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

Operating procedures, techniques, etc., which is considered essential to emphasize. WARNING Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 8 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 Reference Documents ICAO Flight Plan Code Notes RNAV 10 (RNP 10) (Oceanic) FAA Order 8400.12C A1 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 later approved version. This does not constitute an operational approval. Part 91, Part 91 subpart K, 121, 125, and 135 operators require operational approval. B-RNAV/ RNAV 5 (Europe) FAA AC 90-96A CHG 1, EASA AMC 20-4 B2 This does not constitute an operational approval. RNAV 2 FAA AC 90-100A C2 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. RNAV 1 FAA AC 90-100A D2 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 9 of 179 Specification Reference Documents ICAO Flight Plan Code Notes P-RNAV (Europe) FAA AC 90-96A CHG 1, JAA TGL 10 Rev 1 D2 This does not constitute an operational approval. RNP 4 (Oceanic) FAA Order 8400.33 L1 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. 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. RNP 1 FAA AC 90-105 O2 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. 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. RNP APCH LNAV minima FAA AC 90-105, EASA AMC 20-27 S1 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 (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. RNP APCH LNAV/VNAV minima FAA AC 90-105, EASA AMC 20-27 with CM-AS-002 S2 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 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 10 of 179 Specification Reference Documents ICAO Flight Plan Code Notes RNP APCH LP minima FAA AC 90-107 N/A 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. RNP APCH LPV minima FAA AC 90-107, EASA AMC 20-28 N/A 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. 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”. Navigation information is referenced to the WGS-84 reference system. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 11 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 12 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 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 13 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 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 14 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 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 15 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 MMO Maximum operation limit speed in mach 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 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 16 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 17 of 179 VMO 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 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 18 of 179 This page intentionally left blank. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 19 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 20 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 PT6A-41 ENGINES COLOR MARKINGS & RANGES Red Arc/Radial (Minimum Limit) Yellow Arc (Caution) Green Arc (Normal) Yellow Arc (Caution) Red Arc/Radial (Maximum Limit) 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. 60 60 to 105 105 to 135 -- 135 (6)(7) 21,000’ MSL and above 60 to 85 85 to 135 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 21 of 179 OPERATING PARAMETER PT6A-42 ENGINES COLOR MARKINGS & RANGES Red Arc/Radial (Minimum Limit) Yellow Arc (Caution) Green Arc (Normal) Yellow Arc (Caution) Red Arc/Radial (Maximum Limit) 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. 60 60 to 100 100 to 135 -- 135 (6)(7) 21,000’ MSL and above 60 to 85 85 to 135 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 22 of 179 OPERATING PARAMETER PT6A-52 ENGINES COLOR MARKINGS & RANGES Red Arc/Radial (Minimum Limit) Yellow Arc (Caution) Green Arc (Normal) Yellow Arc (Caution) Red Arc/Radial (Maximum Limit) 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. 60 60 to 90 90 to 135 -- 135 (6)(7) 21,000’ MSL and above 60 to 85 85 to 135 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 23 of 179 OPERATING PARAMETER PT6A-61 ENGINES COLOR MARKINGS & RANGES Red Arc/Radial (Minimum Limit) Yellow Arc (Caution) Green Arc (Normal) Yellow Arc (Caution) Red Arc/Radial (Maximum Limit) 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. 60 60 to 90 90 to 135 -- 135 (6)(7) 21,000’ MSL and above 60 to 85 85 to 135 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 24 of 179 PROPELLER TYPES AND INDICATOR MARKINGS Manufacturer Hartzell Hartzell Hartzell Hartzell McCauley McCauley Hub HC-B3TN-3G or -3N HC-D4N-3A HC-E4N-3G HC–E4N-3A 3GFR34C702 4HFR34C771 4HFR34C754 Blades T10178()-3R D9383K Or D9515K D9390SK-1R NC9208K 100LA-2 94LA-0 Normal Operating Range – RPM (Green Arc) 1600-2000 1150-2000 1180-2000 1180-2000 1600-2000 1100-2000 Maximum Limit – RPM (Red Radial) 2000 2000 2000 2000 2000 2000 Transient Limit - RPM 2200 (1) 2200 (2) 2200 (2) 2200 (1) 2200 (1) 2200 (1) 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 25 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 modified by Garmin service bulletin No. 1375:  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. . Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 26 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 27 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 cycle 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 28 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 be 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, 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 29 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 is 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. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 30 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 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. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 31 of 179 AUTOPILOT OPERATION LIMITS One pilot must remain seated at the controls, with seatbelt fastened, during all autopilot operations. Do not use autopilot or yaw damper during takeoff and landing. The GFC 700 AFCS preflight test must complete successfully prior to use of the autopilot, flight director or manual electric trim. The maximum fuel imbalance with the autopilot engaged is 300 pounds. Minimum speed for autopilot or flight director operation is 100 KIAS. Maximum speed limit for autopilot operation is unchanged from the airplane’s maximum airspeed limit (VMO/M MO). Autopilot coupled ILS, LOC, LP/LPV or LNAV/VNAV approaches with the yaw damper inoperative or not engaged is prohibited. The autopilot must be in ROL mode while switching between MAGNETIC and TRUE navigation angles. For airplanes that have GRS 7800 AHRS installed, the autopilot must be in ROL mode while switching between AHRS DG FREE and DG SLAVE Modes. Do not use autopilot below the following altitudes: 1. On takeoff, do not engage the autopilot below ....................................................... 400 feet AGL 2. Enroute .................................................................................................................... 800 feet AGL 3. Approach (GP or GS mode) .................................................................................... 200 feet AGL 4. Approach (FLC, VS, PIT or ALT mode) .................... Higher of 400 feet AGL or Approach MDA SYNTHETIC VISION AND PATHWAYS LIMITS Use of the Synthetic Vision system display elements alone for aircraft control without reference to the G1000 primary flight instruments or the aircraft standby instruments is prohibited. Use of the Synthetic Vision system alone for navigation, or obstacle or terrain avoidance is prohibited. Use of the SVS traffic display alone to avoid other aircraft is prohibited. For airplanes that have GRS 7800 AHRS installed, use of the Synthetic Vision System is prohibited while operating in DG FREE mode. Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 32 of 179 TAWS, GPWS, AND TERRAIN SYSTEM LIMITS Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with TAWS or GPWS warnings. The TAWS databases have an area of coverage as detailed below: a) The terrain database has an area of coverage from North 90° Latitude to South 90° Latitude in all Longitudes. b) The obstacle database has an area of coverage that includes the United States and Europe. Use of the TAWS for navigation or terrain and/or obstacle avoidance is prohibited. NOTE The area of coverage may be modified, as additional terrain data sources become available. NOTE The TAWS page and terrain display is intended to serve as a situational awareness tool only. It may not provide the accuracy, fidelity, or both, on which to solely base decisions and plan maneuvers to avoid terrain or obstacles. To avoid unwanted alerts, inhibit TAWS and/or GPWS when landing at an airport that is not included in the airport database. 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 Terrain and Obstacle databases. Flight crews and operators can view the LOA statuses and areas of degraded terrain performance by selecting the Type 2 LOA status quick link at www.FlyGarmin.com. When responding to a TAWS “Pull Up” warning, the autopilot must be immediately disconnected and the evasive maneuver hand flown by the pilot. TRAFFIC AVOIDANCE SYSTEM LIMITS Use of the MAP - TRAFFIC MAP, Inset Map traffic display, or the SVS display to maneuver the airplane for traffic avoidance without outside visual reference is prohibited. The Traffic Information System (TIS) or optional Skywatch TAS, Skywatch HP, Honeywell KTA-870, and Garmin GTS 820/850/8000 Traffic Systems are intended as an aid for the pilot to visually locate traffic. It is the responsibility of the pilot to see and manually maneuver the airplane to avoid other traffic. Maneuvers based solely on a traffic advisory (TA) or on information displayed on a traffic display are not authorized. Pilots are authorized to deviate from their current ATC clearance to comply with a TCAS II resolution advisory (RA). When responding to a TCAS RA warning, the autopilot must be immediately disconnected and the evasive maneuver hand flown by the pilot. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 33 of 179 DATA LINK WEATHER (XM OR CONNEXT WEATHER) Datalink weather information displayed by the G1000 system is limited to supplemental use only. XM or Garmin Connext weather data is not a source of official weather information. Use of the NEXRAD, PRECIP, XM LTNG and DL LTNG (Datalink Lightning) data on the MAP – NAVIGATION MAP, MAP – WEATHER DATA LINK (XM) or MAP – WEATHER DATA LINK (CNXT) pages for hazardous weather, e.g., thunderstorm penetration is prohibited. NEXRAD, PRECIP, XM LTNG and DL LTNG information on the MAP – NAVIGATION MAP, MAP – WEATHER DATA LINK (XM), or MAP – WEATHER DATA LINK (CNXT) pages is intended only as an aid to enhance situational awareness of hazardous weather, not penetration. It is the pilot’s responsibility to avoid hazardous weather using official weather data sources and the airplane’s in-flight weather radar. OPTIONAL L3 COMMUNICATIONS AVIONICS SYSTEM WX-500 STORMSCOPE Stormscope lightning information displayed by the G1000 system is limited to supplemental use only. The use of the Stormscope lightning data on the MAP – NAVIGATION MAP and/or MAP – STORMSCOPE page for hazardous weather (thunderstorm) penetration is prohibited. Stormscope lightning data on the MAP - NAVIGATION MAP or MAP – STORMSCOPE page is intended only as an aid to enhance situational awareness of hazardous weather, not penetration. It is the pilot’s responsibility to avoid hazardous weather using official weather data sources and the airplane’s weather radar. PLACARDS On Instrument Panel above the Standby Attitude Indicator: STANDBY ALT/AS ALTITUDE – FEET V MO-KIAS S.L TO 15,000 259 15,000 TO 20,000 236 20,000 TO 25,000 213 25,000 TO 30,000 191 ABOVE 30,000 170 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 34 of 179 KINDS OF OPERATION LIMITS The Hawker Beechcraft model 200, 200C, B200 and B200C is approved for the following types of operations when the required equipment, as shown in the airplane AFM/POH Kinds of Operations Equipment List, supplemented by the Kinds of Operations Equipment List from other applicable Airplane Flight Manual Supplements, and the Kinds of Operations Equipment List contained in this Airplane Flight Manual Supplement, is installed and operable. 1. VFR Day 2. VFR Night 3. IFR Day 4. IFR Night 5. Icing Conditions KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR, day or night IFR, and icing conditions when the required systems and equipment are installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The system and equipment listed must be installed and operable for the particular kind of operation indicated unless: The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) issued by the FAA. Or: An alternate procedure is provided in the Pilots Operating Handbook and FAA Approved Flight Manual for the inoperative state of the listed system or equipment and all limitations are complied with. Numbers in the Kinds of Operations Equipment List refer to quantities required to be operative for the specified condition. The list does not include all equipment that may be required by specific operating rules. It also does not include components obviously required for the airplane to be airworthy such as wings, empennage, engines, etc. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 35 of 179 VFR Day VFR Night IFR Day IFR Night System and/or Equipment Icing Conditions Remarks and/or Exceptions ELECTRICAL POWER Inverter 0 0 0 0 0 Removed by G1000 modification INVERTER Annunciator 0 0 0 0 0 Removed by G1000 modification Standby Battery 0 1 1 1 1 ENGINE INDICATIONS No Changes - Refer to Aircraft Flight Manual ENGINE OIL No Changes - Refer to Aircraft Flight Manual ENVIRONMENTAL No Changes – Refer to Aircraft Flight Manual FIRE PROTECTION No Changes - Refer to Aircraft Flight Manual FLIGHT CONTROLS No Changes - Refer to Aircraft Flight Manual FUEL No Changes - Refer to Aircraft Flight Manual ICE AND RAIN PROTECTION No Changes - Refer to Aircraft Flight Manual LANDING GEAR No Changes - Refer to Aircraft Flight Manual LIGHTS No Changes - Refer to Aircraft Flight Manual NAVIGATION INSTRUMENTS Magnetic Compass 1 1 1 1 1 Outside Air Temperature 1 1 1 1 1 G1000 Integrated Avionics GARMIN G1000 Cockpit Reference Guide 1 1 1 1 1 Autopilot 0 0 1 1 0 Required only for operations in RVSM airspace. A flight director is required at all times when conducting procedures containing Radius-to-Fix (RF) segments. Electronic Stability & Protection (ESP) 0 0 0 0 0 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 36 of 179 VFR Day VFR Night IFR Day IFR Night System and/or Equipment Icing Conditions Remarks and/or Exceptions Yaw Damper 0 0 0 0 0 May be required for flight above a certain altitude. Refer to Aircraft’s POH or AFMS for any installed modifications that affect this requirement. Control Wheel Autopilot Disconnect/Trim Interrupt Switches 1 1 1 1 1 Left side is required. Both sides required for two-crew operation. VHF Communications System 0 0 1 1 1 Or as required by operating regulation. Audio Control Panel 1 1 1 1 1 Pilot's audio panel required for single pilot operation. Both sides required for two-crew operation. Primary Flight Display 2 2 2 2 2 Multi Function Display 1 1 1 1 1 Air Data Computer 2 2 2 2 2 Attitude/Heading Reference System (AHRS) 2 2 2 2 2 Standby Attitude Indicator 0 0 1 1 1 Standby Altimeter 1 1 1 1 1 Standby Airspeed Indicator 1 1 1 1 1 ATC Transponder 0 0 1 1 1 Required for RVSM operations, or as required by operating regulation. VHF Navigation Receiver 0 0 1 1 1 Or as required by operating regulation. GPS/SBAS Receiver 1 1 2 2 2 Or as required by operating regulation. Automatic Direction Finder (ADF) 0 0 0 0 0 Or as required by operating regulation. Distance Measuring Equipment (DME) 0 0 0 0 0 Or as required by operating regulation. Radar (Radio) Altimeter 0 0 0 0 0 Or as required by operating regulation. Marker Beacon Receiver 0 0 0 0 0 Or as required by operating regulation. Traffic Collision Avoidance System (TCAS I or II) 0 0 0 0 0 Or as required by operating regulation. Terrain Awareness and Warning System (TAWS) 0 0 0 0 0 Or as required by operating regulation. Ground Proximity Warning System (GPWS) 0 0 0 0 0 Or as required by operating regulation. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 37 of 179 VFR Day VFR Night IFR Day IFR Night System and/or Equipment Icing Conditions Remarks and/or Exceptions Weather Radar 0 0 0 0 0 Or as required by operating regulation. XM or Connext Datalink Weather GSR 56 Satellite Receiver 0 0 0 0 0 0 0 0 0 0 GDU Cooling Fans (3 total) 2 2 2 2 2 For aircraft with G1000 systems installed per Garmin drawing 005-00421-00 Revision 15 or previous and not modified by Garmin service bulletin No. 1375, all fans are required if OAT is above 41°C (106°F) and cabin air conditioning is inoperative. GIA Cooling Fans (2 total) 0 0 0 0 0 For aircraft with G1000 systems installed per Garmin drawing 005-00421-00 Revision 15 or previous and not modified by Garmin service bulletin No. 1375, both fans are required if OAT is above 42°C (107°F). RNAV Operations Equipment and Components GPS/SBAS receiver with GPS Software 3.2 or later approved version **Note 1, 2 GDU 104X Display (PFD) GDU 1500 Display (MFD) GA36 antenna GA37 antenna 1 2 1 1 1 1 2 1 1 1 2 2 1 1 1 2 2 1 1 1 2 2 1 1 1 Equipment and components required for RNAV 2, RNAV 1, B-RNAV/RNAV 5, P-RNAV, Class II navigation, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival Routes (STARs), and enroute RNAV “q” and RNAV “T” routes, and “GPS”, “or GPS”, “RNAV (GPS)”, and RNAV (GNSS) Instrument approach operations NOTE 1: Some approaches require two functioning GPS/SBAS receivers. NOTE 2: If only one is required, and only one is operative, it must be #1. OXYGEN No Changes - Refer to Aircraft Flight Manual PROPELLER No Changes - Refer to Aircraft’s POH or AFMS for any installed modifications VACUUM SYSTEM Gyro Suction Gage 0 0 0 0 1 Instrument Air System 0 0 0 0 1 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 38 of 179 This page intentionally left blank. 190-00915-02 Rev. 7 Hawker Beechcraft 200, 200C, B200, B200C, FAA APPROVED B200GT and B200CGT King Air Page 39 of 179 Section 3 - Emergency Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEM ................................................................ 40 AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY..................................................................... 40 MANUAL AUTOPILOT DISCONNECT .................................................................................................. 41 AUTOPILOT ABNORMAL DISCONNECT ............................................................................................. 41 AUTOPILOT FAILURE ........................................................................................................................... 42 PITCH AXIS FAILURE ............................................................................................................................ 42 ROLL AXIS FAILURE ............................................................................................................................. 43 YAW AXIS FAILURE .............................................................................................................................. 44 (Amber annunciator on PFD) ........................................................................... 44 PITCH TRIM FAILURE ........................................................................................................................... 44 AUTOPILOT PRE-FLIGHT TEST FAIL .................................................................................................. 45 OVERSPEED RECOVERY ..................................................................................................................... 45 AUTOPILOT UNDERSPEED PROTECTION ACTIVATION AND RECOVERY (ESP-Equipped Aircraft Only)........................................................................................................................................................ 46 ENGINE FAILURE .................................................................................................................................. 46 EMERGENCY ENGINE SHUTDOWN .................................................................................................... 46 ENGINE FAILURE IN FLIGHT ............................................................................................................... 46 ELECTRICAL SYSTEM ................................................................................................ 47 DUAL GENERATOR FAILURE [L DC GEN] [R DC GEN] .................................................................... 47 TAWS AND GPWS ....................................................................................................... 49 TAWS OR GPWS WARNING ................................................................................................................. 49 TCAS II ......................................................................................................................... 50 TCAS II RESOLUTION ADVISORY ....................................................................................................... 50 WINDSHEAR ENCOUNTER ........................................................................................ 52 ESP ENGAGEMENT .................................................................................................... 52 Hawker Beechcraft 200, 200C, B200, B200C, 190-00915-02 Rev. 7 B200GT and B200CGT King Air FAA APPROVED Page 40 of 179 Bolded checklist steps in the EMERGENCY PROCEDURES section indicate pilot memory action items. The pilot shall perform these items without reference to the checklist in this section. AUTOMATIC FLIGHT CONTROL SYSTEM AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY These procedures supersede the airplane’s UNSCHEDULED ELECTRIC ELEVATOR TRIM ACTIVATION AFM checklist items. If the airplane deviates unexpectedly from the planned flight path: 1. Control Wheel ............................................................................................................ GRIP FIRMLY 2. AP/YD DISC / TRIM INTRPT Button ................................................................ PRESS AND HOLD (Be prepared for high elevator control forces) 3. Aircraft Attitude ......................................................... MAINTAIN/REGAIN AIRCRAFT CONTROL use standby attitude indicator if necessary NOTE Do not release the AP/YD DISC / TRIM INTRPT Button until after pulling the AFCS SERVO Circuit Breaker. 4. Elevator Trim ........................................................ RE-TRIM if necessary using Elevator Tab Wheel 5. AFCS SERVOS Circuit Breaker ................................................................................................ PULL (Right circuit breaker panel) NOTE Pulling the AFCS SERVOS circuit breaker will render the autopilot and yaw damper systems inoperative. 6. AP/YD DISC / TRIM INTRPT Button ................................................................................ RELEASE IN FLIGHT, DO NOT OVERPOWER THE AUTOPILOT. THE TRIM WILL OPERATE IN THE DIRECTION OPPOSING THE OVERPOWER FORCE, WHICH WILL RESULT IN LARGE OUT-OF-TRIM FORCES. DO NOT ATTEMPT TO RE-ENGAGE THE AUTOPILOT OR USE MANUAL ELECTRIC PITCH TRIM UNTIL THE CAUSE OF THE MALFUNCTION HAS BEEN CORRECTED. WARNING