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SA01535Wi-D

Garmin SA01535Wi-D Airplane Flight Manual Supplement

© Copyright 2014
GARMIN Ltd. or its subsidiaries
All Rights Reserved
GARMIN International, Inc.
1200 E. 151
st
Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8 B200GT and B200CGT King Air Page 2 of 179
GARMIN International, Inc
Log of Revisions
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual
Supplement for
G1000 Integrated Avionics System and GFC 700 AFCS In Hawker Beechcraft 200,
200C, B200 and B200C King Air Aircraft
REV
NO.
PAGE NO(S)
DESCRIPTION
DATE OF
APPROVAL
1 ALL Original Issue 3/14/2009
2 ALL Change 0985.00 to 0985.01 4/7/2009
3 ALL
4 ALL
Incorporate G1000 enhancement and Class A TAWS information
Incorporate system software
0985.03 from 0985.02
12/14/2009
11/23/2010
Incorporate system software
5 ALL
0985.04 from 0985.03,
05/11/2012
miscellaneous editorial changes
FAA APPROVED
Robert G. Murray,
Lead DAS Administrator
GARMIN International, Inc.
DAS-240087-CE
Robert G. Murray,
ODA STC Unit
Administrator
GARMIN International, Inc.
ODA-240087-CE
Robert G. Murray,
ODA STC Unit
Administrator
GARMIN International, Inc.
ODA-240087-CE
Robert G. Murray,
ODA STC Unit
Administrator
GARMIN International, Inc.
ODA-240087-CE
Robert G. Murray,
ODA STC Unit
Administrator
GARMIN International, Inc.
ODA-240087-CE
Incorporate system software
0985.06, revised AHRS areas of operation, added a VNAV
6 ALL
limitation, revised system temperature limitations, revised TAWS database coverage areas,
11/16/2012
Robert G. Murray,
ODA STC Unit
Administrator
GARMIN International, Inc.
ODA-240087-CE
miscellaneous editorial corrections, repaginated
Incorporate system software
7 ALL
0985.07, revised AHRS areas of operation to account for GRS 7800 installations
2/28/2014
Robert G. Murray,
ODA STC Unit
Administrator
GARMIN International, Inc.
ODA-240087-CE
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 3 of 179
Log of Revisions
(Continued)
REV
NO.
8 ALL
PAGE NO(S)
DESCRIPTION
Revised GRS 7800 AHRS areas of operation
DATE OF
APPROVAL
See Cover See Cover
FAA APPROVED
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8 B200GT and B200CGT King Air Page 4 of 179
Table of Contents
Section 1 - General ........................................................................................................ 7
Section 2 - Limitations ................................................................................................ 19
Section 3 - Emergency Procedures ........................................................................... 38
Section 3A - Abnormal Procedures ........................................................................... 53
Section 4 - Normal Procedures .................................................................................. 85
Section 5 – Performance .......................................................................................... 113
Section 6 - Weight and Balance ............................................................................... 115
Section 7 - Systems Description .............................................................................. 117
Section 8 – Handling, Service, and Maintenance ................................................... 169
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 5 of 179
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Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 6 of 179
Section 1 - General
The information in this supplement is FAA-approved material and must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM) when the airplane has been modified by installation of the GARMIN G1000 Integrated Avionics System and GFC 700 Digital Automatic Flight Guidance System in accordance with GARMIN International, Inc. approved data.
The information in this supplement supersedes or adds to the basic POH/AFM only as set forth below. Users of the manual are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of the airplane.
The GARMIN G1000 system installed in the Hawker Beechcraft 200, 200C, B200 and B200C King Air Aircraft provides a fully integrated Display, Communications, Navigation and Flight Control system. Functions provided by the G1000 system include: Primary Flight Information, Powerplant Monitoring, Navigation, Communication, Traffic Surveillance, TAWS Class A or B, Weather Avoidance, and a three-axis automatic flight control / flight director system with optional Electronic Stability & Protection.
Use of this supplement requires Garmin G1000 system software version 0985.07 or later to be installed in the aircraft. Pilots are advised to carefully review the contents of this revision before operating the airplane.
USE OF THE HANDBOOK
The following definitions apply to WARNINGS, CAUTIONS and NOTES found throughout the handbook:
WARNING
Operating procedures, techniques, etc., which could result in personal injury or loss of life if not carefully followed.
CAUTION
Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed.
NOTE
Operating procedures, techniques, etc., which is considered essential to emphasize.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 7 of 179
OPERATIONAL APPROVALS G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT
APPROVALS
The Garmin G1000 Integrated Avionics GNSS navigation system installed in this airplane is a GPS system with a Satellite Based Augmentation System (SBAS) comprised of two TSO-C145a Class 3 approved Garmin GIA 63Ws, TSO-C146a Class 3 approved Garmin GDU 104X and GDU 1500 Display Units, GARMIN GA36 and GA37 antennas, and GPS software version 3.2 or later approved version. The G1000 GNSS navigation system in this airplane is installed in accordance with AC 20-138C.
The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this airplane complies with the requirements of AC 20-138C and is approved for navigation using GPS and GPS/SBAS (within the coverage of a Satellite Based Augmentation System signals complying with ICAO Annex 10) for IFR en route, terminal area, non-precision approach, and approach procedures with vertical guidance operations.
The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this airplane complies with the equipment, performance, and functional requirements to conduct RNAV and RNP operations in accordance with the following table:
Specification
RNAV 10 (RNP 10) (Oceanic)
B-RNAV/ RNAV 5 (Europe)
RNAV 2
RNAV 1
Reference
Documents
FAA Order
8400.12C
FAA AC 90-96A CHG 1, EASA AMC 20-4
FAA AC 90-100A
FAA AC 90-100A
ICAO Flight
Plan Code
GPS Class II navigation in oceanic and remote navigation without reliance on other long-range navigation systems when used in conjunction with the G1000 WFDE Prediction program, part number 006-A0154-01 (010-G1000-00) or
A1
B2 This does not constitute an operational approval.
C2
D2
later approved version.
This does not constitute an operational approval. Part 91, Part 91 subpart K, 121, 125, and 135 operators require operational approval.
Includes RNAV Q and T routes.
In accordance with AC 90-100A, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-100A are authorized to fly RNAV 2 and RNAV 1 procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval. Includes RNAV terminal departure and arrival procedures.
In accordance with AC 90-100A, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-100A are authorized to fly RNAV 2 and RNAV 1 procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval.
Notes
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 8 of 179
Specification
P-RNAV (Europe)
RNP 4 (Oceanic)
RNP 1
RNP APCH LNAV minima
RNP APCH LNAV/VNAV minima
Reference
Documents
FAA AC 90-96A CHG 1, JAA TGL 10 Rev 1
FAA Order
8400.33
FAA AC 90-105
FAA AC 90-105, EASA AMC 20-27
FAA AC 90-105, EASA AMC 20-27 with CM-AS-002
ICAO Flight
Plan Code
Notes
D2 This does not constitute an operational approval.
Primary means of Class II navigation in oceanic and remote navigation without reliance on other long-range navigation systems when used in conjunction with the G1000 WFDE Prediction program, part number 006-A0154-01 (010-G1000-00) or later approved version.
L1
Additional equipment may be required to obtain operational approval to utilize RNP-4 performance.
This does not constitute an operational approval. Part 91, Part 91 subpart K, 121, 125, and 135 operators require operational approval. Includes RNP terminal departure and arrival procedures. For airplanes that have system software 0985.07 or later installed, this includes procedures with RF (radius to fix) legs.
O2
In accordance with AC 90-105, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-105 are authorized to fly RNP 1 procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval. Includes non-precision approaches based on conventional navigation aids with “or GPS” in the title and area navigation approaches titled “GPS”, “RNAV(GPS)”, and “RNAV(GNSS)”. For airplanes with system software
0985.07 or later installed, this includes procedures with RF
S1
(radius to fix) legs.
In accordance with AC 90-105, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-105 are authorized to fly RNP APCH LNAV minima procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval. Includes area navigation approaches titled “RNAV(GPS)” and “RNAV(GNSS).” For airplanes with system software
0985.07 or later installed, this includes procedures with RF (radius to fix) legs. Vertical guidance is based on GPS/SBAS when within SBAS coverage and by baro VNAV (system software 0985.07 or later) when outside
S2
SBAS coverage.
In accordance with AC 90-105, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-105 are authorized to fly RNP APCH LNAV/VNAV minima procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 9 of 179
Specification
RNP APCH LP minima
RNP APCH LPV minima
Garmin International holds an FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153 for database integrity, quality, and database management practices for the Navigation database. Flight crews and operators can view the LOA status at FlyGarmin.com then select” Type 2 LOA Status”.
Reference
Documents
FAA AC 90-107
FAA AC 90-107, EASA AMC 20-28
ICAO Flight
Plan Code
N/A
N/A
Notes
For airplanes with system software 0985.07 or later installed, this includes area navigation approaches titled “RNAV(GPS)” and “RNAV(GNSS)” including procedures with RF legs. LP minima are available only when within SBAS coverage.
In accordance with AC 90-107, Part 91 operators (except subpart K) following the operational considerations and training guidance in AC 90-107 are authorized to fly RNP APCH LP minima procedures. Part 91 subpart K, 121, 125, 133, 135, and 137 operators require operational approval. Includes area navigation approaches titled “RNAV(GPS)” and “RNAV(GNSS).” For airplanes with system software
0985.07 or later installed, this includes procedures with RF (radius to fix) legs. LPV minima are available only when within SBAS coverage.
In accordance with AC 90-107, Part 91 operators (except subpart K) following the operational considerations and training guidance in AC 90-107 are authorized to fly RNP APCH LPV minima procedures. Part 91 subpart K, 121, 125, 133, 135, and 137 operators require operational approval.
Navigation information is referenced to the WGS-84 reference system.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 10 of 179
ELECTRONIC FLIGHT BAG
The G1000 Integrated Avionics System as installed in this aircraft supports approval of AC 120-76A Hardware Class 3, Software Type B Electronic Flight Bag (EFB) electronic aeronautical chart applications when using current FliteChart or ChartView data. Additional operational approvals may be required. Garmin International holds an FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153 for database integrity, quality, and database management practices for the FliteChart database. Flight crews and operators can view the LOA status by selecting the Type 2 LOA status quick link at www.FlyGarmin.com.
For operations under 14 CFR Part 91, it is suggested that a secondary or back up source of aeronautical information necessary for the flight be available to the pilot in the airplane. The secondary or backup information may be either traditional paper-based material or displayed electronically. If the source of aeronautical information is in electronic format, operators must determine non-interference with the G1000 system and existing aircraft systems for all flight phases.
REDUCED VERTICAL SEPARATION MINIMUMS (RVSM)
This airplane is approved as a group aircraft for operations in Reduced Vertical Separation Minimum (RVSM) airspace when required equipment is maintained with the Hawker Beechcraft Super King Air 200 Series Maintenance Manual and Garmin’s G1000/GFC 700 System Maintenance Manual for the Hawker Beechcraft Model 200/B200 Series King Air.
This does not constitute operational approval. Operational approval must be obtained in accordance with the applicable operating rules.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 11 of 179
ABBREVIATIONS AND TERMINOLOGY
The following glossary is applicable within the airplane flight manual supplement
AC Advisory Circular ADC Air Data Computer ADF Automatic Direction Finder AFCS Automatic Flight Control System AFM Airplane Flight Manual AFMS Airplane Flight Manual Supplement AGL Above Ground Level Ah Amp hour AHRS Attitude and Heading Reference System ALT Altitude, or AFCS altitude hold mode, or ALT button on the GMC 710 AFCS
Mode Controller
ALTS AFCS altitude capture using the altitude in the altitude preselect window ALTV AFCS altitude capture using the altitude from the VNAV profile vertical
constraint
AMMD Airport Moving Map Display AP Autopilot APR AFCS Approach mode, or APR button of GMC 710 AFCS mode controller APTSIGNS Airport Signs (SVS softkey on the PFD) APV Approach with Vertical Guidance ATC Air Traffic Control AUX Auxiliary BANK Low-bank mode of the AFCS BARO Barometric Setting BAT Battery BC Back Course BRNAV Basic Area Navigation BRT Bright CB Circuit Breaker CDI Course Deviation Indicator CFR Code of Federal Regulations CLR Clear COM Communication radio CRG Cockpit Reference Guide CRS Course
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 12 of 179
CWS Control Wheel Steering DA Decision Altitude DC Direct Current DG Directional Gyro DH Decision Height DL LTNG Connext Data Link Lightning DME Distance Measuring Equipment DN Down DR Dead Reckoning EC Error Correction EFB Electronic Flight Bag EIS Engine Indication System ELEC Electrical ENT Enter ESP Electronic Stability and Protection FAF Final Approach Fix FD Flight Director FLC AFCS Flight Level Change mode, or FLC button on the GMC 710 AFCS mode
controller
FLTA Forward Looking Terrain Awareness FMS Flight Management System FPM Flight Path Marker or Feet Per Minute FSB Fasten Seat Belts FSD Full Scale Deflection ft Feet ft-lbs Foot-Pounds ft/min Feet/Minute GA Go-around GCU Garmin Control Unit GDC Garmin Air Data Computer GDL Garmin Data Link Radio GDU Garmin Display Unit GEA Garmin Engine/Airframe Unit GEN Generator GEO Geographic GFC Garmin Flight Control GIA Garmin Integrated Avionics Unit
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 13 of 179
GMA Garmin Audio Panel System GMC Garmin Mode Control Unit GP GPS Glide Path GPS Global Positioning System GPWS Ground Proximity Warning System GRS Garmin Reference System (AHRS) GS Glide Slope GSR Garmin Iridium Satellite Radio GTS Garmin Traffic System GWX Garmin Weather Radar HDG AFCS heading mode or the HDG button on the GMC 710 AFCS Mode
Controller
HITS Highway in the Sky HPa Hectopascal HSI Horizontal Situation Indicator IAF Initial Approach Fix IAP Instrument Approach Procedure IAS Indicated Airspeed ICAO International Civil Aviation Organization IFR Instrument Flight Rules ILS Instrument Landing System IMC Instrument Meteorological Conditions in-Hg inches of mercury INH Inhibit ITT Interstage Turbine Temperature KIAS Knots Indicated Air Speed Kt(s) Knot(s) LCD Liquid Crystal Display LDA Localizer Type Directional Aid LNAV Lateral Navigation LNAV + V Lateral Navigation with Advisory Vertical Guidance LNAV/VNAV Lateral Navigation / Vertical Navigation LOA Letter of Acceptance LOC Localizer LOI Loss of Integrity (GPS) LP Localizer Performance LPV Localizer Performance with Vertical Guidance
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 14 of 179
LRU Line Replaceable Unit LTNG Lightning (XM Weather Product) M Mach MAP Missed Approach Point MAXSPD Maximum Speed, AFCS Overspeed Protection mode Mb Millibars MDA barometric minimum descent altitude MEL Minimum Equipment List MFD Multi Function Display MLS Microwave Landing System M
Maximum operation limit speed in mach
MO
MINSPD Minimum Speed, AFCS Underspeed Protection mode MNPS Minimum Navigational Performance Specifications MSL Mean Sea Level NAT North Atlantic Track NAV Navigation, or AFCS navigation mode, or NAV button on the GMC710 AFCS
Mode Controller
NEXRAD Next Generation Radar (XM Weather Product) NM Nautical Mile NPA Non-precision Approaches OAT Outside Air Temperature OBS Omni Bearing Selector ODP Obstacle Departure Procedure OVR Override P/N Part Number PDA Premature Descent Alert PFD Primary Flight Display PFT Pre-Flight Test PIT AFCS pitch mode POH Pilot’s Operating Handbook PRNAV Precision Area Navigation PROC Procedure button on the GDU or GCU 477 PSI Pounds per Square Inch PTCH Pitch PWR Power RA Radar Altimeter, or Radar Altitude, or TCAS II Resolution Advisory RF Radius-to-Fix
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 15 of 179
RNAV Area Navigation RNP Required Navigation Performance ROL AFCS roll mode RPM Revolutions per Minute RVSM Reduced Vertical Separation Minimums SBAS Satellite Based Augmentation System SDF Simplified Directional Facility SID Standard Instrument Departure SPD Speed button on the GMC 710 AFCS Mode Controller. Toggles the FLC
speed between Mach and IAS references. STAR Standard Terminal Arrival Route STBY Standby STC Supplemental Type Certificate STD Standard SUSP Suspend SVS Synthetic Vision System SW Software SYN TERR Synthetic Terrain softkey SYN VIS Synthetic Vision softkey TA Traffic Advisory TAWS Terrain Awareness and Warning System TCAS Traffic Collision Avoidance System TEMP Temperature TIS Traffic Information System TMR Timer TO Take off TOD Top of Descent TSO Technical Standard Order VAPP AFCS VOR Approach Mode VCO Voice Call Out Vdc Volts DC VDI Vertical Deviation Indicator VDP Visual Descent Point VFR Visual Flight Rules VHF Very High Frequency VMC Visual Meteorological Conditions VMI Vibro-meter Inc.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 16 of 179
V
MO
Maximum operation limit speed in knots
VNAV Vertical Navigation VNV Vertical Navigation button on the GMC 710 AFCS Mode Controller VOR VHF Omni-directional Range VPTH Vertical path VS Vertical Speed WAAS Wide Area Augmentation System WFDE WAAS Fault Detection/Exclusion WGS-84 World Geodetic System – 1984 WSHLD Windshield XFR Transfer button on the GMC 710 AFCS Mode Controller XM XM satellite system XPDR Transponder YD Yaw Damper
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 17 of 179
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Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 18 of 179
Section 2 - Limitations
INTRODUCTION
The G1000 Cockpit Reference Guide for Hawker Beechcraft 200, 200C, B200 and B200C (CRG) must be immediately available to the flight crew during all phases of flight. Use the G1000 Cockpit Reference Guide for Hawker Beechcraft 200/B200 Series, GARMIN part number 190-00929-03, Revision A or later revision when system software 0985.07 is installed.
The System Software Version number is displayed at the top right side of the MFD Power-up page.
AIRSPEED LIMITATIONS AND INDICATOR MARKINGS
No changes were made to the airplane’s airspeed limitations. The airspeed indicators on the Primary Flight Displays (PFDs) and the standby airspeed indicator are marked in accordance with the airplane’s POH/AFM.
A red low speed awareness band is marked on the PFDs in red from 20 – 75 KIAS. The low-speed awareness band is suppressed while the airplane is on the ground. The low-speed awareness band appears in flight two seconds after main gear liftoff.
The standby airspeed indicator is marked in accordance with the airspeed markings called out in the airplane’s AFM/POH. The standby airspeed indicator is not marked with a low speed awareness band.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 19 of 179
POWER PLANT LIMITATIONS AND INDICATOR MARKINGS
No changes were made to the airplane’s engine operating limits. The engine gauges are marked as shown in the following tables. Refer to the latest Airplane Flight Manual or appropriate Airplane Flight Manual Supplement for engine and propeller limitations.
OPERATING
PARAMETER
Torque (ft-lbs) -- -- 0 to 2230 -- 2230 (1)
ITT (ºC) -- -- 400 to 750 -- 750 (2)
Prop N2 (rpm) -- -- (3) -- (3)
Gas Generator N1 (%) -- -- 52 to 101.5 -- 101.5 (4)
Oil Temp. (ºC) -40 (5) -40 to +10 (5) 10 to 99 (5) 99 to 104 (5) 99 (5)
Oil Press. (psi)
Less than 21,000’ MSL.
21,000’ MSL and above
Red Arc/Radial
(Minimum Limit)
PT6A-41 ENGINES COLOR MARKINGS & RANGES
Yellow Arc
(Caution)
60 to 105 105 to 135
60
60 to 85 85 to 135
Green Arc
(Normal)
Yellow Arc
(Caution)
-- 135 (6)(7)
Red Arc/Radial
(Maximum
Limit)
Footnotes:
(1) The maximum transient torque value is 2750 ft-lb for up to 5 seconds. Within this transient
value, the torque indicator will display green digits and a white pointer. After 5 seconds, the digits will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Above 2750 FT-LB, the indication immediately begins flashing for 5 seconds before displaying steady white digits on a red background and a red pointer.
(2) A red diamond at 1000°C represents the upper transient limit for engine Starting Mode. Normally,
the ITT indicator will display green digits and a white pointer. Above 800°C, or when between 750°C and 800°C for more than 5 seconds, (or above 1000°C for more than 5 seconds in Starting Mode), the digital indication will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(3) See PROPELLER TYPES AND INDICATOR MARKINGS table.
(4) The maximum transient N1 value is 102.6% for up to 10 seconds. Within this transient value, the
N1 indicator will display green digits and a white pointer. When between 101.5% and 102.6% for more than 10 seconds, or when above 102.6%, the digital indication will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(5) Above 104°C, or between 99°C and 104°C for more than 5 minutes, the digital indication will flash
alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Below 0°C to -40°C, the digital indication will be black digits on a yellow background. Below -40°C, the digital indication will be white digits on a red background.
(6) Above 135 PSI, or below 60 PSI and decreasing oil pressure, the digital indication will flash
alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(7) A red diamond at 200 psi represents the upper transient limit.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 20 of 179
OPERATING
PARAMETER
Torque (ft-lbs) -- -- 0 to 2230 -- 2230 (1)
ITT (ºC) -- -- 400 to 800 -- 800 (2)
Prop N2 (rpm) -- -- (3) -- (3)
Gas Generator N1 (%) -- -- 61 to 101.5 -- 101.5 (4)
Oil Temp. (ºC) -40 (5) -40 to 0 (5) 0 to 99 (5) 99 to 104 99 (5)
Oil Press. (psi)
Less than 21,000’ MSL.
21,000’ MSL and above
Red Arc/Radial
(Minimum Limit)
PT6A-42 ENGINES COLOR MARKINGS & RANGES
Yellow Arc
(Caution)
60 to 100 100 to 135
60
60 to 85 85 to 135
Green Arc
(Normal)
Yellow Arc
(Caution)
-- 135 (6)(7)
Red Arc/Radial
(Maximum Limit)
Footnotes:
(1) The maximum transient torque value is 2750 ft-lb for up to 5 seconds. Within this transient
value, the torque indicator will display green digits and a white pointer. After 5 seconds, the digits will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Above 2750 FT-LB, the indication immediately begins flashing for 5 seconds before displaying steady white digits on a red background and a red pointer.
(2) A red diamond at 1000°C represents the upper transient limit for engine Starting Mode. The
lower Normal Mode transient limit is 850°C. Within this transient value, the ITT indicator will display green digits and a white pointer. After 20 seconds between 800
°
C and 850°C (or above 1000°C for more than 5 seconds in Starting Mode), the digital indication will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. In Normal Mode while above 850
°
C, the indication immediately begins flashing for 5 seconds before displaying steady
white digits on a red background and a red pointer.
(3) See PROPELLER TYPES AND INDICATOR MARKINGS table.
(4) The maximum transient N1 value is 102.6% for up to 10 seconds. Within this transient value, the
N1 indicator will display green digits and a white pointer. When between 101.5% and 102.6% for more than 10 seconds, or when above 102.6%, the digital indication will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(5) Above 104°C, or between 99°C and 104°C for more than 10 minutes, the digital indication will
flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Below 0°C to -40°C, the digital indication will be black digits on a yellow background. Below
-40°C, the digital indication will be white digits on a red background.
(6) Above 135 PSI, or below 60 PSI and decreasing oil pressure, the digital indication will flash
alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(7) A red diamond at 200 psi represents the upper transient limit.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 21 of 179
OPERATING
PARAMETER
Torque (ft-lbs) -- -- 0 to 2230 -- 2230 (1)
ITT (ºC) -- -- 400 to 820 -- 820 (2)
Prop N2 (rpm) -- -- (3) -- (3)
Gas Generator N1 (%) -- -- 61 to 104 -- 104 (4)
Oil Temp. (ºC) -40 (5) -40 to 0 (5) 0 to 110 (5) -- 110 (5)
Oil Press. (psi)
Less than 21,000’ MSL.
21,000’ MSL and above
Red Arc/Radial
(Minimum Limit)
PT6A-52 ENGINES COLOR MARKINGS & RANGES
Yellow Arc
(Caution)
60 to 90 90 to 135
60
60 to 85 85 to 135
Green Arc
(Normal)
Yellow Arc
(Caution)
-- 135 (6)(7)
Red Arc/Radial
(Maximum Limit)
Footnotes:
(1) The maximum transient torque value is 2750 ft-lb for up to 5 seconds. Within this transient
value, the torque indicator will display green digits and a white pointer. After 5 seconds, the digits will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Above 2750 FT-LB, the indication immediately begins flashing for 5 seconds before displaying steady white digits on a red background and a red pointer.
(2) A red diamond at 1000°C represents the upper transient limit for engine Starting Mode. The
lower Normal Mode transient limit is 850°C. Within this transient value, the ITT indicator will display green digits and a white pointer. After 20 seconds between 820
°
C and 850°C (or above 1000°C for more than 5 seconds in Starting Mode), the ITT digital indication will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. In Normal Mode while above 850
°
C, the indication immediately begins flashing for 5 seconds before displaying steady
white digits on a red background and a red pointer.
(3) See PROPELLER TYPES AND INDICATOR MARKINGS table.
(4) Above 104%, the digital indication will flash alternating red and white background with a flashing
red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red
(5) Above 110°C, the digital indication will flash alternating red and white background with a
flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Below 0°C to -40°C, the digital indication will be black digits on a yellow background. Below -40°C, the digital indication will be white digits on a red background.
(6) Above 135 PSI, or below 60 PSI and decreasing oil pressure, the digital indication will flash
alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(7) A red diamond at 200 psi represents the upper transient limit.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 22 of 179
OPERATING
PARAMETER
Torque (ft-lbs) -- -- 0 to 2230 -- 2230 (1)
ITT (ºC) -- -- 400 to 800 -- 800 (2)
Prop N2 (rpm) -- -- (3) -- (3)
Gas Generator N1 (%) -- -- 61 to 104 -- 104 (4)
Oil Temp. (ºC) -40 (5) -40 to 0 (5) 0 to 110 (5) -- 110 (5)
Oil Press. (psi)
Less than 21,000’ MSL.
21,000’ MSL and above
Red Arc/Radial
(Minimum Limit)
PT6A-61 ENGINES COLOR MARKINGS & RANGES
Yellow Arc
(Caution)
60 to 90 90 to 135
60
60 to 85 85 to 135
Green Arc
(Normal)
Yellow Arc
(Caution)
-- 135 (6)(7)
Red Arc/Radial
(Maximum Limit)
Footnotes:
(1) The maximum transient torque value is 2750 ft-lb for up to 5 seconds. Within this transient
value, the torque indicator will display green digits and a white pointer. After 5 seconds, the digits will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Above 2750 FT-LB, the indication immediately begins flashing for 5 seconds before displaying steady white digits on a red background and a red pointer.
(2) A red diamond at 1000°C represents the upper transient limit for engine Starting Mode. The
lower Normal Mode transient limit is 850°C. Within this transient value, the ITT indicator will display green digits and a white pointer. After 20 seconds between 800
°
C and 850°C (or above 1000°C for more than 5 seconds in Starting Mode), the ITT digital indication will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. In Normal Mode while above 850
°
C, the indication immediately begins flashing for 5 seconds before displaying steady
white digits on a red background and a red pointer.
(3) See PROPELLER TYPES AND INDICATOR MARKINGS table.
(4) Above 104%, the digital N1 indication will flash alternating red and white background with a
flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red
(5) Above 110°C, the digital N1 indication will flash alternating red and white background with a
flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Below 0°C to -40°C, the digital indication will be black digits on a yellow background. Below -40°C, the digital indication will be white digits on a red background.
(6) Above 135 PSI, or below 60 PSI and decreasing oil pressure, the digital indication will flash
alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red.
(7) A red diamond at 200 psi represents the upper transient limit.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 23 of 179
PROPELLER TYPES AND INDICATOR MARKINGS
Manufacturer Hartzell Hartzell Hartzell Hartzell McCauley McCauley
Hub
Blades T10178()-3R
Normal Operating Range – RPM (Green Arc)
Maximum Limit – RPM (Red Radial)
Transient Limit
- RPM
HC-B3TN-3G
or -3N
1600-2000 1150-2000 1180-2000 1180-2000 1600-2000 1100-2000
2000 2000 2000 2000 2000 2000
2200 (1) 2200 (2) 2200 (2) 2200 (1) 2200 (1) 2200 (1)
HC-D4N-3A HC-E4N-3G HC–E4N-3A 3GFR34C702
D9383K
Or
D9515K
D9390SK-1R NC9208K 100LA-2 94LA-0
4HFR34C771 4HFR34C754
Footnotes:
(1) This value is time limited to 5 seconds. Within the transient value, the torque indicator will display
green digits and a white pointer. After 5 seconds, the digits will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Above 2200 RPM, the indication immediately begins flashing for 5 seconds before displaying steady white digits on a red background and a red pointer.
(2) This value is time limited to 20 seconds. Within the transient value, the torque indicator will
display green digits and a white pointer. After 20 seconds, the digits will flash alternating red and white background with a flashing red pointer for 5 seconds. After 5 seconds of flashing, the indication is steady white digits/red background and the pointer is red. Above 2200 RPM, the indication immediately begins flashing for 5 seconds before displaying steady white digits on a red background and a red pointer.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 24 of 179
MANEUVER LIMITS
No changes have been made to the airplane’s maneuver limits. The Hawker Beechcraft Super King Air 200, 200C, B200 and B200C are Normal Category airplanes. Acrobatic maneuvers, including spins, are prohibited.
RVSM OPERATIONS
RVSM operations are prohibited if the static ports are damaged or surface irregularities are found within the RVSM critical region.
The pilot and copilot PFDs must display on-side ADC information during RVSM operations.
G1000 INTEGRATED AVIONICS SYSTEM
Tuning of the COM and NAV radios using the GCU477 controller must be done from the Left seat pilot’s station and only referencing the pilot’s PFD.
Required flight crewmembers must wear and use headsets when the overhead cockpit speaker audio is selected OFF.
Do not take off unless all display units are installed and operational.
Do not take off with any display in reversionary mode.
Do not take off with any of the following messages displayed in the ALERTS window:
GPS1 FAIL and GPS2 FAIL simultaneously PFD1 SERVICE
GPS NAV LOST PFD2 SERVICE
GIA1 SERVICE GMA1 SERVICE
GIA2 SERVICE GMA2 SERVICE
MFD SERVICE GEO LIMITS
The G1000 system must be turned on and operated for at least 30 minutes before takeoff if ground outside air temperature is -40°C (-40°F) or below.
The following temperature limitations apply only to aircraft with G1000 systems installed per Garmin
drawing 005-00421-00 Revision 15 or previous and not
• Do not takeoff if the PFD1 FAN FAIL, PFD2 FAN FAIL or MFD FAN FAIL is displayed in the ALERTS
window AND the Outside Air Temperature is greater than 41°C (106°F) AND cabin air conditioning is
inoperative.
• Do not takeoff if GIA1 FAN FAIL or GIA2 FAN FAIL is displayed in the ALERTS window AND the
Outside Air Temperature is greater than 42°C (107°F).
• Ground operation of the G1000 system is limited to 18 minutes when the Outside Air Temperature is
greater than 47°C (116°F) AND cabin air conditioning is inoperative.
modified by Garmin service bulletin No. 1375:
.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 25 of 179
For airplanes with system software 0985.06 or earlier, use of VNAV is prohibited during the intermediate segment of an approach that includes a teardrop course reversal. VNAV will become ‘Unavailable’ at the beginning of the teardrop segment of the course reversal.
Use of VNAV is prohibited with course changes greater than 90°.
The barometric altimeter must be used as the primary altitude reference for all baro VNAV operations, including instrument approach procedure step-down fixes. Use of baro VNAV to a DA is not authorized with a remote altimeter setting. A current altimeter setting for the landing airport is required. When using remote altimeter minima, the baro VNAV function may be used to the published LNAV MDA.
When a flight is predicated on flying a RNP approach with an RF leg at the destination and/or alternate, the pilot must determine that the AFCS is operational. At a minimum, the flight director must be displayed and utilized when conducting procedures containing Radius-to-Fix (RF) segments.
For airplanes with 0985.07 system software, Vector-to-Final transitions are prohibited for the following approaches:
• CYSB VOR/DME Rwy 12
• NZTH GPS 330
• TTPP ILS Rwy 10
The fuel quantity, fuel required, fuel remaining, and gross weight estimate functions of the G1000 are supplemental information only and must be verified by the flight crew.
Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering. SafeTaxi and Chartview functions do not comply with the requirements of AC 20-159 and are not qualified to be used as an airport moving map display (AMMD). SafeTaxi and Chartview are to be used by the flight crew to orient themselves on the airport surface to improve pilot situational awareness during ground operations.
The use of the colors red and amber within the checklist function has not been evaluated or approved by this STC. Use of the colors red and/or amber within user created checklists may require separate evaluation and approval by the FAA.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 26 of 179
G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM LIMITATIONS
NOTE
Limitations are in bolded text for this section only.
The flight crew must confirm at system initialization that the Navigation database is current. The Navigation database is expected to be current for the duration of the flight. If the AIRAC c ycle will
change during flight, the flight crew must ensure the accuracy of navigation data, including suitability of navigation facilities used to define the routes and procedures for flight. If an amended chart affecting navigation data is published for the procedure, the database must not be used to conduct the procedure.
GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless the flight crew verifies and uses a valid, compatible, and current Navigation database or verifies each waypoint for accuracy by reference to current approved data.
Discrepancies that invalidate a procedure must be reported to Garmin International. The affected procedure is prohibited from being flown using data from the Navigation database until a new Navigation database is installed in the aircraft and verified that the discrepancy has been corrected. Navigation database discrepancies can be reported at FlyGarmin.com then select “Aviation
Data Error Report”. Flight crew and operators can view Navigation data base alerts at FlyGarmin.com then select “NavData Alerts”.
For flight planning purposes, in areas where SBAS coverage is not available, the flight crew must check RAIM availability. Within the United States, RAIM availability can be determined via the
following:
• Using G1000 WFDE Prediction program, part number 006-A0154-01 (010-G1000-00) or later approved version with GARMIN GA36 and GA37 antennas selected.
• Via the FAA’s en route and terminal RAIM prediction website: www.raimprediction.net.
• Contacting a Flight Service Station (not DUATS) to obtain non-precision approach RAIM.
Within Europe, RAIM availability can be determined using the G1000 WFDE Prediction program or Europe’s AUGER GPS RAIM Prediction Tool at http://augur.ecacnav.com/augur/app/home. For other areas, use the G1000 WFDE Prediction program. This requirement is not necessary if SBAS coverage is confirmed to be available along the entire route of flight. The route planning and WFDE prediction program may be downloaded from the GARMIN G1000 website on the internet. For information on using the WFDE Prediction Program, refer to GARMIN WAAS FDE Prediction Program, part number 190-00643-01, ‘WFDE Prediction Program Instructions’.
For flight planning purposes, operations within the U.S. National Airspace System on RNP and RNAV procedures when SBAS signals are not available, the availability of GPS integrity RAIM shall be confirmed for the intended route of flight. In the event of a predicted continuous loss of RAIM of
more than five minutes for any part of the intended route of flight, the flight should be delayed, canceled, or re-routed on a track where RAIM requirements can be met.
For flight planning purposes for operations within European B-RNAV and P-RNAV airspace, if more than one satellite is scheduled to be out of service, then the availability of GPS integrity RAIM shall be confirmed for the intended flight (route and time). In the event of a predicted continuous loss
of RAIM of more than five minutes for any part of the intended flight, the flight should be delayed, canceled, or re-routed on a track where RAIM requirements can be met.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 27 of 179
For flight planning purposes, operations where the route requires Class II navigation the aircraft’s operator or flight crew must use the Garmin WFDE Prediction program to demonstrate that there are no outages on the specified route that would prevent the G1000 from providing primary means of Class II navigation in oceanic and remote areas of operation that requires (RNP-10 or RNP-4) capability. If the Garmin WFDE Prediction program indicates fault exclusion (FDE) is unavailable for
more than 34 minutes in accordance with FAA Order 8400.12C for RNP-10 requirements, or 25 minutes in accordance with FAA Order 8400.33 for RNP-4 requirements, then the operation must be rescheduled when FDE is available.
Both GIA 63W GPS/SBAS receivers must be operating and providing GPS navigation guidance to their respective PFD for operations requiring RNP-4 performance.
North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace operations per AC 91-49 and AC 120-33 require both GIA 63W GPS/SBAS receivers to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor. Each display computes an independent navigation solution based on the on-side GPS sensor. However, either display will automatically revert to the cross-side sensor if the on-side sensor fails or if the cross-side sensor is determined to be more accurate. A “BOTH ON GPS1” or “BOTH ON GPS2” message does not necessarily mean that one GPS has failed. Refer to the MFD AUX-GPS STATUS page to determine the state of the unused GPS.
Manual entry of waypoints using latitude/longitude or place/bearing is prohibited. Whenever
possible, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and en route RNAV “Q” and RNAV “T” routes should be loaded into the flight plan from the database in their entirety, rather than loading route waypoints from the database into the flight plan individually. Selecting and inserting individual named fixes from the database is permitted, provided all fixes along the published route to be flown are inserted.
“GPS”, “or GPS”, “RNAV(GPS)”, or “RNAV(GNSS)” instrument approaches using the G1000 System are prohibited unless the flight crew verifies and uses the current Navigation database. GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Navigation database.
Not all published Instrument Approach Procedures (IAP) are in the Navigation database. Flight crew planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must b e loaded from the Navigation database into the FMS flight plan by its name.
IFR non-precision approach approval using the GPS/SBAS sensor is limited to published approaches within the U.S. National Airspace System. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority.
When operating under instrument flight rules, flight plan selection of any required alternate airport may be based on an RNAV approach. For airplanes with system software 0985.06 or earlier, alternate airport selection must be based upon an LNAV approach or an available ground-based approach for which the aircraft is equipped to fly.
For airplanes that have system software 0985.07 or later installed, alternate airport selection may based upon LNAV, LNAV/VNAV (when baro-VNAV is used), or other available ground-based approaches for which the aircraft is equipped to fly. Alternate planning may include the use of an LNAV MDA(h) for circling or LNAV/VNAV DA(h) when baro-VNAV is active.
The navigation equipment required to join and fly an instrument approach procedure is indicated by the
title of the procedure and notes on the IAP chart. Use of the GARMIN G1000 GPS/SBAS receivers to
provide navigation guidance during the final approach segment of an ILS, LOC, LOC-BC, LDA,
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 28 of 179
SDF, MLS or any other type of approach not approved for “or GPS” navigation is prohibited. When using the G1000 VOR/LOC/GS receivers to fly the final approach segment, VOR/LOC/GS navigation data must be selected and presented on the CDI of the pilot flying.
For airplanes that have system software 0985.07 or later installed, all VNAV altitude constraints must be manually entered by the flight crew. The system will not auto-nominate VNAV altitude constraints.
Navigation information is referenced to WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent.
190-00915-02 Rev. 8 Hawker Beechcraft 200, 200C, B200, B200C,
FAA APPROVED B200GT and B200CGT King Air
Page 29 of 179
AHRS AREAS OF OPERATION
For airplanes that have GRS 77 AHRS installed:
Flight operations with the G1000 Integrated Avionics installed are prohibited in the following regions due to unsuitability of the magnetic fields near the Earth’s poles:
1. North of 72° North latitude at all longitudes
2. South of 70° South latitude at all longitudes
3. North of 65° North latitude between longitude 75° W and 120° W (Northern Canada)
4. North of 70° North latitude between longitude 70° W and 128° W (Northern Canada)
5. North of 70° North latitude between longitude 85° E and 114° E (Northern Russia)
6. South of 55° South latitude between longitude 120° E and 165° E (Region south of Australia and New Zealand)
NOTE
The Garmin G1000 system is not designed for use as a polar navigator and operation outside the approved operating area is prohibited. The GRS-77 AHRS internally monitors the magnetic field and will display a GEO LIMITS system message when the magnetic field becomes unsuitable for AHRS operation. When the AHRS can no longer reliably compute heading, heading information will be removed from the HSI.
For airplanes that have GRS 7800 AHRS installed:
Flight operations in the following regions require heading to be in DG FREE Mode when using system software version 0985.07:
1. North of 72° North latitude at all longitudes
2. North of 65° North latitude between longitude 75° W and 120° W (Northern Canada)
3. North of 70° North latitude between longitude 70° W and 128° W (Northern Canada)
4. North of 70° North latitude between longitude 85° E and 114° E (Northern Russia)
Flight operations with the G1000 Integrated Avionics installed are prohibited in the following regions due to unsuitability of the magnetic fields near the Earth’s poles:
1. North of 84° North latitude at all longitudes
2. South of 70° South latitude at all longitudes
3. South of 55° South latitude between longitude 120° E and 165° E (Region south of Australia and New Zealand)
NOTE
The Garmin G1000 system is not designed for use as a polar navigator and operation outside the approved operating area is prohibited.
Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 8
B200GT and B200CGT King Air FAA APPROVED
Page 30 of 179
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