ページ1に含まれる内容の要旨
®
Beechcraft A36/G36
G1000 Pilot’s Guide
®
Integrated Flight Deck
G1000
Pilot’s Guide
Garmin International, Inc.
1200 East 151st Street
Olathe, KS 66062, U.S.A.
p:913.397.8200
f:913.397.8282
Garmin AT, Inc.
2345 Turner Road SE
Salem, OR 97302, U.S.A.
p:503.391.3411
f:503.364.2138
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Houndsdown Business Park
Southampton, SO40 9RB, U.K.
p:44/0870.8501241
f:44/0870.8501251
Garmin Corporation
No. 68, Jangshu 2nd Road
Shijr, Taipei County, Taiwan
B
ページ2に含まれる内容の要旨
SYSTEM OVERVIEW FLIGHT INSTRUMENTS EIS AUDIO PANEL & CNS FLIGHT MANAGEMENT HAZARD AVOIDANCE AFCS ADDITIONAL FEATURES APPENDICES INDEX
ページ3に含まれる内容の要旨
Copyright © 2007-2008 Garmin Ltd. or its subsidiaries. All rights reserved. This manual reflects the operation of System Software version 0464.17 or later for the Beechcraft A36/G36, or System Software version 0858.03 or later for the Beechcraft A36/G36 (WAAS). Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions. Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Tel: 913/397.8200 F
ページ4に含まれる内容の要旨
LIMITED WARRANTY LIMITED WARRANTY This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within this period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts and labor, provided that the customer shall be responsible for any transportation cost. This warranty does not cover failures due to abuse, mis
ページ5に含まれる内容の要旨
WARNINGS, CAUTIONS, AND NOTES WARNING: Navigation and terrain separation must NOT be predicated upon the use of the terrain function. The G1000 Terrain Proximity feature is NOT intended to be used as a primary reference for terrain avoidance and does not relieve the pilot from the responsibility of being aware of surroundings during flight. The Terrain Proximity feature is only to be used as an aid for terrain avoidance and is not certified for use in applications requiring a certified terra
ページ6に含まれる内容の要旨
WARNINGS, CAUTIONS, AND NOTES WARNING: The Garmin G1000, as installed in the Hawker Beechcraft A36/G36 aircraft, has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self- test capability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G1000. It is thus the responsibility of the pilot to detect such an occurrence
ページ7に含まれる内容の要旨
WARNINGS, CAUTIONS, AND NOTES CAUTION: The Garmin G1000 does not contain any user-serviceable parts. Repairs should only be made by an authorized Garmin service center. Unauthorized repairs or modifications could void both the warranty and the pilot’s authority to operate this device under FAA/FCC regulations. NOTE: When using Stormscope, there are several atmospheric phenomena in addition to nearby thunderstorms that can cause isolated discharge points in the strike display mode. However
ページ8に含まれる内容の要旨
REVISION INFORMATION Record of Revisions Part Number Revision Date Page Range Description 190-00595-00 A 10/16/06 All Initial Release 190-00595-01 A 12/21/07 All Updated to GDU SW version 8.10, and added WAAS B 4/08/08 All Change System Software version, update description of two warning messages, and other minor corrections 190-00595-01 Rev. B v Garmin G1000 Pilot’s Guide for the Beechcraft A36/G36
ページ9に含まれる内容の要旨
TABLE OF CONTENTS SECTION 1 SYSTEM OVERVIEW Low Altitude Annunciation (WAAS only) ....................... 75 Minimum Descent Altitude/Decision Height Alerting ...... 76 1.1 System Description ................................................. 1 2.4 Abnormal Operations ........................................... 77 1.2 Line Replaceable Units (LRU) ................................. 2 Abnormal GPS Conditions ........................................... 77 1.3 G1000 Controls .........................
ページ10に含まれる内容の要旨
TABLE OF CONTENTS Split COM ................................................................ 124 Activating a Flight Plan Leg ....................................... 211 Entertainment Inputs ................................................ 125 Inverting a Flight Plan ............................................... 212 Flight Plan Views ...................................................... 213 4.6 Audio Panel Preflight Procedure ....................... 126 Closest Point of FPL ...................
ページ11に含まれる内容の要旨
TABLE OF CONTENTS SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM SECTION 8 ADDITIONAL FEATURES 7.1 AFCS Overview .................................................... 329 8.1 SafeTaxi ................................................................ 377 Additional AFCS Controls .......................................... 331 SafeTaxi Cycle Number and Revision .......................... 380 7.2 Flight Director Operation ................................... 332 8.2 ChartView .............................
ページ12に含まれる内容の要旨
SYSTEM FLIGHT AUDIO PANEL FLIGHT HAZARD ADDITIONAL EIS AFCS APPENDICES INDEX OVERVIEW INSTRUMENTS & cNS MANAGEMENT AVOIDANCE FEATURES SYSTEM OVERVIEW SECTION 1 SYSTEM OVERVIEW 1.1 SYSTEM DESCRIPTION This section provides an overview of the G1000 Integrated Flight Deck as installed in the Beechcraft A36/G36 Bonanza. The G1000 system is an integrated flight control system that presents flight instrumentation, position, navigation, communication, and identification information to the pilot through
ページ13に含まれる内容の要旨
SYSTEM OVERVIEW 1.2 LINE REPLACEABLE UNITS (LRU) • GDU 1040 (1) – The GDU 1040 is configured as a Primary Flight Displays (PFD) that features a 10.4-inch LCD with 1024 x 768 resolution. The display communicates with the MFD and with the #1 GIA 63/63W Integrated Avionics Unit through a High-Speed Data Bus (HSDB) Ethernet connection. • GDU 1043/1045 (1) – The GDU 1043 or GDU 1045 is configured as an MFD that features a 10.4-inch LCD with 1024 x 768 resolution. The display communicates with the
ページ14に含まれる内容の要旨
SYSTEM FLIGHT AUDIO PANEL FLIGHT HAZARD ADDITIONAL EIS AFCS APPENDICES INDEX OVERVIEW INSTRUMENTS & cNS MANAGEMENT AVOIDANCE FEATURES SYSTEM OVERVIEW • GDC 74A (1) – 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 it communicates with the GIA 63(W)s, the displays, and the GRS 77, using an ARINC 429 digital interface (it also interfaces directly with the GTP 59).
ページ15に含まれる内容の要旨
SYSTEM OVERVIEW • GMA 1347 (1) – Integrates NAV/COM digital audio, intercom system and marker beacon controls. This unit also enables the manual control of the display reversionary mode (red DISPLAY BACKUP button) and communicates with the #1 GIA 63(W), using an RS-232 digital interface. • GTX 33 (1) – Solid-state transponder that provides Modes A, C and S capability. The transponder can be controlled from the PFD. The transponder communicates with the GIA 63/63Ws through an RS-232 digital
ページ16に含まれる内容の要旨
SYSTEM FLIGHT AUDIO PANEL FLIGHT HAZARD ADDITIONAL EIS AFCS APPENDICES INDEX OVERVIEW INSTRUMENTS & cNS MANAGEMENT AVOIDANCE FEATURES SYSTEM OVERVIEW GDU 1040 GMA 1347 GDU 1043/1045 Primary Flight Display Audio Panel Multi Function Display Reversionary Reversionary Control Control GDC 74A Air Data Computer OAT No. 1 GIA 63/63W No. 2 GIA 63/63W Airspeed Integrated Avionics Unit Integrated Avionics Unit Altitude Vertical Speed System Inegration Processors System Integration Processors I/O Processo
ページ17に含まれる内容の要旨
SYSTEM OVERVIEW 1.3 G1000 CONTROLS NOTE: The Audio Panel (GMA 1347) and AFCS controls are also described in the CNS & Audio Panel and AFCS sections respectively. The G1000 system controls are located on the PFD and MFD bezels, and the audio panel. The controls for the PFD and MFD are discussed within the following pages of this section. PFD/MFD CONTROLS 1 2 3 4 5 6 7 8 9 17 18 24 13 10 19 25 11 14 20 26 12 15 21 27 22 16 28 23 29 MFD Only Figure 1-2 PFD/MFD Controls 6 Garmin G1000 Pilot’s G
ページ18に含まれる内容の要旨
SYSTEM FLIGHT AUDIO PANEL FLIGHT HAZARD ADDITIONAL EIS AFCS APPENDICES INDEX OVERVIEW INSTRUMENTS & cNS MANAGEMENT AVOIDANCE FEATURES SYSTEM OVERVIEW 1 NAV VOL/ID Knob Turn to control NAV audio volume (shown in the NAV Frequency Box as a percentage) Press to toggle Morse code identifier audio ON/OFF 2 NAV Frequency Trans- Transfers the standby and active NAV frequencies fer Key 3 Turn to tune NAV receiver standby frequencies (large knob for MHz; small for kHz) NAV Knob Press to toggle light blue
ページ19に含まれる内容の要旨
SYSTEM OVERVIEW 16 FMS Knob Press to turn the selection cursor ON/OFF. (Flight Management Data Entry: With cursor ON, turn to enter data in the highlighted field (large knob moves System Knob) cursor location; small knob selects character for highlighted cursor location) Scrolling: When a list of information is too long for the window/box, a scroll bar appears, indicating more items to view. With cursor ON, turn large knob to scroll through the list. Page Selection: Turn knob on MFD to select
ページ20に含まれる内容の要旨
SYSTEM FLIGHT AUDIO PANEL FLIGHT HAZARD ADDITIONAL EIS AFCS APPENDICES INDEX OVERVIEW INSTRUMENTS & cNS MANAGEMENT AVOIDANCE FEATURES SYSTEM OVERVIEW The NAV, CRS/BARO, COM, FMS, and ALT knobs are concentric dual knobs, each having small (inner) and large (outer) control portion. When a portion of the knob is not specified in the text, either may be used. Large (Outer) Knob Small (Inner) Knob Figure 1-3 Dual Concentric Knob The bottom portion of the MFD bezel features 12 softkeys that are des
