G1000 TM System Overview for the Beechcraft A36/G36
Record of Revisions Revision Date of Revision Revision Page Range A 7/19/05 ----------- Description Initial release Garmin G1000 System Overview for the Beechcraft A36/G36 190-00571-00 Rev.
SYSTEM OVERVIEW 2.1 INTRODUCTION 2.2 SYSTEM DESCRIPTION This System Overview Pilot’s Guide provides a basic description of the G1000 System as it pertains to the Beechcraft A36/G36. The description includes the Garmin Automatic Flight Control System (AFCS). This section gives a brief description of the G1000 System. A G1000 system block diagram is given in Figure 2.2.1. Refer to the Pilot’s Guide Appendices for LRU specifications.
SYSTEM OVERVIEW • GDU 1040/GDU 1043 – The G1000 features two displays, the GDU 1040 and GDU 1043. The GDU 1040 is a 10.4-inch LCD display with 1024 x 768 resolution and is configured as a Primary Flight Display. The GDU 1040 displays the Flight Director command bars, system annunciations and alerts, pilot-selectable references, and flight information. The GDU 1043 is configured as a Multi Function Display which contains the dedicated AFCS keys and GPS/Navigation controls.
SYSTEM OVERVIEW • GDC 74A – The GDC 74A Air Data Computer processes information from the pitot/static system as well as the outside air temperature (OAT) sensor. The GDC 74A provides pressure altitude, airspeed, vertical speed and OAT information to the G1000 system, and communicates with the GIA 63s, GDU 1040s and GRS 77 using an ARINC 429 digital interface. • GEA 71 – The GEA 71 receives and processes signals from the engine and airframe sensors.
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SYSTEM OVERVIEW 2 1 18 19 20 3 4 6 5 7 8 9 10 Figure 2.3.1 Display Controls (GDU 1043) 28 24 25 11 15 12 16 13 17 21 22 26 23 27 190-00571-00 Rev.
SYSTEM OVERVIEW 2.3 DISPLAY CONTROLS The G1000 controls and keys have been designed to simplify the operation of the system and minimize workload as well as the time required to access sophisticated functionality. The following list provides an overview of the controls located on the display bezel. • (1) Dual ALT Knob – Sets the reference altitude in the box located above the Altimeter. The large knob selects thousands, while the small knob selects hundreds.
SYSTEM OVERVIEW • (14) Dual FMS Knob – Used to select the page to be viewed (only on the MFD). The large knob selects a page group (MAP, WPT, AUX, NRST), while the small knob selects a specific page within the page group. Pressing the small knob turns the selection cursor ON and OFF. When the cursor is ON, data may be entered in the different windows using the small and large knobs.
SYSTEM OVERVIEW Common AFCS Controls 2.4 SECURE DIGITAL CARDS The following controls appear on both the PFD and MFD and perform specific functions for the AFCS: The GDU 1040 data card slots use Secure Digital (SD) cards. SD cards are used for aviation database updates and terrain database storage. • (1) Dual ALT Knob – Sets Selected Altitude, displayed in the Selected Altitude box.
SYSTEM OVERVIEW 2.5 SYSTEM POWER-UP The G1000 system is integrated with the aircraft electrical system and receives power directly from electrical busses. The Garmin G1000 PFD/MFD and supporting sub-systems include both power-on and continuous builtin test features that exercise the processor, RAM, ROM, external inputs and outputs to provide safe operation. While the system begins to initialize, test annunciations are displayed to the pilot at power-up, as shown in the figure below.
SYSTEM OVERVIEW When the MFD powers up, the MFD Power-up Page displays the following information: • • • • • • • System version Copyright Checklist filename Land database name and version Obstacle database name and version Terrain database name and version Aviation database name, version and effective dates When this information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to continue.
SYSTEM OVERVIEW 2.6 DISPLAY BACKLIGHTING 2.7 SYSTEM OPERATION The G1000 PFD and MFD displays use photocell technology to automatically adjust for ambient lighting conditions. Photocell calibration curves are pre-configured to optimize display appearance through a broad range of cockpit lighting conditions. The PFD, MFD, and GMA 1347 bezel/key lighting is typically controlled directly by the existing instrument panel dimmer bus. If desired, the PFD and MFD display backlighting can be adjusted manually.
SYSTEM OVERVIEW Reversionary Mode Should a failure occur in either display, the G1000 automatically enters reversionary mode. In reversionary mode, all important flight information is shown on the remaining display. An example of reversionary mode entry due to a failed PFD is shown in Figure 2.7.2. If a display fails, the GIA 63-GDU 1040 Ethernet interface is cut off. Thus, the GIA can no longer communicate with the remaining display (refer to Figure 2.2.
SYSTEM OVERVIEW AHRS Operation Air Data Input Failure In addition to using internal sensors, the GRS 77 AHRS uses GPS information, magnetic field data and air data to assist in attitude/heading calculations. In normal (primary) mode, the AHRS relies upon GPS and magnetic field measurements. If either of these external measurements is unavailable or invalid, the AHRS uses air data information for attitude determination.
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