G1000 System Maintenance Manual Hawker Beechcraft G58 Contains Instructions For Continued Airworthiness For STC SA01584WI-D 190-01180-02 April 2012 Revision 3
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© Copyright 2012 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.
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TABLE OF CONTENTS PARAGRAPH 1 INTRODUCTION .................................................................................................................1-1 1.1 1.2 1.3 1.4 1.5 2 SVS/PATHWAYS TROUBLESHOOTING .............................................................................. 5-1 GTS 820 TROUBLESHOOTING ......................................................................................... 5-2 SOFTWARE/CONFIGURATION TROUBLESHOOTING ................................................
7.1 7.2 8 TRANSPONDER TESTING ................................................................................................. 7-1 GTS TRAFFIC SYSTEM.................................................................................................... 7-1 SYSTEM RETURN TO SERVICE PROCEDURE ............................................................... 8-1 8.1 8.2 8.3 8.4 DISPLAY TESTING ...........................................................................................................
LIST OF ILLUSTRATIONS FIGURE PAGE Figure 2.1. Display Unit .............................................................................................................. 2-1 Figure 2.2. Transponder ............................................................................................................ 2-2 Figure 2.3. Magnetometer .......................................................................................................... 2-2 Figure 2.4. GTS Receiver ....................................
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1 1.1 INTRODUCTION CONTENT, SCOPE, PURPOSE This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G1000 integrated avionics as installed in the Hawker Beechcraft G58 as modified under STC SA01584WI-D. This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and Appendix G. Information in this document is required to maintain the continued airworthiness of the G1000.
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. Table 1.
Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealers Only’ section of the Garmin web site. 1.5 ICA REVISION AND DISTRIBUTION This document is required for maintaining the continued airworthiness of the aircraft. When this document is revised, every page will be revised to indicate current revision level. Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center website.
2 2.1 SYSTEM DESCRIPTION EQUIPMENT DESCRIPTIONS The following subparagraphs provide a brief description and picture of each Garmin LRU installed or replaced by this STC. For all other G1000/GFC 700 LRUs, refer to the Hawker Beechcraft Baron (Model G58) Maintenance Manual Supplement for Airplanes with Garmin G1000 Equipment Installed listed in Table 1.1. 2.1.1 GDU 1040 PFD & GDU 1045 MFD One Garmin GDU 1040 display and one GDU 1045 display is installed in the Baron instrument panel.
2.1.2 GTX 33 TRANSPONDER The Garmin GTX 33 transponder communicates with the on-side GIA 63W through RS-232 digital interface. This STC provides for the optional installation of a GTX 33ES transponder that provides extended squitter functionality. The unit is mounted on the back side of the instrument panel. There are no mechanical or electrical interface changes needed GTX 33ES option and is installed in place of the existing GTX 33 if selected.
2.1.4 GTS 820 TRAFFIC SYSTEM The optional GTS 820 system is designed to use active interrogations of Mode S and Mode C transponders to provide Traffic Advisories (TA) to the pilot. Passive surveillance is available only when installed with a GTX 33 with extended squitter. Traffic is displayed on the MFD via Ethernet High Speed Data Bus routed through the existing GDL 69A. The GTS receiver is installed at FS 190. It is powered from the 5 amp Traffic Alert circuit breaker fed from the 28 Vdc Avionics bus.
Figure 2.6 G58 Traffic Antenna 2.1.5 XM REMOTE CONTROL SYSTEM The optional XM remote control system consists of the GRT 10 transceiver and the GRC Remote Control. This system allows for remote control of the XM satellite radio function provided by the existing GDL 69A. The GRT 10 is installed behind the instrument panel on the top of the MFD system rack. It is powered from the existing 3 amp Datalink circuit breaker off the 28 Vdc Avionics Bus. Figure 2.
Figure 2.8 GRC 10 Remote Control 2.1.6 GIA 63W INTEGRATED AVIONICS UNIT (2) Two Garmin GIA 63W Integrated Avionics Units (IAUs) contain the VHF COM/NAV receivers, WAAS GPS receiver, Flight Director, and system integration microprocessors. The GIAs also serve as a communication interface to all other G1000 LRUs in the system. Each GIA 63W communicates directly with the on-side GDU display using a HSDB Ethernet connection. Both GIAs are mounted in the systems rack behind the MFD.
2.2 OPTIONAL FEATURES The following optional features are included with this STC. These features are enabled via individual Enable cards that are to be retained with the aircraft. • • • Synthetic Vision and Pathways TAWS-B Chartview These features will need to be re-enabled after replacement of a display unit.
3 G1000 CONTROL & OPERATION All control and operation of G1000 equipment as normally used in flight occurs through the PFD, MFD, and GMA audio panel. 3.1.1 SOFTKEYS Some pages have commands or selections that are activated by the GDU softkeys. If a softkey is associated with a command, that command will be displayed directly above the key. A grayed-out softkey shows a command that is unavailable. A softkey that is highlighted shows the current active selection. Figure 3.1 - G1000 Softkeys 3.1.
Figure 3.2 - Normal Mode (with SVS enabled) Figure 3.3 - Normal Mode (without SVS enabled) 3.3 REVERSIONARY MODE Reversionary mode allows for display of information related to safe flight in the event of a display communication or hardware failure. As installed in the G58, both manual and automatic reversionary modes are possible. Manual reversionary mode allows the operator to force the PFD or MFD into reversionary mode by pressing the large red button labeled ‘DISPLAY BACKUP’ on the GMA audio panel.
3.4 CONFIGURATION MODE OVERVIEW The Configuration Mode exists to provide the avionics technician with a means of configuring, checking, and calibrating various G1000 sub-systems. Troubleshooting and diagnostics information can also be viewed in this mode. To start the system in Configuration Mode: a. Press and hold the ENT key on the MFD while resetting power using the MFD circuit breaker. b. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the MFD. c.
GRS Page Group 1. Inputs Configuration 2. GRS / GMU Calibration ADC Page Group 1. ADC Configuration 2. GDC Configuration GFC Page Group 1. GFC Configuration 2. GFC Status GMA Page Group 1. GMA Configuration GDL Page Group 1. GDL 69 Config GWX Page Group 1. GWX Configuration GTS Page Group 1. GTS Configuration OTHER Page Group * 1. Stormscope CAL Page Group 1. Fuel Tank Calibration 2. Flap and Trim Calibration 3.
Figure 3.6, Data Transmission Indicators 3.6 G1000 SOFTWARE INFORMATION NOTE The following sections provide a detailed description of loading all G1000 software and configuration files, which may be excessive for individual LRU removal and replacement. If removing and replacing individual LRUs, refer to Section 5.6 of this manual for the necessary steps. 3.6.1 LOADER CARDS NOTE The G1000 has various features that require the use of unlock/enable cards to activate the feature.
card by ordering the Garmin Part Number listed in the General Arrangement Drawing 005-00606-12 referenced in Table 1.1 IMPORTANT To satisfy the requirements of this STC it is critical that the technician install correct software image part number when servicing the G1000 system. Approved software image part numbers are defined on the General Arrangement Drawing 005-00606-12 listed in Table 1.1 CAUTION Be cautious when using software loader cards during maintenance.
b. Click the Agree button on the confidentiality agreement page. c. Select the Download Software link. d. Select the Software Downloads hyperlink on the left hand edge of the page. e. Scroll down until the appropriate software image is visible. Note: the software image version number will be listed in the name column. Select the appropriate software image based upon the information provided in Garmin GA Drawing 005-00606-12. f. Select the Download hyperlink and save the file to the local hard drive.
NOTE 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 i. Ensure the card and correct drive letter is used, and click next. A window will pop-up onto the screen to indicate file progress.
j. Once successfully completed, the following message/window will pop-up. Click Finish to finalize SD card.
3.6.4 SOFTWARE FILES Software files are defined by part number and version number on the General Arrangement Drawing 005-00606-12. Each G1000 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. • Configuration Mode: The SYSTEM STATUS page (SYSTEM page group) reports more detailed LRU information, including software version, part number, and LRU status.
3.7 G1000 SOFTWARE/CONFIGURATION PROCEDURE This section summarizes the procedures required to load software and configuration files to the G1000. It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft. In sections of this manual where software is required to be reloaded, these sections will make reference back to this Section for instructions.
3.7.1 MFD & PFD SOFTWARE LOAD IMPORTANT! When replacing a display, it is REQUIRED to update the system files with the new display in the MFD slot regardless of intended final configuration, PRIOR to loading configuration files. Failure to do so could result in loss of any existing calibration/configuration data. a. Apply power to the G1000 by doing the following: Connect a ground power unit to the external power receptacle, and turn on the ground power unit. b.
m. Verify on the SYSTEM STATUS PAGE that the following are valid. (Indicated by a green checkmark within the status box, as shown above): MFD, PFD, GIA1, GIA2, GDL 69A and GWX. n. Proceed to next section.
3.7.2 BASE CONFIGURATION AND SOFTWARE UPLOAD a. Ensure loader card is inserted into top card slot of PFD. On PFD, select the System Upload page using the PFD small FMS knob. b. Activate the cursor and rotate the PFD small FMS knob to highlight BEECHCRAFT G58 in the AIRFRAME field. Press the PFD ENT key to select the configuration . c. Once an airframe type is selected the cursor moves to the FILE window. Rotate the PFD small FMS knob to activate the drop-down menu.
3.7.3 OPTIONAL EQUIPMENT CONFIGURATION Perform the following steps if any of the following options are installed: • GTS 820 • SKY 497 Skywatch • KN 63 DME • WX-500 Storm Scope • GTX 33 with extended squitter a. Go to the System Upload page and activate cursor. Activate the drop down menu in the AIRFRAME field by rotating the small FMS knob and select G58 OPTIONS and press ENT. b. Activate the drop down menu by rotating the small FMS knob and select the desired option, press ENT. c.
3.7.4 GRC 10 CONFIGURATION (OPTIONAL) For installations with the optional GRT 10/GRC 10 wireless remote system, the GRC 10 must be configured to communicate with the specific GRT 10 that is installed in the aircraft. To configure the RF Pairing ID of the GRC 10: NOTE GRT 10 serial number is required for installation. Serial number is located on the bottom of the unit. a. Insert two AA batteries in GRC 10. b. On the GRC 10 press any key to power the remote. c.
3.8 SOFTWARE LOAD CONFIRMATION Go to the Systems Status page. Activate the cursor and toggle to the LRU window. Highlight each of the following items in the LRU window and verify that the LRU software part number and software version matches the following information. NOTE Verify the software and version levels for the items listed below. a.
b. De-activate the cursor. c. Remove loader card and power down aircraft. IMPORTANT If any software version and/or part number does not match, or is not successfully loaded, do not continue with post installation procedures. Troubleshoot and resolve the issue before continuing.
3.9 AVIATION DATABASE LOADING PROCEDURES 3.9.1 TERRAIN DATA CARD LOADING PROCEDURE a. Remove power from the PFD and MFD by pulling the PFD and MFD circuit breakers. b. Install a GDU 10XX Terrain Data Base Card 010-00330-43 in the bottom slot of the PFD and MFD. c. This completes the installation of the Terrain Data Card. 3.9.2 AVIATION DATABASE LOADING a. Remove power from MFD. b.
3.10 SVS / PATHWAYS ACTIVATION (OPTION) This section provides the requirements and instructions necessary to enable the G1000 Synthetic Vision / Pathways feature. Baseline Software: The Garmin Synthetic Vision and Pathways feature in the Hawker Beechcraft requires GDU software version 11.01 to be installed with the G58-specific software/configuration image prior to activation. See the STC Master Drawing List for specific installation requirements.
3.10.1 SVS ACTIVATION PROCEDURE Activate the SVS/Pathways feature by performing the following steps: a. Apply power to the G1000 system. b. Pull the MFD and PFD circuit breakers. c. A special SVS Enable card is required to activate this feature, refer to Table 3.2. Insert this card in the upper slot of PFD. d. While holding the ENT key on the PFD and MFD restore power to the displays. e. When the words release the ENT key. f.
3.11 CHARTVIEW ENABLE PROCEDURE NOTE • • • The Chart Enable card can only enable Charts on one system (one aircraft). A new Chart Enable card must be used for each aircraft. The required ChartView databases are subscription-based and are to be procured by the installing agency directly from Jeppesen. The G1000 can only be configured for FliteCharts or ChartView but not both. Performing this procedure will automatically disable the FliteChart option. a. Apply power to the G1000 system. b.
3.12 TAWS-B ENABLE PROCEDURE NOTE The TAWS-B Enable card can only enable TAWS on one system (one aircraft). A new TAWS Enable card must be used for each aircraft. a. Remove power from the MFD and PFD by pulling the PFD and MFD circuit breakers. b. Insert the TAWS Enable card, 010-00330-51 in the upper slot of the PFD. c. While holding the ENT key on the PFD and MFD restore power to the displays. d. When the words displays, release the ENT key. appear in the upper left corner of the e.
3.13 AIRCRAFT REGISTRATION NUMBER ENTRY NOTE The large FMS knob changes Groups and the small FMS knob changes Pages within a Group. NOTE If aircraft has a Garmin GTS 8XX Traffic System installed, ensure GTS 8XX system configuration is loaded prior to registration entry for transponder (See Section 3.7.3). a. Remove power (if applied) from PFD by pulling the PFD circuit breaker. b. While holding the ENT key on the PFD, restore power by closing the PFD circuit breaker. c.
4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 4.1 AIRWORTHINESS LIMITATIONS There are no airworthiness limitations associated with this type design change (STC # SA01584WI-D). The previously approved Instructions for Continued Airworthiness defined under TCDS 3A16, and identified in Table 1-1, remain valid and applicable for all other maintenance and ICA aspects of the G1000 and GFC 700 systems. The Airworthiness Limitations section is FAA-approved and specifies maintenance required under § 43.16 and 91.
The following tools are needed to perform maintenance tasks on GMU 44 equipment: • #2 non-magnetic Philips screw driver The following tools are needed to perform maintenance tasks on GTX 33ES transponder: • Calibrated pitot/static tester • Calibrated transponder ramp tester The following tools are needed to perform maintenance tasks on GRT 10 equipment: • 3/32” Hex tool • #2 Philips screw driver The following tools are needed to perform maintenance tasks on GDU 104X equipment: • 3/32” Hex tool F
4.3 MAINTENANCE INTERVALS Table 4.1 below shows the systems and equipment installed by this STC that must undergo any maintenance action and identifies the timeframe in which that activity should occur. The previously approved Instructions for Continued Airworthiness defined under TCDS 3A16, and identified in Table 1-1, remain valid and applicable for all other maintenance and ICA aspects of the G1000 and GFC 700 systems.
Item Description / Procedure Section # Battery replacement Synthethic Vision /Pathways GTX 33ES Tranponder with Extended Sqitter Functionality ** 4.3.1 Interval On Condition Reactivation 3.10 On Condition / after GDU replacement Removal and Replacement 6.7 On Condition 7.1 Every 24 Calendar months Transponder test (required for compliance with Title 14 of the Code of Federal Regulations (14 CFR) §§ 91.411 and 91.
When making any repairs to GTS coax cables installed under this STC, be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation, attenuation balance between cables, phase matching etc. in the Installation Manuals referenced in Table 1.1 4.3.3 ELECTRICAL BONDING TEST The following bonding tests are provided for GTS 820 equipped G58 aircraft as a requirement beyond what is given in the aircraft maintenance manual.
• Metal case of GPA 65 LNA/PA: __________ milli-volts (part of GTS 820 option) Empennage • Metal case of GTS 820: __________ milli-volts (optional equipment) Aircraft Exterior (Antennas) • GA 58 Top traffic antenna mounting screw: __________ milli-volts (optional equipment) • GA 58 Bottom traffic antenna mounting screw: __________ milli-volts (optional equipment) Ensure that at each test point, no more than 10 milli-volts (10 mΩ) are present.
5 TROUBLESHOOTING This section provides instructions and guidance for system troubleshooting additional systems / functions added by this STC. For troubleshooting assistance for all other aspects of the G1000 / GFC 700 refer to the existing Hawker Beechcraft G58 maintenance supplement listed in Table 1.1. IMPORTANT Sections 6, 3.7, and 8 provide detailed instructions on equipment removal, replacement, configuration, and return-to-service testing.
The following table provides SVS/Pathways specific alert messages which may appear in the Alerts Window on the PFD (press the ALERTS softkey on the PFD to view the Alerts Window): Table 5.2 – SVS Alert Messages Failure Message Cause SVS – SVS DISABLED: Out of available terrain region. SVS is disabled because the aircraft exceeded the boundaries of the loaded terrain database.
Problem Cause Solution Electrical Fault Internal Fault Return to Garmin for service Whisper Shout Fault Internal Fault Return to Garmin for service Transmit Power Fault Internal voltages are out of tolerance Verify input voltage and if it continues return to Garmin for service.
• Ensure that LRU is reporting data on System Status page (LRU is ‘ONLINE’). Check data path wiring as needed. • Retry configuration file load or try using a different card. Ensure that the MFD is not touched during the loading process. • Ensure that LRU part number is compatible with Card Loader. Refer to the General Arrangement Drawing 005-00606-12 and to Section 3.6 of this document. • Replace LRU. • Ensure that proper software file part number and version were loaded to LRU.
• SW Loader Card must be inserted in top slot of PFD. • PFD and MFD must be powered on. • PFD and MFD must have correct software. • SW Loader Card must be inserted in top slot of PFD. • G1000 system must be powered on. • PFD and MFD must have correct software. • PFD and MFD must be successfully configured with AIRFRAME, SYSTEM, MANIFEST, MFD, and PFD configuration files. • SW Loader Card must be inserted into PFD top slot. • G1000 must be powered on.
(Rear View) Figure 5.3 - GPA 65 Connector (Rear View) Figure 5.
6 EQUIPMENT REMOVAL & INSTALLATION This section describes how to remove and replace equipment in the G58 that was installed as part of this STC. After removal and replacement, LRUs must be configured and tested as described in Section 7. For removal and replacement instructions for all other G1000 / GFC 700 equipment, refer to existing Hawker Beechcraft G58 Maintenance Supplement listed in Table 1.1. CAUTION When removing and/or replacing any G1000 component, always ensure that aircraft power is off.
6.2 GPA 65 LNA/PA CAUTION After any maintenance or modification is made to the GTS 820 TAS cables such as replacing a connector or entire cable, some important considerations must be made. Be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation, attenuation balance between cables, phase matching etc. in the Installation Manual referenced in Table 1.2. Removal: 1. Remove cabin interior to access FS 124.75 at BL 0.00 on the right side of the fuselage.
6.4 GRT 10 XM REMOTE CONTROL TRANSCEIVER Removal: 1. Gain access to GRT 10 under glareshield on copilot side of cockpit. Refer to the “GRT 10 Equipment Install, Hawker Beechcraft G58” drawing listed in Table 1.1. 2. Disconnect the electrical connector. 3. Remove the three mounting screws that hold the unit to the installation bracket. Reinstallation: 1. Inspect the connector for damaged pins. 2. Reattach the unit to the mounting bracket reusing exiting hardware. 3.
NOTE Failure of the GRC 10 (i.e. dead batteries) has no impact on normal aircraft operations and is only used for passengers to control audio entertainment. NOTE It is not necessary to reconfigure GRC 10 after battery replacement. 6.5 GDU REMOVAL & REPLACEMENT Removal: 1. Make sure all airplane electrical power is disconnected. 3 1 2. Using a /32 hex tool, turn all four /4-turn fasteners, on the display unit, counter-clockwise until they reach their stops.
6.6 GMU 44 REMOVAL & REPLACEMENT Removal: 1. Make sure all airplane electrical power is disconnected. 2. For airplanes with long range fuel tanks -Remove the left wing tip by unscrewing the phillips screws. For airplanes with standard fuel tanks - Remove the square access panel (left wing top). 3. Unscrew the three screws that hold the GMU 44 to its mounting rack. 4. Carefully lift the GMU 44 from its mounting rack. 5. Disconnect the airplane harness connector from the GMU 44 electrical connector. 6.
6.7 GTX 33ES TRANSPONDER REMOVAL & REPLACEMENT Removal: 1. Make sure all airplane electrical power is disconnected. 2. Remove the PFD. 3. Unlock the GTX 33 handle by loosening the Phillips screw on the handle. 4. Pull the handle upward to unlock the GTX 33. Gently remove the unit from the rack. 5. Place protective caps on the GTX 33 electrical connectors and rack connectors. 6. Remove the unit from the airplane. Reinstallation: 1.
6.8 GIA 63W REMOVAL & REPLACEMENT Removal: 1. Make sure all airplane electrical power is disconnected. 2. Remove the MFD. 3. Unlock the GIA 63W handle by loosening the Phillips screw on the handle. 4. Pull the handle upward to unlock the GIA 63W. Gently remove the unit from the rack. 5. Place protective caps on the GIA 63W electrical connectors and rack connectors. 6. Remove the unit from the airplane. Reinstallation: 1.
CAUTION 010-00725-08 Loader Card (006-B0857-08 Software Image) is only compatible with GIA P/N: 011-01105-01. All installations with GIA P/N: 011-01105-20 must use the 006-B0857-09 Software Image. 6. If a new, repaired, or exchange GIA is installed, the correct software and configuration files must be loaded to the unit. See Section 3.7 then continue to Section 8. 7.
7 G1000 EQUIPMENT CONFIGURATION & TESTING Refer to Section 3.6 for information on loading software and configuration of G1000 equipment covered by this STC. 7.1 TRANSPONDER TESTING The integrated transponder/altitude reporting system must be verified in accordance with Title 14 of the Code of Federal Regulations (14 CFR) §§ 91.411 and 91.413. These tests require the use of a Mode S ramp generator. Specific instructions for operating the ramp tester are contained in the applicable operator's manual.
Original GTS 820 Reinstalled No software or configuration loading is required if the removed GTS 820 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GTS 820 Test (Section 7.2.1). New, Repaired or Exchange GTS 820 Installed If a new, repaired or exchange GTS 820 is installed, the correct software and configuration files must be loaded to the unit. See Section 3.
• The intruder should transition from Other Traffic (displayed as an open diamond with 00 displayed above), to proximate traffic (displayed as a filled white diamond with 00 displayed above), to a Traffic Advisory (TA) alarm. • The appropriate TA symbology (yellow filled circle with 00 displayed above and an audio annunciation of “Traffic! 3 O’clock! At Altitude! 3 Miles!”), displayed when the intruder approaches within 3 NM. Antenna Bearing Check a.
o. Toggle intruder traffic to standby or off. p. Reposition ramp test set and directional antenna to an aft position of 180 degrees. q. Reengage the same intruder scenario as above. r. Verify a target is annunciated on the MAP-TRAFFIC MAP page of the MFD at the correct bearing of approximately 180 degree azimuth at 2 NM and co-altitude. s. Toggle intruder traffic to standby or off. t. Reposition ramp test set and directional antenna to a port position of 270 degrees. u.
8 SYSTEM RETURN TO SERVICE PROCEDURE The procedures contained in this section describe the minimum return to service checks that should be performed upon reinstallation of the software and/or reactivation of SVS/Pathways. If the software reload or SVS reactivation was as a result of an LRU replacement, the technician must also perform any additional return to service tests required by the existing Hawker Beechcraft G58 Airplane Maintenance Manual (listed in Table 1.1) for that LRU. 8.
Figure 8.2 – PFD Power Up System Annunciations e. In the normal operating mode, data fields that are invalid have large red Xs through them (Figure 8.2). A valid field does not display a red X (Figure 8.3). Allow the displays to initialize for approximately one minute. Figure 8.
Figure 8.4 – Normal Display (with SVS enabled) f. Check that all COM/NAV fields are valid in the top corners of PFD and MFD. g. Check that altitude, airspeed, vertical speed, TAS, OAT, and ISA fields are valid on PFD and MFD. h. Check that engine instrument fields are valid on the MFD. i. Verify that no MANIFEST alert messages appear in the lower right corner (press the flashing ALERTS softkey to view alert messages).
8.1.1 SVS / PATHWAYS INSTALLATION VERIFICATION (REQUIRED IF ENABLED) a. Apply power to the G1000 system. Allow the AHRS and magnetometer systems to stabilize and align. Verify that air data information becomes valid on the PFD. Check the MFD AUX – System Status page to verify GPS signals acquisition. b. Press the ALERTS softkey on the PFD and verify no database, manifest, or configuration errors exist. c. Press the PFD softkey. Verify a SYN VIS softkey is shown in the lower left corner of the display. d.
Figure 8.6 – PFD with SVS enabled NOTE Screenshots are for reference only and may not be indicative of what is present on the actual aircraft display. f. Installation is complete. Be sure to keep the SVS / Pathways enable card with the aircraft for future use.
8.2 GIA 63W INTEGRATED AVIONICS UNIT GPS Signal Acquisition Figure 8-7 AUX – GPS STATUS Page (MFD) The GIA 63W units should normally acquire a GPS navigation solution within 5 to 10 minutes of startup, provided the aircraft is outside (or indoors with a GPS repeater). Select the GPS STATUS page on the MFD (4th page in AUX group). Two softkeys on the bottom of the display allow the user to toggle between GPS 1 and GPS 2. Verify that both receivers show 3D DIFF NAV on the MFD.
e. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels. f. During the transmit period, verify that the GPS “INTEG” flag does not come into view on the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD. g. Repeat steps e and f and re-transmit while monitoring GPS 2 signal levels on the MFD. h. Repeat steps d through g for each of the following frequencies: • 121.175 MHz • 121.200 MHz • 131.250 MHz • 131.275 MHz • 131.300 MHz i.
Check the VOR, ILS, and Glideslope functions with ramp test equipment. Operate the equipment according to the test equipment manufacturer’s instructions. Adjust the RF signal to a level adequate to perform the test. Select the appropriate HSI source by using the CDI softkey. NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned. GFC 700 VOR/LOC/GS Test a. Simulate a VOR signal on radial 000° with a course-widht of 20°.
8.3.1 AUTOPILOT PRE-FLIGHT TEST NOTE The autopilot pre-flight test will run on every full autopilot power-on. a. Open the AP SERVOS circuit breaker and reset. The AFCS will re-initiate the preflight test. NOTE A red AFCS ( ) annunciation will be displayed until both GIAs, the AHRS, and the autopilot servos are online. b. Verify that a white ‘PFT’ annunciation is displayed on the PFD, as shown in Figure 8.8. Figure 8.8 - GFC 700 Pre-Flight Test c.
checked. If an alert is heard, the audio interface between GIA No. 2 and the audio panel should be checked. 8.3.2 AFCS SWITCH CHECKS To verify that the AFCS system buttons and switches are operating correctly, perform the following checks: a. Actuate both halves of the Manual Electric Trim (MET) switch in the same direction. The trim clutch should engage and the trim wheel should run in the selected direction. Check operation in both directions. b.
q. Press the FD key on the MFD to deactivate the Go Around mode and reset the Flight Director. r. Center the trim wheel if it is not already centered. s. Press the AP key to engage the Autopilot. t. Press the CWS button and verify there is no residual force on the control wheel for the pitch axis. u. Extend the flaps to approach position. The trim wheel should immediately run in the NOSE DOWN direction. v. Retract the flaps. The trim should immediately run in the NOSE UP direction. w.
j. Release the CWS button and verify that servo clutches re-engage before releasing the control wheel. k. Press the NOSE DN key on the MFD twice. Verify that the command bars command down and the control wheel begins moving forward. l. Hold the controls and press CWS to re-center the command bars and stop control wheel movement. m. With the Autopilot still engaged and the CWS button pressed, move the control wheel to its aft limit. n.
8.4 MAINTENANCE RECORDS After complying with the procedures contained in this ICA and any additional return to service procedures contained in the Hawker Beechcraft Maintenance Manual and G58 Maintenance Supplement, listed in Table 1.1, 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.
