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Garmin AS_350B2/B3 Instruction Manual

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1. 211 64412 12 SCREW QTY 6 PART K10 00133 00 G500H INSTALLATION KIT INSTRUMENT PANEL INSTALLATION 4 EUROCOPTER AS350 Figure 31 12 ITEM 4 INSTRUMENT PANEL INSTALLATION Reference Table 31 07 31 00 00 190 00792 12 Rev 1 Instructions for Continued Airworthiness Page 60 of 80 for the Garmin G500H Installation in Eurocopter AS350 Table 31 08 Parts List for Figure 31 13 NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 115 01760 01 OPTION 1 INSTRUMENT PANEL GARMIN 2 1 161 02779 01 FAA PMA LABEL GARMIN 3 4 MS21061L08 NUTPLATE 4 6 MS21069 08 NUTPLATE 5 6 MS21071 06 NUTPLATE 6 2 MS21075 08 NUTPLATE 7 36 MS20426AD3 4 RIVET 5 6 E 4 INSTRUMENT PANEL ASSEMBLY 1 FAA PMA EUROCOPTER 5350 REFERENCE 011 02764 01 FOR BILL OF MATERIAL Figure 31 13 OPTION 1 INSTRUMENT PANEL ASSEMBLY Reference Table 31 08 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 61 of 80 Table 31 09 Parts List for Figure 31 14 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 115 01760 02 OPTION 2 INSTRUMENT PANEL GARMIN 2 1 161 02779 02 FAA PMA LABEL GARMIN 3 4 MS21061L08 NUTPLATE 4 6 MS21069 08 NUTPLATE 5 6 MS21071 06 NUTPLATE 6 2 MS21075 08 NUTPLAT
2. 0 000 10122221 26 ULP 27 Section 12 00 00 Servicing Maintenance Practices esns esns rsnsnsrsnsnsnsnsns 27 Section 12 10 00 Return to Service Practices eee U 28 Section 12 20 00 Calibration eene enne 29 CHAPTER 20 onere petet esses EBENE 30 Section 20 00 00 Standard a i aa 30 Section 20 10 00 Torques Maintenance 222 31 Section 20 30 00 Painting Maintenance Practices esses 35 Section 20 40 00 Corrosion Control Maintenance 2 36 Section 20 50 00 Mechanical Fastener Sealing 5 2 2 4 39 Section 20 90 00 Dye Penetrant Inspection 5 222 222221 40 8 Fui or cd ec 41 Section 31 00 00 Instruments 41 Section 98 00 00 Wiring Diagrams and Pitot Static System Schematics 71 Section 98 10 00 Wiring Diagrams 72 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 2 of 80 Section 98 20 00 Pitot Static System Schematic 10011220211 80 Instructions for Continued Airworthi
3. ARINC 429 IN2A 5 ARINC 429 IN2B 22 d uj 11 RS 232 OUT 1 2320072 282 9 o RS 232N1 RS 232 GND 2 45 B B RS 232 GND 1 LM RS2321N2 11 Bi EEIS TB PA DD RS 23213 12 A RS 232GND3 46 E TIMEMARKIN1A a 4 GPS1 TIMEMARKIN1B 412 Hm A REF ARINC 429 IN3A LW ARINC 429 IN3B 23 2 4 ARINC 429 OUT1 A 3 ARINC 429 OUT1B 20 Fr 1 5 RS 232 IN 4 13 x MO TIMEMARKIN2A HO O GPs 2 A TIME MARK IN2B 43 B tls J ARINC 429 IN 5 A wey REF es E tls e M D us A Note Tw J 98 10 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 77 of 80 GDU 620R PFD MFD 2 0 ARINC 429 IN 4 A NAV 1 ARINC 429 IN 4B AX ARINC 429 IN 6 A 2 ARINC 429 IN 6 B OR RS 232 IN 5 AX NAV 2 RS 232 GND 5 ENTE AUDIO OUT HI AUDIO OUT LO AUDIO INHIBIT IN AUDIO ACTIVE OUT ETHERNET IN 2 ETHERNET 28
4. OUT 2 ETHERNET OUT 2B AX TRAFFIC 4 TAS TEST TIS TAS STANDBY ARINC 429 IN7 A ARINC 429 IN7 B AX SERIAL 8523209 ALTITUDE RS 232 GND 8 GSR RMT PWR ON RS 232 IN6 4 RS 232 OUT 6 GSR 56 RS 232 GND 6 M GSR STATUS IN ETHERNET IN 1A 9 ETHERNET 1B GDL69fA 4 ETHERNET OUT 1A ETHERNET OUT 1B COMPOSITE VIDEO IN 1 COMPOSITE VIDEO RTN COMPOSITE VIDEO IN 2 AIR GROUND STATUS 98 10 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 78 of 80 FREEFLIGHT RA 4500 INTERFACE OPTION 02 Enso Pg ae a te eR ti ii EP ng POA in FREEFLIGHT RA 4500 GDU 6208 PFD MFD A E RADAR ALTIMETER R T askoa qu ARINC4291N8A HO 2 RAD ALT arg s is RAD ALT ARINC 429 OUT I EFIS TB 4B i Er 124 RAD ALTPUSH TEST 46 111 1 ee ee PU D HONEYWELL KRA 405B INTERFACE TOUT NERIS AULUS AU A
5. INDICATED TORQUE L EFFECTIVE LENGTH LEVER E EFFECTIVE LENGTH OF EXTENSION Open End Wrench TORQUE WRENCH Adapter WRENCH HANDGRIP DRIVE CENTERLINE CENTERLINE ADAPTER PREDETERMINED Flare Nut Wrench Adapter TxL FORMULA ce Y EXAMPLE WITH E AS MINUS DIMENSION A q T 435 LB IN Ys qe 1399 1 2 Y UNKNOWN Spanner Wrench L 10 0 IN Adapter E 1 5 IN Y 459 LB IN Figure 20 01 20 10 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 32 of 80 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 Thread Fasteners Thread Size Ser Tension 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 2
6. 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 31 of 80 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 Short Open End Adapter TORQUE ADAPTFR WRENCH HANDGRIP CENTERLINE PREDETERMINED Set Screw Adapter me TxL FORMULA LE 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 E 4 5 IN Y 117 LB IN T ACTUAL DESIRED TORQUE Y APPARENT
7. e Ea te muta ior 1 HONEYWELL KRA 405B GDU 620R PFD MFD N REF m 2 APARAETIMETER IT a wd EFIS IB 4A 8 ARINC4291N8A s HO Q ed XM P L 1 4 i RAD ALT PUSH TO TEST 45 171 w lu PUSH TO TEST I 1 NEMPE le ane On aaa oe OT ee S S d Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 79 of 80 Section 98 20 00 REF INSTRUMENT PANEL Pitot Static System Schematic 11 A R AW HORN 3628 050 5 4246 007 01 355 76607323 33844 23024 58 23024 57 REF PITOT TUBE LOCKWIRE TUBE UNION TEE NUT LABEL STATIC LABEL PITOT CL REF 011 00882 11 AIR DATA COMPUTER GDC 74H REF STATIC TUBE REF STATIC TUBE EUROCOPTER EUROCOPTER EUROCOPTER EUROCOPTER BELL HELICOPTER BELL HELICOPTER 21783 21559 20059 2 20001 120 3005 01 PLUG UNION DUCT UNION UNION DUCT NUT EUROCOPTER EUROCOPTER EUROCOPTER EUROCOPTER EUROCOPTER N N RR Nh gt gt 3 341 78 40 39 2 PART NUMBER FITTING MALE CONNECTOR DESCRIPTION 2 ALTERNATIVE MANUFACTURER
8. 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 40 of 80 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 G500H system and PFD 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 30 circuit breaker panel 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 A
9. 0 12 IN f 3 05mm 94241 3 05mm MINIMUM Figure 20 02 Mechanical Fastener Sealing 20 50 00 190 00792 12 Rev 1 Instructions for Continued Airworthiness Page 39 of 80 for the Garmin G500H Installation in Eurocopter AS350 Section 20 90 00 Dye 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 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
10. 05 RH LH ITEM NUMBER QTY QTY PART NUMBER DESCRIPTION MANUFACTURER 1 1 190 00792 03 SHELF INSTALLATION 1 1 190 00792 03 RH SHELF INSTALLATION 3 1 1 011 00868 20 GRS 77H AHRS GARMIN 4 1 1 115 00459 00 GRS 77 MOUNT RACK GARMIN 5 5 5 MS21075 3 NUTPLATE 6 10 10 MS20426AD3 3 RIVET 7 5 5 AN525 10R8 SCREW GRS 77H AHRS INSTALLATION EXPLODED VIEW OF INSTALLATION ON LH SHELF CABIN FLOOR NOT SHOWN FOR CLARITY REF EXISTING ROTORCRAFT STRUCTURE Figure 31 05 GRS 77H INSTALLATION LH EXPLODED VIEW SHOWN GRS 77H INSTALLATION RH EXPLODED VIEW OPPOSITE NOT SHOWN Reference Table 31 04 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 52 of 80 Table 31 05 Part List for Figure 31 06 NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 M81714 67 18 MOUNTING TRACK 2 REF M81714 60 22 05 TERMINAL BLOCK 3 2 AN525 10R7 SCREW 4 2 NAS1149F0332P WASHER 5 2 521042 3 NUT N TERMINAL BLOCK INSTALLATION gt EXPLODED VIEW CABIN FLOOR NOT SHOWN FOR CLARITY Figure 31 06 TERMINAL BLOCK INSTALLATION EXPLODED VIEW Reference Table 31 05 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 53 of 80 Table 31 06 Parts List f
11. 1 Un latch the Center lower belly access panel Disconnect the retaining straps that prevent the panel from falling to the floor 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 23 of 80 f GTP 59 OAT Probe Installation The GTP 59 OAT Probe is located on the existing belly panel between station 2437 and 2351 Figure 6 06 Figure 6 06 Access Removal and Installation 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 l
12. 1 loel NU Su3iV3ug VHd1V OF 5 VHdTV ve 91 UN g 117130 335 1915 Yd 9 a 8 Md IAA 6 s 6 NI 2 53 8 _ ig GND 174915 TU ry 8100 68 54 2 B E 88 ae 01508 1 6891 54 E 92 Z 2 2 pim U313HOI3N5VH N bb NWD L e LHM DOD FINGOW 91480 LHM Le 7 TBA 24 rao NY 73A NY L 05 JINON 513805 v 03 DINOD x ae 57 aaa 21 SISNOD FINGOW 9IJNO2 LG 96 wau 22 2 OND LN 7 Oz YAMOd IMDA s L Mod may x uoze Suny SUD 98 10 00 190 00792 12 1 Instructions for Continued Airworthiness Page 76 of 80 for the Garmin G500H Installation in Eurocopter AS350 GDU 6208 PFD MFD N GRS 77H AHRS A 14 ARINC 429 OUT 1 A 29 ARINC 429 OUT 1 B ARINC 429 IN1A 4 PY ARINC 429 IN1B 21 26 GPS 1 RS 232 OUT RS 232 OUT 1 27 11 GPS 1 9 232 IN 19 L RS 232IN1 1 RS232GND1 44 LE 41 SIGNAL GND w Mw z RS232OUT4 6 GPS 2RS 232 IN RS232GND4 47 E 35 SIGNAL GND GDC 74H ADC Za 26 ARINC 429 OUT 1 A 27 ARINC 429 OUT 1 A 741
13. 190 00792 11 GDU 620 SOFTWARE AND AIRSPEED SETTINGS 33 RADAR ALTIMETER INTERFACE REQUIRES G500H INSTALLATION WITH OPTION 02 SOFTWARE P6203 PIN 45 MUST BE CONFIGURED FOR RADAR ALTIMETER PUSH TO TEST FUNCTIONALITY SEE GARMIN DOCUMENT 190 00601 04 GDU 620 INSTALLATION MANUAL FOR CONFIGURATION PROCEDURES 34 REFERENCE GARMIN DOCUMENT 190 00792 11 GDU 620 SOFTWARE AND AIRSPEED SETTINGS SPECIFICATION FOR INFORMATION ON DIFFERENT SOFTWARE CONFIGURATIONS THE 02 SOFTWARE IS OPTIONAL BUT MUST BE INSTALLED FOR THE FOLLOWING OPTIONAL SYSTEM INTERFACES TO FUNCTION ARINC 429 RADAR ALTIMETERS ONLY a HONEYWELL KRA 405B P N 066 01153 XXXX b FREEFLIGHT RA 4500 P N 84560 X2 XXXX 98 10 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 72 of 80 OPTIONS 01 G500H WITHOUT RADAR ALTIMETER 02 G500H WITH RADAR ALTIMETER 010 00769 60 SD CARD GDU 6XX INSTALLER UNLOCK 010 00844 00 SD CARD G500H INSTALLER DOWNLOADABLE SW 006 B0223 H1 SOFTWARE VERSION 3 51 GRS77H 006 B0223 H0 SOFTWARE VERSION 3 50 577 006 B1071 30 SOFTWARE VERSION 5 00 GDU620 006 B1071 21 SOFTWARE VERSION 4 01 GDU620 011 00871 00 CONNECTOR KIT GMU44 011 01010 03 CONNECTOR KIT GDC74 011 00869 01 CONNECTOR KIT GRS77 011 01656 00 CONNECTOR KIT GDU620 GARMIN 7274 11 20 CIRCUIT BREAKER 20 AMP 7277 2 5 CIRCUIT
14. 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 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 ama Torques Maintenance Practice 05 20 10 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 13 of 80 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
15. 7 2 01 06310014 01 Instrument Panel 47 80 lbs STA 1120 WL 2066 BL 0 0 01 06310014 02 Instrument Panel 47 80 lbs STA 1120 WL 2066 BL 0 0 01 06310014 03 Instrument Panel 47 80 lbs STA 1120 WL 2066 BL 0 0 01 06310014 04 Instrument Panel 47 80 lbs STA 1120 WL 2066 BL 0 0 08 00 00 190 00792 12 Rev 1 Page 26 of 80 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 27 of 80 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 If alerts are present troubleshoot using Section 31 00 00 Troubleshooting b GDC 74H 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 Veri
16. 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 35 of 80 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 Remo
17. Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 36 of 80 8 5 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 other 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 contami
18. 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 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 Condition The state of an item or component compared to a known standard Standard specified rule or measure that is used to find the condition of a component Damage Physical deterioration of a component Inspection A procedure that includes checking inspecting and examining a system or component 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 Maintenance The servicing and or repair of a rotorcraft a system or a component that keeps it serviceable 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 Garmin Reference System GMU G
19. entry 5 Year Pre inspection UEM 1 Review Airworthiness Directives 5 Year Inspection pM 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 14 of 80 Table 5 04 10 2000 Flight Hour Inspection Registration 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 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 Acc
20. 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 aps Connect the connector to the unit ensuring that each jackscrew is secured Oriqinal GDC 74H is Reinstalled If the original GDC 74H is re installed then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process New Repaired or Exchange GDC 74H is Installed If a new repaired or exchange GDC 74H unit is installed then software must be loaded to the unit Refer to Section 5 4 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 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 cor
21. 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 00792 12 Rev 1 Page 66 of 80 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 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 the 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
22. the Garmin G500H Installation in Eurocopter AS350 Page 65 of 80 4 Troubleshooting guide Iferror 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 These are listed in the Table 31 12 Table 31 13 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 being 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
23. 0 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 7 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 24 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 Size Recommended in Ib m Fractional decimal 20 10 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 34 of 80 Section 20 30 00 Painting Maintenance Practices The following procedures should be used to touch up paint flaking scratches nicks and gouges Warning
24. 0H SYSTEM MUST NOT BE CONNECTED TO AN AVIONICS BUS WHEN INSTALLING THE G500H EFIS SYSTEM IN CONJUCTION WITH A GENEVA AVIATION P132 CONSOLE THE ADC AND AHRS CIRCUIT BREAKERS MAY BE CONNECTED TO EITHER THE 5 PP6 OR PP9 BUS AS ALLOWED BY AN ELECTRICAL LOAD ANALYSIS OF THAT BUS SEE DETAIL A FOR LAYOUT OF TERMINAL BLOCK ITEM 1 IN THE BOM SEE DETAIL C FOR LAYOUT OF TERMINAL BLOCK ITEM 6 GPS 2 IS AN OPTIONAL CONNECTION DO NOT CONNECT IF ONLY ONE GPS IS USED IN THE INSTALLATION Ads THE NAV 1 AND NAV 2 CONNECTIONS MAY BOTH BE ARINC 429 OR ONE ARINC 429 AND ONE RS232 CONNECTION CONNECTIONS MUST ONLY MADE TO AUTHORIZED NAV UNITS REFER TO APPENDIX C 2 OF 190 01150 06 G500H ROTORCRAFT STC INSTALLATION MANUAL FOR ACCEPTABLE NAV UNITS AND FIGURE D 5 IN APPENDIX D FOR CONNECTIONS ONLY APPROVED GPS WAAS UNITS LISTED IN APPENDIX C 1 MAY BE USED REFER TO FIGURE D 4 IN APPENDIX D FOR CONNECTIONS AX THE NAV 2 CONNECTION IS OPTIONAL DO NOT CONNECT IF ONLY ONE NAV IS USED IN THE INSTALLATION A THE RS 232 5 NAV INPUTS MAY BE CONFIGURED AS NAV 1 OR NAV 2 NOT BOTH REFER TO THE G500H INSTALLATION MANUAL FOR CONFIGURATION ON THE GDU 620 A IF THE HSVT TERRAIN FEATURE IN THE GDU 620 IS ENABLED THE AUDIO INPUT OF THE AUDIO PANEL MUST UNSWITCHED 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 G500H INSTALLATION MANUAL APPENDIX E TRAFFIC SYSTEM I
25. 1 PIN 7 TO BE CONNECTED TO AIRCRAFT WEIGHT ON WHEELS OR COLLECTIVE SWITCH CONNECT SO THAT WHEN AIRCRAFT ON GROUND A A GROUND IS PRESENT ON PIN 7 A CONFIGURATION MODULES ARE MOUNTED IN 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 P771 OR P741 FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER AS350 WIRING DIAGRAM MANUAL CHAPTER 24 FOR FURTHER WIRING INFORMATION REFERENCE EUROCOPTER 45350 INSTRUMENT AND CONSOLE LIGHTING WIRING DIAGRAM CHAPTER 33 THE SPLICE MUST INSIDE OF THE CONNECTOR BACKSHELL 620 GRS 77H AND GDC 74H CONNECT SHIELD GROUNDS THE CONNECTOR BACKSHELL THE SHIELD LEADS MUST LESS THAN 3 INCHES DO NOT DAISY A REFER TO P132 GENEVA AVIATION CONSOLE INSTALLATION FOR FURTHER WIRING INFORMATION WIRE NOT TO BE LONGER THAN 8 INCHES A EFIS BUS CIRCUIT BREAKERS LOCATED ON OR BELOW PILOTS INSTRUMENT PANEL WITHIN REACH OF PILOT LABEL CIRCUIT BREAKERS AS SHOWN A INSTALLATION OF THE GMU 44 MAGNETOMETER REQUIRES A COMPLETE SURVEY OF THE PROPOSED MAGNETOMETER LOCATION FOR MAGNETIC INTERFERENCE SURVEY INSTRUCTIONS REFER TO THE GARMIN G500H ROTORCRAFT STC INSTALLATION MANUAL 190 01150 06 REVISION 2 OR LATER FAA APPROVED REVISION FOR THE 5350 STC 32 FOR PROGRAMMING DISPLAYED AIRSPEED MARKINGS ON GDU 620 PFD MFD REFER TO GARMIN DOCUMENT
26. 4 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 34 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 33 of 80 Table 20 02 Recommended Torque Values for Coarse Thread Fasteners Thread Size Shear Tension Fractional decimal Recommended Maximum Recommended Maximum in Ib N 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 10
27. 70AD4 4 RIVET SOLID UNIVERSAL HEAD 5 A R MIL S 8802 SEALING COMPOUND TEMPERATURE RESISTANT HIGH ADHESION 6 3 211 60037 08 SCREW MACHINE PAN HEAD GARMIN CROSS RECESSED BRASS 0 1380 32 2 7 1 115 00481 10 RACK INSTALL MODIFIED GMU 44 GARMIN 8 1 011 00870 10 GMU 44 MAGNETOMETER GARMIN Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 31 00 00 190 00792 12 Rev 1 Page 46 of 80 qai GMU 44 INSTALLATION ISOMETRIC VIEW EXPLODED FOR CLARITY Figure 31 01 GMU 44 MAGNETOMETER INSTALLATION EXPLODED VIEW Reference Table 31 01 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 47 of 80 Table 31 02 Part Lists for Figures 31 02 31 03 ITEM RH LH NUMBER PART NUMBER DESCRIPTION MANUFACTURER 1 1 115 01757 00 BRACKET SUPPORT AFT LH SHELF GARMIN FAA PMA EUROCOPTER AS350 2 2 115 01755 00 BRACKET SUPPORT RH SHELF FAA GARMIN PMA EUROCOPTER AS350 3 1 115 01756 00 BRACKET SUPPORT FWD LH SHELF GARMIN FAA PMA EUROCOPTER AS350 4 1 115 01758 00 SHELF 5 1 115 01759 00 SHELF 6 8 8 AN3 3A BOLT 7 8 8 AN3 4A BOLT 8 8 8 MS21042 3 NUT 9 24 24 NAS1149F0332P WASHER 10 8 8 521075 3 NUTPLATE 11 16 16 MS20426AD3 3 RIVET 12 1 NAS43DD3 24 SPACE
28. 98 10 00 for the Garmin G500H Installation in Eurocopter AS350 Instructions for Continued Airworthiness 2000 TINON 913400 9I IND2 SHN03 INGO LYO IH 390 LYO WMOd LYO 1EINOd 1 NYOMIV TOBANOd 14 VT LNO INR 8T LNO INI 249 ST NI ONT VT NI ONT QINTIOHO 3RL3PIOLANDVII LNO ELL3VIDLINOVIN 2100 262 54 ST NI VENI 59 54 2000 TININ 91300 91400 SHN02 SINGON 9HNO2 HAOd LWYD IND L NY T2HAOd LANDAY H ny e LH 73A L W L 12 U PAS ES T 3ndOW SINO2 EIR es E TN d bd 8 4 are bot a 8 l 66 di9 MU UN gt TU p 99 225 d T 4 5 20 Us 2274 1 beste ee picem ES FLCELO ANY SZZEZ0 GOW 1509 FLCELO ANY SZZEZ0 GOW 1SOd
29. BREAKER 5 AMP KLIXON SWT316 SPIRAL WRAP TEFLON 3 16 IN DALLAS AVIONICS 1N 4006 DIODE M81714 60 22 01 TERMINAL BLOCK B 040 22 N CABLE TERMINATION RG U 179 TYCO ELECTRONICS RG 179 COAXIAL CABLE 75 OHM MIL C 17 094G 392404 ETHERNET CABLE ECS M81714 67 18 TERMINAL BLOCK RAIL N Q s O O M81714 60 22 05 TERMINAL BLOCK PART NUMBER DESCRIPTION 98 10 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 MANUFACTURER 190 00792 12 Rev 1 Page 73 of 80 DETAIL DETAIL 81714 60 22 05 81714 60 22 01 DETAIL D INSTRUMENT DIMMING OPTIONS ros Rb Eo EXISTING 4 28 VDC LIGHTING CUT He u 7 SHEET 3 mE A A AVAILABLE PIN OR 2171 LIGHTING POWER UNIT I 075359 EXISTING oy re I CUTPL2M ee E 1 EELS AVAILABLE PIN Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 74 of 80 DETAIL B N wE A m I I I 1 A PRE MOD 073273 AND 073274 N 30 ALPHA BREAKERS PANEL G12132 11 04 OR Page 75 of 80 190 00792 12 Rev 1
30. E 7 36 MS20426AD3 4 RIVET INSTRUMENT PANEL ASSEMBLY OPTION 2 FAA PMA EUROCOPTER AS350 REFERENCE 011 02764 02 FOR BILL OF MATERIAL Figure 31 14 OPTION 2 INSTRUMENT PANEL ASSEMBLY Reference Table 31 09 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 62 of 80 Table 31 10 Parts List for Figure 31 15 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 115 01760 03 OPTION 3 INSTRUMENT PANEL GARMIN 2 1 161 02779 03 FAA PMA LABEL GARMIN 3 4 MS21061L08 NUTPLATE 4 6 MS21069 08 NUTPLATE 5 6 MS21071 06 NUTPLATE 6 2 MS21075 08 NUTPLATE 7 36 MS20426AD3 4 RIVET 2 1 1 1 4 6 6 4 2 5 ae g S 0 No 2 5 d i 6 lt s C N A vel Bc sb 1 ote 0 0 i amp m 0 0 0 L f D EB i Ux 2 rt ii SN ug 0 a rss 78 0 INSTRUMENT PANEL ASSEMBLY OPTION 3 FAA PMA EUROCOPTER 5350 REFERENCE 011 02764 03 FOR BILL OF MATERIAL 0 Figure 31 15 3 INSTRUMENT PANEL ASSEMBLY Reference Table 31 10 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 63 of 80 Table 31 11 Parts List for Figure 31 16 ITEM NUMBER QUANTITY PART NUMBER DESCRIPT
31. EW Figure 31 08 INSTRUMENT PANEL INSTALLATION Reference Table 31 07 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 ANEL IONS 190 00792 12 Rev 1 Page 56 of 80 i REF 211 64412 12 SCREW QTY 6 PART OF K10 00133 00 G500H INSTALLATION INSTRUMENT PANEL INSTALLATION OPTION 1 EUROCOPTER AS350 Figure 31 09 ITEM 1 INSTRUMENT PANEL INSTALLATION Reference Table 31 07 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 57 of 80 REF 211 64412 12 SCREW QTY 6 26 24 19 19 24 20 PART OF K10 00133 00 G500H INSTALLATION SALA INSTRUMENT PANEL INSTALLATION OPTION 2 EUROCOPTER AS350 Figure 31 10 ITEM 2 INSTRUMENT PANEL INSTALLATION Reference Table 31 07 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 58 of 80 SM LT ih REF 211 64412 12 SCREW QTY 6 PART OF K10 00133 00 G500H INSTALLATION KIT INSTRUMENT PANEL INSTALLATION OPTION 3 EUROCOPTER AS350 Figure 31 11 ITEM 3 INSTRUMENT PANEL INSTALLATION Reference Table 31 07 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 59 of 80 n in
32. Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 70 of 80 CHAPTER 98 Section 98 00 00 Wiring Diagrams Pitot Static System Schematics This chapter includes the Wiring Diagrams and Pitot Static System Schematics for the G500H Flight Display System 98 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 71 of 80 Section 98 10 00 Wiring Diagrams G500H EFIS System Wiring NOTES 1 IS 22759 16 UNSHIELDED HIGH WIRE IS 22759 8 TWISTED SHIELDED WIRES ARE M27500 XX TGXT14 INDICATES AWG X NUMBER NDUCTORS 2 WIRE LEGEND NEW WIRE b EXISTING WIRE ALL WIRES ARE 22 AWG EXCEPT WHERE NOTED OTHERWISE ALL SPLICES ARE MIL S 81824 1 X THE LENGTH OF SHIELD GROUNDS MUST NOT EXCEED 3 INCHES GROUND DESIGNATIONS ARE D SHIELD BLOCK GROUND AIRFRAME GROUND 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 M T C RG 179 IS MIL C 17 094G THE G500H ELECTRICAL BUSSING DEPICTED ARE TYPICAL INSTALLATIONS ACTUAL INSTALLATION MAY VARY THE REQUIRED G500H EQUIPMENT PFD ADC AND AHRS MUST BE CONNECTED TO A BUS THAT RECEIVES POWER AS SOON AS THE BATTERY MASTER SWITCH IS TURNED ON ALL REQUIRED G500H EQUIPMENT MUST BE CONNECTED TO THE SAME BUS THE G50
33. HRS 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 the G500H system unit power up self test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display Whenever removing or installing units remove power from the LRU by removing aircraft power or opening the LRU circuit breaker 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 41 of 80 GMU 44 Magnetometer Removal and Installation 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 Lower the GMU 44 into the rack and secure the plate with the three Phillips screws Original GMU 44 is Reinstalled If the original GMU 44 was
34. ION MANUFACTURER 1 1 115 01760 04 OPTION 4 INSTRUMENT PANEL GARMIN 2 1 161 02779 04 FAA PMA LABEL GARMIN 3 4 MS21061L08 NUTPLATE 4 6 MS21069 08 NUTPLATE 5 6 MS21071 06 NUTPLATE 6 2 MS21075 08 NUTPLATE 7 36 MS20426AD3 4 RIVET INSTRUMENT PANEL ASSEMBLY OPTION 4 FAA PMA EUROCOPTER AS350 REFERENCE 011 02764 04 FOR BILL OF MATERIAL Figure 31 16 OPTION 4 INSTRUMENT PANEL ASSEMBLY Reference Table 31 11 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 64 of 80 Table 31 12 List of Consumable Materials DESCRIPTION P N VENDOR SPECIFICATION THREAD LOCK 242 LOCTITE ADHESIVE 1300L 3M cloth Low Lint Commercial 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 m Dye Penetrant Kit Acetone ASTM D329 Isopropyl Alcohol TT I 735 richloroethane MIL T 81533 Nylon Scouring Pad 3M Scotchbrite 63 3M 240 Grit Sandpaper Commercial B20 Grit Sandpaper Commercial 240 Grit Aluminum Oxide Abrasive Cloth Sealant MIL S 8802 Adhesive transfer tape 950 2 70 0060 3057 4 3M 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for
35. 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 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 12 of 80 59 OAT Probe Installation 1 Access 59 Probe reference Section 6 00 00 Dimensions and Access Inspect 59 OAT and mount for physical damage cracks and corrosion Treat and repair corrosion as required in Section 20
36. Inspection Table 5 01 specifies the requirements of the 90 day inspection b 1Year 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 specifies the requirements of the 1 year annual inspection 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 specifies 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 9 of 80 discrepancies missed It is important to have adequate lighting for all phases of the inspection The special tools necessary
37. Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 Garmin Ltd Or its subsidiaries c o Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Dwg Number 190 00792 12 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 2 4 2014 Initial release Note Document was RSG P N 16E06310001 Rev A Table of Contents Section 01 00 00 IntroducHon n ua um 4 CHAPTER 4 5 Section 04 00 00 Airworthiness Limitations 5 CHAPTER 5 6 Section 05 00 00 Continued Airworthiness Inspections 2 2 2 1 6 Section 05 20 10 Continued Airworthiness Scheduled Inspections 9 Section 05 20 20 Continued Airworthiness Special Inspections 22 17 CHAPTER 6 19 Section 06 00 00 Dimensions and Access_ uuu tea Eas Ex Rec 19 CHAPTER 8 26 8 00 00 Weight and Balance Information
38. 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 10 FAN 2 FAIL Fan 2 has reported 0 RPM when it Inspect the GDU fan for an obstruction was powered with a PWM duty Contact Garmin Technical Support cycle higher than or equal to 10 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 68 of 80 Alert Text 1 GDL69 CONFIG The GDL 69 configuration With the pe 620 in to the GDL 69 page the page information stored inthe GDL69 1 that the SET and ACTIVE and the GDU 620 configuration configuration settings are the same If module do not match not use the SET gt ACTV soft key to copy the configuration settings from the GDU 620 into the GDL 69 The GDL 69 configuration was Update the GDL 69 configuration using the GDU 620 updated using another LRU e g the GMX 200 or 400W 500W GDU CONFIG This error appears whenever the Cycle power to the GDU This error GDU is replaced with a GDU that automatically clears on the second power 4 with different configuration module was configured for different installation Error in the configuration of the GDU 620 GDU 1 2 COOLING Speci
39. OF 20059 UNION IS RENAISSANCE MACHINE LP 3600 NOBLE FORTH AVENUE WORTM TX 76111 PHONE NO 817 759 2122 98 20 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 EUROCOPTER MANUFACTURER 190 00792 12 Rev 1 Page 80 of 80
40. R 13 2 521266 1 Instructions for Continued Airworthiness 31 00 00 for the Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 48 of 80 SHELF INSTALLATION EXPLODED VIEW Figure 31 02 RH SHELF INSTALLATION Reference Table 31 02 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 49 of 80 SHELF INSTALLATION EXPLODED VIEW Figure 31 03 LH SHELF INSTALLATION Reference Table 31 02 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 50 of 80 ep Table 31 03 Parts List for Figure 31 04 RH LH ITEM NUMBER DESCRIPTION MANUFACTURER 1 1 190 00792 03 LH SHELF INSTALLATION GARMIN 2 1 190 00792 03 RH SHELF INSTALLATION GARMIN 3 1 1 011 00882 11 GDC 74H ADC GARMIN 4 4 4 MS21075 3 NUTPLATE 5 8 8 MS20426AD3 3 RIVET 6 4 4 AN525 10R8 SCREW REF EXISTING ROTORCRAFT STRUCTURE Figure 31 04 GDC 74H INSTALLATION LH EXPLODED VIEW SHOWN GDC 74H INSTALLATION RH EXPLODED VIEW OPPOSITE NOT SHOWN Reference Table 31 03 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 51 of 80 Table 31 04 Parts List for Figure 31
41. REF REF REF REF 704447723068 ANNUNCIATOR PANEL EUROCOPTER 9 REF REF EXISTING 3 IN NR TACHOMETER 10 REF REF 4 0118 01 3 EYEBROW LIGHT EUROCOPTER 11 REF REF EXISTING 3 IN AIRSPEED INDICATOR 12 REF EXISTING 3 IN ALTIMETER INDICATOR 13 REF REF 3A43 22 35F 28 1 FU 2 IN ALTIMETER COUNTER DRUM THOMMEN POINTER 14 REF REF MD25 200 2 IN AIRSPEED INDICATOR MID CONTINENT 15 REF REF EXISTING 2 IN NR TACHOMETER 16 REF 5 67 0159 20 2 IN EYEBROW LIGHT EUROCOPTER 17 REF REF 71450B23 LED POST LIGHT EUROCOPTER 18 13 6 15 535214 29 SCREW 19 P EE 535214 31 SCREW 20 535214 33 SCREW 21 6 161616 535214 44 SCREW 22 NAS1149DN632P WASHER 23 6 6 6 6 NAS1149DN832P WASHER 24 15 11 13 9 NAS620 6L WASHER 25 7 E qm MS33737 14C NUT 26 ZEE GE 5 533737 16 27 REF REF REF REF LED 40 17 HE EOG3T VIVISUN LED SWITCH AEROSPACE OPTICS Reference Table 31 08 through 31 11 and Figures 31 13 through 31 16 31 00 00 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 190 00792 12 Rev 1 Page 55 of 80 REF EXISTING INSTRUMENT PANEL GLARE SHIELD REF EXISTING INSTRUMENT PANEL SUPPORT STRUCTURE emenond ML X COMMON EQUIPMENT INSTALLATION T P ALL INSTRUMEN EXPLODED VI
42. Review 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 11 of 80 2 Conduct visual inspection of wires backshells and connectors look
43. S OPTIONAL DO CONNECT IF TRAFFIC SYSTEM IS INCLUDED THE INSTALLATION ALL WIRES REQUIRED FOR EVERY TRAFFIC SYSTEM ONLY CONNECT THOSE WIRES REQUIRED BY THE INSTALLATION REFER TO THE G500H INSTALLATION MANUAL APPENDIX E AX SERIAL ALTITUDE OUT IS OPTIONAL DO NOT CONNECT IF NOT REQUIRED FOR THE INSTALLATION RS 232 DATA IS SHADIN ALTITUDE 9600 BAUD POST MOD 073273 AND 073274 EFIS BUS CIRCUIT BREAKERS LOCATED ON RIGHT HAND SIDE OF THE PEDESTAL THE 44 ALPHA PANEL WIRE LONGER THAN 8 INCHES LABEL CIRCUIT BREAKERS AS SHOWN Ar PRE MOD 073273 AND 073274 EFIS MASTER CIRCUIT BREAKER LOCATED ON LEFT HAND SIDE OF 30 ALPHA SWITCH PANEL WIRE NOT TO BE LONGER THAN 8 INCHES THE GDL 69 69A IS OPTIONAL CONNECTION DO CONNECT IF INCLUDED IN THE INSTALLATION Ad THE GSR 56 IS AN OPTIONAL CONNECTION DO NOT CONNECT IF NOT INCLUDED IN THE INSTALLATION A USE ONLY AIRCRAFT GRADE CATEGORY 5 ETHERNET CABLE SUCH AS P N 392404 FROM ELECTRONIC CABLE SPECIALIST OR P N E10424 FROM PIC WIRE AND CABLE A 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 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 AS350 STC A AIR GROUND STATUS GDU 620 P620
44. armin Magnetometer Unit GDU Garmin Display Unit 05 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 7 of 80 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 AS350 190 00792 12 Rev 1 Page 8 of 80 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 The 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 regardless of hours of operation
45. cated underneath the cabin floor between station 1790 2325 on the left or right side of the aircraft depending on aircraft configuration Figure 6 03 Figure 6 03 Access Removal and Installation Methods i Removal 1 Un screw the Center lower belly access panel Disconnect the retaining straps that prevent the panel from falling to the floor 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 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 21 of 80 d Shelf Installation The shelf installation is located underneath the cabin floor between station 1790 and 2325 on the left or right side of the aircraft dependin
46. e 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 metallic structure Verify that the resistance is less than 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 ensure 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 16 of 80 Section 05 20 20 Continued Airworthiness Special Inspections 1 General Th
47. ess 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 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 15 of 80 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 Referenc
48. fic GDU has poor cooling and Ensure fans on indicated GDU are functioning power usage is being reduced Ensure fans on indicated GDU are not obstructed GDU 1 2 DB ERR Error in specific database where Verify the correct card is installed reload GDU 1 2 DB denotes specific the DB on the card database GDU 1 2 VOLTAGE GDU supply voltage is below 12 Increase the voltage above 12VDC VDC 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 GPS 1 2 PPS Failure This alert will be set if the PPS Ensure GPS 1 2 is turned on signal has not been received in more than 5 sec If the unit is Verify 1PPS wiring from the GPS to the configured for dual GPSs then the GDU 620 side will be specified in the error configured and operating occurred GMU 44 Verify wiring to GMU 44 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 69 of 80 Alert Text Case 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 manife
49. for 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 05 20 10 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 10 of 80 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
50. fy 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 28 of 80 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 Cal
51. g on aircraft configuration Figure 6 04 Figure 6 04 Access Removal and Installation 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 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 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 22 of 80 Terminal Block Installation Terminal Block is located underneath the cabin floor between station 1120 and 1502 on the left side of the aircraft Figure 6 05 Terminal Block Figure 6 05 Access Removal and Installation Methods i Removal
52. ibration 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 00792 12 Rev 1 Page 29 of 80 Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 30 of 80 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 2
53. ing 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 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
54. is 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 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 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 in
55. isconnect 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 removed 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 25 of 80 Section 8 00 00 Weight Balance Information CHAPTER 8 Installation Description Weight CG Location 01E06310002 01 GMU 44 Magnetometer 0 70 Ibs 1215 WL 2225 BL 0 0 01 06310003 01 Shelf 2 20165 STA 2042 WL 2781 600 7 01 06310003 02 Shelf 2 20165 STA 2042 WL 2781 BL 600 7 01 06310004 01 GDC 74H 1 92 165 STA 2003 WL 2745 BL 662 0 01 06310004 02 GDC 74H 1 92 165 STA 2003 WL 2745 BL 662 0 01 06310005 01 GRS 77H AHRS 3 46 Ibs STA 2019 WL 2748 BL 572 0 01 06310005 02 GRS 77H AHRS 3 46 Ibs STA 2019 WL 2748 BL 572 0 01 06310008 01 Terminal Block 0 47 Ibs STA 1265 WL 2659 BL 612 2 01E06310009 01 GTP 59 OAT Probe 0 08 5 STA 2386 WL 2910 BL
56. 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 replaced 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 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 45 of 80 3 Illustrated Parts List This section contains information on parts for the GSOOH 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 01568 00 BRACKET MOUNTING GMU 44 GARMIN FAA PMA EUROCOPTER 5350 2 1 115 01569 00 BRACKET SUPPORT GMU 44 FAA GARMIN PMA EUROCOPTER AS350 3 6 MS20426AD5 5 RIVET SOLID COUNTERSUNK 100 DEG PRECISSION HEAD 5 32 IN OD 5 16 IN LONG 4 16 MS204
57. nates 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 37 of 80 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 treatment 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 p
58. ness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 3 of 80 1 Section 01 00 00 Introduction These are accepted Instructions for Continued Airworthiness for modifications performed in accordance with Eurocopter AS350 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 AS350 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 4 of 80 4 Section 04 00 00 Airworthiness Limitati
59. 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 ifthe 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 typical magnetic anomalies even with a good GPS signal 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 67 of 80 Table 31 14 GDU 620 Alert Troubleshooting Guide AHRS1 GPS AHRS 1 using AHRS i
60. ons 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 88 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 5 of 80 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 G500H Installation requires 90 Day Inspection that must be performed 90 days after installation and then afterwards within 90 days of the last G500H 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 year 12 month
61. or Figure 31 07 ITEM NUMBER QUANTITY PART NUMBER DESCRIPTION MANUFACTURER 1 1 011 00978 00 GTP 59 OAT PROBE GARMIN 2 1 115 01567 00 DOUBLER GARMIN 3 8 CR3213 4 03 RIVET CHERRYMAX 4 A R MIL S 8802 SEALING COMPOUND REF EXISTING OAT PROBE INSTALLATION TYP 2 PLACES EXISTING ROTORCRAFT STRUCTURE REF 212 00026 00 WASHER PART OF 011 00978 00 GTP 590AT PROBE SUB SSEMBLY GTP 59 OAT PROBE INSTALLATION EXPLODED VIEW CABIN FLOOR NOT SHOWN FOR CLARITY REF 210 00055 00 NUT PART OF 011 00978 00 GTP 59 OAT PROBE SUB ASSEMBLY Figure 31 07 GTP 59 OAT PROBE INSTALLATON EXPLODED VIEW Reference Table 31 06 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 54 of 80 Table 31 07 Parts List for Figures 31 08 through 31 12 ITEM QUANTITY sms esc na PART NUMBER DESCRIPTION MANUFACTURER 1 1 c 011 02764 01 INSTRUMENT PANEL ASSEMBLY GARMIN OPTION 1 2 011 02764 02 INSTRUMENT PANEL ASSEMBLY GARMIN OPTION 2 3 e 011 02764 03 INSTRUMENT PANEL ASSEMBLY GARMIN OPTION 3 4 e ree 011 02764 04 INSTRUMENT PANEL ASSEMBLY GARMIN OPTION 4 5 1 1 1 a 011 01264 60 GDU 620 PFD MFD GARMIN 6 REF REF REF REF 5956 28 01 REV A DIMMING CONTROL OVERLAY AERO DYNAMIX 7 1 1 1 1 3500 01 V E M D 8
62. ove 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 2 Connect the rear connectors ensuring that each slidelock is secured on both sides 3 Setthe GDU 620 into place 31 00 00 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 44 of 80 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
63. ower 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 any other 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 24 of 80 g GDU 620 Installation The GDU 620 is located in the right 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 GDU 620 00 00000000 e Figure 6 07 Access Removal and Installation 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 d
64. rect 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 43 of 80 3 Visually inspect the connectors to ensure there are bent or damaged pins Repair any damage 4 Connect the connector to the GRS 77H ensuring that each slidelock is secured on both sides Original GRS 77H is Reinstalled If the original GRS 77H is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Reference 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 Rem
65. 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 500 STC Installation Manual for the GRS 77H GMU 44 Magnetic Calibration New Repaired or Exchange GMU 44 is Installed If a new repaired or exchange GMU 44 unit is installed then software must be loaded and the GRS 77H GMU 44 Magnetic Calibration must be performed Refer to Section 5 of the G500H STC Installation Manual for instructions on software loading 5 4 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 42 of 80 4 Carefully remove the unit from its mounting location
66. roper 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 38 of 80 Section 20 50 00 Mechanical Fastener Sealing Methods Seal mechanical fasteners as shown using the following 1 20 01 01 310 Use of Sealing Compounds 2 MCT 20 05 01 Sealing 0 12 IN 7 0 12 IN 3 05mm N 3 05mm MINIMUM MINIMUM Z BOLT HEAD 0 06 IN 0 06 0 12 1 5mm NUT AND THREAD 1 5mm 3 05mm HA f j 1 1 5 he MINIMUN T MINIMUM i SS E 59
67. s 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 G5OOH 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 6 of 80 G500H Installation has Post Lightning
68. s 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 receiving 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 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 operating in exclusively no l information GPS mode 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 not receiving input from GTP 59 OAT probe Verify wiring is correct ARINC 429 connection from GDC 74H to GRS 77H is not working Verify wiring is correct 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
69. spection 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 17 of 80 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 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 Inspection 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 eee 22222 Ld 1 Verify that the OAT is displayed on the GDU 620 PFD normally 05 20 20 Instructions for Continued Airworthiness 190 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 18 of 80 CHAPTER 6 Section 06 00 00 Dimensions Acce
70. ss 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 tailboom between TB 868 and 1578 Figure 6 01 Yi ss lt fof a a emt TB Se 1578 868 REF REF Figure 6 01 Access Removal and Installation Methods i Removal 1 Un latch and open the baggage compartment door the left side of the aircraft 2 Remove the tail boom closeout panel by loosening the 74 turn fasteners that hold it in place 3 Ifan air conditioner is installed it may be necessary to remove the air conditioner unit to gain access to the magnetometer Consult the manufacturers Installation and removal instructions for proper removal of unit ii Installation 1 Re install air conditioner if removed to gain access to the magnetometer Consult the manufacturers Installation and Removal instructions for proper installation of unit 2 Re install tail boom closeout panel by tightening the turn fasteners that hold it in place 3 Close the baggage compartment door 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 00792 12 Re
71. st 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 A 30 arc second terrain database is being used Update the Supplemental Data card with the 9 arc second terrain database SW MISMATCH GDU software version strings do not match Verify the correct SW is loaded 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 51 lost HSI defaulted to GPS2 TRK TRK TRAFFIC Heading Lost Traffic is now based See HDG errors on track 31 00 00 Instructions for Continued Airworthiness for the
72. v 1 for the Garmin G500H Installation in Eurocopter AS350 Page 19 of 80 b GDC 74H Air Data Computer GDC 74H is located underneath the cabin floor between station 1790 and 2325 on the left or right side of the aircraft depending on aircraft configuration Figure 6 02 Figure 6 02 Access Removal and Installation 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 00792 12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 20 of 80 577 5 GRS 77H is lo
73. val 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 abrasive 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

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