 Section 98-10-00 Wiring Diagrams .................................................................................................. 69 Section 98-20-00 Pitot-Static System Schematic .............................................................................
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).
CHAPTER 4 Section 04-00-00 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.
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.
The G500H Installation has a Post-Lightning 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. 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.
OATGTPADCSTCAHRS- 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 EC130 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.
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). Table 5-01 -90 Day Inspection Registration No. Serial 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.
Table 5-02 -1 year (Annual) Inspection Registration No. Serial No. Helicopter Total Hours 1 Year (Annual) Scheduled Inspection • • • • The 1 Year inspection shall be accomplished at least at an interval of once every year 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. 1 year (Annual) Pre-inspection Requirement Initial 1.
2. Conduct visual inspection of wires, backshells, and connectors looking for 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.
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 Control 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.
Table 5-03 -5 Year Inspection Registration No. Serial 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 Requirement Initial 1. Review Airworthiness Directives.
Table 5-04 -10 Year/2000 Flight Hour Inspection Registration No. Serial No. Helicopter Total Hours 10 Year/ 2000 Flight Hour Scheduled 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.
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. GMU 44 10.
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.
Table 5-05 -Post-Lightning Strike Inspection Registration No. Serial No. Helicopter Total Hours Post-Lightning Strike Inspection • • • • The Post-Lightning Strike Inspection shall be accomplished in the event of a suspected or actual lightning strike to the aircraft. 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.
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) GMU 44 TB 1578 REF TB 868 REF Figure 6-01 Access Methods i. Removal 1. Un-latch and open the battery door on the left side of the aircraft. 2.
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 STA 2249 REF STA 2737 REF 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.
c) 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 STA 2249 REF STA 2737 REF 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.
d) Shelf Installation The shelf installation is located underneath the cabin floor between station 2249 and 2737 on the left side of the aircraft. (Figure 6-04) Shelf STA 2249 REF STA 2737 REF Figure 6-04 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.
e) 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 STA 1703 REF STA 1766 REF Figure 6-05 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.
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) GTP 59 STA 2205 REF STA 2269 REF 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.
g) GDU 620 Installation The GDU 620 is located in the left hand side of the instrument panel (Reference Section 3100-00 Instruments, Figures 31-08 through 31-11 for specific location based on installation configuration) GDU 620 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.
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.
CHAPTER 8 Section 8-00-00 Weight and Balance Information Installation # 190-01527-07 190-01527-02 190-01527-03 190-01527-04 190-01527-05 190-01527-01 190-01527-06 190-01527-12 Description GTP 59 OAT Probe GMU 44 Magnetometer LH Shelf GDC 74H GRS 77H AHRS Instrument Panel Terminal Block Cooling Fan Weight 0.08 lbs 3.49 lbs 2.00 lbs 1.92 lbs 3.46 lbs 47.80 lbs 0.47 lbs 0.70 lbs CG Location STA 2208, WL -2547, BL 7.2 STA 6783, WL -2066, BL 0.0 STA 2463, WL -2780, BL -756.7 STA 2615, WL -2744, BL -731.
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 30 LBS”. 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.
E.F.I.S. Circuit Breaker Installation Circuit Breaker Installation requires 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.
CHAPTER 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.
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 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.
Section 12-20-00 Calibration Requirements Calibrations Required Condition GRS 77H Pitch/Roll Offset See Section 5 of the G500H STC Installation Manual GRS 77H AHRS was removed and/or replaced. The mounting tray was NOT removed and the mounting tray bolts were NOT loosened. GRS 77H AHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts WERE loosened. GRS 77H AHRS Configuration Module was replaced.
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.
Section 20-10-00 Torques Maintenance Practices 1. Torque Wrenches a) Torque 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.
Figure 20-01 20-10-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 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 20-02. Recommended Torque Values for Coarse Thread Fasteners Thread Size Shear Tension Fractional (decimal) Recommended Maximum Recommended Maximum in-lb (N m) in-lb (N m) in-lb (N m) in-lb (N m) 8-32 (0.1640-32) 10-24 (0.1900-24) ¼-20 (0.2500-20) 5/16-18 (0.3125-18) 3/8-16 (0.3750-16) 7/16-14 (0.4375-14) ½-13 (0.5000-13) 9/16-12 (0.5625-12) 5/8-11 (0.6250-11) ¾-10 (0.7500-10) 7/8-9 (0.8750-9) 1-8 (1.0000-8) 1-1/8-8 (1.1250-8) 1-1/4-8 (1.2500-8) 7-9 (0.79-1.02 ) 12-15 (1.36-1.69) 25-30 (2.82-3.
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.
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.
(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.
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).
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 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.
CHAPTER 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. The GDU 620 provides controls for the G500H system and a PFD and MFD 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.
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. Connect the wiring harness to the GMU 44. 3.
4. Carefully remove the unit from its mounting location. ii Installation 1. Position the unit and fasten using the four (4) screws. 2. Connect the pitot/static plumbing. 3. Inspect the connector and pins for damage. Repair any damage. 4. 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.
3. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 4. Connect the connector to the GRS 77H, ensuring that each slidelock is secured on both sides. Original GRS 77H is Reinstalled If the original GRS 77H is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process.
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.
3. Disconnect the connectors. 4. Remove the cooling fan. ii Installation 1. Connect the connectors. 2. Set the 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.
Figure 31-01 GMU 44 MAGNETOMETER INSTALLATION, EXPLODED VIEW (Reference Table 31-01) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 49 of 82
Table 31-02 Part Lists for Figures 31-02 ITEM NUMBER 1 QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 115-01815-00 GARMIN 2 1 115-01816-00 3 4 5 6 7 8 9 1 8 8 16 8 16 24 115-01817-00 AN3-3A AN3-4A MS20426AD3-3 MS21042L3 MS21075L3N NAS1149D0332K FWD GUSSET SUPPORT BRACKET AFT GUSSET SUPPORT BRACKET SHELF BOLT BOLT RIVET NUT NUT WASHER GARMIN GARMIN 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 for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 51 of 82
Table 31-03 Parts List for Figure 31-03 ITEM NUMBER QUANTITY 1 2 3 4 1 4 4 8 PART NUMBER DESCRIPTION 011-00882-11 GDC 74H ADC AN525-10R7 SCREW MS21075L3N NUTPLATE MS20426AD3-3 RIVET MANUFACTURER GARMIN Figure 31-03 GDC 74H INSTALLATION EXPLODED VIEW (Reference Table 31-03) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 52 of 82
Table 31-04 Parts List for Figure 31-04 ITEM NUMBER QUANTITY 1 2 3 4 5 1 1 5 5 10 PART NUMBER DESCRIPTION 011-00868-20 GRS 77H AHRS 115-00459-00 GRS 77 MOUNT RACK AN525-10R7 SCREW MS21075L3N NUTPLATE MS20426AD3-3 RIVET MANUFACTURER GARMIN GARMIN Figure 31-04 GRS 77H INSTALLATION, EXPLODED VIEW (Reference Table 31-04) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 53 of 82
Table 31-05 Part List for Figure 31-05 ITEM NUMBER 1 2 3 4 5 QUANTITY PART NUMBER DESCRIPTION 1 2 1 1 2 M81714/67-18 M81714/60-22-05 AN525-10R7 MS21042L3 NAS1149F0332P RAIL TERMINAL BLOCK SCREW NUT WASHER MANUFACTURER Figure 31-05 TERMINAL BLOCK INSTALLATION, EXPLODED VIEW (Reference Table 31-05) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 54 of 82
Table 31-06 Parts List for Figure 31-06 ITEM NUMBER 1 2 3 4 QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 8 A/R 115-01812-00 011-00978-00 MS20470AD4-3 MIL-S-8802 DOUBLER GTP 59 OAT PROBE RIVET SEALING COMPOUND GARMIN GARMIN Figure 31-06 GTP 59 OAT PROBE INSTALLATON, EXPLODED VIEW (Reference Table 31-06) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 55 of 82
Table 31-07 Parts List for Figures 31-07 ITEM QUANTITY PART NUMBER DESCRIPTION MANUFACTURER NUMBER 1* 1 011-03096-01 INSTRUMENT PANEL ASSEMBLY GARMIN 2 1 011-01264-50 GDU 620 PFD/MFD GARMIN 3 1 233-40024-00 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 7† REF 350A62118800 EMERGENCY BATTERY SWITCH EUROCOPTER 8 REF EXISTING 3 IN AIRSPEED EUROCOPTER 9 REF EXISTING 3 IN ALTIMETER EUROCOPTER 10 REF B19030MD05
Figure 31-07 INSTRUMENT PANEL INSTALLATION (Reference Table 31-07) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 57 of 82
Table 31-08 Parts List for Figure 31-08 ITEM NUMBER 1 2 3 4 5 6 7 QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 4 6 6 2 36 115-01818-01 161-03095-01 MS21061-08 MS21069-08 MS21071-06 MS21075-08 MS20426AD3-4 INSTRUMENT PANEL LABEL NUTPLATE NUTPLATE NUTPLATE NUTPLATE RIVET GARMIN GARMIN 31-00-00 Instructions for Continued Airworthiness for the 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 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 59 of 82
Table 31-09 Parts List for Figure 31-09 ITEM NUMBER 1 2 3 4 5 6 7 8 QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 6 3 3 3 3 7 A/R 013-00103-00 MS20426AD3-3 MS21059L06 MS35206-236 NAS43DD1-20 MB-3A TI8L-0 5700-1 COOLING FAN RIVET NUTPLATE SCREW SPACER CABLE TIE MOUNT TYWRAP COOLING HOSE GARMIN TYTON TYTON EDMO Figure 31-09 COOLING FAN INSTALLATION (OPTIONAL) (Reference Table 31-09) 31-00-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-
Table 31-10 List of Consumable Materials DESCRIPTION THREAD LOCK ADHESIVE Cleaning cloth, Low-Lint P/N 242 1300L -- Mineral Spirits, Cleaning Solvent Alodine Alodine Paint Stripper Polyamide Paint Primer Dye Penetrant Kit Acetone Isopropyl Alcohol Trichloroethane Nylon Scouring Pad 240 Grit Sandpaper 320 Grit Sandpaper 240 Grit Aluminum Oxide Abrasive Cloth Sealant Adhesive transfer tape 950 (2") -Alodine 1200 Iridite 14-2 Turco 5873 -----(3M) Scotchbrite 63 -----70-0060-3057-4 VENDOR/SPECIFICATION LOCT
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 on the GDU 620 MFD. These are listed in the Table 31-12. Table 31-11 GDU 620 Troubleshooting Guide Problem Unit does not power up – blank screen. Cause Solution Improper wiring; circuit breaker open. Ensure power is properly wired to the GDU 620 and the circuit breaker is closed. Unit intensity turned down.
Problem Cause (valid data is being received Wrong device is connected to on the 429 input port as port on GDU 620. shown on the GDU 620 PORT MONITORING page) Solution Use correct ports (refer to interconnect details). On the transmitting LRU, the ARINC 429 transmitter speed is not set correctly. Set the ARINC 429 transmitter speed to correct speed. Wiring is not correct. Check for continuity/shorts and correct as required.
Table 31-12 GDU 620 Alert Troubleshooting Guide Alert Text AHRS1 GPS – AHRS 1 using backup GPS source. Cause AHRS is using the backup GPS information Solution Verify GPS1 power and check the wiring AHRS1 GPS - AHRS is not AHRS is not receiving any GPS receiving any GPS information information. Verify GPS power and check the wiring AHRS1 GPS – AHRS 1 AHRS is not receiving any GPS operating in exclusively in no- information. GPS mode. Ensure that at least one GPS has acquired a valid position.
Alert Text Cause Solution FAN 2 FAIL Fan 2 has reported 0 RPM when it was powered with a PWM duty cycle higher than or equal to 10% Inspect the GDU fan for an obstruction. Contact Garmin Technical Support. GDL69 CONFIG The GDL 69 configuration information stored in the GDL 69 and the GDU 620 configuration module do not match. 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.
Alert Text GPS(1/2) PPS Failure Cause 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. GPS2 FPL USED The GPS1 has failed and GPS2 is configured and operating. HDG FAULT AHRS magnetometer fault has occurred. Heading from the GRS77/ GMU 44 is not valid. Specific LRU should be serviced, where denotes specific LRU.
Alert Text TRAFFIC FAIL Cause The traffic information system has failed. Solution 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.
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 G500H Flight Display System.
Section 98-10-00 Wiring Diagrams 98-10-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 69 of 82
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Section 98-20-00 Pitot-Static System Schematic * *ALT P/N: 12059 UNION, VENDOR: RENAISSANCE MACHINE 98-20-00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter EC130 190-01527-15 Rev 1 Page 82 of 82
