G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90

2.9 DME 42 Option Configuration ..........................................................................................................2-15 2.10 FliteCharts Configuration..................................................................................................................2-16 2.11 ChartView Configuration ..................................................................................................................2-17 2.12 TAWS Configuration.........................................................................................................................2-18 2.13 Aircraft Registration Number Entry ..................................................................................................2-19 2.14 Terrain/Obstacle Database Loading ................................................................................................2-19 2.15 Aviation Database Loading ..............................................................................................................2-20 2.16 Clearing Default User Settings.........................................................................................................2-20 2.17 Software/Configuration Troubleshooting..........................................................................................2-21 3 G1000 INITIAL SYSTEM TESTING 3-1 3.1 Electrical Power Distribution Testing.................................................................................................. 3-1 3.2 Electrical Load Test Procedures ........................................................................................................ 3-5 3.3 Display Testing.................................................................................................................................3-10 3.4 GPS Signal Acquisiton .....................................................................................................................3-13 3.5 GMA 1347D Testing.........................................................................................................................3-14 3.6 VHF COMM Operational Check.......................................................................................................3-15 3.7 Marker Beacon Test .........................................................................................................................3-15 3.8 VHF COM Interference Test ............................................................................................................3-15 3.9 VOR/LOC/GS Test ...........................................................................................................................3-16 3.10 COM Antenna VSWR Checks..........................................................................................................3-16 3.11 GTX 33 Testing ................................................................................................................................3-17 3.12 Pitot Static System Leak Checks .....................................................................................................3-18 3.13 GDC 74B Testing .............................................................................................................................3-19 3.14 GDL 69A Functional Check..............................................................................................................3-22 3.15 GEA Functional Check .....................................................................................................................3-26 3.16 TAWS Functional Check ..................................................................................................................3-27 3.17 FliteCharts Functional Check ...........................................................................................................3-28 3.18 ChartView Functional Check............................................................................................................3-29 3.19 SafeTaxi Functional Check ..............................................................................................................3-30 3.20 Aircraft Weight Configuration Functional Check ..............................................................................3-31 4 INTERFACE TESTING 4-1 4.1 GWX 68 Weather Radar Check ......................................................................................................... 4-1 4.2 Optional Stormscope Functional Check............................................................................................. 4-2 4.3 Optional Traffic System Functional Check ......................................................................................... 4-4 4.4 Optional DME Functional Check ........................................................................................................ 4-5 4.5 Optional ADF Functional Checks ....................................................................................................... 4-6 5 GRS 77/GMU 44 INITIAL ALIGNMENT and STBY COMPASS CALIBRATION 5-1 5.1 Procedure A: GRS 77 Pitch/Roll Offset Calibration .......................................................................... 5-1 5.2 Engine Start........................................................................................................................................ 5-2 5.3 Final GRS 77/GMU 44 Calibration Procedures.................................................................................. 5-3 Page iv G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 6 Final System Checkout 6-1 1. GPS Failure Test................................................................................................................................ 6-1 6.1 GIA Failure Test ................................................................................................................................. 6-2 6.2 Display Failure Test............................................................................................................................ 6-3 6.3 Cooling Fan Failure Annunciations .................................................................................................... 6-5 6.4 Standby Electrical Power Checks ...................................................................................................... 6-5 6.5 G1000 Backup Path Tests ................................................................................................................. 6-7 7 GFC 700 GROUND CHECKS 7-1 7.1 Pre-Flight Test.................................................................................................................................... 7-1 7.2 AFCS Switch Checks ......................................................................................................................... 7-2 7.3 Autopilot Clutch Overpower Check .................................................................................................... 7-3 7.4 Manual Electric Pitch Trim Speed Check........................................................................................... 7-3 7.5 Autopilot Operation Checks ............................................................................................................... 7-3 8 GFC 700, TAWS and POST MODIFICATION FLIGHT TEST PROCEDURE 8-1 8.1 Before Take-Off.................................................................................................................................. 8-1 8.2 Initial Engagement.............................................................................................................................. 8-1 8.3 Vertical Speed (VS) Mode.................................................................................................................. 8-1 8.4 Pitch Mode (PIT) & Altitude Alerting................................................................................................... 8-2 8.5 Flight Level Change (FLC) Mode & Altitude Capture......................................................................... 8-2 8.6 Altitude Hold (ALT) Mode & Heading Select (HDG) Mode ................................................................ 8-3 8.7 Overspeed Protection Mode .............................................................................................................. 8-3 8.8 NAV Modes ........................................................................................................................................ 8-3 8.9 TAWS ‘FIVE HUNDRED’ Call-out...................................................................................................... 8-5 9 SIGNATURES 9-1 LIST OF ILLUSTRATIONS LIST OF TABLES Figure 1-1. G1000 & GFC 700 in King Air C90A/C90GT..........................................................................1-4 Figure 2-1. Software/Configuration Overview ...........................................................................................2-2 Figure 3-1. MFD Power Up Page............................................................................................................3-10 Figure 3-2. PFD Power-up System Annunciations .................................................................................3-11 Figure 3-3. 4th AUX Page .......................................................................................................................3-13 Figure 3-4. Marker Beacon Symbology ..................................................................................................3-15 Figure 5-1. Pitch/Roll Offset ......................................................................................................................5-1 Figure 5-2. G1000 Engine/Airframe Indicators .........................................................................................5-2 Figure 5-3. AHRS Information Valid..........................................................................................................5-7 Figure 5-4. Magnetometer Interference Test ............................................................................................5-8 Figure 7-1. Pre-Flight Test ........................................................................................................................7-1 Table 1-1. Referenced Documentation .....................................................................................................1-2 Table 5-1. Magnetometer Interference Test Sequence ............................................................................5-9 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Page 1-1 190-00682-00 Revision 5 1 INTRODUCTION 1.1 Scope This document presents the post-installation procedures which are required to be performed after installing the G1000 Integrated Cockpit System in the Hawker Beechcraft King Air C90 series aircraft. This document and revision are effective for the following aircraft: Aircraft Model Model Name G1000 System Software Version C90A / C90GT King Air Ref. General Arrangement, G1000/GFC 700 AFCS, King Air C90A/GT (005-00375-22) Refer to the General Arrangement, G1000/GFC 700 AFCS, King Air C90A/GT (005-00375-22) for details on specific aircraft eligibility for this STC. Additional STC documents are listed in the Master Drawing List, 005-00375-30. 1.2 Organization Follow the procedures in this document to configure and test a newly-installed Garmin G1000 Integrated Avionics System with GFC 700 Automatic Flight Control System in the Hawker Beechcraft King Air Model C90A/GT. The person performing the configuration and testing should read through this entire document prior to beginning any procedures. Section 1: Introduction, reference documents, system description and operation. Section 2: Software and system configuration loading procedures. Manual configuration items are also addressed. At the end, all software versions and part numbers are verified against drawing 005- 00375-22 “General Arrangement, King Air C90A/GT”. Section 3: Ground checks include exercising and testing basic G1000 functions. Section 4: Ground checks of G1000 interfaced equipment including GWX 68, StormScope®, Traffic System, DME and ADF. Section 5: AHRS alignment and calibration procedures. Section 6: Final systems checkout. Section 7: Detailed GFC 700 ground checks are given in this section. Section 8: Flight testing procedures are given where mode function checks are conducted, and final autopilot and TAWS checks are made. Page 1-2 G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 1.3 Reference Documents For additional information on the installation, refer to the documents below. GWX 68 Radar Install, King Air C90A/C90GT 005-00375-19 Antenna Install, King Air C90A 005-00375-21 General Arrangement, G1000/GFC 700 AFCS, King Air C90A/C90GT 005-00375-22 Control Wheel Modification G1000/GFC700, King Air C90 005-00375-23 Overhead Control Panel Modification, G1000/GFC700, King Air C90A 005-00375-25 Pedestal Re-configuration, King Air C90A 005-00375-26 Main Instrument Panel Installation, King Air C90A/C90GT 005-00375-28 Circuit Breaker Panel Modification, King Air C90A 005-00375-29 Circuit Breaker Panel Modification, King Air C90A 005-00375-70 Wire Harness Routing, Tail, King Air C90 005-00375-31 Electrical Equipment Install, Nose Bay, King Air C90A 005-00375-34 Removal, Collins AP65 Servos, King Air C90A 005-00375-36 Pitot-Static-Vacuum Line Removal, King Air C90A 005-00375-37 Roll Servo Install, King Air C90A 005-00375-41 Yaw Servo Install, King Air C90A 005-00375-42 Pitch Servo Install, King Air C90A 005-00375-43 Pitch Trim Servo Install, King Air C90A 005-00375-44 Magnetometer Install, King Air C90A/C90GT 005-00375-53 OAT Sensor Install, King Air C90A/C90GT 005-00375-54 Wire Harness Routing, Nose, King Air C90A/C90GT 005-00375-55 Wire Harness Routing, Cabin, King Air C90A 005-00375-56 Wiring Diagram G1000/GFC 700, King Air C90A/C90GT 005-W0022-00 Bracket, Servo Mount, Pitch Trim, C90 115-00860-XX Fan Bracket 115-00861-XX Panel, Main Instrument, G1000, C90 115-00862-XX Cable Assy, GFC 700, C90 233-20006-XX Wire Harness Assy, G1000/GFC 700, King Air C90A/C90GT 320-00326-XX Table 1-1. Referenced Documentation G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Page 1-3 190-00682-00 Revision 5 1.4 System Description 1.4.1 Equipment The G1000 and GFC 700 AFCS is comprised of the following equipment: Control & Display: • Two GDU 1040A PFDs • GDU 1500 MFD • GCU 475 FMS Control Unit Communication, Navigation, & Surveillance: • Two GIA 63W Integrated Avionics Units • Two GMA 1347D Audio Panels • Two GTX 33 Mode S Transponders • GDL 69A Datalink Sensors: • Two GDC 74B Air Data Computers (ADC) • Two GRS 77 Attitude & Heading Reference Systems (AHRS) • Two GMU 44 Magnetometers • Two GEA 71 Engine/Airframe Units • GEA engine parameter function supported by 2 Sandia tach-gen adaptors and a Senior Aerospace fuel flow signal conditioner. Autopilot: • GMC 710 AFCS Mode Controller • GSA 80 Servos (Yaw, Pitch & Roll) • GSA 81 Servos (Pitch Trim) • GSM85 Servo Mount • GSM85A Servo Mount G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Page 1-4 190-00682-00 Revision 5 GDU 1040A (PFD1) GDU 1500 (MFD) No. 1 GIA 63W System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope WAAS VNAV AFCS Mode Logic No. 1 Flight Director Servo Communication No. 1 GDC 74B Air Data Computer Airspeed, Altitude, Vertical Speed, OAT No. 1 GEA Engine / Airframe Unit GSA 80 Roll Servo GSA 81 Pitch Trim Servo GSA 80 Pitch Servo No. 1 GTX 33 Mode S Transponder No. 2 GMA 1347D GDL69A XM Satalite Datalink (WX & Radio) No.1 GTP59 OAT Probe GMC 710 (AFCS Controller) No. 1 GMU44 Magnotometer GSA 80 Yaw Servo DME WX-500 SKY899 No. 2 GIA 63W System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope WAAS VNAV AFCS Mode Logic No. 2 Flight Director Servo Communication No. 2 GDC 74B Air Data Computer Airspeed, Altitude, Vertical Speed, OAT No. 2 GEA Engine / Airframe Unit No. 2 GRS 77 AHRS Atitude Rate of Turn Slip/Skid No. 1 GRS 77 AHRS Atitude Rate of Turn Slip/Skid No. 2 GMU44 Magnotometer No. 2 GTX 33 Mode S Transponder No. 2 GTP59 OAT Probe GDU 1040A (PFD2) No. 1 GMA 1347D GCU 475 (FMS Controller) GWX 68 WX Radar No. 1 ST—26 Tach-Gen Adapter No. 2 ST—26 Tach-Gen Adapter PC-920 FF Signal Conditioner Figure 1-1. G1000 & GFC 700 in King Air C90A/C90GT G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 1-5 190-00682-00 Revision 5 1.4.2 GFC 700 Operation The GFC 700 is a fail-passive digital flight control system composed of multiple G1000 LRUs and servos. The following functions are provided by the GFC 700 in this installation: • Flight Director • Autopilot • Pitch Trim • Yaw Damper Flight Director: The Flight Directors operate within the GIA 63Ws and use data from the G1000 system, including air, attitude, and flight data, to calculate commands for display to the pilot and for the Autopilot. Flight director command bars and mode annunciations are sent to the PFDs through a high-speed Ethernet connection for display to the pilot and copilot. The flight directors operate independently of the autopilot, and allows the pilot to hand-fly the command bars, if desired. The GMC 710 allows the pilot to switch the active director between flight director #1 (GIA1) and flight director #2 (GIA2). Autopilot: The autopilot operates within one GSA 81 servo (pitch trim) and three GSA 80 servos (pitch, roll and yaw). Flight director data is processed within the servos and turned into aircraft flight control surface commands. The autopilot cannot operate unless the flight director is engaged. Manual Electric Trim: When the autopilot is not engaged, the pitch trim servo may be used to provide a Manual Electric Pitch Trim (MEPT) function. This allows the pilot or co-pilot to adjust pitch trim from the PITCH TRIM switch on the control wheel in lieu of using the elevator trim wheel. Trim speeds are scheduled to provide easier control over a wide speed or configuration range. The PITCH TRIM switch is split into two halves. The left half arms MEPT. The right half controls direction. Both halves must be actuated at the same time to command the pitch trim servo to operate. If only one half of the PITCH TRIM switch is actuated for more than 3 seconds, a red PTRM message will appear on the PFDs. Yaw Damper: The yaw damper reduces dutch roll tendencies and coordinates turns. It can operate independently of the autopilot and may be used during normal hand-flight maneuvers. Page 1-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 1.5 G1000 Control Interface Control and operation of the following G1000 and GFC 700 equipment occurs through the PFDs, MFD, GMC , GCU or GMA 1347D audio panels. See the following documents for detailed information regarding control and operation. • G1000/GFC 700 and TAWS in Hawker Beechcraft King Air C90A/GT Airplane Flight Manual Supplement, Garmin P/N 190-00682-02 Revision A or later. • G1000 in Hawker Beechcraft King Air C90A/GT Cockpit Reference Guide, Garmin P/N 190- 00664-00 Revision A or later. 1.5.1 GMC 710 AFCS Controls The dedicated AFCS controls on the GMC 710 allow crew control interface with the various GFC 700 autopilot / flight director functions. GMC 710 controls are discussed in detail in the G1000 CRG. 1.5.2 GCU 475 FMS Controller The GCU 475 functions as the primary control interface to the GDU 1500 MFD, since the MFD does not possess any knobs or controls other than softkeys. 1.5.3 GMA 1347D Control The Garmin GMA 1347D audio panels integrate NAV/COM digital audio, intercom system and marker beacon controls. Manual display reversion mode (red DISPLAY BACKUP button) for PFD1, PFD2, and MFD is controlled by the GMA 1347D. Warning and alert audio received by the GMA 1347Ds is processed by and received from the GIA 63W Integrated Avionics Units (IAUs). 1.5.4 GRS 77 Attitude and Heading Reference System The Garmin GRS 77 is an attitude and heading reference systems (AHRS) that provides aircraft attitude (roll, pitch, and heading), angular rate and acceleration information to the GMUs, GIAs, GDU 1500 and GDU1040A LRUs. 1.5.5 GDC 74B Air Data Computer The Garmin GDC 74B processes data from the pitot/static system as well as the OAT probe. This unit provides pressure altitude, airspeed, vertical speed and OAT information to the G1000 system, and communicates with the on-side GIA 63W, on-side GDU 1040A and on-side GRS 77, using an ARINC 429 digital interface. 1.5.6 GIA 63W Integrated Avionics Unit (IAU) – (WAAS Enabled) The Garmin GIA 63W functions as main communication hub to the G1000 system linking all LRUs with the PFD and MFD displays. The GIA 63W contains the GPS/WAAS receiver, VHF COM/NAV receivers, and system integration microprocessors. 1.5.7 GEA 71 Engine/Airframe Unit The Garmin GEA 71 Engine/Airframe unit receives and processes signals from engine sensors. Communication interface is to GIA63W via RS-485. 1.5.8 GDL 69A Data Link The Garmin GDL 69A Data Link is an XM Satellite Radio data link receiver that receives broadcast weather data and XM Satellite Radio. The GDL 69A is a derivative of the GDL 69 and provides the same functionality as the GDL 69 except for the addition of XM Satellite Radio audio entertainment. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 1-7 190-00682-00 Revision 5 1.5.9 GMU 44 Magnetometer The Garmin GMU 44 Magnetometer senses magnetic field information and sends this data to the GRS 77 ARHS for processing to determine aircraft magnetic heading. 1.5.10 GTX 33 Mode S Transponder The Garmin GTX 33 Mode S Transponder provides Mode A, C, and S capabilities for ATC, TIS and TCAS I surveillance requirements. The GTX 33s interface with the No. 1 and No. 2 GIA63W G1000 LRUs via RS-232. 1.5.11 GSA 80 Servo Actuator The Garmin GSA 80 Servo Actuator is an electromechanical unit that will provide pitch, roll and yaw damp and turn coordination. 1.5.12 GSA 81 Servo Actuator The Garmin GSA 81 Servo Actuator is an electromechanical unit that will provide automatic control of the, pitch trim. 1.5.13 GSM 85/85A The Garmin GSM 85 and 85A Servo Mounts will attach to an adapter plate, which will mount to an existing bracket and is responsible for transferring the output torque of the GSA 80 /81 servo actuators to the mechanical flight control surface linkage. Page 1-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 This page intentionally left blank G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-1 190-00682-00 Revision 5 2 POST INSTALLATION PROCEDURES This section covers the procedures that must be performed after accomplishing the mechanical and electrical installations. It is assumed that the person performing the post-installation checks is familiar with the aircraft, has a working knowledge of typical avionics systems, and has experience using the test equipment defined in this section. All installation work must be completed in accordance with this STC before beginning any of the procedures in this document. Following initial system installation, this entire procedure must be successfully accomplished in order for the G1000 and GFC 700 system to be airworthy in the King Air C90A/GT. 2.1 Required Test Equipment The following test equipment is required to conduct and complete all post installation checkout procedures in this section: (All calibrated test equipment should have current calibration records) • A VHF NAV/COM, ILS, & DME ramp tester • A transponder ramp tester • A pitot/static ramp tester • A Digital Multi-Meter (DMM) • A ground power unit capable of supplying 28 Vdc power to the aircraft systems and avionics • Outdoor line-of-site to GPS satellite signals or GPS indoor repeater • Headset/Microphone • Hand Microphone • Digital Level or equivalent • Plum Bob • In-line type VSWR/wattmeter • Ambient temperature thermometer • ITT, N1, N2, Torque, Fuel Flow test equipment. Reference “Engine Indicating – Maintenance Practices” Raytheon (Hawker Beechcraft) King Air (A/B/C/E) Series Maintenance Manual Part No. 90-590012-13 Revision B11 or later, section 77-00-00. • Clamp-On type Amp Meter (Fluke 336 or equivalent) 2.2 G1000 Hardware/Software Compatibility Check Before installing hardware, the technician must first ensure that hardware part numbers are compatible with the G1000/C90 loader card that is to be used. A G1000/C90 loader card is required to install software and configuration settings to a newly installed G1000 system. The part number of this card is directly associated with the combination of software file part numbers and version levels that are defined on the card. Should software part numbers or versions change, a new loader card part number is issued. The G1000/GFC 700 General Arrangement (GA) drawing, Garmin Part Number 005-00375-22, shows all available combinations of hardware and loader cards. Using the GA drawing, the technician must verify that all hardware part numbers are compatible with the loader card to be used. The GA drawing allows the technician to correlate each LRU hardware part number to a compatible loader card. After verifying hardware/loader card compatibility, record the loader card part number and all LRU hardware part numbers in the appropriate aircraft records before proceeding. Throughout the next section of this document, screen shots and examples are used to illustrate the software and configuration loading process. These screen shots are provided as reference only. Always refer to the General Arrangement drawing for the correct software file names, versions and part numbers. NOTE IMPORTANT NOTE Page 2-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.3 G1000 Software/Configuration Procedure The G1000 is not airworthy unless software and configuration are accomplished successfully as described in these procedures. The following diagram depicts an overview of the software/configuration sequence for the G1000 system. If any problems are encountered during the loading process, see Section 2.17. It is extremely important that each LRU software load be completed successfully. Figure 2-1. Software/Configuration Overview G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-3 190-00682-00 Revision 5 2.3.1 System Power Up Apply power to the G1000 by doing the following: 1. Connect a ground power unit to the external power receptacle, and turn on the ground power unit. 2. Set the BAT, EXT PWR and AVIONICS MASTER switches to ON. 2.3.2 MFD & PFD Software Load 1. Pull the MFD, PFD1 (PRI), PFD1 (SEC) and PFD2 circuit breakers. 2. Insert the correct G1000/C90 Loader Card (Ref. General Arrangement, G1000/GFC 700 AFCS, King Air C90A/GT 005-00375-22) into PFD2 top card slot. 3. While holding the ENT key on PFD2, restore power by closing the PFD2 circuit breaker. 4. When the words appear in the upper left corner of PFD2, release the PFD2 ENT key. 5. Press the PFD2 ENT key to acknowledge the following prompt (NOTE: A softkey labeled ‘YES’ appears in the lower right corner and may be used in lieu of the ENT key): 6. The following screen is displayed. 7. New software is loaded to PFD2. When complete, the PFD starts in configuration mode displaying the “System Status” page . Do not remove power. 8. Remove the G1000/C90 Loader Card from PFD2 and insert it into the top card slot on the MFD. Repeat Steps 3 through 6 for the MFD, using the far right softkey on the MFD in lieu of the ENT key where called out in Steps 3 through 6. Note: The ENT key for the MFD is located on the GCU 475 FMS controller and will not function prior to software load. 9. When MFD update is complete, it starts in the configuration mode. Do not remove power. Repeat Steps 3 through 6 for PFD1. When complete, all three displays should be in configuration mode, with the Loader Card remaining in the top slot of PFD1. For the rest of the software/configuration procedure, do not operate the MFD or PFD2 while loading software or configuration files unless specifically instructed to do so. A failed or cancelled load may result. IMPORTANT Page 2-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.3.3 Initial G1000 Configuration The following “King Air C90 Baseline” is required for all airplanes covered by this STC. 1. Ensure loader card is inserted into top card slot of PFD1. On PFD1, select the “System Upload” page using the PFD1 small FMS knob. 2. Activate the cursor and use the PFD1 small FMS knob to highlight “C90” in the AIRFRAME field. Press the PFD1 ENT key to select the airframe type. 3. Once an airframe type is selected the cursor moves to the FILE window. Rotate the PFD1 small FMS knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” and press ENT on PFD1. Note: The PRODUCT window displays information regarding each G1000 LRU. The LRU column depicts the reported software version of the LRU, whereas the CARD VERS column shows the LRU software version stored on the Loader Card. The SOFTWARE and CONFIGURATION columns default to having all required boxes checked. Each checked file is automatically loaded to the correct G1000 LRU. 4. Press the LOAD softkey. 5. Observe software loading progress and verify software load completes without errors as indicated by the following: • Green “PASS” or N/A in SOFTWARE and CONFIGURATION columns. • “Upload Complete………….COMPLETE” in the summary box. 6. Press PFD1 ENT key to acknowledge the “Upload Complete” box. 7. Remove power form the G1000 system then proceed to section 2.4. IMPORTANT G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-5 190-00682-00 Revision 5 2.4 Software Load Confirmation 1. Start the G1000 system in Configuration Mode. 2. Select the System Status page using the small FMS knob. Activate the cursor and toggle to the LRU window. 3. Highlight each of the following items in the LRU window, and verify that the software part number and version matches the information in G1000/GFC 700 AFCS, King Air C90A/GT 005-00375-22 General Arrangement drawing. Control & Display SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK PFD1 ______ PFD2 FPGA ______ GCU ______ PFD1 FPGA ______ MFD1 ______ GMC ______ PFD2 ______ MFD1 FPGA ______ Page 2-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 CNS: SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK GIA1 ______ GPS2 ______ GDL69 ______ GIA2 ______ GTX1 ______ GWX ______ GMA1 ______ GTX2 ______ GWX FPGA ______ GMA2 ______ GIA1 AUDIO ______ GPS1 ______ GIA2 AUDIO ______ Sensors: SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK GDC1 ______ GMU2 ______ GEA1 ______ GDC1 FPGA ______ GMU2 FPGA ______ GEA2 ______ GDC2 ______ GRS1 ______ GDC2 FPGA ______ GRS1 FPGA ______ GMU1 ______ GRS2 ______ GMU1 FPGA ______ GRS2 FPGA ______ AFCS SYSTEM: SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK GSA PTCH CTL _____ GSA PTCH TRM M _____ GSA YAW CTL _____ GSA PTCH MON _____ GSA ROLL CTL _____ GSA YAW MON _____ GSA PTCH TRM C _____ GSA ROLL MON _____ AFCS CERT GAINS: SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK GFC CERT GIA1 _____ GFC CERT PT C _____ GFC CERT YC _____ GFC CERT GIA2 _____ GFC CERT PT M _____ GFC CERT YM _____ GFC CERT PC _____ GFC CERT RC _____ GFC CERT PM _____ GFC CERT RM _____ 4. De-activate the cursor. If any software version and/or part number does not match those specified by the General Arrangement drawing, or if the software is not successfully loaded, DO NOT continue with post- installation procedures. Troubleshoot and resolve the issue before continuing (see Section 2.17). IMPORTANT G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-7 190-00682-00 Revision 5 2.5 King Air C90 Airframe Configuration 2.5.1 Determining Airframe Configuration. Aircraft in the following serial number range that have not been modified by the STCs listed below do not require additional airframe configuration. Proceed to section 2.5.3. Serial number range – • 1361, 1363-1366, 1368-1372, 1374-1376, 1378-1383, 1385, 1387-1388, 1390-1393, 1395-1396, 1398- 1402, 1404-1410, 1412-1424,1426-1430, 1432-1497, 1499-1537, 1539, 1540-1726, 1728-1753,1755 STCs - • SA10341SC - Installation of Blackhawk Ultra Electronics Engine Instrument. • SA10364SC - Installation of Pratt & Whitney Canada PT6A-135A engines and McCauley 4HFR34C762/94LMA-4 or 4HFR34C768/94LMA-4 propellers. • SA3593NM - Installation of Hartzell/Raisbeck quiet turbofan propeller. For aircraft modified by the Raisbeck and/or Blackhawk STCs above, refer to Table 5 of the General Arrangement drawing 005-00375-22 to determine applicable configuration. Example- ¾ A/C serial number - 1362 ¾ A/C modified by - SA3593NM (Raisbeck) STC with AFMS 86-206C ¾ Configuration to be loaded – King Air C90A – Config 7 Once the correct configuration is determined, load the appropriate King Air C90 configuration per section 2.5.2 below. If the aircraft being modified has incorporated any modifications beyond factory configuration or the STCs listed above that effect engine or airspeed limitations, your configuration may not be supported at this time. It is the responsibility of the installer to ensure compatibility with existing modifications. 2.5.2 Loading Airframe Configuration. 1. While in configuration mode and loader card inserted in the top card slot of PFD1, select the “System Upload” page using the PFD1 small FMS knob. 2. Activate cursor in AIRFRAME window and rotate PFD1 FMS inner knob to display drop down menu. Highlight “C90-Configurations” and press ENT key on PFD1. 3. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 configurations. 4. Use the FMS inner knob to select the correct configuration file as determined above. Press ENT. 5. Verify the correct configuration file is displayed in the “FILE” window (for example “King Air C90A – Config 7”) then press “LOAD”. NOTE Page 2-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 6. Monitor load progress. Verify software load completes without errors as indicated by the following: a. Green “PASS” in Configuration column. b. “Upload Complete………….COMPLETE” in the summary box. 7. Select PFD1 ENT key to acknowledge upload complete. 2.5.3 Airframe Configuration Load Confirmation 1. Deselect cursor if selected, use the large FMS knob to select the GDU page group and the small FMS knob to select “AIRFRAME CONFIGURATION” page. 2. Verify the correct airframe configuration, as loaded above, is displayed in the “IDENTIFICATION” window. If King Air C90 Baseline or King Air C90A — Config 3 was loaded above, verify the values listed in the “AIRSPEEDS” window display 80 kts Vmca. For all other C90A configurations verify the values listed in the “AIRSPEEDS” window display 90 kts Vmca. For the C90GT configuration, verify the values listed in the “AIRSPEEDS” window display 85 kts Vmca. 2.5.4 Weight and Airspeed Configuration In addition to the airframe configuration loaded above, certain installations will require additional steps to configure the G1000 for airframe weight and airspeed markings. 2.5.5 Determining the Correct Weight Configuration If airframe configurations 4, 5, 7, 9 or 10 were loaded in step 2.5.2 • Load weight configuration file King Air C90 – 05-206CGW if operating with Raisbeck AFMS 05- 206CGW , or • Load weight configuration file King Air C90 – 90-206CGW if operating with Raisbeck AFMS 90- 206CGW If airframe configurations 2 or 5 were loaded in step 2.5.2 and the aircraft serial numbers falls within LJ- 1063 through LJ-1137 or LJ-1146 • Load weight configuration file King Air C90 – Weight LJ 1063-1137, All other installations require no further weight configuration steps. 2.5.5.1 Loading Airframe Weight Configurations Follow this procedure to enable the airframe weight configuration. 1. While in configuration mode and loader card inserted in the top card slot of PFD1, select the “System Upload” page using the PFD1 small FMS knob. 2. Activate cursor in AIRFRAME window and rotate PFD1 FMS inner knob to display drop down menu. Highlight “C90-Weight and Airspeed” and press ENT key on PFD1. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-9 190-00682-00 Revision 5 3. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 configurations. 4. Use the FMS inner knob to select the correct airframe weight configuration file, either “King Air C90 – 05-206CGW” or “King Air C90 – 90-206CGW or King Air C90 – Weight LJ 1063-1137,1146” as determined above. Press ENT. 5. Verify the correct configuration file is displayed in the “FILE” window (for example “ King Air C90 – 05-206CGW ”) then press “LOAD”. 6. Monitor load progress. Verify software load completes without errors as indicated by the following: a. Green “PASS” in Configuration column. b. “Upload Complete………….COMPLETE” in the summary box. 7. Select PFD1 ENT key to acknowledge upload complete. 2.5.5.2 Loading Airspeed Indication Marking Configuration Aircraft serial numbers LJ-1063 through LJ-1137 and LJ-1146 must load the airspeed configuration file King Air C90 – Airspeed LJ 1063 – 1137,1146 . All other aircraft not included in this serial number range are not required to load this additional airspeed indication marking configuration. Follow this procedure to enable the airspeed marking configuration. 1. While in configuration mode and loader card inserted in the top card slot of PFD1, select the “System Upload” page using the PFD1 small FMS knob. 2. Activate cursor in AIRFRAME window and rotate PFD1 FMS inner knob to display drop down menu. Highlight “C90-Weight and Airspeed” and press ENT key on PFD1. 3. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 configurations. 4. Use the FMS inner knob to select the airspeed indicator marking configuration file, “King Air C90 – Airspeed LJ 1063 – 1137,1146”. Press ENT. 5. Verify the correct configuration file is displayed in the “FILE” window (for example “ King Air C90 – Airspeed LJ 1063 – 1137,1146 ”) then press “LOAD”. 6. Monitor load progress. Verify software load completes without errors as indicated by the following: a. Green “PASS” in Configuration column. b. “Upload Complete………….COMPLETE” in the summary box. 7. Select PFD1 ENT key to acknowledge upload complete. Page 2-10 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.5.5.3 Airspeed Configuration Load Confirmation 1. Deselect cursor if selected, use the large FMS knob to select the GDU page group and the small FMS knob to select “AIRFRAME CONFIGURATION” page. 2. Verify the correct airspeed configuration, as loaded in step 2.5.5, is displayed in the “AIRSPEED” window. Aircraft LJ-1063 through LJ-1137, and LJ-1146: Vyse = 107 kts, Vmca = 90 kts , Vs 1 = 89 kts G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-11 190-00682-00 Revision 5 2.6 Traffic System Option Configuration 2.6.1 Traffic System Option 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 4.3 “Traffic System Functional Check”. 1. Ensure the loader card is inserted in the top card slot of PFD1. 2. With PFD1 in configuration mode, Select the “System Upload” page on PFD1 using the small FMS knob. 3. Activate cursor and rotate inner knob to display drop down menu. Highlight “C90-Options” and press the PFD1 ENT key. 4. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 options. 5. Use the FMS inner knob to select “King Air C90 – Traffic System Option”. Press ENT. 6. Verify the “King Air C90 – Traffic System Option” configuration file is displayed in the “File” window. Press “LOAD”. 7. Monitor load progress. Verify software load completes without errors as indicated by the following: 8. Green “PASS” in Configuration column. 9. “Upload Complete………….COMPLETE” in the summary box. 10. Select “ENT” to acknowledge upload complete. 2.6.2 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. If not already selected, use the GCU FMS knob to make the following selections: • TRAFFIC MODE – ALL TRAFFIC • TRAFFIC SMBL – 300NM • TRAFFIC LBL – 300NM Return to the Map Page by pressing the GCU FMS knob or momentarily pressing and holding the CLR key. Deactivate cursor. Page 2-12 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.7 StormScope (WX-500) Option Configuration 2.7.1 Stormscope (WX-500) Option 1. With PFD1 configuration mode and loader card inserted in the top card slot of PFD1, select the “System Upload” page using the PFD1 small FMS knob. 2. Activate cursor and rotate inner knob to display drop down menu. Highlight “C90-Options” and press PFD1 ENT key. 3. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 Options. 4. Use the FMS inner knob to select “King Air C90 – WX 500 Option”. Press ENT. 5. Verify the “King Air C90 – WX 500 Option” configuration file is displayed in the “File” window. Press “LOAD”. 6. Monitor load progress. Verify software load completes without errors as indicated by the following: 7. Green “PASS” in Configuration column. 8. “Upload Complete………….COMPLETE” in the summary box. 9. Select PFD1 ENT key to acknowledge upload complete. 10. Deactivate cursor. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-13 190-00682-00 Revision 5 2.7.2 Stormscope (WX-500) Configuration Load Confirmation. With PFD1 in configuration mode, use the PFD1 large FMS knob to select OTHER and the Stormscope configuration page. StormScope Configuration Page (Reference Only) Activate the cursor to highlight the DATA field. Use the small FMS knob to open the drop down menu then select ‘Config’ and press the ENT key on the PFD1. 1. Verify that the DATA window shows the following: Hdg: None: J3-1 Jumper J3-2 Jumper Hdg Valid Flag No Fla Flag Sense +invld J3-4 Open Hdg Value <aircraft heading> Inhibit Line Off Antenna Mount Bottom J3-3 Open 2. Deactivate the cursor Page 2-14 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 StormScope Configuration Page (Reference Only) NOTE The DATA window is only updated once every five seconds. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-15 190-00682-00 Revision 5 2.8 ADF – 60 Option Configuration 1. With PFD1 in configuration mode, use the large FMS knob to select the SYSTEM group. Select the “SYSTEM UPLOAD” page using the small FMS knob. 2. Activate cursor and rotate inner knob to display drop down menu. Highlight C90-Options and press PFD1 ENT key. 3. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 options. 4. Use the FMS inner knob to select “King Air C90 – ADF - 60 Option”. Press ENT. 5. Verify the “King Air C90 – ADF - 60 Option” configuration file is displayed in the “File” window. Press “LOAD”. 6. Monitor load progress. Verify software load completes without errors as indicated by the following: 7. Green “PASS” in Configuration column for GIA2, GMA PIL, and GMA COPIL. 8. “Upload Complete………….COMPLETE” in the summary box. 9. Select “ENT” to acknowledge upload complete. 10. Deactivate cursor. 2.9 DME 42 Option Configuration 1. With PFD1 in configuration mode, Select the “SYSTEM UPLOAD” page using PFD1 small FMS knob. 2. Activate cursor and rotate inner knob to display drop down menu. Highlight C90 -Options and press ENT key on PFD1. 3. Verify cursor drops down to the file box. Rotate the inner FMS knob to view the list of available C90 options. 4. Use the FMS inner knob to highlight “King Air C90 – DME-42 Option”. Press ENT key on PFD1. 5. Verify the “King Air C90 – DME-42 Option” configuration file is displayed in the “File” window. Press “LOAD”. 6. Monitor load progress. Verify software load completes without errors as indicated by the following: 7. Green “PASS” in Configuration column for GIA1, GMA PIL and GMA COPIL. 8. “Upload Complete………….COMPLETE” in the summary box. 9. Select “ENT” to acknowledge upload complete. 10. Deactivate cursor. Page 2-16 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.10 FliteCharts Configuration Follow this procedure to re-enable FliteChart function if ChartView has been enabled for the G1000 system. FliteCharts is a default G1000 system function. If ChartView has not been enabled, the following procedure is not required. If ChartView has previously been enabled, perform the procedure below to return FliteCharts function to the G1000 system if required. This procedure will re-load the C90 baseline configuration. Any options previously enabled such as DME, ADF etc will need to be re-enabled per the instruction contained in this document. NOTE The G1000 can only be configured for FliteCharts or ChartView but not both. Performing this procedure will automatically disable the ChartView function. Coordinate this configuration with section 3.17 “FliteChart Functional Checks”. 1. Ensure the appropriate loader card is inserted in the top card slot of PFD1 2. With PFD1 in configuration mode, select the “System Upload” page using PFD1 small FMS knob. 3. Activate the cursor and use the small FMS knob to highlight “C90” in the AIRFRAME field. Press the ENT key to select the airframe type. Ensure that the correct airframe type is selected before proceeding; otherwise, incorrect configuration information will be loaded. 4. Once an airframe type is selected the cursor moves to the FILE window. Rotate the small FMS knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” and press ENT. Note: The PRODUCT window displays information regarding each G1000 LRU. The LRU column depicts the reported software version of the LRU, whereas the CARD VERS column shows the LRU software version stored on the Loader Card. The SOFTWARE and CONFIGURATION columns default to having all required boxes checked. Each checked file is automatically loaded to the correct G1000 LRU. 5. Press the LOAD softkey. 6. Observe software loading progress and verify software load completes without errors as indicated by the following: a. Green “PASS” or N/A in the Configuration column. b. “Upload Complete………….COMPLETE” in the summary box. 7. Press ENT to acknowledge the “Upload Complete” box. 8. Reload other C90 options as appropriate per instructions contained within this document. IMPORTANT G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-17 190-00682-00 Revision 5 2.11 ChartView Configuration Follow this procedure to activate the ChartView option. A ChartView Enable Card, as specified in 005- 00375-22 “General Arrangement Drawing, King Air C90A/GT” will be required for this procedure. NOTE The required ChartView databases are subscription-based and are to be procured by the installing agency directly from Jeppesen. NOTE The G1000 can only be configured for FliteCharts or ChartView but not both. Performing this procedure will automatically disable the FliteChart option. Coordinate this configuration with section 3.18 “ChartView Functional Checks”. 1. Remove power from the PFD1, PFD2 and MFD by opening the PFD1 PRI / SEC, PFD2 and MFD circuit breakers. 2. An ChartView Enable card is required to activate this feature. Insert the ChartView Enable card in the upper slot of the PFD1. 3. While holding the ENT key on PFD1, PFD2 and MFD (for MFD press and hold the farthest right pushbutton), restore power to the displays by closing the PFD and MFD circuit breakers. 4. When the words appear in the upper left corner of the displays, release the ENT key. 5. On PFD1, go to the System Upload page using the small FMS knob. 6. Activate the cursor. Use the small FMS knob to select Configuration Files in the AIRFRAME field and press the ENT key. 7. Verify the FILE field is highlighted. Use the PFD1 small FMS knob to select the “Enable ChartView” option and press the ENT key on PFD1. All files should be checked. If not, press the CHK ALL softkey. 8. Press the LOAD softkey. 9. Monitor the status of the upload. When the upload is finished, press the ENT key to acknowledge the upload complete confirmation. 10. View the SUMMARY field and ensure that the item is ‘COMPLETED’. 11. De-activate the cursor. 12. Power down the system and remove the ChartView Enable card from PFD1. Page 2-18 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.12 TAWS Configuration Follow this procedure to activate the TAWS option. A TAWS Enable Card, as specified on General Arrangement Drawing 005-00375-22, will be required for this procedure. 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 TAWS Unlock card in the upper slot of PFD1. 4. While holding the ENT key on the PFD1, PFD2 and MFD (for MFD press and hold the farthest right pushbutton), restore power to the displays. 5. When the words appear in the upper left corner of the displays, release the ENT key. 6. On PFD1, go to the System Upload page using the small PFD1 FMS knob. 7. Activate the cursor. Use the small PFD1 FMS knob to select CONFIGURATION FILES in the AIRFRAME field and press the PFD1 ENT key. 8. Highlight the FILE field. Use the PFD1 small FMS knob to select the ‘Enable TAWS’ option and press the PFD1 ENT key. Once the option is selected, the configuration files in the PRODUCT field will be displayed. All files should be checked. If not, press the CHK ALL softkey. 9. Press the LOAD softkey. 10. Monitor the status of the upload. When the upload is finished, press the PFD1 ENT key to acknowledge the upload complete confirmation. 11. View the SUMMARY field and ensure that the item is ‘COMPLETE’. 12. De-activate the cursor. 13. Power down the system and remove the TAWS Enable card from PFD1. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-19 190-00682-00 Revision 5 2.13 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 on PFD1. 3. Select or verify selected, XPDR1 is in the SELECT TRANSPONDER window. 4. Ensure that the ‘ADDRESS TYPE’ is ‘US TAIL’ under the ‘SET’ and ‘ACTIVE’ columns. 5. Activate the cursor and highlight the ‘ADDRESS’ field. Use the small/large FMS knobs to enter the aircraft registration number. 6. Once the correct registration number is entered, press the ENT key. The transponder is configured: 7. Observe the status window. 8. Press the ENT key on PFD1 to acknowledge prompt. 9. Verify FLIGHT ID TYPE = SAME AS TAIL under SET and ACTIVE columns. 10. After the #1 transponder configuration is complete, use the cursor to select XPDR2 and repeat Steps 2 –8. 11. After completing XPDR2 configuration, deactivate the cursor. 2.14 Terrain/Obstacle Database Loading 1. Open PFD1, PFD2 and MFD circuit breakers. 2. Insert an SD card containing current Terrain/Obstacle database cards into the lower slots of PFDs and MFD. Refer to the General Arrangement drawing for correct card part numbers. 3. Close PFD1, PFD2 and MFD circuit breakers. Page 2-20 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.15 Aviation Database Loading 1. Remove power from PFD1, PFD2 and MFD. 2. Insert an SD card containing the latest cycle Jeppesen aviation database (data supplied by Jeppesen) into the top slot of PFD2. 3. Apply power to PFD2. The following prompt is displayed in the upper left corner of PFD2: 4. Press the PFD2 ENT key to confirm the database update. 5. A prompt will be displayed. Press ENT for YES. 6. After the update completes, PFD2 starts in normal mode. Remove the aviation database update SD Card from PFD2. 7. Repeat steps 2 through 4 for the MFD then PFD1 (for MFD press and hold the farthest right pushbutton). 8. The aviation databases are now updated. 9. Confirm that the correct update cycle is loaded at the power-up page of the MFD. 10. Remove the aviation database update SD Card from PFD1. 11. Continue to Section 3 for system testing and checkout. 2.16 Clearing Default User Settings 1. Remove power from PFD1, PFD2 and MFD. 2. While holding the CLR button on PFD1, re-power PFD1. 3. When prompted to clear user settings select the YES softkey. 4. Repeat steps 1 -3 for PFD 2. 5. On the MFD, press and hold the second key from the right side of the unit (beginning on the right side of the MFD, count 2 keys to the left). Re-power MFD. 6. When prompted to clear user settings select the YES softkey. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-21 190-00682-00 Revision 5 2.17 Software/Configuration Troubleshooting Problem Solutions MFD or PFD displays do not power up: • Ensure that the criteria listed in 2.17.1 are fulfilled for the applicable situation. • Ensure power is present at display backshell connector. • Replace display. Software file load fails: • Ensure that criteria listed in 2.17.1 are fulfilled for the applicable situation. • Ensure that LRU is reporting data on System Status page (LRU is ‘ONLINE’). Check data path wiring as needed. • Retry software 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 software version and Card Loader. Refer to the General Arrangement Drawing and to Section 1 of this document. • Replace LRU. Configuration file load fails: • Ensure that criteria listed in 2.17.1 are fulfilled for the applicable situation. • Ensure that LRU is reporting data on System Status page (LRU is ‘ONLINE’). Check data path wiring as needed. • 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 and to Section 1 of this document. • Replace LRU. GIA1 and/or GIA2 to ‘LRU’ data path not working • Ensure that criteria listed in 2.17.1 are fulfilled for the applicable situation. • Ensure GIA1 and GIA2 are configured correctly. • Check wiring, connectors & pins as needed. Software File Mismatch Alert appears in lower right corner of PFD when started in normal mode: • Ensure that proper software file part number and version were loaded to LRU. Refer to the General Arrangement Drawing and to Section 1 and 2.17.1. • Check and ensure that correct Card Loader was used during load process. Refer to the General Arrangement Drawing. • Reload software to LRU. Page 2-22 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 2.17.1 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 • G1000/C90 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. Load AIRFRAME, SYSTEM, MFD1, PFD1, PFD2 and MANIFEST configuration files to MFD and PFDs • G1000/C90 SW Loader Card must be inserted in top slot of PFD1. • PFD1 and MFD must be powered on. • PFD1 and MFD must have correct software. Load Software/Configuration files to GIA 63Ws • G1000/C90 SW Loader Card must be inserted in top slot of PFD1. • G1000 system must be powered on. • PFD and MFD must have correct software. • PFD1 and MFD must be successfully configured with AIRFRAME, SYSTEM, MANIFEST, MFD1, PFD1 and PFD2 configuration files. Load Software/Configuration files to: - GMA 1347D - GDC 74B - GEA 71 - GRS 77 (software only) - GMU 44 (software only) - GTX 33 • G1000/C90 SW Loader Card must be inserted into PFD1 top slot. • G1000 must be powered on. • PFD1 and MFD must have correct software and configuration settings. • GIA 63Ws must have correct software. • GIA 63Ws must be successfully configured with GIA1 and GIA2 configuration files. • Data path from GIA1 to each LRU must be operational. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-1 190-00682-00 Revision 5 3 G1000 INITIAL SYSTEM TESTING 3.1 Electrical Power Distribution Testing Note: Throughout this test, verify only the appropriate system(s) are affected by the circuit breaker (CB) being opened. Between each step, allow enough time for each system to return to normal following CB closure. For the following steps, G1000 interfaced systems include: GWX-68, SKY899 (TCAS) and the L3 Stormscope system. 1. Apply external power. 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. Open PFD1 PRI CB. Verify PFD1 remains powered and no other changes occur to any G1000 or G1000 interfaced system. 3. Open PFD1 SEC CB. Verify PFD1 goes blank. 4. Close PFD1 PRI CB. Verify PFD1 is powered. Close PFD1 SEC CB. 5. Open PFD2 CB. Verify PFD2 is not powered. 6. Close PFD2 CB. Verify PFD2 is powered 7. Open GIA1 PRI CB. Verify GIA1 remains powered by observing the absence of red Xs or alert messages and no other changes occur to any G1000 or G1000 interfaced system. 8. Open GIA1 SEC CB. Verify GIA1 is not powered by observing red Xs and/or alert messages. 9. Close GIA 1 PRI CB. Verify GIA1 is powered by observing the absence of red Xs or alert messages and no other changes occur to any G1000 or G1000 interfaced system. Close GIA 1 SEC CB. 10. Open GIA2 CB. Verify GIA2 is not powered by observing red Xs and/or alert messages. 11. Close GIA 2 CB. Verify GIA2 is powered by observing the absence of red Xs or alert messages and no other changes occur to any G1000 or G1000 interfaced system. 12. Open AHRS1 PRI CB. Verify AHRS1 remains powered and no other changes occur to any G1000 or G1000 interfaced system. 13. Open AHRS1 SEC CB. Verify AHRS1 is not powered by observing red Xs are displayed for AHRS1 attitude information. 14. Close AHRS1 PRI CB. Verify AHRS1 is powered by observing valid AHRS1 attitude information. Close AHRS1 SEC CB. 15. Open AHRS2 CB. Verify AHRS2 is not powered by observing red Xs are displayed for AHRS2 attitude information. 16. Close AHRS2. Verify AHRS2 is powered by observing valid AHRS2 attitude information. 17. Open ADC1 PRI CB. Verify ADC1 remains powered by observing valid ADC1 air data information absence of red Xs or alert messages and no other changes occur to any G1000 or G1000 interfaced system. 18. Open ADC1 SEC CB. Verify ADC1 is not powered by observing red Xs are displayed for ADC1 air data information. Page 3-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 19. Close ADC1 PRI CB. Verify ADC1 is powered by observing valid ADC1 air data information. Close ADC1 SEC CB. 20. Open ADC2 CB. Verify ADC2 is not powered by observing red Xs are displayed for ADC2 air data information. 21. Close ADC2 CB. Verify ADC2 is powered by observing valid ADC2 air data information 22. Open MFD CB. Verify MFD is not powered. 23. Close MFD CB. Verify MFD is powered. 24. Open COMM NO 1 CB. Verified COMM 1 is not powered by observing a red X is displayed in COMM 1 tuning window. 25. Close COMM NO 1 CB. Verify COMM1 is powered by observing a valid frequency in the COMM1 tuning window. 26. Open COMM No. 2 CB. Verified COMM2 is not powered by observing a red X is displayed in COMM 2 tuning window. 27. Close COMM No. 2 CB. Verify COMM2 is powered by observing a valid frequency in the COMM2 tuning window. 28. Open MODE CTL CB. Verify GMC 710 AFCS mode controller is not powered. Close AFCS CTL CB when finished. 29. Open AFCS SERVOS CB. Verify AFCS servos are not powered by observing momentary Red/white AFCS annunciation. 30. Close AFCS SERVOS CB. Verify AFCS servos are powered by observing that the Red/white AFCS annunciation extinguishes. 31. Open DATA LINK CB. Verify GDL 69 is not powered by observing related alert messages. 32. Close DATA LINK CB. Verify GDL 69 is powered. 33. Open FMS CTL CB. Verify the FMS controller is not powered. 34. Close FMS CTL. Verify the FMS controller is powered. 35. Verify STBY Battery power is OFF. 36. Open STBY ATT CB. Verify the standby attitude indicator is not powered. 37. Close STBY ATT CB. Verify the standby attitude indicator is powered. 38. Open STBY ALTM CB. Verify the standby altimeter vibrator is not powered. 39. Close STBY ALTM CB. Verify the standby altimeter vibrator is powered. 40. Open AUDIO 1 CB. Verify GMA1 is not powered. 41. Close AUDIO 1 CB. Verify GMA1 is powered. 42. Open AUDIO 2 CB. Verify GMA2 is not powered. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-3 190-00682-00 Revision 5 43. Close AUDIO 2 CB. Verify GMA2 is powered. 44. Open XPDR No1 CB. Verified XPDR1 is not powered by observing a red X is displayed in XPDR1 display window. 45. Close XPDR No1 CB. Verify XPDR1 is powered by observing a valid XPDR code in the XPDR1 display window. 46. On PFD1, select the XPDR key then select XPDR2. 47. Open XPDR No 2 CB. Verified XPDR2 is not powered by observing a red X is displayed in XPDR2 display window. 48. Close XPDR No2 CB. Verify XPDR2 is powered by observing a valid XPDR code in the XPDR2 display window. 49. Open MFD FAN CB. Verify MFD display fan are not powered and MFD 1 FAN FAIL alert message is displayed on PFD1 and PFD2. 50. Close MFD FAN CB. Verify MFD fan is powered and MFD FAN FAIL message extinguish on PFD1 and PFD2. 51. Open PFD/GIA FANS LEFT CB. Verify PFD1 and GIA1 fans are not powered and AVN FAN 1 FAIL / PFD 1 FAN FAIL alert messages are displayed. Close CBs when finished. 52. Open PFD/GIA FANS RIGHT. Verify PFD2 and GIA2 fans are not powered and AVN FAN2 FAIL / PFD 2 FAN FAIL alert messages are displayed. Close CBs when finished. 53. Open AVIONICS NO 2 CB. Verify the following are not powered: • COMM2 • AUDIO2 (GMA2) • XPDR2 • WX radar (If equipped) • DME (If equipped) 54. Attempt to engage autopilot. Verify Autopilot will not engage. 55. On PFD1, select the XPDR key then select XPDR1. 56. Open AVIONICS NO 1 CB. Verify the following are not powered: • COMM1 • AUDIO1 (GMA1) • XPDR 1 57. Open AVIONICS NO 3 CB. Verify the following are not powered: • GDL 69 • Stormscope • TCAS Page 3-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 58. Open CB Panel No. 1 (Triple Fed Bus 1), PFD1 SEC, AHRS1 SEC, ADC1 SEC, GIA1 SEC. Verify the following are not powered: Note: The triple fed circuit breaker panel is located beneath cockpit floor on the copilot side. • PFD1 • AHRS1 • ADC1 • GIA1 • GEA1 • GMU1 • GMC 710 AFCS Controller 59. Close CB Panel No. 1 (Triple Fed Bus 1). 60. On GMA1, select DISPLAY BACKUP button ( button depressed). 61. Open CB Panel No. 2 (Triple Fed Bus 2) CB. Verify the following are not powered: • MFD • GEA2 62. Close CB Panel No. 2 (Triple Fed Bus 2) CB. 63. On GMA1, de-select DISPLAY BACKUP button ( button extended). 64. Open CB Panel No. 3 (Triple Fed Bus 3) CB. Verify STBY Battery power is OFF. Verify the following are not powered: • PFD2 • MFD Fan • AHRS2 • GIA2 • ADC2 • GCU 475 FMS controller • GMU2 • Standby Attitude Indicator 65. Close CB Panel No. 3 (Triple Fed Bus 3) CB. 66. Remove aircraft power by selecting Avionics Master, EXT PWR and BAT switch to OFF. 67. Select STANDBY BATTERY switch ON (depressed). 68. Verify the following are powered: • STBY ATT indicator motor • STBY ALT vibrator • STBY ATT, STBY Airspeed, and STBY ALT lighting 69. Select STANDBY BATTERY switch OFF (extended). G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-5 190-00682-00 Revision 5 3.2 Electrical Load Test Procedures CAUTION - De-icing heat elements will be energized during this procedure. Ensure aircraft is safe for the application of anti-ice heat. 1. Using a 28 VDC ground power cart apply external power to the aircraft. Set BAT, EXT PWR and AVIONICS MASTER switches to ON. Allow all aircraft systems to complete initialization and operate for 15 minutes. 2. Set the clamp-on meter to read DC amps. Follow meter manufacture instructions to zero the amp- meter. Place meter around the ground power cart DC power cable. 3. Make or verify the following switch selections: Switches not listed are not required. • EXT PWR – OFF • AVIONICS MASTER PWR – OFF • BAT – OFF • GEN 1 – OFF • GEN 2 - OFF • LEFT /RIGHT ENG AUTO IGNITION – OFF • BUS SENSE – NORM • GEN TIES – NORM • LEFT/RIGHT ENGINE ANTI-ICE – OFF • AUTOFEATHER – OFF • LEFT/RIGHT LANDING LIGHTS – OFF • TAXI LIGHTS – OFF • ICE LIGHTS – OFF • NAV LIGHTS – OFF • RECOG LIGHTS – OFF • PILOT WSHLD ANTI-ICE – OFF • COPILOT WSHLD ANTI-ICE – OFF • PROP ANTI-ICE – OFF • LEFT/RIGHT FUEL VENT ICE PROTECTION – OFF • SURFACE DEICE – OFF • STALL WARN ICE PROTECTION – OFF • LEFT/RIGHT PITOT ICE PROTECTION – OFF • BEACON LIGHTS – OFF • STROBE LIGHTS – OFF • TAIL FLOOD LIGHT – OFF • PROP SYNC – OFF (extended) • STANDBY BATTERY – OFF (extended) • CABIN BAR – OFF Page 3-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 • CABIN BRIGHT – OFF • NO SMK & FSB – OFF • VENT BLOWER – AUTO • LEFT/RIGHT BLEED AIR VALVES – CLOSED • ELEC HEAT – OFF • CABIN TEMP MODE – OFF • LEFT/RIGHT TRANS PUMPS – OFF • LEFT/RIGHT BOOST PUMP – OFF • CROSSFEED - CLOSE • MASTER PANEL LIGHTS – OFF • WINDSHIELD WIPERS – OFF • OVERHEAD FLOOD LIGHT CONTROL – OFF • INSTRUMENT INDIRECT LIGHT CONTROL – OFF • PILOT PFD LIGHT CONTROL – OFF • STBY INSTR LIGHT CONTROL – OFF • MFD LIGHT CONTROL – OFF • OVHD PED & SUBPANEL LIGHT CONTROL – OFF • SIDE PANEL LIGHT CONTROL – OFF • CLOCKS LIGHT CONTROL – OFF • COPILOT PFD LIGHT CONTROL – OFF • INSTRUMENT EMERG LIGHTS – OFF 4. Ensure all circuit breakers (CBs) are closed. 5. Open the following circuit breakers: • COM 1 • AUDIO 1 • XPDR 1 • COM 2 • AUDIO 2 • XPDR 2 • RADAR • DME • AFCS SERVOS • DATA LINK • RADIO ALT (if installed) • ADF • STORM SCOPE • TRFC • MFD • VOICE RECORDER • CABIN AUDIO G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-7 190-00682-00 Revision 5 • AURAL WARN (if installed) • MODE CTL • STBY ALTM • PFD 1 (sec) • AHRS 1 (sec) • ADC 1 (sec) • GIA 1 (sec) • PFD/GIA FANS (right) • PFD/GIA FANS (left) • PFD 1 (prim) • AHRS 1 (prim) • ADC 1 (prim) • GIA 1 (prim) • MFD FAN • PFD 2 • AHRS 2 • ADC 2 • GIA 2 • FMS CTL • STBY ATT • STBY AUX BAT • AVIONICS MASTER • R TORQ • R PROP/N1 TACH • R ENG INST • R FUEL FLOW • R OIL PRESS • L TORQ • L PROP/N1 TACH • L ENG INST • L FUEL FLOW • L OIL PRESS 6. Make the following switch selections: • EXT PWR – ON 7. Observe the non-switchable DC electrical load (EXT PWR ON) from the amp meter and record in Table 1 as DP1. (Note: This load may be extremely low and can be considered negligible if under 1 amp) 8. Verify the aircraft is secure. This test should be limited in duration to minimize risks to the aircraft systems and/or airframe. Activate the following systems: • BATT switch ON • ICE LIGHTS switch to ON • NAV LIGHTS switch to ON • BEACON LIGHTS switch to ON • STROBE LIGHTS switch to ON • TAIL FLOOD LIGHT switch to ON • LEFT/RIGHT LANDING LIGHTS switch to ON Page 3-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 • TAXI LIGHTS switch to ON • RECOG LIGHTS switch to ON • PILOT WSHLD ANTI-ICE switch to ON • COPILOT WSHLD ANTI-ICE switch to ON • STALL WARN ICE PROTECTION switch to ON • LEFT/RIGHT FUEL VENT ICE PROTECTION switch to ON • LEFT/RIGHT PITOT ICE PROTECTION switch to ON • ELEC HEAT switch to NORM • LEFT/RIGHT BLEED AIR VALVES switch to OPEN • LEFT/RIGHT ENGINE ANTI-ICE switch to ON • CABIN TEMP MODE switch to AUTO • PROP SYNC switch to ON (depressed) • BOOST PUMP-LEFT switch to ON • BOOST PUMP-RIGHT switch to ON • SURFACE DEICE switch to SINGLE 9. Observe the DC electrical load (EXT PWR ON, BATT charge, External lights, anti-ice systems) from the amp meter and record in Table 1 as DP2. 10. Turn off all switches referenced in paragraph 8. 11. Configure the aircraft to measure G1000/GFC700 system loads by making or verifying the following switch selections: 12. Ensure that the circuit breakers in paragraph 5 are closed with the exception of RADAR circuit breaker. • EXT PWR – ON • AVIONICS MASTER PWR – ON • BUS SENSE – NORM • GEN TIES – NORM • MASTER PANEL LIGHTS – ON • OVERHEAD FLOOD LIGHT CONTROL – ON and adjusted to max brightness • INSTRUMENT INDIRECT LIGHT CONTROL – ON and adjusted to max brightness • PILOT PFD LIGHT CONTROL – ON and adjusted to max brightness • STBY INST LIGHT CONTROL - ON and adjusted to max brightness • MFD LIGHT CONTROL - ON and adjusted to max brightness • OVHD PED & SUBPANEL LIGHT CONTROL - ON and adjusted to max brightness G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-9 190-00682-00 Revision 5 • SIDE PANEL LIGHT CONTROL - ON and adjusted to max brightness • CLOCKS LIGHT CONTROL - ON and adjusted to max brightness • COPILOT PFD LIGHT CONTROL - ON and adjusted to max brightness • INSTRUMENT EMERG LIGHTS – ON • CABIN BAR – ON • NO SMK & FSB – ON NEVER OPERATE THE WINDSHIELD WIPERS ON A DRY WINDSHIELD - Remove the spring tension on the hub end of the wiper arm by inserting a 1/8-inch-diameter pin through the hole in each side of the wiper arm. • WINDSHIELD WIPERS – ON • AUTOPILOT – ENGAGED with pitch, pitch trim, and roll servos running Tune VHF COMM NO. 1 to a frequency appropriate for test transmissions. Transmit on COMM No. 1 (no modulation is necessary). 13. Observe the G1000/GFC700 DC electrical load from the amp meter and record in Table 1 as DP3. 14. Discontinue transmitting on COM 1. Disengage Autopilot 15. Turn off windshield wipers and remove the pin from the holes in the wiper arm. 16. Close the circuit breaker for Radar. Data Point Bus Amps DC DP1 Non-switchable DC electrical load (EXT PWR ON) DP2 DC electrical load (EXT PWR ON, BATT charge, External lights, anti-ice systems DP3 G1000/GFC700 DC Electrical load (AFCS engaged, COM TX) Table 1 - Measured DC Electrical Loads 17. Using the data points from Table 1, obtain the total electrical load by the following formula: DP2 + DP3 – DP1 +2 amps = Total Electrical Load _________________ DC amps ( GWX 68 maximum power loads is 2 amps ) Verify adequate capacity of the aircraft electrical system with the addition of the G1000 and GFC 700 systems. CAUTION Page 3-10 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 3.3 Display Testing The G1000 system is tested while operating in the normal mode unless otherwise specified. If the system is in configuration mode, restart the displays by cycling the PFD1, PFD2 and MFD circuit breakers to start the display in the normal mode. 1. Apply aircraft power. Observe the MFD power-up screen. Verify the display is formatted as shown below in Figure 3-1. Figure 3-1 is a format reference, the illustration on the left may vary. Note database versions and system software represented in the upper right corner. Refer to General Arrangement Drawing 005-00375-22 drawing for the correct database and system software versions. Figure 3-1. MFD Power Up Page (format reference) 2. The ‘System’ number reflected in the upper right hand corner is the System Software Version. It correlates to the G1000 SW Loader Card used to load the software to the system. For example: EXAMPLE: System Software Version ‘0xxx.xx’ = Loader Card P/N 010-00xxx-xx 3. Verify that the System Software Version is correct per General Arrangement Drawing 005-00375-22. 4. Press the GCU ENT key to acknowledge the agreement on the MFD (NOTE: The rightmost softkey may also be used to acknowledge the agreement). G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-11 190-00682-00 Revision 5 Figure 3-2. PFD Power-up System Annunciations In the normal operating mode, data fields that are invalid have large red X’s through them (Figure 3-2). A valid field does not display a red X. Allow the displays to initialize for approximately one minute. The GDC 74Bs requires a longer initialization period than do the other LRUs. During normal operation, this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid during the first ~40-60 seconds of PFD power-up. Outputs from the GRS 77 AHRS and GMU 44 are not valid until the units have been calibrated as described later in this chapter. 5. Check that all COM/NAV fields are valid in the top corners of PFD1 and PFD2. 6. Check that altitude, airspeed, vertical speed, TAS, and OAT fields are valid on PFD1 and PFD2. 7. 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. 8. Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2. Verify that data from both GRS 77s is valid on both displays. 9. Check that engine instrument fields are valid on the MFD. 10. Verify that no MANIFEST alert messages appear in the lower right corner (press the flashing ALERTS softkey to view alert messages). If any MANIFEST errors appear, the correct software to the related LRU must be loaded before proceeding (refer to Section 2). NOTE Page 3-12 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 3.3.1 Cooling Fan Check 1. Confirm equipment fan operation by verifying the absence of the following alert messages: • PFD 1 FAN FAIL • PFD 2 FAN FAIL • MFD FAN FAIL • AVN 1 FAN FAIL • AVN 2 FAN FAIL 3.3.2 Reversion Mode Check 1. Push the red DISPLAY BACKUP button on the pilot-side GMA 1347D. Verify that the pilot-side PFD and MFD displays enter reversion mode. MFD should have valid altitude, airspeed, vertical speed, COMM1, COMM2, NAV1, NAV2 and engine instruments. 2. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD1 and MFD return to normal display modes. 3. Repeat Step 1 using GMA2. Ensure that PFD2 and MFD enter reversion mode and MFD displays valid altitude, airspeed, vertical speed, COMM1, COMM2, NAV1, NAV2 and engine instruments. 4. De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD2 and MFD return to normal display modes. 5. Open PFD1 (PRI) and PFD1 (SEC) circuit breakers. Verify the PFD1 goes blank and MFD display remains in normal mode. 6. Push the red DISPLAY BACKUP button on the pilot-side GMA 1347D. Verify that the MFD displays enter reversion mode. MFD should have valid altitude, airspeed, vertical speed, COMM2, NAV2 and engine instruments. 7. Close PFD1 (PRI) and PFD1 (SEC) circuit breakers and de-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD1 and MFD return to normal display modes G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-13 190-00682-00 Revision 5 3.4 GPS Signal Acquisiton Figure 3-3. 4th AUX Page 1. Select the GPS status page on the MFD (4th page in AUX group). Toggle between GPS 1 and GPS 2 using the two softkeys on the bottom of the display. Verify that both receivers show 3D DIFF NAV on the MFD. (The GIA 63W units should normally acquire a 3D GPS navigation solution within 2 minutes of startup, provided the aircraft is outside or indoors with a GPS repeater). Page 3-14 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 3.5 GMA 1347D Testing Perform the following checks in the aircraft with known good hand microphone and headset. 3.5.1 Intercom System (ICS) Check 1. Ensure that the MAN SQ key is off (no light). 2. Adjust GMA1 and GMA2 ICS volume to a comfortable level. 3. Plug in a headset at each COCKPIT ICS position. One at a time, plug a headset into each left and right CABIN ICS jack location (one headset on right, one headset on left). 4. Verify the following: • Two-way communication between each CABIN ICS jack position. • CABIN ICS positions cannot be heard by the pilot or copilot. 5. Select GMA1 pilot ICS ISOLATION button and verify the following: • Passengers can communicate with each other. • The copilot cannot hear pilot and the pilot cannot hear passengers or copilot. 6. Deselect GMA1 pilot ICS ISOLATION. 7. Repeat steps 5-6 using GMA2 for copilot. 8. On GMA1 select COM1 MIC and AUDIO. 9. Ensure INTR COM is deselected on GMA1 or GMA2. Verify an active (green) COM frequency is displayed on both PFDs . 10. On GMA1, select PA and verify the PA select annunciator is illuminated on GMA1. Verify COM1 active frequency is displayed white. 11. On GMA 2, select PA and verify the PA select annunciator is illuminated on GMA2. Verify COM2 active frequency is displayed white 12. Initiate passenger address using pilot’s headset boom mic by keying the pilots PTT. Verify clear PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator on GMA1 flashes ~ once per second during PA address. Repeat using pilot hand mic. 13. Initiate passenger address using copilot’s headset boom mic by keying the copilots PTT. Verify clear PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator on GMA1 flashes ~ once per second during PA address. Repeat using copilot hand mic. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-15 190-00682-00 Revision 5 3.6 VHF COMM Operational Check Perform a ramp test radio check by exercising the installed transceivers, boom mic, hand mic, microphone key and audio over the headphones and speaker. Verify that communications are clear and PTT operation is correct for each pilot position. 1. 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 headsets. 2. Press the SPKR key and verify that the selected audio is heard over the speaker. 3.6.1 Failsafe Operation Check 1. Open AUDIO No 1 CB. 2. Check the failsafe operation by exercising the COM 1 boom mic, hand mic, microphone key and audio over the headphones. All volume control for the COM audio should be through the PFD1 and PFD2 volume control. Verify proper operation of COM 1 using the failsafe operation. 3. Close AUDIO No 1 CB. 3.7 Marker Beacon Test Figure 3-4. Marker Beacon Symbology Using a ramp tester, simulate the outer marker, middle marker and inner marker signals by following the test equipment manufacturer’s instructions. Verify that each marker audio signal is present over the pilot and co-pilot headphones and cockpit speaker. Verify that the outer, middle, and inner annunciations appear on PFD1 and PFD2 when the corresponding signal is applied. Marker beacon annunciations appear at the upper left corner of the altitude indicator on the PFD (Figure 3-4). Operate the MKR MUTE key on GMA1 and GMA2 and ensure that the audio signal is muted. 3.8 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 from Section 3.4 has been completed successfully, perform the following steps: 1. On the MFD, monitor GPS1 signal strength bars on the 4th AUX page. 2. On PFD1 and PFD2, ensure that the CDI is set to GPS. If it is not, press the ‘CDI’ softkey until GPS ENR is displayed. 3. Verify that the GPS “INTEG” flag is out of view. 4. Select 121.150 MHz on the No. 1 COM transceiver. 5. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels. 6. During the transmit period, verify that the GPS “INTEG” flag does not come into view on either PFD and verify that GPS1 does not lose a 3-D navigation solution on the MFD. Page 3-16 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 7. Repeat steps 5 and 6 for each of the following frequencies: • 121.175 MHz • 121.200 MHz • 131.250 MHz • 131.275 MHz • 131.300 MHz 8. Repeat steps 3 through 7 while monitoring GPS2 signal levels on the MFD. 9. Repeat steps 3 through 8 for the No. 2 COM transceiver. 10. On the MFD, select AUX page 5. 11. Under the COM CONFIG field, change the COM channel spacing from 25 kHz to 8.33 kHz. 12. Re select AUX page 4 and monitor GPS1 signal strength bars. 13. Select 121.185 MHz on the No. 1 COM transceiver. 14. Transmit for a period of 35 seconds while monitoring GPS1 signal strength levels. 15. During the transmit period, verify that the GPS “INTEG” flag does not come into view on either PFD and verify that GPS1 does not lose a 3-D navigation solution on the MFD. 16. Repeat steps 14 through 15 for each of the following frequencies: • 121.190 MHz • 130.285 MHz • 131.290 MHz 17. Repeat steps 13 through 16 while monitoring GPS2 signal levels on the MFD. 18. Repeat steps 13 through 17 for the No. 2 COM transceiver. 19. On the MFD, select AUX page 5 and return the COM channel spacing to 25 kHz. 3.9 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. 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. Simulate a VOR signal on radial 360°. Verify full scale deflection of the CDI while applying a 10° deviation signal. Exercise the CDI with both right and left deviations for both VOR 1 and VOR 2 receivers. Repeat using a simulated localizer signal. Exercise the Glideslope deviation indicator with up and down deviation indications and verify proper direction of deviation. 3.10 COM Antenna VSWR Checks Check for insertion loss and VSWR (Voltage Standing Wave Ratio). VSWR should be checked with an in-line type VSWR/wattmeter inserted in the coaxial transmission line between the transceiver and the antenna. The VSWR should be inserted as close to the transceiver as possible. Any problem with the antenna installation is most likely seen as high reflected power. A VSWR of 3:1 may result in up to a 50% loss in transmit power. Ideally, the VSWR should be 2.5:1 or less. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-17 190-00682-00 Revision 5 3.11 GTX 33 Testing Operation of the GTX 33 Mode-S transponder is accomplished using PFD1, PFD2 or MFD. Refer to G1000 in Hawker Beechcraft King Air C90A/GT Cockpit Reference Guide, Garmin P/N 190-00664-00, for basic operation. 1. Ensure XPDR NO 1 CB is closed and open XPDR NO2 CB. Ensure XFR on the AFCS mode controller is coupled left as indicated by a left pointing arrow. 2. Using a ramp tester, measure XPDR1 RF power output. Verify a power output of 125 - 500 Watts. 3. Using a ramp tester, measure XPDR1 mode S receiver sensitivity. Verify receiver sensitivity of -74dBm ± 3.0dBm. 4. Using a ramp tester, measure XPDR1 ATCRBS Side Lobe Suppression (SLS) level. Verify reply if P1 exceeds P2 by 9dB or more No reply if P2 equals or exceeds P1. 5. Using a ramp tester, measure XPDR1 ATCRBS reply. Verify replies to interrogations. F1 to F2 spacing, 20.3 μsec. to 0.1 μsec. F1 and F2 pulse width, 0.45 μsec. ± 0.10 μsec. 6. Using a ramp tester, evaluate XPDR1 mode S (tail number) interrogation. Verify proper mode S reply. 7. Using an air data and XPNDR ramp tester, evaluate XPDR1 mode C interrogations. Verify XPDR1 altitude indicates current pressure altitude displayed on PFD1 within +/- 125 ft. 8. On the AFCS mode controller press XFR button to couple to the right as indicated by a right pointing arrow. Verify XPDR1 altitude indicates current pressure altitude displayed on PFD2. 9. On the AFCS mode controller press XFR button to couple to the left as indicated by a left pointing arrow. Press the XPDR softkey on the PFD1. 10. Press the CODE softkey. Verify that a white cursor activates in the transponder squawk code field and begins to blink. 11. Use the large and small FMS knob to enter a transponder code of 1234 and press the ENT key. Verify proper squawk code reply on a ramp tester. 12. Select IDENT on PFD1, PFD2 pilot’s and co-pilots control wheel one at a time. Verify IDENT reply on ramp tester from each IDENT button location. 13. Using a ramp tester, evaluate XPDR1 Squitter. Verify 0.8 to 2.4 seconds. 14. Close XPDR No 2 CB and open XPDR No 1 CB. 15. Repeat steps 2 – 13 utilizing XPNDR No 2. Page 3-18 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 3.12 Pitot Static System Leak Checks With a pitot-static test set connected to the aircraft perform a leak test of the aircraft static plumbing at an altitude of 30,000 ft and airspeed of 120 knots. When static pressure has stabilized, verify and record the cumulative leak rate is 200ft/minute or less. ALTITUDE ft/min: With a pitot-static test set connected to the aircraft perform a leak test of the aircraft pitot plumbing at an altitude of 30,000 ft and airspeed of 226 knots. When pitot pressure has stabilized, verify and record the cumulative leak rate is 1 knot/minute or less. AIRSPEED kts/min: G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-19 190-00682-00 Revision 5 3.13 GDC 74B Testing NOTE Allow the unit to warm up for 15 minutes before performing the following tests. 3.13.1 Preperation for Air Data Validation Test Verification of the altimeter and airspeed must be performed using an air data test set (ADTS). The pitot / static system and altimeter must be verified in accordance with Title 14 of the Code of Federal Regulations (CFR) § 91.411 and Part 43 Appendix E. PFD1 must be in configuration mode and the MFD must be in Reversionary mode to perform the tests as outlined in Part 43 Appendix E. To prepare the G1000 System for Part 43 Appendix E testing: 1. Start the G1000 system in normal mode. 2. Remove power to PFD1 by opening the PFD1 (PRI) and PFD1 (SEC) circuit breakers. 3. Start PFD1 in configuration mode by pressing and holding the PFD1 ENT key while closing PFD1 (PRI) and PFD1 (SEC) circuit breakers. 4. Release the ENT key after “INITIALIZING SYSTEM” appears in the upper left corner of PFD1. CAUTION Configuration mode contains certain pages and settings that are critical to aircraft operation and safety. These pages are protected and cannot be modified, unless the technician is properly authorized and equipped. However, most protected pages are viewable to allow system awareness for troubleshooting. 5. Use the FMS knob on PFD1 to select GRS page group. Use the B ALT 1 and B ALT 2 fields for all CFR Part 43 Appendix E tests for G1000 altitude. 6. Place the MFD in reversionary mode by pressing the red “display backup” button on the GMA1. The Baro setting can then be read from the MFD for the CFR Part 43 Appendix E tests. The Baro setting on the MFD will apply to the values displayed on PFD1 in configuration mode for both ADC1 and ADC2 regardless of the sensor selected on the MFD. The copilot's display can be ignored. Page 3-20 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 3.13.2 Air Data Validation Test 1. Simulate the air speeds shown in the table below. Wait for ADTS to report that target values have been achieved. 2. Verify that computed air speeds shown for ADC1, ADC2 and STBY ALT are within the tolerances specified in the table below: Test Point Altitude Airspeed PFD1 PFD2 STBY PFD1 PFD2 STBY Tolerance Tolerance Tolerance Tolerance Tolerance Tolerance ALT AS Actual Actual Actual Actual Actual Actual +/-20 +/-20 +/-20 N/A N/A N/A 0 N/A +/-20 +/-20 +/-20 +/-2 +/-2 +/-5 -1000 50 +/-20 +/-20 +/-20 +/-2 +/-2 +/-5 500 50 +/-20 +/-20 +/-20 +/-2 +/-2 +/-5 1000 50 +/-25 +/-25 +/-25 +/-2 +/-2 +/-5 1500 50 +/-25 +/-25 +/-30 +/-2 +/-2 +/-5 2000 50 +/-30 +/-30 +/-30 +/-2 +/-2 +/-5 3000 80 +/-35 +/-35 +/-35 +/-2 +/-2 +/-5 4000 80 +/-40 +/-40 +/-40 +/-2 +/-2 +/-5 6000 80 +/-60 +/-60 +/-60 +/-2 +/-2 +/-5 8000 80 +/-30 +/-30 +/-80 +/-2 +/-2 +/-5 10000 120 +/-35 +/-35 +/-85 +/-2 +/-2 +/-5 11000 120 +/-40 +/-40 +/-95 +/-2 +/-2 +/-5 13000 150 +/-40 +/-40 +/-100 +/-2 +/-2 +/-5 14000 150 +/-45 +/-45 +/-110 +/-2 +/-2 +/-5 16000 180 +/-45 +/-45 +/-115 +/-2 +/-2 +/-5 18000 210 +/-50 +/-50 +/-140 +/-2 +/-2 +/-5 20000 210 +/-50 +/-50 +/-180 +/-2 +/-2 +/-5 22000 100 +/-50 +/-50 +/-155 +/-2 +/-2 +/-5 25000 100 +/-50 +/-50 +/-180 +/-2 +/-2 +/-5 31000 100 +/-50 +/-50 +/-170 +/-2 +/-2 +/-5 28000 70 +/-50 +/-50 +/-145 +/-2 +/-2 +/-5 23000 190 +/-60 +/-60 +/-60 +/-2 +/-2 +/-5 8000 226 G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-21 190-00682-00 Revision 5 3. Return PFD1 and MFD to normal mode by pressing the red “DISPLAY BACKUP” button on the GMA1. Return PFD1 to normal mode by cycling power. 3.13.3 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 the table below: Vertical Speed, feet/minute Allowed tolerance, ±feet/minute 2000 100 1000 50 500 45 200 45 0 N/A (No VS Display) -200 45 -500 45 -1000 50 -2000 100 3.13.4 OAT Probe Check Ensure on-side sensors for PFD1 and PFD2. Verify that the outside air temperature (OAT) measurement shown on PFD1 and PFD2 indicates ambient temperature. Page 3-22 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00 3.14 GDL 69A Functional Check NOTE This section verifies correct installation in the aircraft. It does not activate the GDL 69A XM data link radio. If the XM Radio is activated, the channel list will contain more channels than the three that are shown for a radio that has not been activated. Complete instructions for activating the XM data link can be found in document 190-00355-04 “GDL 69/69A XM Satellite Radio Activation Instructions”. 1. Select the AUX – XM RADIO page on the MFD. 2. Verify that you can increment and decrement the channels (the whit