G1000 / GFC 700 System Maintenance Manual Hawker Beechcraft Model 200/B200 Series King Air Contains Instructions For Continued Airworthiness For STC SA01535WI-D 190-00915-01 July 2012 Revision 6
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TABLE OF CONTENTS PARAGRAPH PAGE 1 INTRODUCTION ............................................................................................................................ 1-1 1.1 CONTENT, SCOPE, PURPOSE ........................................................................................................ 1-1 1.2 ORGANIZATION............................................................................................................................ 1-3 1.3 DEFINITIONS/ABBREVIATIONS .............
3.35 3.36 3.37 3.38 3.39 AIRCRAFT REGISTRATION NUMBER ENTRY .......................................................................... 3-47 SPLASH SCREEN LOADING ..................................................................................................... 3-48 NAVIGATION DATABASE LOADING ....................................................................................... 3-49 CONFIGURATION OF NAVIGATION MAP FOR TRAFFIC SYSTEM.............................................
6 EQUIPMENT REMOVAL & INSTALLATION .......................................................................... 6-1 6.1 GDU 1040A/1500........................................................................................................................ 6-2 6.2 GMA 1347D AUDIO PANEL ........................................................................................................ 6-2 6.3 GIA 63W INTEGRATED AVIONICS UNITS ..........................................................................
7.17 7.18 7.19 7.20 7.21 7.22 7.23 7.24 7.25 7.26 7.27 7.28 7.29 8 CHARTVIEW FUNCTIONAL CHECK ........................................................................................ 7-38 SAFETAXI FUNCTIONAL CHECK ............................................................................................ 7-39 DME FUNCTIONAL CHECK .................................................................................................... 7-40 ADF FUNCTIONAL CHECK ..................................
LIST OF ILLUSTRATIONS FIGURE PAGE Figure 2-1, Display Units ........................................................................................................................... 2-1 Figure 2-2, Audio Panel ............................................................................................................................. 2-2 Figure 2-3, AFCS Controller .....................................................................................................................
Figure 3-31, Stormscope Configuration.................................................................................................. 3-33 Figure 3-32, ESP Support Configuration ................................................................................................. 3-34 Figure 3-33, ESP Support Configuration ................................................................................................. 3-35 Figure 3-34, GDL 59 Configuration ..................................................
Figure 7-5, Aircraft Registration.............................................................................................................. 7-12 Figure 7-6, Engine Run-Up Test Page ..................................................................................................... 7-24 Figure 7-7, Normal Mode AHRS Check ................................................................................................ 7-25 Figure 7-8, Low Speed Awareness Band Symbolization..............................
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1 INTRODUCTION 1.1 Content, Scope, Purpose This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control System (AFCS) as installed in the Hawker Beechcraft Model 200/B200 series King Air, under STC SA01535WI-D. This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and Appendix G.
IMPORTANT! If the technician is unsure of an aircraft’s STC configuration, perform the following: After acknowledgement of the splash screen, use the FMS knob on the GCU 477 controller to go to the AUX – SYSTEM STATUS page on the MFD. In the AIRFRAME section (upper right corner,) the display shows the current G1000 airframe configuration and system software version number.
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 installing the G1000 integrated cockpit system in the 200/B200 Series King Air. An overview of the G1000 and GFC 700 system interface is also provided. Section 3: G1000 Control & Operation Presents basic control and operation information specifically tailored to maintenance practices.
1.
1.4 Publications The following documents are required by this maintenance manual to perform maintenance. 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.
The following publications are recommended to be on hand during the performance of maintenance activities.
2 SYSTEM DESCRIPTION 2.1 Equipment Descriptions 2.1.1 GDU 1040A PFD (2) & GDU 1500 MFD Two Garmin GDU 1040A displays and one GDU 1500 display are installed in the King Air instrument panel. The GDU 1040A units, 10.4 inch LCD displays with 1024x768 resolution, are configured as PFD 1 and PFD 2; the GDU 1500 unit, a 15 inch LCD display with 1024x768 resolution, is configured as a MFD. All displays provide control and display of nearly all functions of the G1000 integrated cockpit system.
2.1.2 GMA 1347D Audio Panel (2) The Garmin GMA 1347D Audio Panel integrates NAV/COM digital audio, intercom system and marker beacon controls. The 200/B200 installation includes two GMA 1347D panels. The GMA 1347D panels provide control of all cockpit intercom/mic systems as well as NAV/COM/ILS audio. The units also provide display reversion mode control through a large red button.
2.1.4 GCU 477 FMS Control Unit The GCU 477 functions as the primary control interface to the GDU 1500 MFD. The GCU 477 provides alphanumeric, softkey, and flight planning function keys used to interface with the G1000; the MFD does not possess any knobs or controls other than softkeys. The GCU 477 is powered by the Essential Bus. The GCU 477 also provides the crew with the added functionality of tuning their receivers via the GCU as well as the PFD.
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 1040A display using a HSDB Ethernet connection. Both GIAs are located remotely in the nose equipment bay.
2.1.7 GEA 71 Engine/Airframe Unit (2) The Garmin GEA 71 Engine/Airframe Units provide engine/airframe data to the G1000 system. Data received from transducers/sensors is processed and sent to GIA 63Ws (via RS-485 digital interface), and subsequently to the GDU 1500 MFD. Engine parameters are normally displayed on the MFD. In the event of MFD failure, the engine parameters can be displayed on PFD 1 and/or PFD 2 using display reversion.
2.1.8 GDC 74B Digital Air Data Computer (2) The Garmin GDC 74B computers compile information from the pitot/static system and various outside air temperature (OAT) and awareness sensors and provide digital air data computations to the G1000 system. The GDC 74B communicates with the GIA 63W, GDU 1040A, and GRS 77 using ARINC 429 digital interface. The unit is mounted behind the instrument panel.
2.1.10 GRS 77 Attitude & Heading Reference System (2) The Garmin GRS 77 AHRS units provide attitude and heading information to the G1000 system. The units, mounted in the nose equipment bay, contain advanced tilt sensors, accelerometers, and rate sensors. The unit interfaces with the GDC 74B and GMU44 Magnetometer and utilizes GPS signals from the GIA 63Ws. Actual attitude and heading information is sent using ARINC 429 digital interface to both GDU 1040As and GIA 63Ws.
2.1.12 GDL 69A Datalink The GDL 69A provides the interface to the GWX 68 weather radar and optional GDL59 wi-fi datalink by acting as a communications hub between the MFD and GWX 68 and GDL 59 via HSDB. The GDL 69A also provides XM Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A is mounted behind the instrument panel. Power to the GDL 69A is received from the Avionics No. 2 bus.
2.1.14 GSR 56 Satellite Receiver (optional) The GSR 56 provides airborne low speed data link and voice communication capability to Garmin Integrated Flight Deck installations. The GSR 56 contains a transceiver that operates on the Iridium Satellite network. The GSR 56 interfaces directly to the GDL 59 via an RS-232 interface. The GSR 56 is located in the aft cabin floor area, just forward of the cabin door. The GSR 56 is powered from the Avionics No. 2 bus. Figure 2-14, GSR 56 Satellite Receiver 2.1.
2.1.17 GSA 80 Servos and GSM 85A/86 Servo Gearboxes (4) The Garmin GFC 700 AFCS uses GSA 80 high torque servos to automatically control aircraft pitch, roll, yaw damper/turn coordination and pitch trim. The pitch trim variant of the GSA 80 is a high speed servo actuator. The GSA 80 contains a motor-control and monitor circuit board, as well as a solenoid and a brushless DC motor. The GSA 80 servo receives serial RS-485 data packets from the GIA 63Ws.
2.1.20 Standby Airspeed Indicator A Standby Airspeed indicator, Aerosonic part number 25030-0184, is installed between PFD 1 and the MFD. Due to varying airspeed marking requirements, four marking options are used. To determine the appropriate option for a specific aircraft configuration, refer to the General Arrangement drawing, Garmin Document 005-00421-03.
2.3 Electrical Power Distribution This airplane uses a multi-bus system, as detailed below and in Figure 2-18. This Figure shows the system post installation of this STC. Although this STC made several bussing changes to the distribution system, the core electrical generation and distribution system remains unchanged from the basic airplane design. Figure 2-19 shows the power sources for all equipment used by this STC. Each bus used or modified by this installation is described below.
Figure 2-18, 200/B200 Electrical Distribution (Post G1000 STC) G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air 190-00915-01 Page 2-13 Revision 6 N O.1 AV IONICS BUS L EFT S T/GEN A VIONICS MSTR L GEN L IN E CONTAC TOR F WD ELECT RIC HEAT PILOT WIN DSHIELD ANT I-ICE E XT P OWER R ECEP TACLE L EFT GE NE RA TOR BUS S TANDBY B ATTERY C ON DENSER BLOWER PWR E XT PWR S TB Y IN STRU L IGHTS S TBY ATT S TB Y ALTM H OT B ATTE RY BUS N O.4 DU AL FED BUS N O.
DUAL FED BUS 2 DUAL FED BUS 1 ESS BUS SEC L BLEED AIR WARN PFD NO.1 SEC PFD/GIA NO.1 FAN AURAL WARN ADC NO.1 SEC LANDING GEAR WARN VOICE RCDR L ENG INSTR PWR L GEN CTRL PFD NO.2 GIA NO.1 SEC ANNUNCIATOR PWR AHRS NO.
L/H PITOT MAST R/H PITOT MAST #2 AIR DATA COMPUTER OAT PROBE #1 AIR DATA COMPUTER FORWARD PRESSURE BULKHEAD DATA BUS OAT PROBE PILOT PFD MFD COPILOT PFD STANDBY ALTIMETER STANDBY AIRSPEED DRAIN DRAIN DRAIN ALTERNATE STATIC SELECTOR VALVE ALTERNATE STATIC PORT BOTTOM TOP BOTTOM TOP AFT PRESSURE BULKHEAD L/H STATIC PORTS R/H STATIC PORTS 2.
2.5 Shield Block Grounds The connectors on Garmin G1000 LRUs utilize the Shield Block grounding system to provide necessary ground reference to wire shielding and/or transducers. The shield block termination method allows multiple grounds to be terminated directly to a block mounted to the connector backshell assembly. Shielding and grounding requirements for all other LRUs and connectors are shown in the respective install drawings. 2.
3 G1000 Control & Operation All control and operation of G1000 equipment as normally used in flight occurs through the PFDs, MFD, GMC 710, GCU 477 and GMA 1347D audio panel. Figure 3-1 through Figure 3-6 identify various interface buttons for these units. 3.1 GDU 1040A and GDU 1500 Displays Figure 3-1 and Figure 3-2 provide identification of the GDU 1040A PFD and GDU 1500 MFD controls.
Figure 3-2, GDU 1500 Control Interface 3.1.1 Softkeys Some pages have commands or selections that are activated by the GDU 1040 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. Figure 3-3, G1000 Softkeys 3.1.2 FMS Knob The FMS knob is the primary control for the G1000 system.
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 GCU 477 - MFD Controller The MFD controls are located on the GCU 477 as show in Figure 3-4. Figure 3-4, MFD Controls (GCU 477 shown) 3.3 GMC 710 - AFCS Controls The dedicated AFCS controls located on the GMC 710 are discussed in detail in the G1000 CRG.
3.4 GMA 1347D Audio Panel Figure 3-6 provides the audio panel controls.
3.5 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 BAT switch to ‘ON’. The following G1000 equipment is powered: • PFD displays & MFD display • GRS 77 AHRS Units • GDC 74B Air Data Computers • GIA 63W Integrated Avionics Units • GEA 71 Engine/Airframe Units • GCU 477 FMS Control Unit • GMC 710 Autopilot Control Unit 2. Set the AVIONICS MASTER switch to ‘ON’.
3.6 Reversionary Mode Reversionary mode allows for display of information related to safe flight in the event of a display communication or hardware failure. For software version 0985.04 and later, the pilot’s PFD automatically goes into reversionary mode when communication to the MFD is lost. Manual reversionary mode allows the operator to force the pilot or copilot’s PFD into reversionary mode by pressing the large red button labeled ‘DISPLAY BACKUP’ on the respective GMA 1347D audio panel.
3.7 Configuration Mode Overview Throughout this document, references are made to the PFD1, PFD2 and/or MFD being in configuration mode. 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 G1000 system in configuration mode, follow these steps: 1.
Data can be manually copied from one column to the other (and consequently from PFD memory to the LRU memory and vice-versa) by using the following two softkeys, when available: • SET>ACTV (read ‘Set to Active’) softkey: Allows the installer to send the information in the SET column (data stored in the master config module) to the ACTV column (data used by LRU). • ACTV>SET (read ‘Active to Set’) softkey: Causes the LRUs current settings to be copied to the master configuration module as SET items.
When troubleshooting the system, technicians can look for inequalities between SET and ACTIVE columns. Certain problems can be resolved simply by pressing the SET>ACTV softkey, which reloads settings to the specific LRU from the PFD. (Note that this can also be accomplished by reloading the configuration files for the LRU. Section 7 describes this process for each LRU). A blank active column, as shown in Figure 3-11, represents loss of communication between the display and the particular unit.
3.7.4 Configuration Mode Navigation Using the FMS knob as described in Section 3.1.2, 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 System Maintenance Manual listed in Table 1-3. System Page Group 1. System Status 5. System Upload 9. System Data Path Configuration 2. Time Configuration 6. Diagnostics Terminal 10. System Setup 3. Lighting Configuration 7. OEM Diagnostics 11.
3.8 G1000 / GFC 700 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 6 of this manual for the necessary steps. 3.8.1 G1000 Software Image All software and configuration files were certified by Garmin and are considered part of FAA-approved Type Design data.
3.8.2 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 create a software loader card, follow the procedures outlined below. NOTE In order to create a 200/B200 loader card, the individual/facility completing these procedures, must be an authorized King Air 200/B200 service center to gain access to the necessary data via the Garmin website. 1. Go to www.garmin.
7. Double-click the .exe file that was downloaded. The following window will pop-up on the screen. Ensure that there is an empty SD card in the card reader, and then click Setup. 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.
8. Ensure the card and correct drive letter is used, and click next. Select drive 9. A window will pop-up onto the screen to indicate file progress.
10. Once successfully completed, the following message/window will pop-up. Click Finish to finalize SD card. 3.8.3 Software Files Software files are defined by part number and version number on the General Arrangement drawing. See Table 1-2 for the correct General Arrangement drawing part numbers. Each G1000 / GFC 700 LRU reports the software version it currently contains to the user in two places. • Normal System Mode: The AUX – SYSTEM STATUS page lists each LRU and the reported software version.
3.8.5 Configuration File Storage The G1000 system is designed to store all configuration settings in various places so that the configuration is retained in the aircraft during maintenance of units. During system configuration, each file is sent directly to the applicable LRU where it is stored in local LRU memory (except GRS 77 & GDC 74B). Each file is also stored in the PFD internal memory.
The GRS 77 and GDC 74B configuration modules function differently than the rest of the system. The GDC 74B’s configuration file is loaded directly to GDC internal memory. A copy of the file is stored in the GDC configuration module. The GRS 77 configuration module does not store any configuration settings. Instead, it stores calibration data recorded during installation calibration procedures.
3.9 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.
3.9.1 MFD & PFD Software Load Follow this procedure to load software to either PFD or the MFD. 1. With the G1000 and GFC 700 powered on, pull the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers. 2. Insert the software loader card into top card slot in the desired PFD or MFD. See Section 3.8 for information on creating or obtaining a software loader card. NOTE If loading software to all displays, it is preferred to load PFD 2 first, followed by the MFD and then PFD 1. 3.
3.9.2 G1000 System Software Upload The System Upload page allows a technician to load LRU software and system configuration files individually or in an automated sequence. Depending on what maintenance is performed, software and/or configuration files may need to be reloaded to LRUs. Follow the steps below as a guide to use the System Upload page. The figures contained in the following sections represent software version 0985.04 and later. Earlier software versions are similar.
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. If an inequality between the LRU VERS and CARD VERS columns is detected, the SOFTWARE and CONFIGURATION boxes will be pre-selected (checked) for each LRU reporting a different software version than the one on the card.
3.9.3 Software Check Anytime software and configuration loading procedures are accomplished during maintenance, conduct a final software review of the system. 1. Start the PFD in Configuration Mode as described in Section 3.7. 2. Go to the System Status page using the FMS knob. Activate the cursor and toggle to the LRU window. Figure 3-20, System Status 3. The PFD System Status page shows a list of LRUs in the LRU window. Activate the cursor and highlight the LRU window.
Table 3-1, Software Verification SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM *COM 1 GFC CERT YM GSA PTCH MON *COM 2 GIA1 GSA PTCH TRM C GCU GIA1 AUDIO GSA PTCH TRM M GDC1 GIA2 GSA ROLL CTL GDC1 FPGA GIA2 AUDIO GSA ROLL MON GDC2 GMA1 GSA YAW CTL GDC2 FPGA GMA2 GSA YAW MON GDL69 GMC GWX GEA1 GMU1 GWX FPGA GEA2 GMU1 FPGA MFD1 GFC CERT GIA1 GMU2 MFD1 FPGA GFC CERT GIA2 GMU2 FPGA *NAV 1 GFC CERT PC GPS1 *NAV 1 FPGA GFC CERT PM GPS2 *NAV 2 GFC CERT PT C GRS1
3.10 TAWS-A Support Configuration This section applies only to installations with the TAWS-A option. The procedures outlined in this section must be followed to load the necessary configuration files required to enable TAWS-A gear and flap messages. A TAWS-A enable card is also required for this option (see Section 3.31.) 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2.
3.11 TAWS-A Voice No Callout Option Configuration This section applies only to installations with the TAWS-A option. If TAWS-A voice callouts (400, 300, 200, 100) are not desired, follow the procedures outlined in this section to load the necessary configuration files to disable TAWS-A voice callouts. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2.
3.12 TAWS-A Voice Callout Option Configuration This section applies only to installations with the TAWS-A option. This step is necessary only if TAWS-A voice callouts (400, 300, 200, 100) have been disabled and are now desired. TAWS-A voice callouts are the default configuration. Follow the procedures outlined in this section to load the necessary configuration files to enable TAWS-A voice callouts. 1.
3.13 ADF Option Configuration This section loads the necessary configuration files for those aircraft equipped with an ADF. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob. 2. Activate cursor and rotate the small FMS knob to display drop down menu. Highlight King Air - Options and press ENT key on PFD1. 3. Rotate the small FMS knob to select “ADF Option”. Press ENT key on PFD1. 4.
3.14 DME Option Configuration This section loads the necessary configuration files for those aircraft equipped with a DME. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2. Activate cursor and rotate the small FMS knob to display drop down menu. Highlight King Air - Options and press ENT key on PFD1. 3. Rotate the small FMS knob to highlight “DME Option”. Press ENT key on PFD1. 4.
3.15 RAD ALT Option Configuration This section loads the necessary configuration files for those aircraft equipped with a radio altimeter. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2. Activate cursor and rotate the small FMS knob to display drop down menu. Highlight King Air - Options and press ENT key on PFD1. 3. Rotate the small FMS knob to highlight “RAD ALT Option”. Press ENT key on PFD1. 4.
3.16 Non-Garmin Traffic System Option Configuration Follow this procedure to enable the traffic system function for the G1000 system if required. NOTE The G1000 can only be configured for TIS or TAS but not both. Performing this procedure will automatically disable the TIS function. Coordinate this configuration with section 7.13 “Traffic System Functional Check”. 1.
3.17 GTS 8XX Traffic System Configuration Follow this procedure to enable the GTS 8XX traffic system function for the G1000 system if required. NOTE The G1000 can only be configured for TIS or TAS/TCAS but not both. Performing this procedure will automatically disable the TIS function. Coordinate this configuration with Section 7.26 “GTS 8XX Traffic System Functional Check”. NOTE Configuration of the GTS 8XX TAS/TCAS I will require the GTS system to be configured with the aircraft mode S address.
3.18 StormScope (WX-500) Option Configuration Follow this procedure to enable the lightning system option (WX-500) for the G1000 system if required. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “System Upload” page using the PFD1 small FMS knob. 2. Activate cursor and rotate the small FMS knob to display drop down menu. Highlight King Air - Options and press ENT key on PFD1. 3. Rotate the small FMS knob to highlight “Lightning System Option”.
3.19 Stormscope (WX-500) Configuration Load Confirmation. 1. With PFD1 in configuration mode, use the PFD1 large FMS knob to select OTHER and the Stormscope configuration page. Figure 3-30, Stormscope Configuration Page 2. Activate the cursor to highlight the DATA field. Use the small FMS knob to open the drop down menu then select ‘Config’ and press ENT key on the PFD1. Figure 3-31, Stormscope Configuration 3.
3.20 ESP Support (with AOA) Option Configuration This section applies only to installations with the ESP option with AOA modes. A new Safe Flight lift computer is used for this configuration. The procedures outlined in this section must be followed to load the necessary configuration files required to enable ESP messages and functions. An Enhanced AFCS unlock card is also required for this option (see Section 3.34.) 1.
3.21 ESP Support (no AOA) Option Configuration This section applies only to installations with the ESP option without AOA modes (available in software version 0985.04 and later.) The original Safe Flight lift computer is used for this configuration. The procedures outlined in this section must be followed to load the necessary configuration files required to enable ESP messages and functions. An Enhanced AFCS unlock card is also required for this option (see Section 3.34.
3.22 GDL 59 Wi-Fi Data Link Option Configuration Follow this procedure to enable the optional GDL 59 Wi-Fi data link function. Note that if the GDL 59 option is reloaded for any reason, the GSR 56 option must also be reloaded per Section 3.23. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2. Activate cursor and rotate the small FMS knob to display drop down menu.
3.23 GSR 56 Satellite Reciever Option Configuration Follow this procedure to enable the optional GSR 56 satellite receiver function. Note that the GDL 59 wi-fi data link option must be loaded per Section 3.21 prior to loading the GSR 56 option. 1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2. Activate cursor and rotate the small FMS knob to display drop down menu.
3.24 POTS Handset Configuration Follow this procedure to enable a POTS handset if installed. Note that the GDL 59 wi-fi data link option must be loaded per Section 3.21 prior to loading the POTS handset configuration. 1. Power up the PFD1 in configuration mode. 2. On the PFD1, select GDL page group using the large FMS knob. 3. Using the small FMS knob select the GDL 59 Configuration page. 4. Activate the cursor. Use the large FMS knob to select POTS CONNECTED in the PHONE SETTINGS field. 5.
3.26 GSM 86 Servo Mount Configuration For software versions 0985.04 and later, the section 4.9.1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured. If a GSM 85A servo gearbox is replaced by a GSM 86 servo gearbox, follow the steps below to load the configuration. It is not necessary to load this configuration if GSM 86 servo gearboxes are already installed for all servos (default configuration.) 1.
3.27 Verification of Servo Mount Configuration For software versions 0985.04 and later, the section 4.9.1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured. The following procedure verifies the type of servo gearbox that is configured for each servo. 1. With PFD1 in configuration mode, use the large FMS knob on PFD1 to select the GDU page, then select “AIRFRAME CONFIGURATION” using the small FMS knob. 2.
3.28 FliteCharts Configuration If ChartView has previously been enabled, and is no longer desired, follow the procedures outlined in this section to return the G1000 system to the basic FliteChart functions. If ChartView has not been enabled, the following procedure is not required. Loading of the baseline configuration for the specific airframe is required for enabling FliteChart functions. Reload the baseline configuration and all applicable options as described in Section 3.9.
7. De-activate the cursor. 8. Power down the system and remove the ChartView Enable card from PFD1. 3.30 TAWS-B Enable Follow this procedure to enable the TAWS Class B function. A TAWS-B Enable Card, as specified on General Arrangement Drawing 005-00421-03, will be required for this procedure. 1. With the TAWS-B Enable card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1. 2.
3.31 TAWS-A Enable Follow this procedure to enable the TAWS Class A function. A TAWS-A Enable Card, as specified on General Arrangement Drawing 005-00421-03, will be required for this procedure. NOTE Ensure that the TAWS-A Support Configuration has been loaded per Section 3.10. Ensure that the RAD ALT Option Configuration has been loaded per Section 3.15. 1.
3.32 Supplemental Database Loading 1. Open PFD1, PFD2 and MFD circuit breakers. 2. Remove the SD card containing the supplemental databases from the lower slot of the MFD. Supplemental databases include basemap, Safetaxi, airport terrain, obstacle, airport directory and terrain databases. 3. Download the current supplemental databases to the SD card. 4. Reinsert the SD card containing the current supplemental databases into the lower slot of the MFD. 5. Close PFD1, PFD2 and MFD circuit breakers. 6.
3.33 SVS/Pathways Enable Follow this procedure to enable the Synthetic Vision option. An SVS/Pathways Enable Card, as specified on General Arrangement Drawing 005-00421-03, will be required for this procedure. NOTE 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 Terrain/Obstacle/SafeTaxi database card installed in the lower slot.
3.34 ESP Enable Follow this procedure to enable the Electronic Stability and Protection (ESP) function. An Enhanced AFCS Unlock Card, as specified on General Arrangement Drawing 005-00421-03, will be required for this procedure. 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’.
3.35 Aircraft Registration Number Entry 1. If not applied, apply power to the G1000 system. 2. With PFD1 in configuration mode, select the GTX page group, then select the TRANSPONDER CONFIGURATION page. 3. The ‘ADDRESS TYPE’ default is ‘US TAIL’. To enter a non-US Mode-S registration number set the ‘ADDRESS TYPE’ field to ‘HEX ID’. 4. Activate the cursor and highlight the ‘MODE S ADDRESS’ field. Use the small/large FMS knobs to enter the US aircraft registration number or other Mode-S registration number.
3.36 Splash Screen Loading When all software and configuration has been loaded, the splash screens must be loaded to all display units (PFD1, PFD2 and MFD). 1. If not applied, apply power to the G1000 system. 2. Remove power from PFD1, PFD2 and MFD by opening the PFD1 PRI/SEC, PFD2 and MFD circuit breakers. 3. Insert the software loader card in the upper slot of PFD2. 4. Apply power to PFD2. 5. When prompted to update system files, press the NO softkey. 6.
3.37 Navigation Database Loading A new navigation database cycle may be loaded before it is effective. The new database will be stored on the G1000 bottom SD card until it becomes effective. The G1000 will automatically update to use the new database at the first on-ground power-on after its effectivity date. Follow this procedure to load the navigation database: 1. Remove power from the PFD1, PFD2 and MFD. 2.
7. The system will synchronize and automatically update as necessary. Monitor the synchronization process on the AUX – SYSTEM STATUS page in the SYNC STATUS sub-section within the DATABASE window This sub-section is only present when a sync is occurring or has occurred on the current power cycle. Figure 3-46, Navigation Database Synchronization 8.
3.38 Configuration of Navigation Map for Traffic System 1. With the MFD in normal mode, use the GCU FMS knob to select the Navigation Map page then press GCU MENU key to display the PAGE MENU. 2. Turn the small right knob to select or verify selected ‘Map Setup’ and press the ENT key and verify TRAFFIC is selected ON. 3. Verify the flashing cursor highlights the GROUP field. 4. Turn the GCU small FMS knob to select Traffic and press ENT on GCU. 5.
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4.2 Servicing Information G1000 LRU maintenance is ‘on condition’ only. No component-level overhaul is required for this type 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.
4.2.
4.3 Maintenance Intervals Table 4-1 shows systems and items, installed by this STC, which must undergo tests or checks at specific intervals. If the interval is shown to be in flight time as well as calendar months, the first interval reached should be used as the limit. The inspection time tables used for this STC are aligned with the existing maintenance 200 hr phase inspection program used in the current King Air 200 Series Maintenance Manual.
Item GFC700 Periodic Check Description/Procedure Verify proper operation of the GFC700 by performing the following: Pre-Flight Test AFCS Switch Checks Autopilot Operation Checks For installations with the GSM 86 servo gearbox: Autopilot Clutch Overpower Check Manual Section No. Interval 8.2.1, 8.2.2, 8.2.5 Phase 2 and 4 8.2.3 TAWS Functional Check Periodic TAWS function check 7.15 Phase 4 GDU 1040A PFD (Qty 2) Removal & Replacement 6.1 On Condition GDU 1500 MFD Removal & Replacement 6.
Item Description/Procedure GDL 59 Wi-Fi Datalink Manual Section No. Interval 6.33 Removal & Replacement GSR 56 Satellite Receiver On Condition 6.30 G1000 Cooling Fan Fail Annunciation Check* Verify the operation of the fan power and fan speed monitoring circuits for GIA1 Fan, GIA2 fan, PFD1 fan, MFD fan and PFD2 fan and fan fail messages 8.1.4 Phase 1, 2, 3 & 4 Nose Avionics Compartment Fans Operational Check* Functional test of the GIA1 and GIA2 ported fans.
Item Description/Procedure Manual Section No. Interval 6.11 On Condition 6.12 On Condition Removal & Replacement. GSA 80 Servos (all) GSM 85A /86 Servo Gear Box (all) Refer to Master Drawing List, listed in Table 1-2, for installation drawings. Removal & Replacement. Refer to the servo install drawings listed in Master Drawing List, listed in Table 1-2.
Item Description/Procedure Manual Section No. Interval N/A On Condition Engine/Airframe Sensors ITT Thermocouple Cable (Qty 2) Oil Pressure Sensor (Qty 2) Oil Temperature Sensor (Qty 2) Removal & Replacement: Torque Transmitter (Qty 2) Refer to King Air 200 Series Maintenance Manual listed in Table 1-2. Fuel Flow Transmitter (Qty 2) Prop Tachometer (Qty 2) Engine Speed Tachometer (Qty 2) signal conditioner (Qty 2) 6.22 Removal & Replacement Annunciator/Switch – Prop Sync On Condition 6.
4.3.1 Discontinued Maintenance Table 4-2 shows a list of inspections and tests that are listed in the King Air 200 Series Maintenance Manual, but may be no longer required post incorporation of this STC. It is the responsibility of the installer to ensure that there are no post factory installations that would require these checks to remain.
4.4 Visual Inspection Perform a visual inspection in accordance with requirements in Table 4-1. Check for corrosion, damage, or other defects for each of the items listed in Table 4-3 through Table 4-8. Replace any damaged parts as required. Inspection may require the temporary removal of a unit or units to gain access to connectors. Follow guidance in Section 6 for equipment removal and replacement.
Table 4-5, Pilot’s Compartment Visual Inspection Procedure Item Description/Procedure Initials Locate equipment in the aft pedestal for the following inspection. a) Inspect the GCU 477 unit and connector for corrosion or other defects. Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment. a) Inspect the ADF control unit and connector for corrosion or other defects.
Item Description/Procedure Initials the harness connector assembly as well as the integrity of the individual shields and their attachment. PFD and MFD Fans (Qty 3) a) Inspect fans for accumulation of dirt and other damage. Remove excess dirt as required. a) Inspect the GDL 69A unit, rack, and connectors for corrosion or other defects. Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment.
Table 4-7, Cabin Area Visual Inspection Procedure Item Antennas Description/Procedure Initials Inspect all external antennas for leading edge erosion and condition of base seals (GPS/WAAS, top diversity transponder(s), Iridium, top and bottom GA 58 traffic antennas, if installed) To gain access for the following Inspections, remove floorboards in cabin at FS 185.00 and FS 246.
Table 4-8, Rear Fuselage and Empennage Visual Inspection Procedure Item Wi-fi Antenna Description/Procedure Initials Inspect the external wi-fi antenna (if installed) for leading edge erosion and condition of base seals. To gain access for the following Inspections, refer to the servo installation drawings and the King Air 200 Series Maintenance Manual, listed in Table 1-2.
4.5 Electrical Bonding Test The following bonding tests are provided for G1000-equipped 200/B200 King Air aircraft as a requirement beyond what is given in the aircraft maintenance manual. The electrical bonding checks are split into two tests, Phase 3 Electrical Bonding Test and Phase 4 Electrical bonding test. This places the bonding test requirement for each G1000 LRU in the same phase as the visual inspection of that zone to minimize access requirements. 4.5.
Pilot Compartment • Top metal case of PFD 1: __________ milli-volts • Top metal case of PFD 2: __________ milli-volts • Top metal case of MFD: __________ milli-volts • Top metal case of GMA 1347D #1: __________ milli-volts • Top metal case of GMA 1347D #2: __________ milli-volts • Top metal case of GCU 477: __________ milli-volts • Top metal case of GMC 710: __________ milli-volts • GEA 71 #1 body: __________ milli-volts • GEA 71 #2 body: __________ milli-volts • GDC 74B #1 body: ________
4.5.4 Phase 4 Electrical Bonding Procedure 1. Connect the positive lead of the power supply to the engine compartment grounding bracket (battery negative connection to the airframe). 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.
4.6 GRS 77 Earth Magnetic Field Updates The GRS 77 utilizes an Earth magnetic field model which is updated once every five years. The update is expected to be available from Garmin in each of the following years: 2010, 2015, and every five years thereafter, as long as the GRS 77 remains a Garmin-supported product. The G1000 system alerts the operator that the magnetic field database is out of date by issuing the message “AHRS SERVICE – AHRS Magnetic-field model needs update”.
4.8 Flaps-in-motion Discrete Input Check To perform this check, all G1000 and GFC 700 equipment must be installed and operational. Start PFD1 in Configuration Mode and go to the GIA Page Group and select the GIA I/O Configuration Page using the FMS knob. Perform the following checks: Figure 4-1, GIA I/O Page Invalid Valid Figure 4-2, Discrete Valid/Invalid Indications 1. Verify the DATA indicators of the discrete inputs labeled ‘FLAP EXTEND’ and ‘FLAP RETRACT’ show an invalid condition. 2.
4.9 GSM 85A/GSM 86 Slip Clutch Torque Check Procedure Perform the test per section 4.9.1, 4.9.2 or 4.9.3. The following test procedures are the same for both the GSM 85A and the GSM 86 servo gearboxes. 4.9.1 Automated Slip Clutch Test Procedure (SW version 0985.04 and later) 1. Verify the correct type of servo gearbox is configured for each servo per Section 3.27. 2. With the MFD in Normal Mode, press the red DISPLAY BACKUP button on the pilot’s GMA audio panel to place the MFD in reversion mode.
4.9.2 Manual Slip Clutch Test Procedure (SW version 0985.03 and earlier) 1. With PFD1 in Configuration Mode, go to the GFC Page Group and select the GFC STATUS Configuration Page using the FMS knob. Figure 4-4, GFC Status Page IMPORTANT! It is highly recommended that the following test be performed at temperatures between 50° F and 120° F. 2. Use the FMS knob to select the desired servo. 3. Verify that the PFT status field shows PASSED. 4.
12. Allow the servo to continue driving against the control stop for at least 50 seconds. Observe the TORQUE values displayed in the Servo Data field and record the maximum and minimum values in Table 4-10 or in the appropriate aircraft maintenance records. 13. Manually select 0.00 rpm for the Drive Servo and press ENT. Allow the servo to stop. 14. Manually select -2.50 for the Drive Servo and press ENT.
4.9.3 Servo Gearbox Adjustment Fixture Procedure This test is an alternative to the automated and manual slip clutch test procedures. Only the GSM 85A servo gearbox slip clutch can be adjusted. The GSM 86 servo gearbox does not have an adjustable slip clutch; however, the torque value can be measured using this procedure. IMPORTANT! This adjustment requires the use of the Garmin servo adjustment fixture, P/N T10-00110-01.
4.
(B) AHRS and ADC data path check 1. Verify there are no AHRS loss of data messages, such as: • AHRS not receiving any GPS information • AHRS not receiving backup GPS information • AHRS using backup GPS source 2. Place the G1000 in configuration mode. 3. In the GIA page group, go to the GIA RS-232/ARINC 429 CONFIG page. 4. With GIA1 selected in the SELECT UNIT window, verify the RS232 Channel 1 (GDC74 #1) and RS232 Channel 6 (GRS77 #1) indicators are green. Ref. Section 5.2.1.2. 5.
(D) Engine data availability to the displays and GPS data availability to the AHRS with either GIA inoperative check 1. Open GIA1 primary and secondary CBs. 2. Verify the following: • NAV 1 and COMM1 tuning fields on PFD 1 and PFD 2 are invalid (red X). • L/R engine data remains valid. • XPDR1 is Inoperative. • GMA1 is Inoperative. • AHRS1 is using backup GPS source. • AHRS2 not receiving backup GPS Information. • An amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2.
4.11 Engine Data Check (GIA 1 or GIA 2 Inoperative) NOTE This procedure should be accomplished in conjunction with the engine run-up. Valid engine indications will be needed. Do the following to verify the engine data availability and validity, with GIA 1 or GIA 2 inoperative: 1. Ensure the G1000 is in normal mode. 2. With engines running, note the indication values for torque, ITT and oil pressure. 3. On the right hand circuit breaker panel, open the GIA1 (PRI) and GIA1 (SEC) circuit breakers. 4.
14. Hold the control yoke in the forward position and center the pitch trim wheel. 15. Engage the autopilot, maintain the control yoke in the forward position and keep the pitch-trim wheel from rotating for approximately five seconds. 16. Quickly release the trim wheel and verify that the red PTRM annunciator is displayed on both PFD 1 and PFD 2. 17. Disengage the autopilot and use the pitch-trim switch (or the pitch-trim wheel) to trim full down. 18. Hold the control yoke in the full forward position. 19.
2. Connect a pitot/static test set to the aircraft ADC1 pitot and static ports (Pilot’s side). (Do not connect the pitot/static tester to ADC2 ports at this time.) 3. Set the baro-correction on PFD1 and PFD2 to 29.92. 4. On the AFCS mode controller, press the ALT, HDG, and AP buttons and verify autopilot engages. 5. Slowly increase the pitot/static test set to simulate an ADC1 / ADC2 altitude miscompare of greater than 200 ft.
17. Replace AHRS1 to normal attitude and verify that attitude display on PFD1 displays current aircraft attitude. 18. Repeat Steps 13 through 17 for AHRS2. 19. The G1000 Miscompare checks are complete. 4.14 Nose Avionics Compartment Fans Operational Check This procedure will verify that airflow is present from the ported avionics cooling fans to the #1 and #2 GIA units. The fan speed monitoring circuits and annunciations are checked by the G1000 Cooling Fan Fail Annunciation Check in Section 8.1.
4.16 Standby Battery Periodic Checks 4.16.1 Charge Check Refer to the PS-835 Emergency Power Supply Installation Manual listed in Table 1-2. With the PS-835 battery installed in the aircraft and aircraft power applied, verify all four Battery Voltage LEDs are lit to indicate the battery is being charged (see Figure 4-5). With the PS-835 battery installed in the aircraft and no aircraft power applied, press TEST SWITCH (Figure 4-5, Item 4) into TEST position for 5 seconds.
4.16.2 Capacity Test NOTE The PS-835 Emergency Power Supply must have completed a full charge prior to any discharge testing. This test is performed with the battery removed from the aircraft. A. Press and hold TEST SWITCH (Figure 4-5, Item 4) and observe the OUTPUT VOLTAGE MONITOR LED's. 1) If the 24VDC OUTPUT VOLTAGE MONITOR LED comes on, proceed with Discharge Test procedure. 2) If OUTPUT VOLTAGE MONITOR LED's do not come on, check fuses at bracket next to battery and replace if blown.
4) Connect the Load Resistor across J1 connector pins 11 (+) and7 (-) and start timing the discharge period with a stopwatch. 5) Monitor and plot voltage values at 10-minute intervals. 6) At 48.0 minutes note voltage on Digital Voltmeter. This voltage must be greater than 20.0 Vdc. a. All INDIVIDUAL CELL MONITOR LED’s (Figure 4-5, Item 1) must remain on. b. Any LED that does go OFF will represent a defective individual cell, which must be replaced.
4.17 Power Bus Check 4.17.1 Power Bus Feeder Check This procedure will verify the availability of the feeders to the essential bus and the No.1 and No.2 dual feed buses. 1. Apply external power. Turn BATT and AVIONICS MASTER switches to ON position. Verify all circuit breakers are closed. Observe PFD1, PFD2 and MFD displays and verify all displays are powered and in normal format. Verify the absence of red Xs or alert messages. Select, or verify selected, on-side sensors for PFD1 and PFD2. 2.
5. Apply external power. Turn BATT and AVIONICS MASTER switches to ON position. 6. Bus voltage SHOULD be present on the right isolation bus (W109). Verify that the GDL69 FAIL alert message is NOT shown on the PFD. Operation of the GDL 69A verifies continuity of the right isolation limiter (F132). 7. By observing the following annunciators, power to each of the four buses will be verified: L FUEL PRESS, R FUEL PRESS, L BL AIR FAIL and R BL AIR FAIL.
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5 TROUBLESHOOTING This section provides instructions and guidance for G1000 system troubleshooting, as installed in the King Air 200/B200. IMPORTANT! Sections 6, 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 6, 7 and 8 to ensure proper operation of the system.
5.1 G1000 Alerting System Figure 5-2, Alerts & Annunciations The G1000 Alert System conveys alerts to the pilot using combinations of the following features: Alert Window: The Alert window displays alert text messages. Pressing the ALERTS softkey displays the Alerts window. Pressing the ALERTS softkey again removes the Alerts window from the display. Softkey Annunciation: When the G1000 Alerting System issues an alert, the ALERTS softkey is used as a flashing annunciation to accompany the alert.
Aural & Audio Alerts The G1000 system is capable of issuing audio and aural (voice) alerts for various situations.
5.2 System Annunciations If data fields become invalid due to an LRU failure, the PFD/MFD typically annunciates the failure with a large red X, as shown in Figure 5-4. Figure 5-4, System Annunciations 5.2.1 Failed Path Messages The following message indicates there is a data path connected to the GDU (PFD1, PFD1, or MFD) or the GIA 63W (1 or 2) that has failed. FAILED PATH – A data path has failed. The FAILED PATH message is triggered by a timeout of any one digital channel.
The applicable data paths can be verified by viewing the following configuration mode pages. 5.2.1.1 GDU RS-232 / ARINC 429 CONFIG Page PFD 1 RS-232 Channel LRU Indicator Green Status PFD1/GMC 710 data path is functioning correctly. PFD1/GMC 710 data path is not functioning correctly. • Verify GMC710 is powered on. o CHNL 2 GMC 710 Red If GMC 710 will not power on, remove unit and verify power and ground are present at the GMC connector.
PFD 1 ARINC 429 Channel LRU Indicator Green Status PFD1/GRS 77 #1 data path is functioning correctly. PFD1/GRS 77 #1 data path is not functioning correctly. • IN 1 GRS 77 #1 Red Verify GRS77 #1 status is “OK” using the System Status page on the MFD. If it is not, correct condition before proceeding, reference GRS troubleshooting sections. o Swap GRS1 and GRS2 (no reconfiguration required) to confirm if the problem is in the original GRS1.
PFD 2 RS-232 Channel LRU Indicator Green Status PFD2/GMC 710 data path is functioning correctly. PFD2/GMC 710 data path is not functioning correctly. • Verify GMC 710 is powered on. o CHNL 2 GMC 710 Red If GMC 710 will not power on, remove unit and verify power and ground are present at the GMC connector. If power or ground is not present, troubleshoot aircraft wiring for faults. If power and ground are present, replace GMC 710. • Load PFD2 and GMC 710 configuration files.
PFD 2 ARINC 429 Channel LRU Indicator Green Status PFD2/GRS 77 #2 data path is functioning correctly. PFD2/GRS 77 #2 data path is not functioning correctly. • IN 1 GRS 77 #2 Red Verify GRS77 #2 status is “OK” using the System Status page on the MFD. If it is not, correct condition before proceeding, reference GRS troubleshooting sections. o Swap GRS1 and GRS2 (no reconfiguration required) to confirm if the problem is in the original GRS1.
MFD1 RS-232 Channel LRU Indicator Green Status MFD1/GCU 477 data path is functioning correctly. MFD1/GCU 477 data path is not functioning correctly. • Verify GCU 477 is powered on. o CHNL 1 GCU 477 If GCU 477 will not power on, remove unit and verify power and ground are present at the GCU connector. If power or ground is not present, troubleshoot aircraft wiring for faults. If power and ground are present, replace GCU 477. Red • Load MFD1 and GCU 477 configuration files.
5.2.1.2 GIA RS-232 / ARINC 429 CONFIG Page GIA1 RS-232 Channel LRU Indicator Green Status GIA1/GDC 74 #1 data path is functioning correctly. GIA1/GDC 74 #1 data path is not functioning correctly. CHNL 1 GDC 74 #1 • Load GIA1 and GDC 74 #1 configuration files. • Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA1. Red o • Replace original GIA1 if box turns green after swapping units.
GIA1 RS-232 (continued) Channel LRU Indicator Green Status GIA1/GRS 77 #1 data path is functioning correctly. GIA1/GRS 77 #1 data path is not functioning correctly. • Load GIA1 configuration files. • Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA1. o CHNL 6 GRS 77 #1 Red • Replace original GIA1 if box turns green after swapping units.
GIA1 ARINC 429 Channel LRU Indicator Green Status GIA1/GDC 74 #1 data path is functioning correctly. GIA1/GDC 74 #1 data path is not functioning correctly. IN 5 GDC 74 #1 • Load GIA1 and GDC 74 #1 configuration files. • Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA1. Red o • Replace original GIA1 if box turns green after swapping units. Check the GIA1/GDC 74 #1 interconnect wiring for faults.
GIA2 RS-232 Channel LRU Indicator Green Status GIA2/GDC 74 #2 data path is functioning correctly. GIA2/GDC 74 #2 data path is not functioning correctly. CHNL 1 GDC 74B #2 • Load GIA2 and GDC 74 #2 configuration files. • Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA1. Red o • Replace original GIA2 if box turns green after swapping units. Check the GIA1/GDC 74 #2 interconnect wiring for faults.
GIA2 RS-232 (continued) Channel LRU Indicator Green Status GIA2/GRS 77 #2 data path is functioning correctly. GIA2/GRS 77 #2 data path is not functioning correctly. • Load GIA2 configuration files. • Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA1. o CHNL 6 GRS 77 #2 Red • Replace original GIA2 if box turns green after swapping units.
GIA2 ARINC 429 Channel LRU Indicator Green Status GIA2/GDC 74 #2 data path is functioning correctly. GIA2/GDC 74 #2 data path is not functioning correctly. IN 5 GDC 74 #2 • Load GIA2 and GDC 74 #2 configuration files. • Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA2. Red o • Replace original GIA2 if box turns green after swapping units. Check the GIA2/GDC 74 #2 interconnect wiring for faults.
5.2.1.3 GIA CAN / RS-485 CONFIGURATION Page GIA1 RS-485 Channel LRU Indicator Green Status GIA1/GEA1 data path is functioning correctly. GIA1/GEA1 data path is not functioning correctly. CHNL 1 GEA1 • Verify GEA1 is powered on using the GEA Status page. • Load GIA1 and GEA1 configuration files. • Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA1. o Red • Replace original GIA1 if box turns green after swapping units.
GIA2 RS-485 Channel LRU Indicator Green Status GIA2/GEA1 data path is functioning correctly. GIA2/GEA1 data path is not functioning correctly. • Verify GEA1 is powered on using the GEA Status page. • Load GIA2 and GEA1 configuration files. • Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GIA2. o CHNL 1 GEA1 Red • Replace original GIA2 if box turns green after swapping units.
5.2.2 System Failure Troubleshooting The following table provides basic troubleshooting guidance for LRU failures. Refer to G1000/GFC 700 Wiring Diagram, listed in Table 1-2, as needed to verify interconnects. Invalid Data Field Associated LRU(s) Low Speed Awareness Band permanently displayed Solution • With aircraft weight on wheels and the G1000 in Configuration Mode, check that the RH GEAR ON GROUND Discrete In indication for GIA2, on GIA I/O CONFIGURATION page is illuminated.
Invalid Data Field Associated LRU(s) GPS LOI GIA1 or GIA2 XPDR FAIL GTX 33 Solution • Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Check GPS1 and GPS2 signal strength on AUX page 4. Refer to GIA GPS section if GPS can not acquire a position lock for troubleshooting. • Check corresponding GPS antenna and cable for faults. • Check Ethernet interconnect between the PFD1 to GIA1 or PFD2 to GIA2 for faults.
Invalid Data Field Associated LRU(s) Solution • Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Cycle GRS 77 power to restart initialization. • Ensure GRS 77 connecter is secure and proper wire harness strain relief is provided.
Invalid Data Field HDG FAIL Associated LRU(s) GRS 77 & GMU 44 GRS 77 & GMU 44 Solution • Ensure metal objects (tool boxes, power carts, etc.) are not interfering with the magnetometer and aircraft is not in hangar, near other buildings, parked over metal drainage culverts or on hard surfaces that may contain steel reinforcements • Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin.
Invalid Data Field Associated LRU(s) Solution • If software was loaded to a new GDU display, be sure that the user settings for the replaced display were cleared. Clear user settings by pressing the CLR key on the replaced display while applying power to it. Acknowledge the on-screen prompt by pressing the ENT key or the right-most softkey. • Check for GEA related Alert messages on the PFD. Correct any Alerts concerning software or configuration errors by reloading software or configuration as noted.
5.2.3 Engine/Airframe Instrument Failures The following table provides guidance for troubleshooting individual engine/airframe sensor failures. Be sure to also follow previous guidance given for the GEA 71. The technician should troubleshoot to isolate the fault by checking sensor-to-GEA wiring, replacing the suspect sensor, and finally by replacing the GEA 71. Replace one part at a time. Refer to Section 7.4.1 to check for correct operation of the sensors and GEA 71 after any part has been replaced.
5.2.4 ADF/DME Failure A DME or ADF failure is represented by the following red X’s. Refer to G1000/GFC 700 Wiring Diagram and King Air 200 Series Maintenance Manual (listed in Table 1-2,) as needed. Invalid Field Sensor Solutions • Ensure that GIA 63 #2 is properly functioning. • Reload the ADF option configurations. • Check for proper operation of the ADF receiver. Ensure that the receiver is receiving power. • Check ADF – GIA2 interconnect.
5.3 200/B200 Specific Alerts The following alerts are configured specifically for the King Air 200/B200 installation: ANNUNCIATION ADVISORY Alerts Message Advisory Solution TAWS GEAR FAULT – Landing Gear detected in the DOWN position • Check the gear down wiring input to the GIAs. Refer to G1000/GFC 700 Wiring Diagram, listed in Table 1-2. TAWS FLAP FAULT – Flaps detected in the LDG position • Check the flap full down wiring input to the GIAs.
5.4 TAWS Troubleshooting Annunciation Cause Solution • If message occurred on the first power up after unlocking TAWS, cycle power to initialize TAWS. • Ensure each GDU contains the correct database data card. • Ensure the G1000 is configured for TAWS: A TAWS system failure has occurred. 9 • Verify GIAs are online. • Ensure a database or GDU SW mismatch has not occurred. 9 If a mismatch has occurred, load correct database/software files or replace the terrain card.
5.5 Synthetic Vision and Pathways Troubleshooting The SVS/Pathways software feature requires the following G1000 sensors/data to be valid: • AHRS • Heading • GPS Position • 9 Arc-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 annunciations may appear in the AFCS Annunciation field: Table 5-3, AFCS Annunciation Troubleshooting Annunciation Condition AFCS System Failure Pitch Axis Failure Pitch Trim Axis Failure Yaw Axis Failure Roll Axis Failure AHRS Monitor Failure Elevator Mis-Trim Down Elevator Mis-Trim Up Page 5-28 Revision 6 Resolution • Confirm AFCS Servos circuit breaker IN • Ensure that the G1000 system is in proper working order.
Annunciation Condition Resolution Aileron Mistrim Right • Check for possible fuel imbalance. • Check aileron control adjustments. • If mistrim condition still exists remove and replace the roll servo. • Check rudder control adjustments. • If mistrim condition still exists remove and replace the yaw servo. • Allow the system to complete pre-flight tests. • The preflight test should finish within 2 minutes. If it does not pass, the red ‘PFT’ annunciation is shown.
5.6 GFC 700 AFCS Troubleshooting The GFC 700 is a digital Automatic Flight Control System (AFCS) which is integrated into various components of the G1000. This section touches upon key items to note while troubleshooting the GFC 700. Should a problem be encountered during the operation of the GFC 700, the pilot and technician should first evaluate the overall status and condition of the G1000 system at the AUX – System Status page (on MFD).
5.6.1 GFC Status Page The GFC Status page is presented in configuration mode and gives status information regarding the GFC 700. Figure 5-6, GFC Status Page GIA STATUS AP DISCONNECT: Shows the condition of the AP DISC +28 VDC input to the GIAs and servos, which is required for the Autopilot to operate. A green status indicator shows the AP DISC switch is closed and the GFC 700 is activly receiving 28. volts.
SERVO DATA Shows real-time reported data including servo voltage, speed, motor current, load cell torque, and clutch solenoid status. A green box indicates the servo clutch is engaged. SLIP CLUTCH TEST RESULTS This window is used during the automatic slip clutch torque measurement check. 5.6.
9. The GIA Maintenance Log can record any of the following faults: • FCS Task not started: Bad gains The FCS task has not started because the gains are not present or have been corrupted. Reload the gain files to correct. • FCS Task not started: Gain structure out of range The FCS task has not started because the gains are not compatible with the GIA software. Reload the gain files to correct.
• PRMTR: MODE: Parameter lost The mode specified by has been disengaged because the parameter specified by has become invalid. The following is a list of some of the possible values for : a. AD TDM Comm Valid: The specified mode has been disengaged because communication with the servos, via the Time Division Multiplexer protocol, has been lost. b. AP Pitch MET not stuck: The specified mode has been disengaged due to a stuck pitch MET switch.
PFT step 5: System initialization, verify servo PFT is complete This step is checking to make sure that all servos have completed their own PFT. This does not check whether the servo PFT passed or failed. It verifies that the servo PFT is no longer in progress. PFT step 6: Verify cross GIA is initialized This step is checking to make sure the other GIA is also on step 6 of its PFT. If this step fails, try cycling power on GIA1, GIA2, and all servos.
PFT step 12: Verify AP disconnect enabled This step is checking to make sure GIA1, GIA2, and all servos have are connected to a 28 volt AP disconnect. If this step fails, make sure the AP disconnect input to GIA1, GIA2, and all servos is connected and registering 28 volts. Make sure the AP disconnect switch has been installed in the aircraft. Make sure no one is holding the AP disconnect switch down on the yoke.
5.6.3.1 Servo Faults and Troubleshooting Whenever a servo fault occurs, a status message is logged to the corresponding servo control or monitor maintenance log. This information is also accompanied by a time and date stamp. An “RTC DATE” entry is made every time a servo is powered on, it is normally not useful for troubleshooting. The following is a listing of possible faults that could be reported in a GSA fault log.
PFT Faults MONITOR PFT STEP "INTERNAL COMM FAIL" NOTES This can sometimes be a result of a failure on the other internal servo board, check faults on the other processor "UNSW POWER INV" Check unit power "MON SOL PWR ON FAIL" Check unit power and AP Disconnect power "CTL SOL PWR ON FAIL" Check unit power and AP Disconnect power "SOL PWR FAIL" Check unit power and AP Disconnect power "CERT DATA UNINSTALLED" Upload the certification gain file to the Monitor board "STRAP CODE MISMATCH" Check the c
Control Processor The control processor contains the logs that are found in these processors – 3 – Pitch Servo 5 – Roll Servo 7 - Yaw 9 – Pitch Trim Servo There are two main groupings of faults that can occur in the control processor. The first grouping of faults can occur during the GSA unit pre-flight test (PFT). If there is a fault during PFT the unit will not be able to transition to normal mode and the only way to clear this state would be to cycle unit power.
Normal Mode Faults CONTROL FAULT "GIA DIS FAULT" NOTES Check the AP Disconnect power into the unit "HOST DATA DIF" Check the AHRS wiring to the system "HOST DATA INV" Check the AHRS wiring to the system "SVO PWR INV" Check unit power and AP Disconnect power “STRP CODE CHNG” Check the connector strap inputs to the unit “MET STUCK SWTCH” Check the MET switch inputs into the system “MET STATUS DIF” Check the MET switch inputs into the system Page 5-40 Revision 6 G1000 / GFC 700 System Maintenanc
5.6.3.2 Downloading GIA and GSA Maintenance Logs If additional assistance is needed troubleshooting autopilot faults, the Maintenance logs can be downloaded to an SD card as a text file (.txt) and emailed to Garmin Aviation Product Support. Please call Garmin Aviation Product Support before you send a Maintenance Log to notify them you are sending it to prevent a delay in response.
12. While you are waiting for the data to be saved to the SD card, record the order of the LRU’s and/or Servos were downloaded so that you can provide that information to Cessna or Garmin to help decipher the order of the error data. 13. Power down the G1000 System and remove the SD card. 14. Insert the SD card in the card reader of a laptop or desktop computer and open the “diag_buf_log.txt” file from the SD card using the WordPad program.
5.7 5.7.1 Backup Communications Path Checks Overview The G1000 system architecture is designed with redundant communication ports for several LRUs so that critical information can continue to be displayed in the event of an equipment or wiring failure. Of most importance is flight attitude, heading, and air data information. The GRS 77 and GDC 74B each have four separate ARINC 429 data lines which are all capable of sending data to the displays.
5.8 5.8.1 GDU 104X Troubleshooting GDU 104X Common Problems Symptom Recommended Action • Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Cycle power. Display is blank 9 • Display resets • Use a bright light to verify LCD is active. 9 Adjust avionics dimmer control full clockwise. 9 Manually turn up backlight on the PFD and load configuration files to the GDU.
Symptom Terrain/Obstacle/Safetaxi does not display Display will not track dimmer bus Recommended Action • Ensure supplemental data cards are inserted correctly in the lower slots of all three GDU’s. • Allow the system to verify the data on the cards for approximately five minutes after power-up. • If a database does not activate, reload the problem database onto the SD Card or replace the card. • Reload GDU configuration files.
5.9 5.9.1 GDU 104X Alerts Software/Configuration Alerts Failure Message Cause SW MISMATCH – GDU software version mismatch. Xtalk is off. The system has found the PFDs and/or MFD software versions do not match. MANIFEST – PFD 1 software mismatch. Communication Halted. MANIFEST – PFD 2 software mismatch. Communication Halted. MANIFEST – MFD1 software mismatch. Communication Halted. The system has detected an incorrect software version loaded in the specified PFD.
Failure Message Cause MFD1 CONFIG – MFD1 configuration error. Config service req’d. PFD 1 CONFIG – PFD 1 configuration error. Config service req’d. A configuration mismatch has occurred between the display and the Master Configuration Module. Solution • Reload the display configuration files from SD Loader Card. • Reload system configuration files by pressing the UPDT CFG softkey on the Configuration Upload Page in the PFD1 System Page Group to load configuration files into the configuration module.
5.9.2 Database Alerts Failure Message Cause MFD1 DB ERR – MFD1 aviation database error exists. PFD 1 DB ERR – PFD 1 aviation database error exists. The MFD or specified PFD has encountered an error in the Jeppesen aviation database. Solution • Reload aviation database into the display. • Contact Garmin Technical Support for assistance. • Confirm supplemental data card is inserted fully. • Reload the database or replace the supplemental datacard.
Failure Message Cause DB MISMATCH – Airport Terrain database version mismatch. Xtalk is off. The PFDs and/or MFD have different Airport Terrain database versions installed. DB MISMATCH – Terrain database version mismatch. The PFDs and/or MFD have different terrain database versions installed. DB MISMATCH – Obstacle database version mismatch. The PFDs and/or MFD have different obstacle database versions installed. DB MISMATCH – Terrain database type mismatch.
5.9.4 Key Alerts Failure Message Cause Solution MFD1 “key” KEYSTK – key is stuck. The SYSTEM has determined a key is stuck on MFD1. • PFD 1 “key” KEYSTK – key is stuck. The system has determined a key is stuck on the PFD 1. Go to the GDU TEST page in configuration mode and verify key is stuck (if key is stuck the corresponding indicator will be green). • Exercise suspected stuck key and reset GDU TEST page to see if indicator remains green without pressing the key.
Failure Message MFD1 SERVICE – needs service. Return unit for repair. Cause Solution • Ensure the MFD connector is fully seated and locked. • If the unit was started in a very dark environment the photocells may not have enough light to initially raise the CCFT level. Go to the GDU STATUS page in configuration mode, ensure CCFT CRNT 1 & 2 levels are above 50. The G1000 has determined MFD1 needs service. MFD1 VOLTAGE – MFD1 has low voltage. Reducing power usage. The MFD supply voltage is low.
5.9.6 GMA Common Problems Symptom/Failure Message Recommended Action Noise in Audio Most often the cause of the noise is external to the GMA. Try the following to locate the source of the noise before replacing the GMA: • Try a different pair of headsets. Noise cancelling headsets may pick up and/or generate more noise than standard headsets from their own circuitry. • Check for noise with the engine turned off.
5.9.7 GMA Alerts Failure Message GMA1 SERVICE – GMA1 needs service. Return unit for repair. GMA2 SERVICE – GMA2 needs service. Return unit for repair. Cause Solution The system has determined that the specified GMA 1347D needs service. • Replace GMA . • Ensure GMA1 is receiving power. • Ensure both GIAs are receiving power. • Ensure all GDUs are receiving power. • Ensure the GMA/GIA RS-232 data lines are working properly. • Ensure the GIA/GDU Ethernet data lines are working properly.
5.10 GIA 63 Troubleshooting 5.10.1 COM Symptom Recommended Action • Weak COM transmit power • Weak COM receiver • No COM sidetone Switch GIA1 and GIA2, to verify location of problem: 9 If problem follows unit, replace GIA. 9 If problem does not follow unit, check COM antenna and cabling for faults. Switch GIA1 and GIA2, to verify location of problem: 9 If problem follows unit, replace GIA. 9 If problem does not follow unit, check COM antenna and cabling for faults.
5.10.4 GPS Symptom Recommended Action • Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Using the MFD AUX – GPS Status page, verify the signal strength bars are not erratic. If so, this indicates outside interference is affecting the GPS receivers. Find and remove the source of interference (i.e. cell phones, FBO datalink antennas, etc.). • Check date and time on Date/Time Setup Page.
5.11 GIA Alert Messages 5.11.1 COM Alerts Failure Message Cause Solutions COM1 SERVICE – COM1 needs service. Return unit for repair. The system has determined COM1 needs service. • Replace GIA1 according to instructions in Section 6. COM2 SERVICE – COM2 needs service. Return unit for repair. The system has determined COM2 needs service. • Replace GIA2 according to instructions in Section 6. • Press the push-to-talk switch(s) again to cycle its operation.
Failure Message Cause Solutions Press the COM1 external remote transfer switch again to cycle its operation. Check COM1 external remote transfer switch and wiring. COM1 RMT XFR – COM1 remote transfer key is stuck. The COM1 external remote transfer switch is stuck in the enabled (or “pressed”) state. Switch GIA1 and GIA2, to identify whether the unit or connectors/wiring is at fault (Both GIAs must be configured when swapped, see Section 3.9) 9 If problem follows the unit, replace GIA1.
5.11.2 NAV Alerts Failure Message Cause Solution NAV1 SERVICE – NAV1 needs service. Return unit for repair. The system has detected a failure in NAV1 receiver. • Replace GIA1. NAV2 SERVICE – NAV2 needs service. Return unit for repair. The system has detected a failure in NAV2 receiver. • Replace GIA2. Press the NAV1 external remote transfer switch again to cycle its operation. Check NAV1 remote transfer switch and wiring. NAV1 RMT XFR – NAV1 remote transfer key is stuck.
5.11.3 Glideslope Alerts Failure Message Cause Solution G/S1 SERVICE – G/S1 needs service. Return unit for repair. The system has detected a failure in G/S1 receiver. • Replace GIA1. G/S2 SERVICE – G/S2 needs service. Return unit for repair. The system has detected a failure in G/S2 receiver. • Replace GIA2. • Switch GIA1 and GIA2 to verify location of problem: G/S1 FAIL – G/S1 is inoperative. 9 The system has detected a failure in G/S1 receiver.
Failure Message Cause Solution LOI – GPS integrity lost. Crosscheck with other NAVS. If the primary receiver is a WAAS sensor, the alert indicates that GPS position data has timed out. • GPS NAV LOST – Loss of GPS navigation. Insufficient satellites. There is no GPS position fix available or the system is in dead reckoning mode. GPS NAV LOST – Loss of GPS navigation. Position error. The G1000 has detected an internal position warning has occurred.
5.11.5 GIA Cooling Alerts Failure Message Cause GIA1 COOLING – GIA1 temperature too low. GIA1 operating temperature is too low. • Allow unit to warm up. GIA2 COOLING – GIA2 temperature too low. GIA2 operating temperature is too low. • Allow unit to warm up. GIA1 COOLING – GIA1 over temperature. GIA2 COOLING – GIA2 over temperature. GIA1 has exceeded its operating temperature range. GIA2 has exceeded its operating temperature range.
5.11.6 GIA Configuration Alerts Failure Message Cause Solution MANIFEST – GIA1 software mismatch. Communication Halted. The system has detected an incorrect software version loaded in GIA1. • MANIFEST – GIA2 software mismatch. Communication Halted. The system has detected an incorrect software version loaded in GIA2. Load the correct software. See Section 3.9 for the Software Loading procedure. • Reload audio configuration files. • Load the configuration files for that GIA. See Section 3.
5.12 GEA Troubleshooting 5.12.1 GEA Alerts Failure Message MANIFEST – GEA1 software mismatch. Communication halted. MANIFEST – GEA2 software mismatch. Communication halted. Cause The system has detected an incorrect software version loaded in the specified GEA 71. Solution Load the correct software verion. See Section 3.9 for GEA 71 Software Load Procedure. • GEA1 CONFIG – GEA1 configuration error. Config service req’d. • Load GEA configuration files. See Section 3.
5.13 GTX Troubleshooting 5.13.1 GTX Alerts Failure Message MANIFEST – GTX1 software mismatch. Communication halted. MANIFEST – GTX2 software mismatch. Communication halted. Cause Solutions The system has detected an incorrect software version loaded in the specified GTX 33. • Reload software. See Section 3.9 for the Software Load Procedure. • Perform a SET>ACTV configuration reset on the GTX Config page and verify the aircraft registration is present.
5.14 GDL 69A Troubleshooting 5.14.1 GDL 69A Common Problems Symptom Recommended Action No XM audio is heard • • Ensure the following items are not preventing the audio panel from distributing XM audio (reference applicable G1000 Pilot’s Guide): 9 Verify the XM volume is not muted on the AUX – XM RADIO page on the MFD. 9 Verify the COM squelch is not open. 9 Verify the ICS squelch is not open. 9 Verify the marker beacon tones are not being received.
5.14.2 GDL 69A Alerts Failure Message Cause GDL 69 FAIL – GDL 69 has failed. The G1000 has detected a failure in the GDL 69A. GDL69 CONFIG – GDL 69 configuration error. Config service req’d. The G1000 has detected a GDL 69A configuration mismatch. MANIFEST – GDL software mismatch. Communication halted. The system has detected an incorrect software version loaded in the GDL 69A. Page 5-66 Revision 6 Solutions • Replace GDL 69A. • Check GDL 69A antenna and cabling.
5.15 GRS 77/GMU 44 Troubleshooting 5.15.1 AHRS Common Problems Symptom AHRS does not complete initialization Recommended Action • Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Ensure GPS has acquired at least four satellites, has a 3D navigation solution, and a DOP of less than 5.0. This is particularly important if this issue appears during ground operation only. • Calibrate the GRS 77.
5.15.2 GRS Alerts Failure Message MANIFEST – GRS1 software mismatch. Communication halted. MANIFEST – GRS2 software mismatch. Communication halted. AHRS1 SERVICE – AHRS1 magnetic-field model needs update. Cause Solutions The system has detected an incorrect software version loaded in the specified GRS 77. • Load correct software version. See Section 3.9 for the Software Load Procedure. • Load updated AHRS magnetic field file. See Section 4.6.
Failure Message MAG VAR WARN – Large magnetic variance. Verify all course angles. Cause Magnetic variance value from GMU 44 is not accurate. Solutions • If flying near large radio towers or other sources of possible electromagnetic interference, the condition should correct itself as the aircraft leaves the area. • If problem persists, run magnetic interference check in Section 5.15.4 to check for magnetic interference in the aircraft. 5.15.
5.15.4 Calibration Procedure E: Magnetometer Interference Test A magnetometer interference test is available for troubleshooting and/or verifying a magnetically ‘clean’ installation of the GMU 44. This test exercises various devices on the aircraft that could potentially affect the magnetic field as measured by the GMU 44. NOTE This test is used to validate that no electronic device interferes with the operation of the GMU 44 magnetometer.
3. This page is protected and requires a keystroke password to perform this test. Press the following softkeys in sequence: (as counted from left to right on lower bezel of MFD) • softkey 9 • softkey 10 • softkey 11 • softkey 12 4. Select MAG INTERFERENCE TEST and press the PFD1 ENT key. 5. Follow the checklist items displayed on the PFD1, and press the ENT key as each one is completed or confirmed.
Table 5-5, Magnetometer Interference Test Sequence Elapsed Time since Start of Test (min:secs) 0:00 0:05 0:10 0:20 0:30 0:40 0:50 1:00 1:20 1:40 1:50 2:00 2:10 2:20 2:30 2:40 2:50 3:00 3:10 Action Test begins Tail Flood lights on Navigation lights on Navigation lights off Landing lights on Landing lights off Taxi lights on Taxi lights off Strobes on Strobes off Recognition lights on Recognition lights off Beacon on Beacon off Rudder full left Rudder full right Elevator full nose UP Elevator full nose DN En
NOTE It is important that the “time equals zero” moment corresponds with the moment the PFD first displays the blinking TEST COMPLETE? Message. 7. The operator should carry out the actions called for in the prepared test sequence. NOTE It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence. 8.
5.16 GDC 74B Troubleshooting 5.16.1 Air Data Common Problems Symptom Recommended Action • Perform a pitot/static check per Section 7.6 of this manual. • Determine which instrument is outside limits and replace. The GDC may be field adjusted per Garmin Service Advisory 0720. Note: Both units may individually be in spec but show a difference in altitude. Do not return the GDC to Garmin for service if not outside limits.
5.17 GWX 68 Troubleshooting 5.17.1 GWX 68 Alerts and Problems WARNING: Before energizing the equipment, be sure microwave radiation safety precautions including both fuel and personnel safety considerations have been observed. These include clearing all personnel to an area beyond the maximum permissible exposure level (MPEL) boundary. The MPEL for the GWX 68 is 11 feet. Failure Message Cause Solutions • Load GWX configuration files, • Replace GWX.
5.18 GMC 710 Troubleshooting 5.18.1 GMC 710 Alerts and Problems Failure Message Cause Solutions • Load GMC configuration files. • Replace GMC. • If problem persists, replace master configuration module, check config module wiring for faults and replace if necessary. NOTE GMC CNFG – GMC Config error. Config service req’d. The G1000 has detected a GMC 710 configuration mismatch. GMC FAIL – GMC is inoperative. The G1000 has detected a failure in the GMC 710. MANIFEST – GMC software mismatch.
5.19 GCU 477 Troubleshooting 5.19.1 GCU 477 Alerts and Problems Failure Message Cause Solutions • Load GCU configuration files. • Replace GCU. • If problem persists, replace master configuration module, check config module wiring for faults and replace if necessary. NOTE GCU CNFG – GCU Config error. Config service req’d. The G1000 has detected a GCU 477 configuration mismatch. GCU FAIL – GCU is inoperative. The G1000 has detected a failure in the GCU 477. MANIFEST – GCU software mismatch.
5.20 Software/Configuration Troubleshooting Problem Solutions MFD or PFD displays do not power up: • Ensure that the criteria listed in Section 5.20.1 are fulfilled for the applicable situation. • Ensure power is present at display backshell connector. • Troubleshoot per the “Blank Display” GDU section. • Ensure that criteria listed in Section 5.20.1 are fulfilled for the applicable situation. • Ensure that LRU is reporting data on System Status page (LRU is ‘ONLINE’).
5.20.1 System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation: Desired Operation Criteria for Success Load Software to MFD or PFD Displays • SW Loader Card must be inserted in top slot for each display to be loaded. • CLR & ENT keys must be held during power up of display. • Power on only one display at a time during software loading. • SW Loader Card must be inserted in top slot of PFD 1. • PFD 1 and MFD must be powered on.
5.21 Backshell/Backplate Connectors The following figures depict the backplate connectors as viewed with the LRU removed.
P712 1 2 3 4 5 6 7 8 P711 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 Figure 5-9, GEA 71 Backplate Connectors P13472 P13471 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 7
Figure 5-12, GDU 1040A/1500 Backshell Connector (P10401 or P15001) Figure 5-13, GRS 77 Backshell Connector (P771) Figure 5-14, GDC 74B Backshell Connector (P74B1) Figure 5-15, GDL 69A Backplate Connector (P69A1) Page 5-82 Revision 6 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air 190-00915-01
Figure 5-16, GCU 477 Backshell Connector (P4751) Figure 5-17, GMC 710 Backshell Connector (P7101) Figure 5-18, GWX 68 Backshell Connector (P681) 60 40 61 21 1 62 41 42 22 2 63 43 23 3 64 44 24 4 65 45 25 5 66 46 26 6 67 47 27 7 68 48 28 8 69 49 29 9 30 10 70 50 71 72 51 52 31 11 32 12 73 53 33 13 74 54 34 14 75 55 35 15 76 56 36 16 77 37 17 78 58 57 38 18 59 39 19 20 Figure 5-19, GTS 820/850 Mating Connectors (P8001 and P8002) (Rear View) 1 2 3 4 5 6 7 8 9 10 1
Figure 5-21, GPA 65 Mating Connector (P651) (Rear View) Figure 5-22, Signal Conditioner (1PVIB1 and 2PVIB1) (Rear View) 60 40 61 21 1 62 22 2 63 43 41 42 23 3 64 44 24 4 65 45 25 5 66 46 26 6 67 47 27 7 68 48 28 8 69 49 30 29 9 70 50 10 71 72 51 52 31 11 32 12 73 53 33 13 74 54 34 14 75 55 35 15 76 56 36 16 77 37 17 78 58 57 38 18 59 39 19 20 Figure 5-23, GDL 59 Mating Connector (1P591) (Rear View) 15 14 30 13 29 44 12 28 43 11 27 42 10 26 41 9 25 40
5.22 Standby Attitude Indicator Troubleshooting Symptom Recommended Action • Perform the Standby Instrument Electrical Power Checks in Section 8.1.5. • Remove the unit per Section 6.27 and inspect the electrical connector. • Check to ensure appropriate electrical power is being supplied to the instrument. Warning flag pops into view, indicating that the gyro motor is not receiving sufficient power to operate Unit fails to perform to specifications 5.
5.24 Standby Altimeter Troubleshooting Symptom Recommended Action Altimeter lighting is inoperative or malfunctioning • Perform the Standby Instrument Electrical Power Checks in Section 8.1.5. • Remove standby altimeter per Section 6.26 and inspect the electrical connector. • Check that electrical power is being appropriately supplied to the instrument. Altimeter Vibrator is inoperative or malfunctioning or fail flag is displayed Altitude displayed is incorrect 5.
• If the 28 VDC is missing, check the C/B. • If 28 VDC power to the computer is present, check the transducer excitation voltage on TP 24 (Hi) and TP 25 (Lo). The voltage should be 10 ± 0.75 VAC at 720 ± 72 Hz. • If the excitation voltage is not within the ranges specified, replace the computer. • If the excitation voltage is within the ranges specified, check the LAA output on TP 18 (Lo) and TP 19 (Hi). The output is a varying DC voltage based on the transducer vane position.
26 I Lift Transducer Secondary (Fast) Input 27 I Lift Transducer Center Tap (Common) 28 I Lift Transducer Secondary (Slow) Input Lift Transducer Secondary Input into the computer. 5.25.
5.27 GSR 56 Troubleshooting Symptom Recommended Action No communication with GSR 56 No or low-quality Iridium signal • Check power wiring and pin out of GSR 56 unit. • Ensure GSR 56 configuration option has been loaded. • Ensure the Iridium antenna has an unobstructed view of satellite constellation. • Check the Iridium antenna cable and connectors. • Verify antenna ground plane is adequate.
Problem Cause Solution 1030 MHz Fault Internal Fault connected in their proper place. Verify input voltage and if it continues return to Garmin for service. Return to Garmin for service 1090 MHz Fault Internal Fault Return to Garmin for service PA/LNA Fault Antenna connections or internal fault Receiver Fault Antenna connections or internal fault Transmitter Fault Antenna connections or internal fault Baro Altitude Fault Baro Altimeter is not powered on or improper wiring.
6 Equipment Removal & Installation This section describes how to remove and replace equipment in the King Air 200/B200 associated with this STC. After removal and replacement, LRUs must be configured and tested as described in Section 7. CAUTION: When removing and/or replacing any G1000 component, always ensure that aircraft power is off. Unplug any auxiliary power supplies.
6.1 GDU 1040A/1500 Removal: 1. Using a 3/32” hex tool, rotate all four ¼-turn fasteners counter-clockwise until they reach their stops. 2. Carefully remove the display from the panel. 3. While supporting the display, disconnect the connector. Reinstallation: 1. Visually inspect the connector and pins for signs of damage. Repair any damage. While supporting the display, connect the connector to the rear of the unit. 2.
6.3 GIA 63W Integrated Avionics Units Removal: 1. Gain access to the forward avionics compartment in the nose of the aircraft. 2. Unlock the GIA 63W handle by loosening the Phillips screw on the handle. 3. Pull the handle upward to unlock the GIA 63W. Gently remove the unit from the rack. Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 2. Gently insert the GIA 63W into its rack. The handle should engage the dogleg track. 3.
6.5 GTX 33( ) Transponder Removal: 1. Gain access by removing the cabin center floor panel at the main entry door. 2. Remove the remote equipment shelf. Alternately, detach the two rack mount angles from the shelf. Retain all mounting hardware. 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. Reinstallation: 1.
6.8 GRS 77 AHRS Removal: 1. Gain access to the forward avionics compartment in the nose of the aircraft. 2. Disconnect the AHRS connector. 3. Loosen the four Phillips thumbscrews with a screwdriver until they are free from the rack. 4. Gently lift the GRS 77 from the mounting rack. (If the mounting rack is removed, the GRS 77 must be re-calibrated. Do not loosen mounting bolts. See Section 7.7) Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins.
5. Configure and test the GDL 69A according to Section 7.8. 6.11 GSA 80 Servos Removal: 1. Gain access to the desired servo(s). 2. Disconnect the servo harness connector. 3. Use a socket or open-wrench to loosen and remove the servo attachment bolts. The Pitch-Trim servo bracket will need to be removed to access all the Pitch-Trim servo attachment bolts. 4. Carefully remove the servo and place a protective cover on the output gear. 5. Place a protective cover over the GSM 85A/86 servo gearbox.
6.12 GSM 85A/86 Servo Gearbox Removal: 1. Remove the desired servo(s) per Section 6.11. 2. For the Roll, Pitch and Yaw Servos: remove the servo bridle cables from the control cable clamps. For the Pitch-Trim Servo: disconnect the servo cable at the forward turnbuckle and aft terminal. 3. Use a socket or open-wrench to loosen and remove the servo attachment bolts. 4. Carefully remove the servo gearbox(es). 5.
6.14 GMC 710 Removal: 1. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn counterclockwise until they reach their stops. 2. Disconnect backshell assembly from unit. Reinstallation: 1. Inspect connector(s) for damaged pins. 2. Connect backshell assembly to unit. 3. Hold unit flush with the mounting bracket, ensuring locking stud alignment marks are in the vertical position. 4. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn clockwise.
6.16 Configuration Module Removal & Replacement Configuration modules (Item 1 shown below) are located in the following LRU harness connector backshells (Item 6): GDU 1040A PFD, GRS 77 AHRS, GDC 74B Air Data Computer, and the GEA 71 Engine/Airframe Unit. Refer to the Master Drawing List, listed in Table 1-2, for specific installation drawings.
6.16.1 Configuration Module Checkout If a GRS 77 AHRS Configuration Module is replaced: All three GRS 77/GMU 44 calibration procedures must be performed. Proceed to Section 7.7.3. If a GDC 74B Configuration Module is replaced: Configuration settings must be reloaded to the GDC 74B per Section 3.9, then proceed to Section 7.6.1. If a GEA 71 Configuration Module is replaced: Proceed to Section 7.4.1.
6.17 GEA 71 Backshell Thermocouple Removal & Replacement The GEA 71 has a K-Type thermocouple (Item 1 shown below) installed in its backshell, in addition to the configuration module. The thermocouple is used in conjunction with the configuration module temperature sensor to compensate for temperature probe errors resulting from the dissimilar metals at the pin contacts. Figure 6-3, GEA Backshell Thermocouple Table 6-2, Thermocouple Kit (011-00981-00) Item # Description Qty.
Replacement: 1. Crimp pins, item 2, onto each of the thermocouple wires, item 1. Ensure that pre-stripped wire length is 1/8” prior to crimping. 2. Insert newly crimped pins and wires into the appropriate connector housing location, item 4, as specified by King Air 200/B200 Wiring Diagram, listed in Table 1-2. 3. Place thermocouple body, item 1, onto the backshell boss, item 5. Place the thermocouple as shown in Figure 6-3 so that the wires exit towards the bottom of the backshell. 4.
6.20 Iridium Antenna Removal: 1. Gain access to the antenna coaxial cable connector by removing the aft cabin ceiling panel. Refer to the Antenna Install drawing listed in Table 1-2. 2. Disconnect the antenna coaxial cable. 3. Remove the antenna mounting screws. 4. Remove antenna. Reinstallation: 1. Install antenna using retained mounting screws. 2. Connect the antenna coaxial cable. 3. Fillet seal around antenna. Refer to the Antenna Install drawing listed in Table 1-2. 4.
5. If planning to reinstall the same unit, it is not necessary to disconnect the ground strap from the unit ground stud. If replacing with a new unit, disconnect the ground strap from the removed unit and retain the ground strap and associated hardware for reinstallation on the new unit. Reinstallation: 1. Reinstallation of the Signal Conditioners is the reverse of the removal. Note that the p/n 85-292-2 and 85-292-4 units are interchangeable.
6.25 Standby Airspeed Indicator Removal: 1. Remove MFD per Section 6.1. 2. Disconnect pitot-static plumbing from the back of the standby airspeed indicator. Take necessary precautions to prevent foreign object debris from entering the pitot-static lines during maintenance. 3. Disconnect the electrical connector from the standby airspeed indicator. 4. Use a Phillips screwdriver to remove the attachment screws from the front of the standby airspeed indicator. 5. Remove the standby airspeed indicator.
6.27 Standby Attitude Indicator Ensure the standby attitude indicator gyro is not spinning—this may take 10 minutes or longer after the unit has been turned off. This unit is very delicate; handle like eggs. Refer to the 4200 Series Attitude Indicator Installation Manual, listed in Table 1-2, for more handling instructions. Removal: 1. Remove MFD per Section 6.1. 2. Disconnect the electrical connector of the standby attitude indicator. 3. Use a 0.
Reinstallation: 1. Reinstallation of the Sandia GDU cooling fan is the reverse of the removal. Reference the Main Instrument Panel Installation drawing, listed in Table 1-2, for more details. 2. If further maintenance is not required, proceed to Section 8. 6.
7. No configuration is required for the GPA 65. Test the GTS 8XX per Section 7.26. 6.32 GA 58 Traffic Antennas Removal: 1. Gain access to the antenna coaxial cable connectors by removing the cabin interior ceiling panel. Refer to the Antenna Install drawing listed in Table 1-2. 2. Disconnect the four coax “quick-lock” connectors. 3. Remove the antenna mounting screws. 4. Remove antenna. Reinstallation: 1. Install antenna using retained mounting screws. 2. Connect the four coax connectors.
5. Reinstall the cabin center floor panel. 6. If new unit is installed, register with Garmin Flight Data Services per Section 7.27. 7. Configure the GDL 59 per Section 3.21 and 3.23. Test the GDL 59 per Section 7.28. 6.34 GSR 56 Satellite Receiver Removal: 1. Gain access by removing the cabin center floor panel at the main entry door. 2. Detach the two rack mount angles from the remote equipment shelf. Retain all mounting hardware. 3.
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7 G1000 Equipment Configuration & Testing This section provides procedures to be followed after a piece of G1000 equipment is replaced. At the beginning of each LRU section, instructions are given to guide the technician for various removal/replacement scenarios. These instructions define necessary procedures to be followed for situations where original equipment was reinstalled as well as for situations where new equipment (new serial number) is installed.
7.1.1 PFD/MFD Test 1. Allow displays to initialize for ~1 minute. 2. Check that all COM/NAV display fields are valid in the top corners of both PFDs. 3. Check that attitude, heading, altitude, airspeed, vertical speed and OAT fields are valid within 2 minutes of power up on both PFDs. 4. Press the SENSOR softkey on each PFD and switch between ADC1 and ADC2. Verify that data from both GDC 74Bs is valid on both displays. 5. Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2.
7.2 GMA 1347D Audio Panel Original GMA 1347D Reinstalled No software/configuration loading or testing is required if the removed GMA 1347D 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 final return-to-service checks in Section 8.
Transceiver Operational Check Perform a ramp test radio check by exercising the installed transceivers, microphone, microphone key and audio over the headphones and speaker. Verify that communications are clear and PTT operation is correct for each pilot position. 1. On the pilot’s audio panel, select the audio source corresponding to each installed avionics unit (i.e. NAV1, NAV2, COM1, COM2, ADF and DME) and check for audio over the pilot’s headset. 2.
7.2.2 Landing Gear Aural Alert Check This check should be conducted in conjunction with the Phase 2 and Phase 4 Landing Gear Retraction, Warning Horn check, in the existing King Air Maintenance Program. NOTE This procedure is applicable only to aircraft equipped with a tone generator as part of the aircraft audio system. Refer to the appropriate aircraft wiring diagrams to determine if a tone generator is installed.
7.3 GIA 63W Integrated Avionics Unit Original GIA 63W(s) Reinstalled No software or configuration loading is required if the removed GIA is re-installed in its 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. Continue to the return-toservice checks in Section 8.
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: 1. On the MFD, monitor GPS signal strength bars on the AUX – GPS STATUS page. 2. On the PFD, ensure that the CDI is set to GPS. If it is not, press the ‘CDI’ softkey until GPS ENR is displayed. 3.
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 1.
7.4 GEA 71 Engine/Airframe Unit Original GEA 71 Reinstalled No software or configuration loading is required if the removed GEA 71 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 return-to-service checks in Section 8.
7.4.2 GEA Engine Indication Checks Perform engine indicating systems checks for the following left and right engine indications: Reference King Air 200 Series Maintenance Manual, Chapter 77-00-00, “Engine Indicating – Maintenance Practices”. • • • • 7.4.3 ITT N1 N2 Torque GEA Fuel Flow Indication Functional Check The special tools and equipment listed in Table 7-1 are provided for reference only and are not specifically required. Any product conforming to the specification listed may be used.
7.4.4 GEA Oil Pressure Indication Functional Check The special tools and equipment listed in Table 7-3 are provided for reference only and are not specifically required. Any product conforming to the specification listed may be used. It is the responsibility of the technician or mechanic to determine the applicable specification prior to testing.
7.5 GTX 33( ) Transponder Original GTX 33( ) is Reinstalled No software or configuration loading is required if the removed GTX 33 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 GTX 33 Test (Section 7.5.2). Original GTX 33( ) Installed in Opposite Locations for Troubleshooting No software loading is required if the original GTX #1 and GTX #2 are installed in opposite locations.
6. After each configuration setting change, press the ENT key to configure the transponders. 7. Press the ENT key on PFD1 to acknowledge prompt. 8. After completing transponder configuration, deactivate the cursor. 7.5.2 GTX 33( ) Test Operation of the GTX 33 or GTX 33D Mode-S transponder is accomplished using PFD 1, PFD 2 or the MFD. Refer to G1000 in King Air 200/B200 Cockpit Reference Guide, listed in Table 1-2, for basic operation.
7.6.1 Air Data Test (GDC 74B) The G1000 system must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1-3 and appropriate regulations.
Table 7-5, Air Data System Test Test Point Altitude (FT) Airspeed (KIAS) AIR DATA 1 AIR DATA 2 Nominal Altitude ALT AS 0 0 0 99 0 132 0 198 0 50 1000 50 2000 80 4000 80 8000 260 8000 10000 120 10000 11000 120 11000 13000 150 13000 14000 150 14000 16000 180 16000 18000 210 18000 19000 138 18983 19000 162 18971 19000 185 18958 19000 209 18947 19000 221 18947 19000 233 18947 0 0 0 1000 2000 4000 8000 8000 AIR DATA 1 AIR DATA 2 Tolerance Tolerance Tolerance T
Air Data System Test (Continued) Test Point ALT AS 29000 Altitude (FT) Nominal Altitude 111 28999 29000 130 28982 29000 150 28967 29000 169 28953 178 28946 188 28937 196 28928 97 35016 114 34996 130 34978 147 34961 156 34953 164 34946 29000 29000 29000 35000 35000 35000 35000 35000 35000 35000 171 34939 Aircraft S/N: _____________________ ADTS Make: _______________________ Model: _______________________ S/N: _______________________ Cal.
7.6.2 Static Port Vertical Speed (Rate of Climb) Test 1. Command ADTS to change the altitude at the rates shown in the table below. 2. Wait for ADTS to report that target rates have been achieved. 3. Verify that the Rate of Climb reported by the Vertical Speed field on PFD1 and PFD2 are within the tolerances specified in Table 7-6: Table 7-6, Vertical Speed Table Vertical Speed, feet/minute 2000 1000 500 200 0 -200 -500 -1000 -2000 7.6.
7.7 GRS 77 AHRS / GMU 44 Magnetometer Original GRS 77 is Reinstalled If the original GRS 77 is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. If the GRS rack was not removed or loosened, continue to the GRS/GMU Test (Section 7.7.6). If the GRS rack was removed or loosened, continue to the GRS/GMU Calibration Procedures (Section 7.7.1).
7.7.1 GRS/GMU Calibration Procedures GRS/GMU Recalibration Criteria The following calibration procedures are provided for the GRS 77 and GMU 44: • Pitch/Roll Offset: (Procedure A1, PROVIDED IN SECTION 7.7.2) • Magnetometer Calibration: (Procedure B, PROVIDED IN SECTION 7.7.4) • Engine Run-Up Vibration Test: (Procedure D, PROVIDED IN SECTION 7.7.5) • Magnetometer Interference Test: (Procedure E, PROVIDED IN SECTION 5.15.
7.7.2 Procedure A1: GRS 77 Pitch/Roll Offset Calibration This procedure must be performed for both GRS 77 units installed in the aircraft. This first procedure must be carried out with the engine off. 1. Level the aircraft to within ±0.25° of zero pitch and zero roll using a digital level. (Follow instructions in King Air 200 Series Maintenance Manual, listed in Table 1-2, for leveling) 2. Start the G1000 system in Configuration mode. 3.
11. The result of the pitch/roll offset compensation is displayed on the PFD. If successful, the AHRS records the required pitch and roll offsets, informs the operator of a successful conclusion and returns to normal operation. 12. Press the ENT key on the PFD to conclude this procedure for GRS 77 #1. 13. Repeat steps 1 through 6 for GRS 77 #2. NOTE The Magnetometer Calibration Procedure that follows in Section 7.7.
7.7.4 1. Procedure B: GRS 77/GMU 44 Magnetic Calibration NOTE Procedure A-1 (Section 7.7.2) must first be successfully accomplished before performing Procedure B, only for situations where the GRS 77 was replaced with a new unit. Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free of environmental magnetic disturbances. Attempting to carry out this maneuver on a typical ramp area may not yield a successful calibration.
12. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 25° to 30° of turn from the last heading, the PFD display advises the operator to stop the aircraft. NOTE Due to the difficulties in executing smooth, accurate turns the PFD may incorrectly interpret a station and instruct to “HOLD POSITION” prior to full completion of a 30° turn.
7.7.5 Procedure D: Engine Run-Up Vibration Procedure NOTE Calibration Procedure D is performed in order to guarantee that the AHRS mounting is sufficiently rigid and insensitive to vibration. This procedure must be performed for both GRS 77 units installed in the aircraft. Calibration Procedures A1 and B (Sections 7.7.2 and 7.7.4 respectively) are not required prior to this procedure. Figure 7-6, Engine Run-Up Test Page 1. Press the FMS small knob to highlight GRS 77 #1.
NOTE Should a failure occur, the technician may perform the Engine Run-up test up to 3 times successively before corrective action must be taken. If the test does not pass after three attempts, then the installation should not be considered reliable until the source of the vibration problem is identified and remedied. In the event of repeated failure of the engine run-up test, record the values that are reported to be out of range for future reference.
7.8 GDL 69A XM Data Link Original GDL 69A is Reinstalled No software or configuration loading is required if the removed GDL 69A 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 GDL 69A Test (Section 7.8.1).
7.10 GCU 477 FMS Controller Original GCU 477 Reinstalled No software or configuration loading is required if the removed GCU 477 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 GCU 477 Test (Section 7.10.1). New, Repaired or Exchange GCU 477 Installed If a new, repaired or exchange GCU 477 is installed, the correct software and configuration files must be loaded to the unit.
23. Using GCU477 keypad, enter in a frequency of 123.450. Verify COMM2 frequency changes as entered. 24. Press the NAV key until 1 is lit. Verify the tuning box is present around the NAV 1 frequency on PFD1. 25. Using GCU477 keypad, enter in a frequency of 108.00. Verify NAV1 frequency changes as entered. 26. Press the NAV key until 2 is lit. Verify the tuning box is present around the NAV 2 frequency on PFD1. 27. Using GCU477 keypad, enter in a frequency of 108.00.
7.11 GMC 710 AFCS Controller Original GMC 710 Reinstalled No software or configuration loading is required if the removed GMC 710 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 GMC 710 Test (Section 7.11.1). New, Repaired or Exchange GMC 710 Installed If a new, repaired or exchange GMC 710 is installed, the correct software and configuration files must be loaded to the unit.
7.12 GWX 68 Weather Radar Original GWX 68 Reinstalled No software or configuration loading is required if the removed GWX 68 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 GWX 68 Test (Section 7.12.1). New, Repaired or Exchange GWX 68 Installed If a new, repaired or exchange GWX 68 is installed, the correct software and configuration files must be loaded to the unit.
7.13 1. Non-Garmin Traffic System Functional Check Select the TRAFFIC MAP page on the MFD. 2. Verify that the STANDBY, OPERATE, TEST and ALT MODE soft keys are available on the bottom of the MFD. Verify that an operating mode; STANDBY, OPERATE, or TEST (not TAS FAIL) is displayed in the upper left corner of the traffic map. Verify that NO DATA is not displayed in yellow in the center of the display over the aircraft symbol.
7.14 Stormscope Functional Check Reference Section 3.17, Stormscope (WX-500) Configuration, for configuring Stormscope. This procedure assumes familiarity with the set-up and operation of the WX-PA portable analyzer kit. 1. Apply power to the WX-500 and verify that no failed test messages appear. If fault messages do appear, refer to the WX-500 Installation Manual for troubleshooting. 2. Following successful power up, verify the following modes: • Access to both 3600 and 1200 weather view modes.
15. Press MENU/ENTER to start the test. 16. Observe the MFD to ensure the proper positioning of the strikes, based on range and azimuth settings on the WX-PA. Change the cardinal bearings and verify correct test strikes. Verify the strikes are within 10 degrees of the selected azimuth and plot at 60NM (1/2 120 NM). 17. Verify after 20 seconds of operation the strike counter reads 580 +/-40. 18. After testing for all ranges and bearings indicated, press 2ND then MENU/ENTER to return to the main menu. 19.
7.15 TAWS Functional Check 7.15.1 Functional Check for TAWS-B 1. With the G1000 in Normal Mode, use the GCU FMS knob to select the MAP group and TAWS page on the MFD. 2. Verify that the title at the top of the page reads “MAP – TAWS-B”. 3. NOTE If TAWS has not been enabled, the title will read “MAP – TERRAIN PROXIMITY” or “MAP – TERRAIN”. Refer to section 3.30 for TAWS Configuration for configuring TAWS. Press the GCU MENU button and select “Test TAWS System” from the pop-up menu.
7.15.2 Functional Check for TAWS-A 1. With the G1000 in Normal Mode, use the GCU FMS knob to select the MAP group and TAWS page on the MFD. 2. Verify that the title at the top of the page reads “MAP – TAWS-A”. 3. NOTE If TAWS has not been enabled, the title will read “MAP – TERRAIN PROXIMITY” or “MAP – TERRAIN”. Refer to section 3.30 for TAWS Configuration for configuring TAWS. Press the GCU MENU button and select “Test TAWS System” from the pop-up menu.
16. Ensure cockpit speaker is selected ON. Use the PFD1 FMS knob to highlight each of the following messages then select PLAY.
7.16 FliteCharts Functional Check Reference Section 3.20, FliteCharts Configuration, for configuring FliteCharts. NOTE This test is not required if ChartView is enabled. 1. With the G1000 in Normal Mode, use the GCU FMS knob to select ‘AUX – System Status’ page, then select MFD1 DB softkey. 2. Use the small FMS knob to scroll to CHART. 3. Verify “FliteCharts” is displayed in blue text adjacent to “CHART”. 4.
7.17 ChartView Functional Check ChartView must be enabled using a ChartView Enable Card, as specified in the General Arrangement Drawing listed in Table 1-2, and a current ChartView database. Reference section 3.29, “ChartView Configuration” for enabling procedures. NOTE The required ChartView databases are subscription-based and are to be procured by the aircraft owner directly from Jeppesen. 1.
7.18 SafeTaxi Functional Check The maximum map ranges for enhanced detail are configurable by the flight crew. When zoomed in close enough to show the airport detail, the map reveals runways with numbers, taxiways with identifying letters/numbers, and airport landmarks including ramps, buildings, control towers, and other prominent features. Resolution is greater at lower map ranges.
7.19 DME Functional Check This check verifies that the DME-to-G1000 interface operates correctly. NOTE Support for a single Collins DME-42 system is provided as an option in the G1000. If the DME option is selected, the DME channel one audio level must be adjusted by the procedure contained within Collins DME-42 Transceiver Repair Manual 523-0772458, Maintenance Section 523-0772460-006118, to adjust DME channel one audio level. Recommended nominal DME audio output level is 4.46 Vpp + 0.10 Vpp.
7.20 ADF Functional Check This check verifies that the ADF / G1000 interface operates correctly. 1. Press the PFD softkey on PFD1 and PFD2. Toggle the BRG1 and BRG2 softkey until the ADF bearing is shown on PFD1 and PFD2. 2. Verify that the ADF window is not invalid (no red ‘X’). 3. Using the ADF control head select a known valid local ADF. Verify that the ADF bearing pointer moves towards a bearing and stabilizes. 4. Select ADF and SPKR on GMA1 and GMA2. Using the ADF control head, select, ANT mode.
7.22 Weight on Wheels and Low Speed Awareness Band Check This procedure will verify that the GDU air ground status uses valid Weight on Wheels (WOW) inputs. 1. Ensure aircraft is positioned with weight on wheels. 2. Apply external power to the aircraft. Set BATT and AVIONICS MASTER switches to ON and wait for all aircraft and avionics systems to complete their initialization and begin operating normally. 3. Verify there are no WOW INVALID or WOW FAULT messages. Refer to Section 5.
7.23 RVSM Checks The following are required initial and continued airworthiness checks to verify proper configuration for operation in RVSM airspace. RVSM operations are prohibited until the all of the RVSM checks are completed successfully. 7.23.1 RVSM Required Avionics Check With the PFD in configuration mode, select the System Status page using the small FMS knob. Press the small FMS knob to activate the cursor.
7.23.2 RVSM Critical Region Visual Inspection The RVSM critical region is a 24 x 24 inch area around the static ports on both sides of the airplane. The corners of the RVSM critical region are to be marked on the aircraft with placards or paint of a contrasting color (see Figure 7-9.) The RVSM critical region must meet the following visual inspection criteria: 1. The fuselage skin must be free from damage. All skin repairs within the RVSM critical region must be flush (no external doublers).
7.23.3 RVSM Static Port Height Inspection The Gauging Assembly p/n SPF-4 (A1M-BCH-GE) is available from Hawker Beechcraft. Any alternate tool authorized in the King Air 200 Series Maintenance Manual for RVSM static port measurements may be substituted for this tool. Initialize the tool as follows: 1. Make sure the dial indicator reads negative when the plunger is pressed and positive when the plunger is free. 2. Place the gauging assembly on a flat surface (gauge block or equivalent.) 3.
NOTE The dial indicator shows 0.100 inch when completely flush. Therefore subtract the readings from 0.100 inch to determine the actual static port height. This should be completed before making any calculations. 3. For each static port, measure the static port height at the A, B, C and D locations as shown in Figure 7-12. Record the measurements in the measurement log, Figure 7-13. 4.
7.23.4 RVSM Air Data System Check Perform the Air Data Test per Section 7.6.1 If either the pilot or copilot air data system does not meet the tolerances specified, have maintenance checks performed on the air data system or the pitot/static system. IMPORTANT! RVSM operations are prohibited until the air data system meets all test conditions.
7.23.5 RVSM In-Flight Altitude Hold Check RVSM operation requires that the autopilot system accurately maintain the acquired altitude during nonturbulent, non-gust cruise conditions. The autopilot must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1-3. The autopilot must be shown to meet the performance specification of the following in-flight altitude hold test. 1.
7.24 Safe Flight Lift Computer Ground Calibration NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection (ESP) feature with Angle of Attack (AoA) modes and the Safe Flight Lift Computer p/n C-05606-1. Prior to removal of the lift computer, it is recommended that Section 7.24.1 be accomplished to record the existing stall warning points for Pots 0, 1 and 2.
CAUTION The anchor tab of the force applicator can be bent if the knob that applies tension to the transducer mounting plate is over tightened. Use care when installing the force applicator to prevent damage to the anchor tab. Refer to the data supplied with the force applicator. 6. Install the 1952-3 gauge (2 to 15 gram scale), in the force applicator (see Figure 7-16) onto the left wing in accordance with the manufacturer's instructions. Refer to the data supplied with the force applicator.
13. Place the BATT master switch to the OFF position. 14. Remove external power to the aircraft. 15. Remove the breakout box from the aircraft. 16. Reinstall the potentiometer access cover plate on the lift computer. 7.24.2 Calibration of the C-05606-1 Lift Computer NOTE For calibration of the stall warning points, reference King Air 200 Series Maintenance Manual, listed in Table 1-2, section 27-31-00.
Using the force applicator, deflect the transducer vane forward (UP) to the (Pot 0) TG force measured in step 10 in Section 7.24.1. If the stall warning horn is already ON, turn (Pot 0) CCW until the horn is OFF and then slowly turn the (Pot 0) CW until the horn is ON again. Press down on the vane until the horn is OFF and slowly release the vane. If the horn is not ON when the vane is released, turn the (Pot 0) until the horn is ON. c.
Example: If the (Pot 2) force is -10 TG, add +17 TG and the (Pot 5) force is +7 TG. e. Install voltmeter leads between TP18 (Lo) and TP19 (Hi) of the SK100360 Breakout Box. f. Apply the calculated (Pot 5) TG force to the vane with the force applicator. g. Adjust the (Pot 5) on the lift computer until the voltage output from TP18 (Lo) and TP19 (Hi) reads 2.2 ± 0.2 VDC on the voltmeter. h. Return the force on the force applicator to 0 TG. 12.
Figure 7-14, C-05606-1 Lift Computer Page 7-54 Revision 6 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air 190-00915-01
Figure 7-15, Breakout Box G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air 190-00915-01 Page 7-55 Revision 6
Figure 7-16, Force Applicator Usage Instructions Page 7-56 Revision 6 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air 190-00915-01
7.24.3 Safe Flight Lift Computer Flight Calibration NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection (ESP) feature. 1. Disable the STABILITY & PROTECTION item via the MFD AUX – SYSTEM SETUP 2 page. Verify that the message “ESP OFF” is present. 2. Perform the “Flight Test and Calibration” procedure in accordance with the King Air 200 Series Maintenance Manual, listed in Table 1-2, Section 27-31-00. 3.
5. On the GMC 710 couple the Flight Director to the left side by pressing the XFR button. The arrow that is illuminated indicates which side is coupled. No flight director modes should be active at this time. 6. On the GCU, rotate the inner FMS knob to activate the AUX – SYSTEM SETUP page on the MFD. 7. On the MFD AUX – SYSTEM SETUP page press the SETUP 2 softkey. 8. Verify that on the MFD SETUP 2 page there is a window for Stability & Protection and the status is “ENABLED”. 9.
17. Verify on PFD 1 and PFD 2 that there is an “ESP OFF” and for installations with AOA mode, an “ESP DEGRADE” alert message. 18. Remove the cover from both GPS1 and GPS2 antennas. 19. Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to OFF. 20. Wait ~ 1 minute before re-applying aircraft power. 21. Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to ON. 22.
24. On the GCU, rotate the inner FMS knob to activate the AUX – SYSTEM SETUP page. 25. On the MFD AUX – SYSTEM SETUP page press the SETUP 2 softkey. 26. Verify that on the MFD SETUP 2 page there is a window for Stability & Protection and the status is “ENABLED”. 27. Verify on PFD 1 and PFD 2 that there are no “ESP FAIL”, “ESP OFF”, or “ESP DEGRADE” alert messages. 28. On the GMC 710, couple the Flight Director to the right side by pressing the XFR button.
7.26 GTS 8XX Traffic System Functional Check Perform the following tests to verify GTS 8XX operational and surveillance functions. Use a ramp tester such as a TIC TR220 or equivalent to perform the tests. To perform these tests, the aircraft must be on the ground and the GTS 8XX must be in Ground Test mode. On the MAP-TRAFFIC MAP page of the MFD, press the softkey sequence: 3, 4, 4, 3 The GND TEST softkey will appear. Press the GND TEST softkey to activate Ground Test mode.
3. Set up a stationary intruder by selecting the following on the ramp tester: • Intruder type: ATCRBS. • Intruder Start Distance: 2 nm • Intruder Start Altitude: 50,000 ft • Vertical Speed: 0 fpm • Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario.) 4. Position ramp tester at 0 degrees. 5.
NOTE The aural TA annunciations are muted if the gear is extended (and the Radio Altimeter indicates below 400 feet). 7.27 Activation of Garmin Flight Data Services In order to activate the optional GDL 59 wi-fi datalink and optional GSR 56 satellite receiver for Garmin Flight Data Services, contact Garmin Product Support at one of the following numbers (M-F, 7:00 a.m. to 7:00 p.m. Central Standard Time, - Central USA): • 1.866.739.5687 (toll free in USA) • +1.913.440.
For previously activated systems, if the GSR 56 satellite receiver unit is replaced, the new unit serial number must be registered with Garmin Flight Data Services. Contact Garmin Product Support and follow the activation procedure as described previously in this section. For previously activated systems, if the GDL 59 wi-fi datalink unit is replaced, the system must be registered again.
7.28 GDL 59 Wi-Fi Data Link Functional Check This check verifies GDL 59 Wi-Fi Data Link interface is configured and is functional. This check requires an operating and available wireless network to be within range of the aircraft. NOTE This check only verifies the data output from the G1000 equipment. Any equipment/wiring added that is not part of the installation data will need separate testing and verification not covered as part of this document. 1. Start the G1000 System in Normal Mode. 2.
7.29 GSR 56 Satellite Receiver Functional Check 1. Power up the PFD1 in configuration mode. 2. On the PFD1, select GDL page group using the large FMS knob. 3. Using the small FMS knob select the GSR56 Configuration page. Verify the page can be displayed and information is available. Figure 7-18, GSR56 Configuration Page 4. Restart the G1000 System in Normal Mode. 5. Using the large FMS knob, select the AUX page group on the MFD. Using the small FMS knob, select the AUX-TELEPHONE page. 6.
8 System Return to Service Procedure After reinstalling any G1000 LRU, verify the correct LRU software part numbers and versions against the numbers listed on the General Arrangement drawing listed in Table 1-2. To check an LRU software part number and/or version, follow the procedure defined in Section 3.9.3.
8.1 Backup Path System Testing This final checkout tests various secondary communications paths to ensure that the paths function correctly. Perform the following steps and verify the results of each test. Before starting, create a simple Direct-To flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position. Verify that the phase of flight displayed on the GPS CDI is ENR. 8.1.1 GPS Failure Test Step Single GPS Failure Condition: 1.
8.1.2 GIA Failure Test Step Desired Result GIA 1 Failure Condition: For a GIA 1 failure condition, the following shall occur: 1. Ensure GPS satellites are acquired. • NAV 1 and COMM1 tuning fields on PFD1 and PFD2 are invalid (red X). 3. Verify desired results. • L/R engine data remains valid 4. Close GIA1 primary and secondary CBs. Allow system to re-acquire satellites and return to normal display modes. • XPDR1 is Inoperative. • GMA1 Is Inoperative. • AHRS1 is using backup GPS source.
8.1.3 Display Failure Test Step Desired Result MFD Failure Condition: For an MFD failure condition, the following shall occur: 1. Open MFD CB. 2. Verify desired results. 3. Close MFD CB. PFD2 Display Failure Condition: 1. Open PFD 2 CB. 2. Verify desired results. 3. Close PFD 2 CB. PFD1 Display Failure Condition: 1. Open PFD 1 PRI and PFD1 SEC circuit breakers. • MFD goes blank. • All PFD1 and PFD2 primary flight information is retained.
8.1.4 G1000 Cooling Fan Fail Annunciation Check Do the following to verify the cooling fans and annunciations are functioning properly Step Desired Result Cooling Fan Failure Conditions: For the cooling fan failure conditions, verify that the following alert messages are displayed: 1. Ensure the G1000 is in normal mode and verify that there are no fan related alert messages displayed in the PFD1 or PFD2 Alerts Window. 2.
Step Desired Result 5. Select (depress) the STANDBY BATTERY switch. Verify the following: • STBY Attitude indicator motor is energized as indicated by the indicator motor and the absence of flag. • STBY altimeter vibrator is active as indicated by vibrator noise and absence of flag. • STBY attitude, STBY Altimeter, STBY Airspeed indicators are illuminated full bright. • Amber “ON” is annunciated full bright on the STANDBY BATTERY switch.
8.1.6 G1000 Backup Path Test 1. Remove power from the displays by pulling the following circuit breakers: • PFD1 PRI • PFD1 SEC • PFD2 • MFD 2. Reboot PFD1, PFD2 and MFD while holding the ENT key on each display (far right key on MFD) until the words INITIALIZING SYSTEM appear. 3. In configuration mode, go to the GDU Page Group on PFD1. 4. On PFD1, activate the cursor and select PFD1 in the SELECT UNIT field and press ENT. 5. Observe the GRS 77 and GDC 74 DATA indicators in the ARINC 429 window.
Figure 8-2, GIA Data Verification (ARINC429/RS-232) 15. Activate the cursor and select GIA2 in the SELECT UNIT field, and then press the ENT key. 16. Repeat Steps 13 and 14.
17. On PFD1, go to the CAN / RS-485 CONFIGURATION page in the GIA Page Group. 18. Verify that GIA1 is selected in the SELECT UNIT field. 19. Observe the data indicators for all configured RS-485 channels. 20. Verify all DATA indicators are GREEN, indicating the channels are receiving data as shown: Figure 8-3, GIA Data Verification (RS-485) 21. Activate the cursor and select GIA2 in the SELECT UNIT field, and then press the ENT key. 22. Repeat Steps 18 and 19.
8.2 GFC 700 Ground Checkout The following procedures verify the proper operation of the GFC 700 AFCS, after maintenance has been performed. The technician performing these checks should be thoroughly familiar with the G1000 and GFC 700. Information on the installation and operation of the GFC 700 can be found by referring to Sections 6.11, 6.14 and the G1000 in King Air 200/B200 Cockpit Reference Guide, listed in Table 1-2.
8.2.2 AFCS Switch Checks Verify that the AFCS system buttons and switches are operating correctly by performing the following: 1. Actuate both sections of the PITCH TRIM (NOSE UP/NOSE DN) switch to activate Manual Electric Pitch Trim (MEPT). Verify the trim clutch engages and the trim wheel drives in the requested direction. Check operation in both the up and down direction. 2. Press the AP/YD DISC TRIM INTRPT switch and hold while actuating the manual electric trim switch.
12. Disengage the autopilot by pressing the AP/YD DISC TRIM INTRPT switch on the co-pilot’s control wheel. Engage VS mode by pressing the VS key on the AFCS mode controller. Verify PFD1 and PFD2 display ‘VS’ in green and indicates a pitch reference of ‘0 FPM’. 13. Press the FLC key on the AFCS mode controller and verify that ‘FLC’ is annunciated on PFD1 and PFD2 in green with a reference of 100 KTS. 14.
8.2.5 Autopilot Operation Checks NOTE For aircraft with software version 0985.03 and the Electronic Stability and Protection (ESP) option, an airspeed of 200 knots must be input using a pitotstatic test set. 1. Engage the Autopilot by pressing the AP key on the AFCS mode controller. Push the HDG knob to synchronize the heading bug to the current aircraft heading. Select HDG mode by pressing the HDG key on the AFCS mode controller. Verify the command bars are level and the control wheel is stationary.
8.2.6 VOR/LOC/GS Test Perform the following test using ramp test equipment. Operate the equipment according to the test equipment manufacturer’s instructions. NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned. 1. Ensure FD is coupled to PFD1 as indicated by a left pointing arrow next to the XFR button. 2. Simulate a VOR signal on a radial equivalent to the aircraft heading. Tune the NAV 1 and NAV 2 receivers to the simulation frequency. 3.
8.3 Maintenance Records After conducting required return-to-service procedures in accordance with the King Air 200 Series Maintenance Manual, listed in Table 1-2, the aircraft may be returned to service. Record the following information in appropriate aircraft maintenance logs: • Part number of the G1000 software loader card used to perform software loading or software updates. • Record part and serial numbers of any LRU which was replaced.
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