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Garmin Software Version 0858.09 Instruction Manual

1. NOTE It may be necessary to temporarily disable or move away from GPS repeaters while testing as repeaters may adversely affect GPS receiver performance 6 VHF COM Interference Test This test must be conducted outside Use of a GPS repeater inside a hangar may result in a failed test This procedure assumes that the system is currently set to 25 kHz COM channel spacing Once the signal acquisition test has been completed successfully perform the following steps a On the MFD monitor GPS signal strength bars on the AUX GPS STATUS page b On the PFD ensure that the CDI is set to GPS If it is not press the CDI softkey until GPS ENR is displayed c Verify that the GPS INTEC flag is out of view d Select 121 150 MHz on the No 1 COM transceiver Page 8 6 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 e Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels f During the transmit period verify that the GPS INTEC flag does not come into view on the PFD and verify that GPS 1 does not lose a 3 D navigation solution on the MFD g Repeat steps e and f and re transmit while monitoring GPS 2 signal levels on the MFD h Repeat steps d through g for each of the following frequencies 121 175 MHz 121 200 MHz 131 250 MHz 131 275 MHz 131 300 MHz i Repeat steps d through h for the No 2 COM transceiver GIA2 j On the MFD
2. turn fasteners clockwise to lock the display unit to the instrument panel 6 If display is new perform software loading and configuration of display in accordance with the steps beginning in Section 3 7 1 7 If display is existing proceed to Section 8 1 for display checkout Page 6 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 6 6 GMU 44 Removal amp Replacement Removal 1 Make sure all airplane electrical power is disconnected 2 Remove the square access panel left wing top 3 Unscrew the three screws that hold the GMU 44 to its mounting rack 4 Carefully lift the GMU 44 from its mounting rack 5 Disconnect the airplane harness connector from the GMU 44 electrical connector 6 Place protective caps on the GMU 44 connector and on the harness connector 7 Remove the unit from the airplane Reinstallation 1 Remove the protective caps from the GMU 44 electrical connector and its associated airplane harness connector Visually inspect the electrical connectors to make sure there are no bent or damaged pins Repair any damage 2 Connect the airplane harness connector to the GMU 44 electrical connector 3 Lower the GMU 44 into the locator pins on the mounting rack Make sure the GMU 44 direction arrow aligns with the mounting rack direction arrow CAUTION It is recommended that new screws are used to secure the GMU 44 to the mounting rack If the original screws must be re use
3. select the AUX SYSTEM SETUP page k Under the COM CONFIG field change the COM channel spacing from 25 kHz to 8 33 kHz Go back to the AUX GPS STATUS page m Select 121 185 MHz on the No 1 COM transceiver n Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels o During the transmit period verify that the GPS INTEG flag does not come into view on the PFD and verify that GPS 1 does not lose a 3 D navigation solution on the MFD p Repeat steps n and o and re transmit while monitoring GPS 2 signal levels on the MFD q Repeat steps n through p for each of the following frequencies 121 190 MHz 130 285 MHz e 131 290 Mhz r Repeat steps n through q for the No 2 COM transceiver GIA2 s On the MFD select the AUX SYSTEM SETUP page and change the COM channel spacing back to 25 kHz Continue to the VOR LOC GS Test G1000 System Maintenance Manual Hawker Beechcraft G36 Page 8 7 190 01259 00 Rev 5 VOR LOC GS Test Check the VOR ILS and Glideslope functions with ramp test equipment Operate the equipment according to the test equipment manufacturer s instructions Adjust the RF signal to a level adequate to perform the test Select the appropriate HSI source by using the CDI softkey NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned GFC 700 VOR LOC GS Test a Simulate a VOR signal on radial 000 with a
4. 00 3 7 4 GRC 10 configuration Optional For installations with the optional GRT 10 GRC 10 wireless remote system the GRC 10 must be configured to communicate with the specific GRT 10 that is installed in the aircraft To configure the RF Pairing ID of the GRC 10 NOTE GRT 10 serial number is required for installation Serial number is located on the bottom of the unit a Insert two AA batteries in GRC 10 b On the GRC 10 press any key to power the remote c When the GRT 10 not found message is displayed on the GRC 10 press the following buttons in order UP DOWN LEFT RIGHT MINUS PLUS PSET d Use the arrow buttons on the GRC 10 to enter the serial number of the GRT 10 transceiver that is installed in the aircraft Verify that the correct GRT 10 transceiver serial number has been entered e Press the XM button to store the GRT 10 serial number G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 15 190 01259 00 Rev 5 3 8 Software Load Confirmation Go to the Systems Status page Activate the cursor and toggle to the LRU window Highlight each of the following items in the LRU window and verify that the LRU software part number and software version matches the following information NOTE Verify the software and version levels for the items listed below a Highlight each of the following items in the LRU window by scrolling with the small FMS knob and verify that the softwa
5. 00 136 975 136 888 com Hau 108 10 136 975 COM2 HDG NO COMP ROL NO COMP PIT NO COMP IAS NO COMP SENNA ALT NO COMP 12200 12100 cu F 12000 11909 11800 EES GS OKT TAS__ OKT EE GND_R LOL 09 52 35 A ALERTS NOTE Screenshots are for reference only and may not be indicative of what is present on the actual aircraft display f Installation is complete Be sure to keep the SVS Pathways enable card with the aircraft for future use G1000 System Maintenance Manual Hawker Beechcraft G36 Page 8 5 190 01259 00 Rev 5 8 2 GIA 63W Integrated Avionics Unit GPS Signal Acquisition nav1 109 08 gt 108 00 136 97 108 15 136 97 SATELLITE STATUS 4 GPS_STATUS EPU ACTIVE GPS HDOP HFOM GPS SOLUTION VFOM 5 E POSITION RAIM PREDICTION WAYPOINT ARV TIME ARV DATE TIME ALTITUDE GROUND SPEED TRACK OIL TEMP GPS SIGNAL STRENGTH RK OIL PRES 8 ALT LOAD H kan Fc BUS VOLTS Ch a FUEL QTY GAL es d ENGINE A Figure 8 7 AUX GPS STATUS Page MFD The GIA 63W units should normally acquire a GPS navigation solution within 5 to 10 minutes of startup provided the aircraft is outside or indoors with a GPS repeater Select the GPS STATUS page on the MFD 4th page in AUX group Two softkeys on the bottom of the display allow the user to toggle between GPS 1 and GPS 2 Verify that both receivers show 3D DIFF NAV on the MFD Continue to the VHF COM Interference test
6. Beechcraft G36 Rev 5 190 01259 00 3 7 2 Base Configuration and Software Upload a Ensure loader card is inserted into top card slot of PFD On PFD select the System Upload page using the PFD small FMS knob b Activate the cursor and rotate the PFD small FMS knob to highlight BEECHCRAFT G36 in the AIRFRAME field Press the PFD ENT key to select the configuration c Once an airframe type is selected the cursor moves to the FILE window Rotate the PFD small FMS knob to activate the drop down menu Move the cursor to highlight the appropriate configuration for the aircraft and press ENT on PFD NOTE The PRODUCT window displays information regarding each G1000 LRU The LRU column depicts the reported software version of the LRU whereas the CARD VERS column shows the LRU software version stored on the Loader Card The SOFTWARE and CONFIGURATION columns default to having all required boxes checked Each checked file is automatically loaded to the correct G1000 LRU Figure 3 8 Configuration Software Load Page LRU VERS CARD VERS CARD PART NUM SOFTHARE CONFIGURATION N A MANIFEST N A AIRFRAME N A AIRFRAME PROP N A AIRFRAME ENGINE N A ALERTS N A MFD 1 N A PFD 1 N A PFD 2 N A GIA 1 T5 80bd 006 B0544 2V E RAQHRARRRARM d Press the LOAD softkey e Observe software loading progress and verify software load completes without errors as indicated by the following f Green PASS or White N A in SOFTWARE and CONFIGURATI
7. Continued Airworthiness defined under TCDS 3A15 and identified in Table 1 1 remain valid and applicable for all other maintenance and ICA aspects of the G1000 and GFC 700 systems The Airworthiness Limitations section is FAA approved and specifies maintenance required under 43 16 and 91 403 of Title 14 of the Code of Federal Regulations unless an alternative program has been FAA approved 4 2 Servicing Information G1000 LRU maintenance is on condition only No component level overhaul is required for this design change 4 2 1 On Condition Servicing On Condition replacement and or servicing should occur when an item exhibits conditions symptoms and or abnormalities defined in Section 5 of this manual Replacement and or servicing should be made only after the technician troubleshoots the system to the extent determined necessary by using the guidance in this manual along with common avionics maintenance practices IMPORTANT It is impossible to provide guidance for every conceivable failure scenario within the scope of this manual Every effort has been made to provide comprehensive guidance for possible failures The information in this document should always be combined with common sense and a thorough knowledge of the system Use sound avionics maintenance practices when working around or on G1000 equipment IMPORTANT All structural repairs associated with this installation are to be addressed in accordance with
8. Disconnect the eight coax quick lock connectors 3 Disconnect the three electrical connectors 4 Unlock the unit from the rack by loosening the ratcheting latch mechanism 5 Remove the unit from the rack Reinstallation 1 Inspect the connectors for damaged pins 2 Insert the unit into the installation rack 3 Lock the unit into the rack by using the ratcheting latch mechanism 4 Reconnect the eight coax quick lock connectors and the three electrical connectors 5 Configure and test the GTS 820 according to 7 1 G1000 System Maintenance Manual Hawker Beechcraft G36 Page 6 1 190 01259 00 Rev 5 6 2 GPA 65 LNA PA CAUTION After any maintenance or modification is made to the GTS 820 TAS cables such as replacing a connector or entire cable some important considerations must be made Be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc in the Installation Manual referenced in Table 1 2 Removal 1 Remove cabin interior to access FS 124 75 at BL 0 00 on the right side of the fuselage Refer to the GTS 820 Equipment Install Hawker Beechcraft G36 drawing listed in Table 1 1 2 Disconnect the eight coax quick lock connectors 3 Disconnect the electrical connector 4 Remove the four mounting bolts that hold the unit to the installation bracket Reinstallation 1 Inspect the connectors for dam
9. G1000 EQUIPMENT CONFIGURATION amp TESTING Refer to Section 3 6 for information on loading software and configuration of G1000 equipment covered by this STC 7 1 Transponder Testing The integrated transponder altitude reporting system must be verified in accordance with Title 14 of the Code of Federal Regulations 14 CFR 91 411 and 91 413 These tests require the use of a Mode S ramp generator Specific instructions for operating the ramp tester are contained in the applicable operator s manual Refer to 14 CFR Part 43 Appendices E and F for testing criteria The transponder is tested while operating in the normal mode unless otherwise specified Perform the following procedures using an appropriately rated transponder test set 7 1 1 Extended Squitter Test For those aircraft with extended squitter enabled perform the following test procedures The transponder is tested while operating in the normal mode unless otherwise specified Perform the following procedures using an appropriately rated transponder test set a On PFD press the XPDR softkey and verify that ADS B TX softkey is available Select ADS B TX selection will be greyed out b Using a transponder ramp tester evaluate ADS B Using an appropriately rated ADTS input an airspeed of 50 knots Verify the following information is displayed on the test set e Squitter Type e Altitude Altitude Source e Squitter Period e Latitude and Longitude D Aircraft Type
10. PA LNA Fault Antenna connections or internal Ensure all antenna connections Receiver Fault are correct otherwise return to faui Garmin for Service Antenna connections or internal Ensure all antenna connections Transmitter Fault are correct otherwise return to fault Garmin for Service Baro Altimeter is not powered on Verify that the baro altimeter has or improper wiring power and is properly wired Baro Altitude Fault Verify the configuration is set Improper configuration settings correctly using the GTS 8XX Install Tool Ensure the port is properly wired Red X on a data port on the Improper wiring wrong port or to the GTS 820 and the correct configuration page speed selected settings are selected on the configuration page 5 3 Software Configuration Troubleshooting Problem Solutions Ensure that criteria listed in Section 5 4 are fulfilled for the applicable situation Ensure that LRU is reporting data on System Software file load fails Status page LRU is ONLINE Check data path wiring as needed FILE UPLOAD FAIL Retry software file load or try using a different card Ensure that the MFD is not touched during the loading process OK Ensure that LRU part number is compatible with software version and Card Loader Refer to the General Arrangement Drawing and to Section 3 6 of this document Replace LRU i SE l Ensure that the criteria listed in Section 5 4 Configuration file load f
11. aircraft a Remove power from the MFD and PFD by pulling the PFD and MFD circuit breakers b Insert the TAWS Enable card 010 00330 51 in the upper slot of the PFD c While holding the ENT key on the PFD and MFD restore power to the displays d When the words MIME appear in the upper left corner of the displays release the ENT key e On the PFD go to the System Upload page f Activate the cursor and use the small FMS knob to activate the drop down menu and select CONFIGURATION FILES in the AIRFRAME field Press ENT g Use the small FMS knob to activate the drop down menu and select ENABLE TAWS in the FILE field Press ENT h Verify there is a check mark in the box in the configuration column for AIRFRAME i Press the LOAD softkey j Monitor the status of the upload When the upload is finished Complete and Pass is displayed Press ENT k De activate the cursor Power down the system and remove the TAWS B Enable card from the PFD Page 3 22 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 13 Aircraft Registration Number Entry NOTE The large FMS knob changes Groups and the small FMS knob changes Pages within a Group NOTE If aircraft has a Garmin GTS 8XX Traffic System installed ensure GTS 8XX system configuration is loaded prior to registration entry for transponder See Section 3 7 3 Remove power if applied from PFD by pulling the PFD circuit breaker While holding
12. data defining this modification is contained in the Master Drawing List 005 00620 18 Modification of an aircraft by this Supplemental Type Certificate STC obligates the aircraft operator to include the maintenance information provided by this document in the operator s Aircraft Maintenance Manual and the operator s Aircraft Scheduled Maintenance Program 1 2 Organization The following outline briefly describes the organization of this manual Section 2 System Description Provides a complete description of the type design change associated with updating the G1000 system in the Hawker Beechcraft G36 Section 3 G1000 Control amp Operation Presents basic control and operation information specifically tailored to maintenance practices Basic G1000 Configuration Mode operation is also described Section 4 Instructions for Continued Airworthiness Provides maintenance instructions for continued airworthiness of the G1000 systems Section 5 Troubleshooting Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000 Section 6 G1000 Equipment Removal amp Replacement Gives instructions for the removal and replacement of G1000 equipment associated with this modification Section 7 G1000 Equipment Configuration amp Testing Gives instructions for loading software configuring and testing of G1000 equipment Section 8 System Return to Service Procedure Specifies return to service
13. e Squitter Period 7 2 GTS Traffic System CAUTION After any maintenance or modification is made to the GTS 820 TAS cables such as replacing a connector or entire cable some important considerations must be made Be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc in the Installation Manual referenced in Table 1 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Page 7 9 190 01259 00 Rev 5 Original GTS 820 Reinstalled No software or configuration loading is required if the removed GTS 820 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GTS 820 Test Section 7 2 1 New Repaired or Exchange GTS 820 Installed If a new repaired or exchange GTS 820 is installed the correct software and configuration files must be loaded to the unit See Section 3 7 and then continue to the GTS 820 Test Section 7 2 1 7 2 1 GTS 820 Test NOTE The GTS 8XX Traffic System must be calibrated using the GTS 8XX Install Tool Garmin Part Number 006 A0242 00 prior to accomplishment of the functional check Reference the GTS 8XX GPA 65 Installation Manual 190 00587 00 for instructions on the use of the GTS 8XX Install Tool for calibration and accomplishment of the functional check The following
14. own aircraft at a rate of 0 1 NM sec Page 7 10 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 e The intruder should transition from Other Traffic displayed as an open diamond with 00 displayed above to proximate traffic displayed as a filled white diamond with 00 displayed above to a Traffic Advisory TA alarm e The appropriate TA symbology yellow filled circle with 00 displayed above and an audio annunciation of Traffic 3 O clock At Altitude 3 Miles displayed when the intruder approaches within 3 NM Antenna Bearing Check a Position the test set directional antenna with a clear line of sight to the GTS820 antenna b Ensure that the transmitter or receiver RX TX that you are testing is significantly closer to the ramp tester than another operating RX TX or erroneous and inaccurate results may occur All four quadrants forward starboard aft and port will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the MAP TRAFFIC MAP page of the MFD c Using the ramp tester select the proper antenna gain and distance to aircraft d Position ramp test set at O degrees e Turn the test set on f Connect the directional antenna to the ramp test set g Set the multifunction test set to perform TCAS testing Configure the GTS 8XX to the normal operating mode h Program a stationary intruder per the following
15. page The following table provides SVS Pathways specific alert messages which may appear in the Alerts Window on the PFD press the ALERTS softkey on the PFD to view the Alerts Window G1000 System Maintenance Manual Hawker Beechcraft G36 Page 5 1 190 01259 00 Rev 5 Failure Message SVS SVS DISABLED Out of available terrain region Table 5 2 SVS Alert Messages SVS is disabled because the aircraft exceeded the boundaries of the loaded terrain database Solution Geographical operation limitations are defined in the SVS Pathways AFMS which is referenced in Table 1 1 Ensure that operations are within this geographic area SVS SVS DISABLED Terrain DB resolution too low 5 2 SVS is disabled because a 9 Arc Second or better database is not currently loaded GTS 820 Troubleshooting Ensure the P N 010 00330 43 Terrain Cards are installed in the lower slot of each display If terrain data has been recently updated ensure that the correct 9 Arc Second databases were used Problem cause Jn Unit does not power up Data failed message Improper wiring circuit breaker open Ensure power is properly wired to the GTS 820 and the circuit breaker is closed Improper configuration Verify using the USB install tool that the GTS 820 is configured correctly for the desired display GTS 8XX Install Tool won t Improper wiring circuit breaker Ensure USB is
16. properly wired to the GTS 820 and the circuit display any pages open breaker is closed Improper wiring Volume not set Ensue Mic audicls propery No Audio alerts i wired from the GTS 820 and correctly volume is not set too low Calibration Fault Factory calibration invalid If the unit fails to go into operate mode then return to Garmin for service Configuration Fault Both internal and external configuration checks failed Verify the configuration via the GTS 8XX Install Tool Verify wiring to the configuration module and replace if necessary FPGA Fault Internal Fault Return to Garmin for service ROM Fault Internal Fault Return to Garmin for service Execution Fault Internal Fault Return to Garmin for service Electrical Fault Internal Fault Return to Garmin for service Whisper Shout Fault Internal Fault Return to Garmin for service Transmit Power Fault Internal voltages are out of tolerance Verify input voltage and if it continues return to Garmin for Page 5 2 Rev 5 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 Problem Gass Solution service 1030 MHz Fault Internal Fault Return to Garmin for service 1090 MHz Fault Internal Fault Return to Garmin for service Ensure all antenna connections are correct otherwise return to Garmin for Service Antenna connections or internal fault
17. test will be performed using an appropriate laptop computer with GTS 8XX Install Tool GPN 006 A0242 00 installed a USB A to USB B cable and suitable ramp tester such as a TIC TR220 or equivalent To select a scenario that will properly converge and intercept the GTS 8XX the GTS 8XX must be in ground test mode Activate ground test mode by enabling the Ground Test field on the Normal tab of the GTS 8XX Install Tool To enable ground test mode the aircraft must be on the ground and the GTS 8XX must be in normal system mode and in standby NOTE Using the GTS 8XX Install Tool Garmin Part Number 006 A0242 00 place the Ground Sense and Squat Switch Sense to OPEN under the CONFIGURATION tab prior to accomplishment of the functional check Reference the GTS 8XX GPA 65 Installation Manual 190 00587 00 for instructions on the use of the GTS 8XX Install Tool a Position the test set directional antenna with a clear line of sight to the GTS 820 antenna at 90 degrees With the GTS 820 powered up and in Standby mode indicated on the MFD cycle the GTS 820 to Operate b On the test set select the following e Set the intruder type as ATCRBS e Intruder Start Distance 10 nm e Intruder Start Altitude 50 000 ft e Vertical Speed 0 fpm e Velocity 360 kts c Initiate the intruder scenario and observe the following e Traffic should be acquired at approximately 10 NM at 90 degree bearing and co altitude Observe intruder closes on
18. the ENT key on the PFD restore power by closing the PFD circuit breaker When the words INITIALIZING SYSTEM appear in the upper left corner of the PFD release the ENT key Rotate the outer FMS knob to activate the GTX group then rotate the small FMS knob to select the TRANSPONDER CONFIGURATION page on PFD Ensure that the ADDRESS TYPE is US TAIL under the SET and XPDR ACTIVE columns Ensure that the FLIGHT ID TYPE is SAME AS TAIL under the SET and ACTIVE columns Activate the cursor and highlight the MODE S ADDRESS field Use the small large FMS knob to enter the aircraft registration number Once the correct registration number is entered press the ENT key to configure the transponder Observe the status window and press the ENT key on PFD to acknowledge the OK prompt once configuration is complete 3 14 Clearing Default User Settings Remove power from PFD and MFD While holding the CLR button on PFD re power PFD When prompted to clear user settings select the YES softkey Repeat steps a c for MFD G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 23 190 01259 00 Rev 5 This page intentionally left blank Page 3 24 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 4 1 Airworthiness Limitations There are no airworthiness limitations associated with this type design change STC SA1595WI D The previously approved Instructions for
19. 5 2 2 Optional features The following optional features are included with this STC These features are enabled via individual Enable cards that are to be retained with the aircraft e Synthetic Vision and Pathways e TAWS B e Chartview These features will need to be re enabled after replacement of a display unit Page 2 6 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 G1000 CONTROL amp OPERATION All control and operation of G1000 equipment as normally used in flight occurs through the PFD MFD and GMA audio panel 3 1 1 Softkeys Some pages have commands or selections that are activated by the GDU softkeys If a softkey is associated with a command that command will be displayed directly above the key A grayed out softkey shows a command that is unavailable A softkey that is highlighted shows the current active selection NATAS ANLG IN CRNT MNTRENG TEMP BKSHELL ANNUNC DIGITAL DISCRETE COPY VERIFY Figure 3 1 G1000 Softkeys 3 1 2 FMS Knob The FMS knob is the primary control for the G1000 system Operation is similar to the Garmin 400 500 Series units To cycle through different configuration screens To change page groups Rotate the large FMS knob To change pages in a group Rotate the small FMS knob To activate the cursor for a page press the small FMS knob directly in as one would push a regular button To cycle the cursor through different data fields ro
20. 63Ws must be successfully configured GTX 33 with GIA1 and GIA2 configuration files Data path from GIA1 to each LRU must be GDL 69A operational SW Loader Card must be inserted into PFD top slot G1000 must be powered on PFD and MFD must have correct software and configuration settings GTS 820 GIA 63Ws must have correct software GIA 63Ws must be successfully configured with GIA1 and GIA2 configuration files Data path from MFD to GDL 69A must be operational 5 6 Backshell Backplate Connectors 0 0090 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 000000000000000000090 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 KL 0000000000090 26 27 28 29 30 31 32 33 34 35 36 37 38 39 000000000000 00000000 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 nO NO 30 S 50 O Figure 5 1 GTS 820 Mating Connector Rear View Figure 5 2 GTS 820 Mating Connector Rear View G1000 System Maintenance Manual Hawker Beechcraft G36 Page 5 5 190 01259 00 Rev 5 E y 00 O Figure 5 3 GPA 65 65 Connector Rear View Figure 5 4 GRT 10 Mating Connector Rear View Page 5 6 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 6 EQUIPMENT REMOVAL amp INSTALLATION This section describes how to remove and replace equipment in the G36 that was installed as part of this STC After removal and replacement LRUs must be confi
21. 9 921N OIL PRES ALT LOAD BUS VOLTS FUEL QTY GAL LOL Sa P l POR MR REI R e In the normal operating mode data fields that are invalid have large red Xs through them A valid field does not display a red X Figure 8 3 Allow the displays to initialize for approximately one minute Figure 8 3 Normal Display without SVS enabled nav11109 00 108 00 pis 107 Innere 317 136 975 o 118 000 com nav2117 30 108 15 A ENTE 118 000 conz TRAFFIC for 1200 ALT ejo 140351 Ce Page 8 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 Figure 8 4 Normal Display with SVS enabled nav1109 80 108 00 KICT ors 1072317 136 JE 118 000 com nave LELE A O E comz PFD XPDR IDENT TMR REF Ver f Check that all COM NAV fields are valid in the top corners of PFD and MFD g Check that altitude airspeed vertical soeed TAS OAT and ISA fields are valid on PFD and MFD h Check that engine instrument fields are valid on the MFD i Verify that no MANIFEST alert messages appear in the lower right corner press the flashing ALERTS softkey to view alert messages If any MANIFEST errors appear the correct software to the related LRU must be loaded before proceeding refer to Section 3 7 j Verify no other alert messages are displayed If any alert messages are displayed resolve prior to proceding G1000 System Maintenance Manual Hawker Beechcra
22. A GARMIN G1000 System Maintenance Manual Hawker Beechcraft G36 Contains Instructions For Continued Airworthiness For STC SA1595WI D nav1 109 00 gt 108 00 ors A A ers 178 136 975 gt 118 000 com Nava MBA cone i MAN IN HG H 24 8 16 cu 1500 K 2300 eaj ariba 1400 11300 OIL TEMP E 29 921N OIL PRES 7 ALT LOAD g a BUS VOLTS H 2 FUEL QTY GAL an ioe 6 37 190 01259 00 January 2012 Rev 5 This page intentionally left blank Copyright 2012 Garmin Ltd or its subsidiaries All Rights Reserved Except as expressly provided herein no part of this manual may be reproduced copied transmitted disseminated downloaded or stored in any storage medium for any purpose without the express prior written consent of Garmin Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 www garmin com Garmin Europe Ltd Liberty House Bulls Copse
23. CRIPTIONS ct AER AE 2 1 22 OPTIONAL FEATURES doe eege e Id dS Hath AL ON 2 6 3 G1000 CONTROL amp OPERATION oocononcnocccnnnncnononcnnnncnnnnnnonnnrn narco anne ana nero narrar narrar 3 1 3 2 G1000 NORMAL len 3 1 3 3 REVERSIONARY MODE Nee ana 3 2 3 4 CONFIGURATION MODE OVERVIEW ccccceeeecceeeececeeceeeceeeeceeceeceeeeceeeeceeeecseeeeceeeeneeeensess 3 3 3 5 CONFIGURATION MODE NAVIGATION 3 3 3 6 G1000 SOFTWARE INFORMATION 3 5 3 7 G1000 SOFTWARE CONFIGURATION PROCEDURE 0ccooccconccconcccnnnccnnnccnnnccnoncccnnnccnonecinneces 3 10 3 8 SOFTWARE LOAD CONEIRMATION ttrt eer r ner A eer E REEERE E EEEE E EEEE EEEren 3 16 3 9 AVIATION DATABASE LOADING PROCEDURES ccconccconncononccnonccnonccnnnncnnonccnoneconnnccnnnccnnnenes 3 18 3 10 SVS PATHWAYS ACTIVATION OPTION E 3 19 3 11 CHARTVIEW ENABLE PROCEDURE 0secceeeecceeecceeeeceeeecuueeceaeeecaeeecaeeesneeeeeeeceeeeeaes 3 21 3 12 TAWS B ENABLE PROCEDURE ccccoooccnnncccnncccnnncnnnnccnnnccnnncnnnnnnnnnnnnnnnrrnnnrrnnnncnnnnrnennnnnnss 3 22 3 13 AIRCRAFT REGISTRATION NUMBER ENTREE 3 23 3 14 CLEARING DEFAULT USER SETTINGS 2 00 ccecccsecccececeeeeceseeceueeccaeeecateeceueecaneeecaeeesaeeeeaes 3 23 4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ccccccceececeeesceeescceeseceeeseneeseeeees 4 1 4 1 AIRWORTHINESS LIMITATIONS 0ocoooccccnccconccnnnncnonncnnoncnnonnrnnnnr rro nr r non r non n rn nnnrrn nn ne nnrnennnnnnns 4 1 4 2 SERVICING INFORMATION 4 1 4 3 MAINTENA
24. D circuit breakers c A special SVS Enable card is required to activate this feature refer to Table 3 2 Insert this card in the upper slot of PFD d While holding the ENT key on the PFD and MFD restore power to the displays e When the words MIA AAN appear in the upper left corner of the displays release the ENT key f From PFD accomplish the following g Goto the System Upload page using the small FMS knob e Activate the cursor Use the small FMS knob to select CONFIGURATION FILES in the AIRFRAME field and press the ENT key e Highlight the FILE field Use the small FMS knob to select the Enable SVS option and press the ENT key Once the option is selected the configuration files in the PRODUCT field will be displayed All files should be checked If not press the CHK ALL softkey e Press the LOAD softkey e Monitor the status of the upload When the upload is finished press the ENT key to acknowledge the upload complete confirmation h View the SUMMARY field and ensure that the item is COMPLETE i De activate the cursor j Power down the system and remove the SVS Enable card from the PFD Page 3 20 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 11 Chartview Enable Procedure NOTE e The Chart Enable card can only enable Charts on one system one aircraft A new Chart Enable card must be used for each aircraft e The required ChartView databases are subscription based an
25. Manual Hawker Beechcraft G36 Page 3 9 190 01259 00 Rev 5 3 7 G1000 Software Configuration Procedure This section summarizes the procedures required to load software and configuration files to the G1000 It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft In sections of this manual where software is required to be reloaded these sections will make reference back to this Section for instructions The technician should use proper judgment regarding the context of maintenance required while following this section The following diagram depicts an overview of the software configuration sequence for the G1000 system This applies mostly to a new G1000 system which has not previously been powered up and is for informative purposes only Initial GDU Software Load Software is first loaded to the existing PFD Power up of existing PFD display with new loader card inserted in top slot Press YES softkey when prompted to Update System Files Using the PFD the technician goes to the System Upload Page and presses the UPDT CFG softkey l G1000 System Upload Selection After software is loaded to the MFD and PFD the displays are placed in configuration mode Using the PFD the technician goes to the System Upload page From the System Upload page software and configuration files are selected to create an automated profile to load Once all desired files are checked the G1000 aut
26. N A green check could also indicate that the parameter component is working correctly e Red X Expected data is not received A red X could also indicate that a parameter component is invalid e White N A Expected data is OFF or no data is expected e Amber Data is unknown SYSTEM CONFIGURATION Figure 3 6 Data Transmission Indicators Page 3 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 6 G1000 Software Information NOTE The following sections provide a detailed description of loading all G1000 software and configuration files which may be excessive for individual LRU removal and replacement If removing and replacing individual LRUs refer to Section 5 6 of this manual for the necessary steps 3 6 1 Loader cards NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this document these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Table 3 1 Required Loader Cards 010 00726 07 or 010 00726 08 2 or 010 00726 09 G1000 G36 Loader card contains 006 B0858 07 Software Image or G1000 G36 Loader card contains 006 B0858 08 Software Image or G1000 G36 Loader card contains 006 B0858 09 Software Image 010 00330 43 2 Required Terrain Obstacle Ai
27. NCEINTERVALS an aea aaa aa a aa ERSE atA 4 3 5 TROUBLESHOOTING ie G GE e ee e NEEN ENNEN SE Gate EA DESEN E Ee 5 1 5 1 SVS PATHWAYS TROUBLESHOOTING 0occcoocccnnncccnncncnnnccnnnnonnnncnnnnnonnnrcnnnrnnnnrrnnnrrnnnnncnnrnnines 5 1 5 2 GTS 820 TROUBLESHOOTING gedet NEE SEENEN EEN 5 2 5 3 SOFTWARE CONFIGURATION TROUBLESHOOTING 0ccoooccnnncccnncncnnnccnnnncnnnncnnncnonanccnnnncnnancnnos 5 3 5 4 GRT10 GRC 10 XM REMOTE CONTROL TROUBLESHOOTING ococoocccnncncnnoccnnnccnonccinncnnnns 5 4 5 5 SYSTEM COMMUNICATION HIERARCHY s ssaseessenneeneeerreerrenrirerreetrerr rnrn ernten rnrn rnrn nnee n nnen 5 4 5 6 BACKSHELL BACKPLATE CONNECTORS 0coooccnnncccnncccnnnnonnnccnnnncnnnnnonnnnonnnr rn nn rrnnnrrnnnnnennnnnnne 5 5 6 EQUIPMENT REMOVAL 8 INSTALLATION coonnccoconcconncconncononcnnonnno narco anno annrnn na rnnnarnniannn 6 1 6 1 GTS 820 TAS PROCESSOR A A a eee eae 6 1 6 2 GPAG5 ENA PA EE 6 2 6 32 STASIANTENNAS sees e ee eee RO I EEN d Mee ET 6 2 6 4 GRT 10 XM REMOTE CONTROL TRANSCEIVER ccooccconoccnnncccnnnnonnnnonancnnnnnnnnnnnonnnnonnnnnnnrcnnnos 6 3 6 5 GDU REMOVAL REPLACEMENT ooccconcccnnoccnnncccnnccnnnononnnccnnnccnnnrnonnnno nn re nnnrrrnnrrennnccnnnninnes 6 4 6 6 GMU 44 REMOVAL amp REPLACEMENT ssissoesseennerererrnerirrierter reenter rrr rrr errar nn renr n rnern ren 6 5 6 7 GTX 33ES TRANSPONDER REMOVAL amp REPLACEMENT occcooccconnccnnnccnnncnnnncncnnnccnnnccnnncncnns 6 6 6 8 GIA 63W REMOVAL amp REPLACEMENT 0cccoooccnnnc
28. ON columns g Upload Complete COMPLETE in the summary box h Press PFD ENT key to acknowledge the Upload Complete box i Press the UPDT CFG softkey on PFD and acknowledge prompt by pressing the ENT key on PFD j Proceed to the next section G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 13 190 01259 00 Rev 5 3 7 3 Optional Equipment Configuration Perform the following steps if any of the following options are installed e GTS 820 e SKY 497 Skywatch e KN63 DME e WX 500 Storm Scope e GTX 33 with extended squitter a Go to the System Upload page and activate cursor Activate the drop down menu in the AIRFRAME field by rotating the small FMS knob and select G36 OPTIONS and press ENT b Activate the drop down menu by rotating the small FMS knob and select the desired option press ENT c Press the LOAD softkey d Observe software loading progress and verify software load completes without errors as indicated by the following e Green PASS or White N A in SOFTWARE and CONFIGURATION columns f Upload Complete COMPLETE in the summary box g Press PFD ENT key to acknowledge the Upload Complete box h For other installed options repeat steps b thru e by rotating the large FMS knob and highlighting the File Field i De activate the cursor Figure 3 9 Option Selection AIRFRAME Page 3 14 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259
29. Road Hounsdown Business Park Southampton SO40 9RB UK Phone 44 0 23 8052 4000 Fax 44 0 23 8052 4004 RECORD OF REVISIONS Description Revision Date 6 9 10 Initial release 9 3 10 Updated Figure 3 10 3 8 11 Revised to add 20 GIA63W 9 21 11 Added UPDT CFG step to Section 3 7 2 Added 09 software image and updated loader card creation procedures in Section 3 Revision 1 6 12 DOCUMENT PAGINATION Section Pagination Table of Contents iv Section 1 1 1 1 4 Section 2 2 1 2 6 Section 3 3 1 3 24 Section 4 4 1 4 6 Section 5 5 1 5 6 Section 6 6 1 6 6 Section 7 7 9 7 4 Section 8 8 1 8 11 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations EAR issued by the United States Department of Commerce 15 CFR Chapter VII Subchapter C and which may not be exported released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license The preceding statement is required to be included on any and all reproductions in whole or in part of this manual This product its packaging and its components contain chemicals known to the State of California to cause cancer birth defects or reproductive harm This Notice
30. act on normal aircraft operations and is only used for passengers to control audio entertainment NOTE It is not necessary to reconfigure GRC 10 after battery replacement 6 5 GDU Removal amp Replacement Removal 1 Make sure all airplane electrical power is disconnected 3 1 2 Using a hex tool turn all four turn fasteners on the display unit counter clockwise until they reach their stops NOTE The display unit harness is protected by a flexible chain link conduit that protects the harness and eases the retraction of the harness back into the rack when installing the display unit 3 While supporting the display unit carefully pull the unit aft to access the single harness connector Reinstallation 1 Remove the protective caps from the display unit and harness connectors Visually inspect the display unit harness connector for damage Repair any damage 2 While supporting the display unit connect the harness connector to the rear of the display unit NOTE The display unit harness is protected by a flexible chain link conduit that protects the harness and eases the retraction of the harness back into the rack when installing the display unit 1 3 Carefully insert the display unit into the panel cutout Make sure all four turn fasteners align with the corresponding panel holes 4 Seat the display unit in the panel cutout Do not use excessive force 4 5 Once the display unit is seated turn all four
31. afe flight in the event of a display communication or hardware failure As installed in the G36 both manual and automatic reversionary modes are possible Manual reversionary mode allows the operator to force the PFD or MFD into reversionary mode by pressing the large red button labeled DISPLAY BACKUP on the GMA audio panel In addition to the manual mode the system will detect when a display failure has occurred and will put the still functioning display into reversionary mode automatically NOTE When the DISPLAY BACKUP button is pushed to exit reversionary mode there is a 5 second debounce or the GDU waits for 5 consecutive seconds and then returns to normal mode if no other input is received If the DISPLAY BACKUP button is pushed again during this 5 second interval the timer will repeat the count Figure 3 4 Display Reversionary Mode Page 3 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 4 Configuration Mode Overview The Configuration Mode exists to provide the avionics technician with a means of configuring checking and calibrating various G1000 sub systems Troubleshooting and diagnostics information can also be viewed in this mode To start the system in Configuration Mode a Press and hold the ENT key on the MFD while resetting power using the MFD circuit breaker b Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner of
32. age 2 GIA RS 485 Configuration 4 GIA Configuration 6 GIA CAN Configuration GEA Page Group 1 Engine Data 2 GEA Status Page 3 GEA Configuration GTX Page Group 1 Serial Configuration 2 Transponder Configuration GRS Page Group G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 3 190 01259 00 Rev 5 1 Inputs Configuration 2 GRS GMU Calibration ADC Page Group 1 ADC Configuration 2 GDC Configuration GFC Page Group 1 GFC Configuration 2 GFC Status GMA Page Group 1 GMA Configuration GDL Page Group 1 GDL 69 Config GTS Page Group 1 GTS Configuration OTHER Page Group 1 Stormscope CAL Page Group 1 Fuel Tank Calibration 2 Flap and Trim Calibration 3 HSCM Calibration OTHER Page Group will not be present unless Stormscope is configured ON 3 5 1 Configuration Prompts When configuration settings are changed the technician receives on screen prompts and or confirmations such as those shown in Figure 3 5 Section 7 shows other prompts encountered during the configuration process GIA 1 CONFIGURED CONFIGURING GIA 1 OK Figure 3 5 Configuration Status 3 5 2 Data Transmission Indicators Several configuration screens utilize an indicator light system to show discrete ON OFF data and or hardware component status Unless otherwise noted the following applies to all such status indicators e Green Checkmark Expected data is successfully received and is O
33. aged pins 2 Reattach the unit to the mounting bracket reusing exiting hardward 3 Connect the eight coax connectors Note the color coded bands which match the mating connectors on the unit Reconnect the electrical connector pigtail Ensure that all connectors coax and electrical are locked in place No configuration is required for the GPA 65 Test the GTS 820 according to 7 1 6 3 TAS Antennas 1 Remove and install the TAS TCAS antennas in accordance with the GTS 820 Equipment Install Hawker Beechcraft G36 drawing GPN 005 00620 08 CAUTION After any maintenance or modification is made to the GTS 820 TAS cables such as replacing a connector or entire cable some important considerations must be made Be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc in the Installation Manual referenced in Table 1 2 2 Procede to 7 2 for testing of the GTX 820 TAS Page 6 2 Rev 5 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 6 4 GRT 10 XM Remote control transceiver Removal 1 Gain access to GRT 10 under glareshield on copilot side of cockpit Refer to the GRT 10 Equipment Install Hawker Beechcraft G36 drawing listed in Table 1 1 2 Disconnect the electrical connector 3 Remove the three mounting screws that hold the unit to the installation bracket Reinstallation 1 I
34. ails are fulfilled for the applicable situation Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wiring as needed CONFIGURATION UPLOAD FAIL OKI Retry configuration file load or try using a different card Ensure that the MFD is not touched during the loading process G1000 System Maintenance Manual Hawker Beechcraft G36 Page 5 3 190 01259 00 Rev 5 Ensure that LRU part number is compatible with Card Loader Refer to the General Arrangement Drawing 005 00620 06 and to Section 3 6 of this document Replace LRU Ensure that proper software file part number and version were loaded to LRU Refer to the Software File Mismatch Alert appears in lower G q eneral Arrangement Drawing 005 00620 06 right corner of PFD when started in normal mode and to Section 5 4 Check and ensure that correct Card Loader was used during load process Refer to the General Arrangement Drawing 005 00620 06 Reload software to LRU 5 4 GRT 10 GRC 10 XM Remote control troubleshooting Verify GRT 10 is receiving power GRT 10 not found Verify the RF pairing ID entered into GRC 10 is correct Verify that the GRC 10 is in RF range of the GRT 10 GRT 10 connection lost Verify GRT 10 wiring and power Verify wiring between GDL 69A and GRT 10 GDL 69A not found Verify GDL 69A is powered on Verify wiring between GDL 69A and GRT 10 GDL 69A connection is lost Verif
35. be valid e AHRS e Heading e GPS Position e 9Arc Second Terrain Data In the event that one the above items fails or is unavailable the SVS Pathways feature is automatically removed from the PFD The following table describes possible symptoms associated with the SVS Pathways feature and provides corresponding actions for troubleshooting Table 5 1 SVS Troubleshooting Symptom Recommended Action Verify that the PFD and MFD software versions are shown to be 11 01 or later by checking the AUX System Status Page on the MFD SYN VIS softkey does not appear on PFD softkey tier If version 11 01 or later software is installed in the MFD and PFDs follow the steps in Section 3 10 1 to reactivate the SVS Pathways feature Verify that P N 010 00330 43 terrain datacards are installed in the lower slot of the PFD and MFD Verify that no alert messages are shown in the PFD Alerts Window Verify that the G1000 AHRS and heading data are valid on the PFD 3D terrain presentation does Verify that a valid GPS 3D position solution is being received not appear on PFD Troubleshoot these systems in accordance with the existing Piper PA 46 500TP Airplane Maintenance Manual as referenced in Table 1 1 If a terrain database update has just been performed allow the system time to initialize and verify the data When the databases have been verified the current database cycle and version are reported on the MFD AUX System Status
36. ccnncncnnnncnnnncnnnncnnnnnonnnncnnnrnnnnccnnnnrennrnennncnnnes 6 7 7 G1000 EQUIPMENT CONFIGURATION 8 TESTING ess keek KKK KR KAER KEREN KKK R KENE 7 9 G1000 System Maintenance Manual Hawker Beechcraft G36 Page i 190 01259 00 Rev 5 ZG LRANSPONDER TESTING ia aan 7 9 Ted GIS TRAFFIC SYSTEM 0 cc bs A eee avs Fee es Aes a ete ces 7 9 8 SYSTEM RETURN TO SERVICE PROCEDURE o cocccccccccocncnnnnnoncnconcnnannnnancnnnnnnnnnnnannnnnnnns 8 1 8 1 DISPLAY TESTING o ea Ms 8 1 8 2 GIA 63W INTEGRATED AVIONICS UNI 8 6 8 3 GFC 700 AUTOPILOT GROUND CHECKS doooocooccccccccccococonnnnncncnnnnconnnnnnnnnonnoroncnnannannnns 8 8 8 4 MAINTENANCE RECORDS oocccccccccccccncoconennncnonononenononnnononononenennnnnononnnnnnnnnnnnnnnononinnnneneninnns 8 13 Page ii G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 LIST OF ILLUSTRATIONS FIGURE PAGE Figure 21 Display ITI EE 2 1 PIQUE 2 2 TIENS DONAR EE 2 2 Figure 2 3 MaQnetOmeten EEN 2 2 Figure 2 4 EE 2 3 Figure 2 5 GPA 65 PAILNAJMOGUIC E 2 3 Figure 2 6 G36 Traffic Anel 2 4 ie 2 F GRT AO Ri EE 2 4 Figure 2 8 GRC 10 Remote e LEE 2 5 Figure 2 9 GIA Uni a 2 5 Figure 3 1 e a Lal Eet 3 1 Figure 3 2 Normal Mode with SVS enabled ooocoooococoncccnnoncccccnonancnononcnnnnnnnnnn nn nnnnnnnnnnnnnnnnns 3 2 Figure 3 3 Normal Mode without SVS enabled oooccococccoccccccnccocccaoaoncnonnnnnnncnnnanononnnnnnnnnnnnns 3 2 Figure 3 4 Display Reversiona
37. ce It is the responsibility of the owner operator to ensure latest versions of these documents are used during operation servicing or maintenance of the airplane Table 1 1 Required Documents P N Description 005 00620 06 005 W0225 00 General Arrangement G1000 Update with Options G36 Wiring Diagram Optional GRT 10 Hawker Beechcraft G36 Update 005 W0224 00 Wiring Diagram Optional GTS 820 Hawker Beechcraft G36 Update 005 00620 07 GRT 10 Equipment Install Hawker Beechcraft G36 005 00620 08 GTS 820 Equipment Install Hawker Beechcraft G36 005 00620 09 GTS 820 Wire Harness Installation Hawker Beechcraft G36 005 00620 10 GRT 10 Wire Harness Installation Hawker Beechcraft G36 320 00609 XX 320 00610 XX Harness and Coax Fabrication GTS 820 Option Hawker Beechcraft G36 Harness Fabrication GRT 10 Option Hawker Beechcraft G36 36 590001 11B or subsequent revision Hawker Beechcraft Bonanza Model G36 Maintenance Manual Supplement for Airplanes with Garmin G1000 Equipment Installed 36 590001 15C or subsequent revision Hawker Beechcraft Bonanza G36 Avionics Wiring Diagram Manual 36 590001 9C1 or subsequent revision Hawker Beechcraft Bonanza A36 B36TC G36 Maintenance Manual Hawker Beechcraft document The following publications are recommended to be on hand during the performance of maintenance activities Table 1 2 Ref
38. course widht of 20 Verify full scale deflection of the CDI while applying a 10 deviation signal b Exercise the CDI with both right and left deviations for both NAV1 and NAV2 c Exercise the Glideslope deviation indicator with up and down deviation indications 8 3 GFC 700 AUTOPILOT GROUND CHECKS The following procedure will verify the proper operation of the GFC 700 AFCS and are only required after conducting maintenance on either GIA 63W or any of the GSA 81 servo units This procedure is designed to test the installation of the AFCS only after the G1000 testing in previous sections has been conducted The technician performing these checks should be thoroughly familiar with the GFC 700 by studying the following Pilot s Guide for Beechcraft G36 Garmin P N 190 00595 02 Revision A or later NOTE Servo torque settings must be maintained in accordance with Hawker Beechcraft AMM Chapter 22 14 07 CAUTION When the autopilot is engaged flight control surface movement can occur Page 8 8 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 8 3 1 Autopilot Pre Flight Test NOTE The autopilot pre flight test will run on every full autopilot power on a Open the AP SERVOS circuit breaker and reset The AFCS will re initiate the pre flight test NOTE A red AFCS annunciation will be displayed until both GIAs the AHRS and the autopilot servos are online b Verify that a white PFT a
39. d Gain access for the procedure listed below as required and in accordance with the Bonanza G36 Maintenance Manual 4 3 3 2 Test Equipment A milli ohm meter and Kelvin probes are recommended for this test However a standard voltmeter power supply with adjustable current limit and ammeter may be substituted The following procedure is written using the voltmeter power supply and ammeter All test equipment must have valid calibration records 4 3 3 3 Electrical Bonding Procedure Test Preparation All electrical connectors including coaxial cable connectors must be disconnected during bonding checks 1 Connect the positive lead of the power supply to a nearby exposed portion of aircraft metallic structure such as a frame as close as possible to the unit under test Do not use the units own installation rack Connect touch the positive lead of the voltmeter to the same point NOTE Ensure that the voltmeter and power supply probes do not touch so as not to induce contact resistance 2 Touch negative lead of power supply to each of the test points listed while performing Step 3 At each point configure the power supply to produce 1 amp before measuring voltage Use an ammeter to ensure current is within 1 amp 100 milli amp at each point 3 Set the voltmeter to measure milli volts and null the reading Measure the voltage from ground point step 1 to each of the following points and record the voltage Perform Step 2 at eac
40. d coat the screw threads with Loctite 242 blue thread locking compound to restore their anti rotational properties Securing screws MUST be non magnetic 4 Secure the GMU 44 to the mounting rack with three phillips screws 5 Make sure the location of the electrical connector and the routing of the associated electrical wire harness are as noted in the removal process 6 Make sure all tools and equipment are removed from the area 7 Install the square access panel left wing top 8 No software or configuration loading is required if the removed GMU is reinstalled This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Proceed to Section 8 9 If a new repaired or exchange GMU is installed the correct software and configuration files must be loaded to the unit See Section 3 7 then continue to Section 8 G1000 System Maintenance Manual Hawker Beechcraft G36 Page 6 5 190 01259 00 Rev 5 6 7 GTX 33ES Transponder Removal amp Replacement Removal 1 Make sure all airplane electrical power is disconnected 2 Remove the PFD 3 Unlock the GTX 33 handle by loosening the Phillips screw on the handle 4 Pull the handle upward to unlock the GTX 33 Gently remove the unit from the rack 5 Place protective caps on the GTX 33 electrical connectors and rack connectors 6 Remove the unit from the airplane Reinstallation 1 Remove t
41. d are to be procured by the installing agency directly from Jeppesen e The G1000 can only be configured for FliteCharts or ChartView but not both Performing this procedure will automatically disable the FliteChart option a Apply power to the G1000 system b Pull the PFD and MFD circuit breakers c Insert the Chart Enable card 010 00330 50 in the upper slot of the PFD d While holding the ENT key on the PFD and MFD restore power to the displays e When the words INITIALIZING SYSTEM appear in the upper left corner of the displays release the ENT key f On the PFD go to the System Upload page g Activate the cursor and rotate the small FMS knob to activate the drop down menu and select CONFIGURATION FILES in the AIRFRAME field Press ENT h Rotate the small FMS knob to activate the drop down menu and select ENABLE CHARTVIEW in the FILE field Press ENT i Verify there is a check mark in the box in the configuration column for AIRFRAME j Press the LOAD softkey k Monitor the status of the upload When the upload is finished Complete and Pass is displayed Press ENT De activate the cursor m Power down the system and remove the ChartView Enable card from the PFD G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 21 190 01259 00 Rev 5 3 12 TAWS B Enable Procedure NOTE The TAWS B Enable card can only enable TAWS on one system one aircraft Anew TAWS Enable card must be used for each
42. d configuration files must be loaded to the unit See Section 3 7 then continue to Section 7 1 1 Page 6 6 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 6 8 GIA 63W Removal amp Replacement Removal 1 2 5 6 Make sure all airplane electrical power is disconnected Remove the MFD Unlock the GIA 63W handle by loosening the Phillips screw on the handle Pull the handle upward to unlock the GIA 63W Gently remove the unit from the rack Place protective caps on the GIA 63W electrical connectors and rack connectors Remove the unit from the airplane Reinstallation 1 Remove the protective caps from the GIA 63W electrical connectors and rack connectors Visually inspect the electrical connectors to make sure there are no bent or damaged pins Repair any damage NOTE A handle lock mechanism is used to guide and lock the LRU into place The handle has a locking stud that engages a dogleg shaped track on the LRU rack After engaging the dogleg the handle can be pushed down and locked This action seats the LRU against the rear plate and connectors A single Phillips screw is used to fasten the lever to the LRU body Gently insert the GIA 63W into its rack The handle should engage the dogleg track CAUTION Some pressure is required to seat the LRU and lock the handle The unit should be gently worked into position using the lever Do not use excessive force inserting the LRU I
43. e MAP TRAFFIC MAP page of the MFD at the correct bearing of approximately 270 degree azimuth at 2 NM and co altitude w Toggle intruder traffic to standby or off x If the bearing is not as anticipated or multiple targets are displayed during tests recheck the antenna coaxial connections by verifying the following e QMA connectors are snapped firmly in place e Connections are made to the proper channels and color coded heat shrink is the same color on both ends of cable e QMA connectors are correctly installed on cables e Correct antenna type is selected in the configuration Page 7 12 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 8 SYSTEM RETURN TO SERVICE PROCEDURE The procedures contained in this section describe the minimum return to service checks that should be performed upon reinstallation of the software and or reactivation of SVS Pathways If the software reload or SVS reactivation was as a result of an LRU replacement the technician must also perform any additional return to service tests required by the existing Hawker Beechcraft G36 Airplane Maintenance Manual listed in Table 1 1 for that LRU 8 1 Display Testing The G1000 system is tested while operating in the normal mode unless otherwise specified If the system is in configuration mode restart the displays by cycling the PFD and MFD circuit breakers to start the display in the normal mode a Apply aircraft power Observe t
44. e screen to indicate file progress Transferring Data Page 3 8 Rev 5 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 j Once successfully completed the following message window will pop up Click Finish to finalize SD card 3 G1000 Software Update GARMIN 3 6 4 Software Files Software files are defined by part number and version number on the General Arrangement Drawing 005 00620 06 Each G1000 LRU reports the software version it currently contains to the user in two places e Normal System Mode The AUX SYSTEM STATUS page lists each LRU and the reported software version e Configuration Mode The SYSTEM STATUS page SYSTEM page group reports more detailed LRU information including software version part number and LRU status Software files are loaded to LRUs from the SYSTEM UPLOAD page in configuration mode 3 6 5 Configuration File Descriptions There are configuration files for baseline settings and various options Configuration files contain preset selections for input output channels aircraft specific settings and LRU specific settings IMPORTANT Certain software and configuration files are REQUIRED to be re loaded during maintenance that involves removal and replacement of G1000 equipment Refer to Section 7 for re configuration requirements for each G1000 LRU Pay special attention to the configuration of options for the G1000 G1000 System Maintenance
45. e target 1 amp current then the allowable voltage measurement would be 20 high 2 5 milli volts would now be 3 0 milli volts If one or more bonding checks fails i e the resistance is higher than those listed above then clean and rebond as necessary Re attach equipment racks appliance antenna and complete electrical bonding test based on the original installation requirements Refer to the applicable installation drawing referenced in Table 1 1 for the bonding requirements After bonding checks are complete ensure all electrical and coaxial cable connectors are reconnected and all systems are working properly Page 4 6 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 5 TROUBLESHOOTING This section provides instructions and guidance for system troubleshooting additional systems functions added by this STC For troubleshooting assistance for all other aspects of the G1000 GFC 700 refer to the existing Hawker Beechcraft G36 maintenance supplement listed in Table 1 1 IMPORTANT Sections 6 3 7 and 8 provide detailed instructions on equipment removal replacement configuration and return to service testing Anytime a G1000 component or LRU is removed swapped or replaced the technician must follow the procedures given in Sections 3 7 and 8 to ensure proper operation of the system 5 1 SVS Pathways Troubleshooting The SVS Pathways software feature requires the following G1000 sensors data to
46. enance action and identifies the timeframe in which that activity should occur The previously approved Instructions for Continued Airworthiness defined under TCDS 3A15 and identified in Table 1 1 remain valid and applicable for all other maintenance and ICA aspects of the G1000 and GFC 700 systems This STC does not remove or allieviate any of the existing maintenance requirements for the Hawker Beechcraft G36 aircraft unless specifically stated Table 4 1 Maintenance Intervals Item Description Procedure Section Interval Annual inspection Visual Inspection Complete visual inspection of 4 3 1 y i 3 l La new equipment and wiring in conjunction with existing visual inspection requirements Conduct electrical bonding SSES Electrical Bonding checks of new LRUs and 4 3 3 l l seat tests A in conjunction with existing ntenna f 3 visual inspection requirements Inspect antenna and surrounding structure to ensure there is no Suspected lightning structural damage where strike to GA58 lightning may have attached If 6 3 On Condition antenna there is visible damage to the equipment then it should be replaced GDU 1040 PFD Remove and Replacement On Condition 6 5 GDU 1045 MFD Remove and Replacement On Condition GIA 63W Remove and Replacement 6 8 On Condition Nee Remove and Replacement 6 6 On Condition Magnetometer GTS 820 Traffic Remove and Replacement 6 1 On Conditon receiv
47. ent GMU 44 unit is mounted in L H wing tip GMU 44 There are no mechanical or electrical interface changes needed for the new The This STC approved an alternate part number of the magnetometer and it is installed in place of the existing part if selected Refer to the General Arrangement Drawing 005 00620 06 listed in Table 1 1 for part number information cl l U sf Figure 2 3 Magnetometer Page 2 2 Rev 5 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 2 1 4 GTS 820 Traffic System The optional GTS 820 system is designed to use active interrogations of Mode S and Mode C transponders to provide Traffic Advisories TA to the pilot Passive surveillance is available only when installed with a GTX 33 with extended squitter Traffic is displayed on the MFD via Ethernet High Speed Data Bus routed through the existing GDL 69A The GTS receiver is installed at FS 190 It is powered from the 5 amp Traffic Alert circuit breaker fed from the 28 Vdc Avionics bus The GPA 65 is a power amplifier low noise amplifier PA LNA module installed between the top antenna and the GTS receiver just forward of FS 140 behind the headliner A top GA 58 antenna is installed on the top of the aircraft just forward of FS 106 25 A lower GA 58 antenna is installed on the bottom of the aircraft between FS 131 00 and FS 151 00 Figure 2 4 GTS Receiver Figure 2 5 GPA 65 PA LNA Module G1000 System Maintenance Man
48. er GPA 65 Traffic D PA LNA Removal and Replacement 6 2 On Condition GA 58 Antenna Remove and Replacement 6 3 On Condition GBT 10AM remo Removal and Replacement 6 4 On Condition control transceiver G1000 System Maintenance Manual Hawker Beechcraft G36 Page 4 3 190 01259 00 Rev 5 Item Description Procedure Section Interval Replacement Reconfiguration On Condition GRC 10 XM remote 6 4 1 control A Battery replacement On Condition Synthethic Vision ere On Condition after GDU Pathways DESEN lO replacement Removal and Replacement 6 7 On Condition GTX 33ES Tranponder with Transponder test Extended Sqitter required for compliance with Functionality Title 14 of the Code of Federal AOS Regulations 14 CFR 88 91 411 and 91 413 4 3 1 Visual Inspection Requirements In conjuction with existing Annual visual inspection requirements conduct the following Inspect all new appliances antennas and electrical connectors and coax connectors for corrosion or other defects Check the integrity of all shield block ground attachments to the harness connector as well as integrity of the individuals shields Inspect all exposed wiring for chaffing damage proper routing and security of attachment Signs of corrosion on equipment racks aircraft structure relied upon for ground and connectors backshells wire attachment Conduct a visual inspection of the antennas and mounting Verify
49. erence Publications P N Description 190 01258 00 FAA Approved Airplane Flight Manual Supplement G1000 Integrated Avionics Update with Options Including Synthetic Vision Pathways on Hawker Beechcraft G36 190 00525 03 Cockpit Reference Guide for the Hawker Beechcraft G36 190 01257 00 Post Installation Checkout Procedures Hawker Beechcraft G36 190 00355 04 GDL 69 69A XM Satellite Radio Activation Instructions 190 00907 00 G1000 System Maintenance Manual 190 00587 00 GTS 8XX GPA 65 Installation Manual G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 Page 1 3 Rev 5 Generic installation manuals for individual Garmin LRUs are also available through the Dealers Only section of the Garmin web site refer to Section 1 5 for details 1 5 Distribution This document is required for maintaining the continued airworthiness of the aircraft When this document is revised every page will be revised to indicate current revision level Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center website Owner operators may obtain the latest revision of this document from the https fly garmin com Support page or by contacting a Garmin dealer contacting Garmin Product Support at 913 397 8200 toll free 866 739 5687 or using around the world contact information on https fly garmin com A Garmin Service Bull
50. ernal video input and have an additional HSDB Ethernet connection There are no mechanical or electrical interface changes needed for these new part number displays Refer to the General Arrangement Drawing 005 00620 06 listed in Table 1 1 for part number information NOTE While the alternate part numbers of displays authorized by this STC include an external video input and HDSB Ethernet connection this STC does not approve any interfaces to these ports Any interfaces to these ports will require additional airworthiness approvals Figure 2 1 Display Unit G1000 System Maintenance Manual Hawker Beechcraft G36 Page 2 1 190 01259 00 Rev 5 2 1 3 GMU 44 Magnetometer 2 1 2 GTX 33 Transponder The Garmin GTX 33 transponder communicates with the on side GIA 63W through RS 232 digital interface This STC provides for the optional installation of a GTX 33ES transponder that provides extended squitter functionality The unit is mounted on the back side of the instrument panel There are no mechanical or electrical interface changes needed GTX 33ES option and is installed in place of the existing GTX 33 if selected Refer to the General Arrangement Drawing 005 00620 06 listed in Table 1 1 for part number information Y 0 OI it Figure 2 2 Transponder The GMU 44 provides horizontal and vertical magnetic field information to the GRS 77 AHRS This allows heading to be calculated and provides assistance during AHRS alignm
51. etin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant Page 1 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 2 SYSTEM DESCRIPTION 2 1 Equipment Descriptions The following subparagraphs provide a brief description and picture of each Garmin LRU installed or replaced by this STC For all other G1000 GFC 700 LRUs refer to the Hawker Beechcraft Bonanza Model G36 Maintenance Manual Supplement for Airplanes with Garmin G1000 Equipment Installed listed in Table 1 1 2 1 1 GDU 1040 PFD amp GDU 1045 MFD One Garmin GDU 1040 display and one GDU 1045 display is installed in the Bonanza instrument panel The GDU 104X units 10 4 inch LCD displays with 1024x768 resolution are configured as PFD and an MFD Both displays provide control and display of nearly all functions of the G1000 integrated cockpit system The PFD is located on the left side of the MFD The GDU 1045 communicates with the GDU 1040 and the GDL 69A through a high speed data bus HSDB Ethernet connection The GDU 1045 also communicates with the GTS 820 through the HSDB via the GDL 69A The GRS 77 and GDC 74A send information to the GDU 1045 via ARINC 429 data bus The display units communicate with each other and the GIA 63W units through a high speed data bus HSDB Ethernet connection This STC installation approves alternate part numbers for these displays that accept ext
52. f the LRU binds or is caught stop and remove it Check and make sure the rear plate and connectors are floating freely in the LRU rack before attempting to re install Push down on the GIA 63W handle to lock the unit into the rack Lock the handle to the GIA 63W body using the Phillips screw Reinstall the MFD No software or configuration loading is required if the removed GIA is reinstalled in it s original position GIA1 and GIA2 in their original racks This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Proceed to Section 8 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Page 6 7 190 01259 00 Rev 5 CAUTION 010 00726 07 Loader Card 006 B0858 07 Software Image is only compatible with GIA P N 011 01105 01 All installations with GIA P N 011 01105 20 must use the 006 B0858 08 Software Image 6 If a new repaired or exchange GIA is installed the correct software and configuration files must be loaded to the unit See Section 3 7 then continue to Section 8 2 7 No software loading is required if the originally installed GIA units are re installed in opposite positions GIA1 and GIA2 in opposite unit racks However configuration loading is required See Section 3 7 and then continue to the GIA 63W Test Section 8 2 Page 6 8 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 7
53. ft G36 Page 8 3 190 01259 00 Rev 5 8 1 1 SVS Pathways Installation Verification REQUIRED IF ENABLED a Apply power to the G1000 system Allow the AHRS and magnetometer systems to stabilize and align Verify that air data information becomes valid on the PFD Check the MFD AUX System Status page to verify GPS signals acquisition b Press the ALERTS softkey on the PFD and verify no database manifest or configuration errors exist c Press the PFD softkey Verify a SYN VIS softkey is shown in the lower left corner of the display d Press the SYN VIS softkey then press the SYN TERR softkey to activate the Synthetic Vision terrain display feature Verify that the traditional blue brown attitude depiction is replaced with the Synthetic Vision rendering within 2 3 minutes of activation See figures below for reference e Press the PFD softkey Press the SYN VIS softkey and verify the following softkeys are present and selectable e PATHWAY e HRZN HDG e APT SIGNS Figure 8 5 PFD Display without SVS enabled nav1118 98 gt 108 00 136 975 136 888 com NAV2 188 1 136 975 COH2 HDG NO COMP ROL NO COMP PIT NO COMP IAS NO COMP ALT NO COMP Som QA 11988 11800 KT OAT 9 C ANI AD R LCL 09 51 24 INSET SENSOR PFD XPDR IDENT TMR REF NRST ALERTS Page 8 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 Figure 8 6 PED with SVS enabled nav1 118 98 lt 108
54. gured and tested as described in Section 7 For removal and replacement instructions for all other G1000 GFC 700 equipment refer to existing Hawker Beechcraft G36 Maintenance Supplement listed in Table 1 1 CAUTION When removing and or replacing any G1000 component always ensure that aircraft power is off Unplug any auxiliary power supplies Unplug the aircraft battery Before performing maintenance it is required that the technician verify the LRU software part number and version number matches the software configuration listed in the General Arrangement Drawing 005 00620 06 listed in Table 1 1 To check an LRU software part number and or version follow the procedure defined in Section 3 7 If a faulty LRU is not reporting its software version and part number check aircraft maintenance logs for last software version loaded and verify against the General Arrangement Drawing 005 00620 06 The Software Manifest page may also be used to check part numbers and versions 6 1 GTS 820 TAS Processor CAUTION After any maintenance or modification is made to the GTS 820 TAS cables such as replacing a connector or entire cable some important considerations must be made Be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc in the Installation Manual referenced in Table 1 2 Removal 1 Gain access to the tail section 2
55. h point to ensure that 1 amp 100 milli amp is present before measuring G1000 System Maintenance Manual Hawker Beechcraft G36 Page 4 5 190 01259 00 Rev 5 Pilot Compartment e Top metal case of PFD milli volts e Top metal case of MFD milli volts e GTX 33 top milli volts e GIA 1 top milli volts e GIA 2 top milli volts e GMU metal base milli volts Ensure that at each PFD or MFD test point no more than 20 milli volts 20 mQ are present In this case voltage is equivalent to resistance Q given that precisely 1 amp reference current is present For all other LRUs see requirements below Cabin Compartment e Metal case of GPA 65 LNA PA milli volts part of GTS 820 option Empennage e Metal case of GTS 820 milli volts optional equipment Aircraft Exterior Antennas e GA58 Top traffic antenna mounting screw milli volts optional equipment e GA 58 Bottom traffic antenna mounting screw milli volts optional equipment Ensure that at each test point no more than 10 milli volts 10 mQ are present In this case voltage is equivalent to resistance Q given that precisely 1 amp reference current is present TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and 1 amp reference current Calculate the percentage difference and apply this to the voltage reading to obtain the equivalent resistance Example If the measured current is 1 2 amps 20 high from th
56. he MFD power up screen Verify the display is formatted as shown below Figure 8 1 is a format reference the illustration on the left may vary Note database versions and system software represented in the upper right corner Refer to General Arrangement Drawing 005 00620 06 drawing for the correct database and system software versions Figure 8 1 MFD Initial Power Up page format reference ETTUTOUIS Beechcraft A36 G36 Sy tom X004 36 c 2802 10 Garmin Ltd o ebe Y BEECH d DATABASE ARA A l TA Checklist File N A TTTTTT Y Basenop Lond 3 00 LEA MMAM 1 ade Terrain 2 04 em g Airport Terrain 2 04 N A 7K ot lt gt 7 All map and terrain data provided is only to be used as a general reference to your surrounding and as an aid to situational awareness PILOT PROFILE DEFAULT PROFILE Press FMS knob to change profile Press ENT or rightmost softkey GARMIN to continue l b The System number reflected in the upper right hand corner is the System Software Version It correlates to the G1000 SW Loader Card used to load the software to the system c Verify that the System Software Version is correct per General Arrangement Drawing 005 00620 06 d Press the ENT key to acknowledge the correct pilot profile on the MFD G1000 System Maintenance Manual Hawker Beechcraft G36 Page 8 1 190 01259 00 Rev 5 Figure 8 2 PFD Power Up System Annunciations La IN HG Y 10 FFLOW GPH 6 CHT OIL TEMP 2
57. he protective caps from the GTX 33 electrical connectors and rack connectors Visually inspect the electrical connectors to make sure there are no bent or damaged pins Repair any damage NOTE A handle lock mechanism is used to guide and lock the LRU into place The handle has a locking stud that engages a dogleg shaped track on the LRU rack After engaging the dogleg the handle can be pushed down and locked This action seats the LRU against the rear plate and connectors A single Phillips screw is used to fasten the lever to the LRU body Gently insert the GTX 33 into its rack The handle should engage the dogleg track CAUTION Some pressure is required to seat the LRU and lock the handle The unit should be gently worked into position using the lever Do not use excessive force inserting the LRU If the LRU binds or is caught stop and remove it Check and make sure the rear plate and connectors are floating freely in the LRU rack before attempting to re install 2 Push down on the GTX 33 handle to lock the unit into the rack 3 Lock the handle to the GTX 33 body using the Phillips screw 4 Reinstall the PFD 5 No software or configuration loading is required if the removed GTX is reinstalled This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Proceed to Section 7 1 1 6 If a new repaired or exchange GTX is installed the correct software an
58. irections Press the AP DISC button and hold while actuating the MET switch The trim wheel should stop running Release the AP DISC button The trim wheel should resume running Release the MET switch Engage the Autopilot by pressing the AP key on the MFD Press and hold the left half of the MET switch The Autopilot should command a normal disengagement and the trim wheel should stop moving and rotate freely when moved manually A disconnect tone will be heard and a flashing amber AP will be visible on the PFD Engage the Autopilot again by pressing the AP key on the MFD The pitch and roll clutches should engage resisting movement of the control wheel Press and hold the CWS switch The control wheel should now move freely when moved manually Release the CWS switch The Autopilot should hold the control wheel in its present attitude Press the AP DISC switch The Autopilot should command a normal disengagement A disconnect tone will be heard and a flashing amber AP will be visible on the PFD Verify that the control yoke is free in pitch and roll axes Engage the Autopilot again by pressing the AP key on the MFD Pull the AP SERVOS circuit breaker The Autopilot should command an abnormal disconnect consisting of a continuous disconnect tone and flashing red AP and amber YD annunciation No AFCS annunciations e g AFCS PFT Mistrim should remain on the PFD Reset the AP SERVOS breake
59. is being provided in accordance with California s Proposition 65 If you have any questions or would like additional information please refer to our web site at www garmin com prop65 CAUTION The GDU lens is coated with a special anti reflective coating that is very sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings IMPORTANT All G1000 screen shots used in this document are current at the time of publication Screen shots are intended to provide visual reference only All information depicted in screen shots including software file names versions and part numbers is subject to change and may not be up to date Page B G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 TABLE OF CONTENTS PARAGRAPH PAGE T INTRODUCTION ssc ices uge ee Saad et A Hee de e av es 1 1 121 5 CONTENT SCOPE PURPOSE E 1 1 a2 ORGANIZATIONS A A A E AEAEE 1 1 1 3 DEFINITIONS ABBREVIATIONS sansseenneenneennerinerioerinnt tetter AeneA nEn E EEEE E EEEE EEEE EEE EEEE EnEn rnern 1 2 t4 PUBLICATIONS e aea aae 1 3 10 DISTRIBUTION E EA ee ee GREEN AEA TA A A ETE 1 4 2 SYSTEM DESCRIPTION ccccccceccecececcesecceeececeeeseeneeeeaeeeeaeeeeeneeenaeeonaeeesaeeseaneeeaeeecaseeenees 2 1 21 EQUIPMENT DES
60. n servicing the G1000 system Approved software image part numbers are defined on the General Arrangement Drawing 005 00620 06 listed in Table 1 1 CAUTION Be cautious when using software loader cards during maintenance The G1000 system immediately initializes the card upon power up On screen prompts must be given careful attention in order to avoid potential loss of data 3 6 3 Software Loader Card Creation The software image is an executable self extracting file which builds the correct file structure onto an SD card for use loading software to the G1000 and GFC700 To obtain the current file follow the procedures outlined below NOTE In order to create a loader card the installer completing these procedures must be an authorized Hawker Beechcraft service center to gain access to the necessary data via the Garmin website NOTE Screenshots contained in this section is dependent upon the computer being used to download the updates and its operating system portion of the home page Enter User name and Password in the Sign In area at the left of the page Sign In Username Password By signing in you agree to the Garmin Confidentiality Agreement Reset Password b Click the Agree button on the confidentiality agreement page a Go to www garmin com and click on the Dealer Resource Center link in the lower c Select the Download Software link Page 3 6 G1000 System Maintenance Manual Hawker Beechcraft G36 Re
61. ner and may be used in lieu of the ENT key DO YOU WANT TO UPDATE SYSTEM FILES NO WILL BE ASSUMED IN 30 SECONDS h The following screen is displayed DO YOU WANT TO UPDATE SYSTEM FILES NO WILL BE ASSUMED IN 30 SECONDS UPDATING SYSTEM FILES PLEASE WAIT i New software is loaded to MFD When complete the MFD starts in configuration mode displaying the System Status page Do not remove power j Remove the loader card from MFD and insert it into the top card slot on the PFD Repeat Steps e through h for the PFD k When PFD update is complete it starts in the configuration mode Do not remove power When complete both displays should be in configuration mode with the Loader Card remaining in the top slot of PFD IMPORTANT For the rest of the software configuration procedure do not operate the MFD while loading software or configuration files unless specifically instructed to do so A failed or cancelled load may result L On PFD verify on the SYSTEM CONFIGURATION PAGE that the following LRUs are present status box is green as shown below MFD PFD GIA1 GIA2 GDL 69A G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 11 190 01259 00 Rev 5 m Verify on the SYSTEM STATUS PAGE that the following are valid Indicated by a green checkmark within the status box as shown above MFD PFD GIA1 GIA2 GDL 69A n Proceed to next section Page 3 12 G1000 System Maintenance Manual Hawker
62. nnunciation is displayed on the PFD as shown in Figure 8 8 nevil110 40 113 08 wr prs otk TRK357 134 0000 118 000 com nave 110 60 38m con Ge de Por 5537 IDNT TA INSET PFD CDI ADF DME XPDR IDENT TMR REF NRST ALERTS Figure 8 8 GFC 700 Pre Flight Test c Upon successful completion of the pre flight test a normal AP disconnect tone will sound and the PFT annunciation will clear Continue to Section 8 3 2 NOTE If the PFT annunciation turns red the test has failed and additional troubleshooting will have to be performed prior to continuing with the test NOTE If the aural alert is not heard but pre flight testing passed engage the Autopilot by pressing the AP key and disengage the Autopilot by pressing the AP key again Visual and aural disconnect alerting should occur If no alert is heard the audio interface between GIA No 1 and the audio panel should be checked If an alert is heard the audio interface between GIA No 2 and the G1000 System Maintenance Manual Hawker Beechcraft G36 Page 8 9 190 01259 00 Rev 5 audio panel should be checked 8 3 2 AFCS Switch Checks To verify that the AFCS system buttons and switches are operating correctly perform the following checks a Actuate both halves of the Manual Electric Trim MET switch in the same direction The trim clutch should engage and the trim wheel should run in the selected direction Check operation in both d
63. nspect the connector for damaged pins 2 Reattach the unit to the mounting bracket reusing exiting hardware 3 Reconnect the electrical connector and ensure it is locked in place If GRT or GRC is replaced system must be reconfigured in accordance with instructions in Section 3 7 4 6 4 1 GRC 10 Remote Control Battery Replacement If the unit does not turn on or the battery level indicator on the display shows no bars replace the batteries To replace the batteries in the GRC 10 Remote Control remove the back cover of the remote Insert two fresh AA batteries with the orientation as shown in the diagram in the battery compartment Both batteries should be replaced with fresh batteries at the same time Figure 6 1 Battery Compartment WARNING Do not use lithium batteries in the GRC 10 NOTE Remove batteries when the GRC 10 is stored for extended periods CAUTION When replacing batteries use only new or fully charged batteries Do not mix new and old batteries as this can cause battery leakage and damage to the unit Do not mix battery types i e rechargeable with non rechargeable CAUTION Remove batteries if the GRC 10 will not be in use for several months Storing batteries in the unit for prolonged periods may result in leakage and damage to the battery compartment G1000 System Maintenance Manual Hawker Beechcraft G36 Page 6 3 190 01259 00 Rev 5 NOTE Failure of the GRC 10 i e dead batteries has no imp
64. omatically loads the selected files in the correct sequence to the LRUs G1000 System Verification After software is loaded to the system the technician verifies that each LRU reports the correct version and software part number and the configuration is correct on the Airframe Configuration page Figure 3 7 Software Configuration Overview Page 3 10 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 7 1 MFD amp PFD Software Load IMPORTANT When replacing a display it is REQUIRED to update the system files with the new display in the MFD slot regardless of intended final configuration PRIOR to loading configuration files Failure to do so could result in loss of any existing calibration configuration data a Apply power to the G1000 by doing the following Connect a ground power unit to the external power receptacle and turn on the ground power unit b Turn on the BAT 1 BAT 2 and AVIONICS MASTER switches At this moment all G1000 equipment is receiving power c Pull the MFD and PFD circuit breakers d Insert the loader card into the MFD top card slot e While holding the ENT key on MFD restore power by closing the MFD circuit breaker f When the words MAA EU appear in the upper left corner of MFD release the MFD ENT key g Press the MFD ENT key to acknowledge the following prompt NOTE A softkey labeled YES appears in the lower right cor
65. on a RED E ine A A 8 9 LIST OF TABLES TABLE PAGE Table 1 1 Required Documents 1 3 Table 1 2 Reference PublicatiONS ooiononoconnnninic KEEN 1 3 Table 3 1 Required Loader Cards cocccccccccccccccconccconononono nono non 3 5 RR Card A RE eae hee ae Gat at ee es Eura E ink 3 19 Table 4 1 Maintenance Intervalo a 4 3 Table 5 1 SVS Troubleshooting is ics ete Biches Seay Sse nate teen ey betes eae 5 1 Table 5 2 SVS Alert leese Eeer eege Eeer 5 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Page iii 190 01259 00 Rev 5 This page intentionally left blank Page iv G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 1 INTRODUCTION 1 1 Content Scope Purpose This document provides Instructions for Continued Airworthiness ICA for the Garmin G1000 integrated avionics as installed in the Hawker Beechcraft G36 as modified under STC SA1595WI D This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23 1529 and Appendix G Information in this document is required to maintain the continued airworthiness of the G1000 This document is intended to be used in conjunction with the existing Hawker Beechcraft Bonanza 36 Maintenance Manual and the Hawker Beechcraft Bonanza Model G36 Maintenance Manual Supplement listed in Table 1 1 1 1 1 Applicability This document applies to all G36 aircraft that have been modified in accordance with STC SA1595WI D The
66. procedures to be performed upon completion of maintenance of the G1000 system G1000 System Maintenance Manual Hawker Beechcraft G36 Page 1 1 190 01259 00 Rev 5 1 3 Definitions Abbreviations AFCS Automatic Flight Control System CFR Code of Federal Regulations DME Distance Measuring Equipment VHF Very High Frequency AC Advisory Circular AFMS Airplane Flight Manual Supplement FPGA Field Programmable Gate Array FPM Flight Path Marker HSDB High Speed Data Bus GDU Garmin Display Unit GDC Garmin Air Data Computer GTS Garmin Traffic System GRT Garmin Remote Transceiver GTX Garmin Transponder GDL Garmin Datalink GMU Garmin Magnetometer GA Garmin Antenna GIA Garmin Integrated Avionics GMA Garmin Audio Panel GPS Global Position System GRS Garmin AHRS HSI Horizontal Situation Indicator LCD Liquid Crystal Display LRU Line Replaceable Unit MDL Master Drawing List MFD Multi Functional Display PFD Primary Flight Display STC Supplemental Type Certificate SVS Synthetic Vision System TCAS Traffic Collision Avoidance System TAWS Terrain Awareness and Warning System WAAS Wide Area Augmentation System 1 3 1 Units of Measure Unless otherwise stated all units of measure are English units Page 1 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 1 4 Publications The following documents are required by this maintenance manual to perform maintenan
67. proper Hawker Beechcraft Aircraft Company standards 4 2 2 Required Tools The following tools are needed to perform maintenance tasks on GTS 820 equipment e Outdoor line of site to GPS satellite signals or GPS indoor repeater e TIC TR 220 Test set or equivalent e Headset microphone e Ground Power Unit Capable of supplying 28 Vdc e Laptop with Garmin GTS 8XX Installation software installed The Installation software is available for download from the dealers only portion of the Garmin website www garmin com G1000 System Maintenance Manual Hawker Beechcraft G36 Page 4 1 190 01259 00 Rev 5 The following tools are needed to perform maintenance tasks on GMU 44 equipment e 2 non magnetic Philips screw driver The following tools are needed to perform maintenance tasks on GTX 33ES transponder e Calibrated pitot static tester e Calibrated transponder ramp tester The following tools are needed to perform maintenance tasks on GRT 10 equipment e 3 32 Hex tool e 2 Philips screw driver The following tools are needed to perform maintenance tasks on GDU 104X equipment e 3 32 Hex tool For any other tools required to maintain the G1000 GFC 700 refer to the existing Hawker beechcraft ICA listed in Table 1 1 Page 4 2 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 4 3 Maintenance Intervals Table 4 1 below shows the systems and equipment installed by this STC that must undergo any maint
68. r and then press the AP DISC switch to silence the autopilot abnormal disconnect tone Wait for the pre flight test sequence to successfully complete again Press the GO AROUND button GA should be annunciated on the PFD for both pitch and roll modes and the command bars should indicate a wings level climb to 7 degrees Page 8 10 Rev 5 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 V W Press the FD key on the MFD to deactivate the Go Around mode and reset the Flight Director Center the trim wheel if it is not already centered Press the AP key to engage the Autopilot Press the CWS button and verify there is no residual force on the control wheel for the pitch axis Extend the flaps to approach position The trim wheel should immediately run in the NOSE DOWN direction Retract the flaps The trim should immediately run in the NOSE UP direction Disengage the Autopilot by pressing the AP DISC switch 8 3 3 Manual Electric Trim Speed Check a b Run Manual Electric Trim MET in one direction until it runs against the stop Using a stop watch or equivalent device time the trim speed from one end of travel to the opposite stop The elapsed time should measure 13 5 seconds for each direction 8 3 4 Autopilot Operation Checks a Push the HDG knob in to synchronize the heading bug to the present aircraft heading on the HSI Engage the Autopilot by pressing the AP ke
69. re a Remove power from the PFD and MFD by pulling the PFD and MFD circuit breakers b Install a GDU 10XX Terrain Data Base Card 010 00330 43 in the bottom slot of the PFD and MFD c This completes the installation of the Terrain Data Card 3 9 2 Aviation Database Loading a Remove power from MFD b Insert an SD card containing the latest cycle Jeppesen aviation database data supplied by Jeppesen into the top slot of MFD c Apply power to MFD The following prompt is displayed in the upper left corner of MFD DO YOU WANT TO UPDATE THE AVIATION DATABASE PRESS CLR FOR NO AND ENT FOR YES YOU HAVE 289 SECONDS BEFORE NO IS RETURNED d Press the MFD ENT key to confirm the database update e A prompt will be displayed Press ENT for YES f After the update completes MFD starts in normal mode g Rotate FMS knob to select AUX SYSTEM STATUS page h Press the SYNC DBS softkey on the MFD i Acknowledge the prompt Enable automatic database synchronization by pressing the ENT key on the MFD j The aviation databases are now updated k Confirm that the correct update cycle is loaded at the power up page of the MFD Page 3 18 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 3 10 SVS Pathways Activation option This section provides the requirements and instructions necessary to enable the G1000 Synthetic Vision Pathways feature Baseline Software The Garmin Synthe
70. re part number and version matches the information in General Arrangement Arrangement drawing SYSTEM GDC1 GDC1 FPGA GDL69 GEA1 GFC CERT GIA1 GFC CERT GIA2 GFC CERT PC GFC CERT PM GFC CERT PTC GFC CERT PT M GFC CERT RC GFC CERT RM GFC CERT YC GFC CERT YM GIA1 GIA1 AUDIO NAV 2 BB SYSTEM GIA2 GIA2 AUDIO GMA1 GMU1 GMU1 FPGA GRS1 GRS1 FPGA GRS1 MV DB GSA PTCH CTL GSA PTCH MON GSA PTCH TRM C GSA PTCH TRM M GSA ROLL CTL GSA ROLL MON GSA YAW CTL GSA YAW MON NAV 2 FPGA G1000 Update with Options G36 005 00620 06 General SYSTEM SW VER OK GTS GTS AUDIO GTS FPGA GTS MAGNETIC VA GTS RGN LIST GTX1 MFD1 MFD1 FPGA PFD1 PFD1 FPGA COM 1 COM 2 NAV 1 NAV 1 BB NAV 1 FPGA NAV 2 Only applicable to those installations using GIA 63W P N 011 01105 20 Page 3 16 Rev 5 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 b De activate the cursor c Remove loader card and power down aircraft IMPORTANT If any software version and or part number does not match or is not successfully loaded do not continue with post installation procedures Troubleshoot and resolve the issue before continuing G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 17 190 01259 00 Rev 5 3 9 Aviation Database Loading Procedures 3 9 1 Terrain Data Card Loading Procedu
71. rport Supplemental Data plus Garmin Safe Taxi and NOS Flight Charts Remains in the bottom slot of the PFD and MFD 010 00330 50 ChartView Enable Card see note 010 00330 51 TAWS Enable Card see note 010 00330 54 SVS Enable Card see note 1010 00726 07 Loader card contains the 006 B0858 07 software image and is only compatible with aircraft that have GIAG3W P N 011 01105 01 installed 2 010 00726 08 Loader card contains the 006 B0858 08 software image 3010 00726 09 Loader card contains the 006 B0858 09 software image 3 6 2 G1000 Software Image All software and configuration files were certified by Garmin as part of the FAA approved Type Design data Approved software and hardware definitions are defined on the General Arrangement drawing 005 00620 06 G1000 software and configuration files are controlled via the approved software image part number listed on the General Arrangement drawing 005 00620 06 This software image is loaded into the G1000 using a software loader card NOTE Installers may obtain the G1000 software image already on a loader card by ordering the Garmin Part Number listed in the General Arrangement Drawing 005 00620 06 referenced in Table 1 1 G1000 System Maintenance Manual Hawker Beechcraft G36 190 01259 00 Page 3 5 Rev 5 IMPORTANT To satisfy the requirements of this STC it is critical that the technician install correct software image part number whe
72. ry Mode 222 cccccccsececcccceeeeeeeedeeeneeeeeeeeeeeeeeeeneeeeeeeeeeeeeeeenens 3 2 Figure 3 9 COnngQuration StAtUs cla it A AAA A Sea 3 4 Figure 3 6 Data Transmission Indicators neeeneeeeee eneee eneen neen ne nnne ennnen nenn nn ennnen Ennn nnen nanne 3 4 Figure 3 8 Software Configuration Overview ooococccononoooncconccccnnnnnnnonnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnns 3 10 Figure 3 9 Configuration Software Load Page 3 13 FIQUIE 3 10 le lei NEE 3 14 Figure 5 1 GTS 820 Mating Connector cuota aa o dee Edge 5 5 Figure 5 2 GTS 820 Mating Connector acia iaa 5 5 Figure 5 3 GPA 65 Connector eier deg deg ba 5 6 Figure 5 4 GRT 10 Mating Connectors csck scale gek iecaess ce cicedben stag oa aaadinticdetesdavsaacetbacdonbeaegecdebe 5 6 Figure 6 1 Battery Compartment ooocccn nononicocococonononannnccccnnonn ocn rn mannas 6 3 Figure 8 1 MFD Initial Power Up page format reference ooocoooocococcccncccccccconanannncncncnnnnnnnns 8 1 Figure 8 2 PFD Power Up System Annunciations oooooooocccccn nccccconaoncnnnnnnnnnnnnnnnna no ncnnnnnnnnnnnnns 8 2 Figure 8 3 Normal Display without SVS enabled 8 2 Figure 8 4 Normal Display with SVS enabled 8 3 Figure 8 5 PED Display without SVS enabled enk 8 4 Figure 8 6 PFD with SVS enabled WEE 8 5 Figure 8 7 AUX GPS STATUS Page MFD ccecccccceeeeeeeeeesenecceeeeeeeeeeeseneeeeeneeeeeneneaees 8 6 Figure 8 8 GFC 700 Pre Flight Test c
73. scenario NOTE If using the TIC TR 220 test set a stationary intruder is programmed by not starting the scenario as programmed e Intruder Start Distance 2 nm e Intruder Start Altitude 50 000 ft i Set the intruder type as ATCRBS j Verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co altitude read as 00 above a filled diamond indicating proximate traffic k Toggle intruder traffic to standby or off Reposition ramp test set and directional antenna to a starboard position of 90 degrees m Reengage the same intruder scenario as above n Verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the correct bearing of approximately 90 degree azimuth at 2 NM and co altitude G1000 System Maintenance Manual Hawker Beechcraft G36 Page 7 11 190 01259 00 Rev 5 o Toggle intruder traffic to standby or off p Reposition ramp test set and directional antenna to an aft position of 180 degrees q Reengage the same intruder scenario as above r Verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the correct bearing of approximately 180 degree azimuth at 2 NM and co altitude s Toggle intruder traffic to standby or off t Reposition ramp test set and directional antenna to a port position of 270 degrees u Reengage the same intruder scenario as above v Verify a target is annunciated on th
74. tate the large FMS knob To change the contents of a highlighted data field rotate the small FMS knob This action either brings up an options menu for the particular field or in some cases allows the operator to enter data for the field To confirm a selection press the ENT key To cancel a selection press the small FMS knob in again deactivating the cursor The CLR key may also be used to cancel a selection or deactivate the cursor 3 2 G1000 Normal Mode To start the G1000 system in Normal Mode 1 With a ground power unit connected to the external power receptacle set the L and R BAT switch to ON 2 Set the AVIONICS MASTER switch to ON The G1000 system is now powered in the normal mode In the normal operating mode data fields that are invalid have large red X s through them A valid field does not display a red X Allow the displays to initialize for approximately one minute The PFD and MFD will function as specified in the Cockpit Reference Guide for the Hawker Beechcraft G36 when the system has been correctly installed and configured G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 1 190 01259 00 Rev 5 3 3 Figure 3 3 Normal Mode without SVS enabled EO O e W E ERD Figure 3 2 Normal Mode with SVS enabled 1109 00 108 00 os 136 975 118 000 cow 188 15 136 975 om Reversionary Mode Reversionary mode allows for display of information related to s
75. the MFD Press the ENT key or the YES softkey to update system files if prompted Repeat steps a through c on the PFD using the PFD circuit breaker to apply power CAUTION The Configuration Mode contains certain pages and settings that are critical to aircraft operation and safety These pages are protected and cannot be modified unless the technician is properly authorized and equipped However most protected pages are viewable to allow system awareness for troubleshooting NOTE For a complete description and breakdown of each Configuration Mode page refer to the G1000 System Maintenance Manual listed in Table 1 2 3 5 Configuration Mode Navigation Using the FMS knob a user can navigate through different pages and page groups in the Configuration Mode For complete description and breakdown of each page refer to the G1000 Line Maintenance amp Configuration manual System Page Group 1 System Status 6 File Manager 11 System Setup 2 Time Configuration 7 Diagnostics Terminal 12 Manifest Configuration 3 Lighting Configuration 8 OEM Diagnostics 13 Maintenance Log 4 System Audio 9 System Configuration 5 System Upload 10 System Data Path Configuration GDU Page Group 1 Serial Configuration 4 Diagnostics 7 Airframe Configuration 2 CDU Status Page 5 Ethernet Test 8 TAWS Configuration 3 Key Test 6 Alert Configuration GIA Page Group 1 Serial Configuration 3 GIA I O Configuration 5 GIA Status P
76. there are no cracks in the antenna no deformation in the mounting structure and that all sealing fillets around the antennas are in good condition If the antenna is broken cracked dented etc then it must be replaced If the attachment is not secure re work the installation and complete electrical bonding test based on installation requirements In the event the antenna seal shows sign of damage or decomposition re seal and complete the Electrical bonding test to installation requirements 4 3 2 Coax Cable Maintenance CAUTION After any maintenance or modification is made to the GTS 820 TAS cables such as replacing a connector or entire cable some important considerations must be made Page 4 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 When making any repairs to GTS coax cables installed under this STC be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc in the Installation Manuals referenced in Table 1 1 4 3 3 Electrical Bonding Test The following bonding tests are provided for GTS 820 equipped G36 aircraft as a requirement beyond what is given in the aircraft maintenance manual NOTE It is recommended that these tests be conducted after visual inspections of each zone to minimize access requirements 4 3 3 1 Requirements All GTS equipment must be installe
77. tic Vision and Pathways feature in the Hawker Beechcraft requires GDU software version 11 01 or later to be installed with the G36 specific software configuration image prior to activation See the STC Master Drawing List for specific installation requirements Database Cards The Garmin Synthetic Vision and Pathways feature requires 9 arc second high resolution terrain databases to function Each G1000 display must be equipped with the P N 010 00330 43 Terrain Obstacle SafeTaxi database card installed in the lower slot SVS Pathways Enable Card The following enable card is required to activate the SVS Pathways feature for G1000 G36 installations Table 3 2 SVS Enable Card QTY GARMIN PART NUMBER DESCRIPTION 1 010 00330 54 Synthetic Vision amp Pathways Enable 1 PFD IMPORTANT When the SVS Pathways option is enabled for the first time the G1000 writes its unique system ID to the physical card and locks the files to this unique ID This prevents the SVS Pathways enable card from ever being used to activate the SVS Pathway feature in other G1000 systems This card MUST be kept with the aircraft for situations where SVS Pathways must be re activated G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 19 190 01259 00 Rev 5 3 10 1 SVS Activation Procedure Activate the SVS Pathways feature by performing the following steps a Apply power to the G1000 system b Pull the MFD and PF
78. ual Hawker Beechcraft G36 Page 2 3 190 01259 00 Rev 5 Figure 2 6 G36 Traffic Antenna 2 1 5 XM remote control system The optional XM remote control system consists of the GRT 10 transceiver and the GRC Remote Control This system allows for remote control of the XM satellite radio function provided by the existing GDL 69A The GRT 10 is installed behind the instrument panel on the top of the MFD system rack It is powered from the existing 3 amp Datalink circuit breaker off the 28 Vdc Avionics Bus Figure 2 7 GRT 10 Transceiver Page 2 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 Figure 2 8 GRC 10 Remote Control 2 1 6 GIA 63W Integrated Avionics Unit 2 Two Garmin GIA 63W Integrated Avionics Units IAUs contain the VHF COM NAV receivers WAAS GPS receiver Flight Director and system integration microprocessors The GIAs also serve as a communication interface to all other G1000 LRUs in the system Each GIA 63W communicates directly with the on side GDU display using a HSDB Ethernet connection Both GIAs are mounted in the systems rack behind the MFD GIA 1 is powered through Bus 2 and immediately powers up when the battery 1 or Battery 2 master switch is turned on GIA 2 receives power through the Avionics Bus and powers up when the avionics master switch is turned on Figure 2 9 GIA unit G1000 System Maintenance Manual Hawker Beechcraft G36 Page 2 5 190 01259 00 Rev
79. utopilot still engaged and the CWS button pressed move the control wheel to its aft limit Release the CWS button and apply continuous forward pressure slowly moving the control wheel After 1 or 2 seconds the trim wheel should begin moving in a trim up direction Grip the control wheel and press the CWS button Trim motion should stop Move the control wheel to the forward limit and release the CWS button Slowly pull back on the control wheel After a similar delay the trim wheel should begin to trim down Relieve pressure on the wheel and the trim motion should stop Verify that the trim wheel is free to turn Hold the control wheel and press the AP DISC switch to disconnect the Autopilot Engage VS mode by pressing the VS key on the MFD Verify the PFD display VS in green and indicates a pitch reference of 0 FPM Press the ALT key on the MFD and verify that the ALT annunciation is displayed in green on the PFD with an altitude reference equal to the aircraft altitude within the nearest 20 feet Press the FD key and verify that the mode annunciations and command bars are removed from the display NOTE To fully verify the yaw damper function it must be checked in flight w Press the YD key and verify that the YD annunciation is displayed in green on the PFD x Press the rudder pedals and verify that the yaw servo is resisting movement of the rudder pedals y Press the AP DISC button and
80. v 5 190 01259 00 Dealer Resource Home Popular Tasks a L 4 a Media Gallery Find Marketing Pricing amp Download Find Technical Memos Product Details Software Publications d Select the Software Downloads hyperlink on the left hand edge of the page e Scroll down until the appropriate software image is visible Note the software image version number will be listed in the name column Select the appropriate software image based upon the information provided in Garmin GA Drawing 005 00606 12 f Select the Download hyperlink and save the file to the local hard drive Note part number shown below is for reference only Opening 006 B0858 08_04 exe g Double click the exe file that was downloaded The following window will pop up on the screen Click Yes G1000 Software Update 006 B0858 08_04 exe 23 o Ee T e h Ensure that there is an empty SD card in the card reader and then click Next G1000 System Maintenance Manual Hawker Beechcraft G36 Page 3 7 190 01259 00 Rev 5 G1000 Software Update GARMIN NOTE When the extraction begins the program automatically deletes all current files on the SD card and copies the selected files to it regardless of the file format on the SD card Ensure files are not necessary or card is empty before proceeding 4 61000 Software Update GARMIN Ensure the card and correct drive letter is used and click next A window will pop up onto th
81. verify that a flashing yellow YD annunciation is displayed on the PFD z Verify that the rudder pedals move freely Page 8 12 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 8 4 Maintenance Records After complying with the procedures contained in this ICA and any additional return to service procedures contained in the Hawker Beechcraft Maintenance Manual and G36 Maintenance Supplement listed in Table 1 1 the aircraft may be returned to service Record the following information in appropriate aircraft maintenance logs e Part number of the G1000 software loader card used to perform software loading or software updates e Record part and serial numbers of any LRU which was replaced e Record any database updates which were performed during maintenance e Any other applicable information related to the maintenance work performed on the aircraft G1000 System Maintenance Manual Hawker Beechcraft G36 Page 8 13 190 01259 00 Rev 5
82. y GDL 69A is powered on Verify batteries are installed GRC 10 will not power on Install fresh batteries See Section 7 3 5 5 System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation Desired Operation Criteria for Success e SW Loader Card must be inserted in top slot for each display to be loaded e CLR amp ENT keys must be held during power Load Software to MFD or PFD Displays up of display e Power on only one display at a time during software loading e SW Loader Card must be inserted in top slot Load AIRFRAME SYSTEM MFD PFD and of PFD MANIFEST configuration files to MFD and PFD e PFD and MFD must be powered on e PFD and MFD must have correct software e SW Loader Card must be inserted in top slot of PFD Load Software Configuration files to GIA 63Ws Page 5 4 G1000 System Maintenance Manual Hawker Beechcraft G36 Rev 5 190 01259 00 G1000 system must be powered on PFD and MFD must have correct software PFD and MFD must be successfully configured with AIRFRAME SYSTEM MANIFEST MED and PFD configuration files Load Software Configuration files to SW Loader Card must be inserted into PFD top slot GMA 1347 P G1000 must be powered on GDC 74A PFD and MFD must have correct software GEA 71 and configuration settings GRS 77 software only GIA 63Ws must have correct software GMU 44 software only GIA
83. y on the MFD Select Heading mode by pressing the HDG key on the MFD The command bars should be level and the control wheel should be stationary very slow movement acceptable due to the aircraft not being perfectly level Turn the HDG knob to the left and verify that the command bars move to the left and the control wheel turns to the left counter clockwise Turn the HDG knob to the right and verify that the command bars move to the right and the control wheel turns to the right clockwise Push the CWS button and pull the control wheel to the middle of the pitch control range Release the CWS button Verify that the Autopilot clutches re engage and hold the wheel stationary Holding the control wheel lightly press the NOSE UP key on the MFD twice to increase the pitch reference Verify that the command bars move up approximately one degree and the control wheel begins moving aft Hold the control wheel and press the CWS button re synchronizing the pitch reference and re centering the control wheel G1000 System Maintenance Manual Hawker Beechcraft G36 Page 8 11 190 01259 00 Rev 5 Release the CWS button and verify that servo clutches re engage before releasing the control wheel Press the NOSE DN key on the MFD twice Verify that the command bars command down and the control wheel begins moving forward Hold the controls and press CWS to re center the command bars and stop control wheel movement With the A

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