Page 2 - Hawker Beechcraft C90A and C90GT King Air; Garmin Ltd. or its subsidiaries; Street
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 2 of 95 © Copyright 2007 - 2008 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage...
Page 3 - Garmin International, Inc; Supplement for
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 3 of 95 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 C90A and C90GT King Air Aircr...
Page 5 - Table of Contents
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 5 of 95 Table of Contents Section 1 – General (Not FAA Approved).................................................................... 7 Section 2 – Limitations (FAA Approved) ..............................................................
Page 7 - OPERATIONAL APPROVALS; G1000 GPS/SBAS NAVIGATION SYSTEM
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 7 of 95 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 i...
Page 8 - NOTE; ELECTRONIC FLIGHT BAG
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 8 of 95 North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace per AC 91-49 and AC 120-33. Both GPS/SBAS receivers are required to be operating and receiving usable signals except for routes requiring on...
Page 9 - Section 2 - Limitations
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air FAA APPROVED Page 9 of 95 Section 2 - Limitations INTRODUCTION The G1000 Cockpit Reference Guide for Hawker Beechcraft C90A/GT (CRG) must be immediately available to the flight crew. Use the G1000 Cockpit Reference Guide for Hawker Beechc...
Page 10 - SBAS AUGMENTED GPS SYSTEM LIMITATIONS
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 10 of 95 FAA APPROVED GIA1 SERVICE GMA1 SERVICE GIA2 SERVICE GMA2 SERVICE MFD SERVICE GEO LIMITS Do not take off if MFD FAN FAIL is displayed in the ALERTS window AND the Outside Air Temperature is greater than 33 O C (91 O F). Do no...
Page 11 - FAA APPROVED; crew must ensure that the planned approach is in the database.
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air FAA APPROVED Page 11 of 95 crew must ensure that the planned approach is in the database. RNP operations are not authorized except as noted in the Operational Approvals section. When an approach being flown requires a course reversal and ...
Page 12 - AHRS AREAS OF OPERATION; TAWS AND TERRAIN SYSTEM LIMITS
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 12 of 95 FAA APPROVED AHRS AREAS OF OPERATION Flight operations with the G1000 Integrated Avionics installed are prohibited north of 70° North latitude or south of 70° South Latitude due to unsuitability of the magnetic fields near t...
Page 14 - On Instrument Panel above the Standby Attitude Indicator:
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 14 of 95 FAA APPROVED PLACARDS On some aircraft, placards “On Instrument Panel Adjacent to Each Gyroscopic Instrument (Except for Flight Director)” were installed to identify the power source for the instrument (ref. AFM limitations ...
Page 18 - This page intentionally left blank.
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 18 of 95 FAA APPROVED This page intentionally left blank.
Page 19 - Section 3 - Emergency Procedures
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 19 of 95 Section 3 - Emergency Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEM ................................................................ 20 AUTOPILOT MALFUNCTION / ELEVATOR TRIM RUNAWAY ..............................
Page 20 - AUTOMATIC FLIGHT CONTROL SYSTEM; AUTOPILOT MALFUNCTION / ELEVATOR TRIM RUNAWAY; (Be prepared for possible high elevator control forces)
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 20 of 95 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...
Page 21 - MANUAL AUTOPILOT DISCONNECT; annunciator on PFD)
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 21 of 95 MANUAL AUTOPILOT DISCONNECT If necessary, the autopilot can be manually disconnected using any one of the following methods. 1. AP/YD DISC / TRIM INTRPT Button ............................................................ PRE...
Page 22 - ROLL AXIS FAILURE; YAW AXIS FAILURE; AUTOPILOT PRE-FLIGHT TEST FAIL
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 22 of 95 ROLL AXIS FAILURE (Red annunciator on PFD) • Indicates a failure of the roll axis of the autopilot. The autopilot will be inoperative. YAW AXIS FAILURE (Red annunciator on PFD) • Indicates a failure of the yaw axis of the au...
Page 23 - AUTOPILOT OVERSPEED RECOVERY; When overspeed condition is corrected:; Engine Failure Procedure in; POWER AND CONFIGURATION CHANGES; ELECTRICAL SYSTEM; If Left Generator Will Not Reset:
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 23 of 95 AUTOPILOT OVERSPEED RECOVERY (Yellow MAXSPD on PFD) 1. Throttle ............................................................................................................................... REDUCE When overspeed condition ...
Page 24 - If Neither Generator Will Reset:
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 24 of 95 If Neither Generator Will Reset: 7. Avoid IFR conditions if possible and LAND AT THE NEAREST SUITABLE AIRPORT. 8. Standby Battery Switch ............................................................................... INDICAT...
Page 25 - TAWS; TAWS WARNING; on PFD and aural “PULL UP”); ALLOWABLE; After Warning Ceases
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 25 of 95 TAWS TAWS WARNING (Red on PFD and aural “PULL UP”) 1. AP/YD DISC / TRIM INTRPT Button ............................................. PRESS and RELEASE (To disconnect the autopilot) 2. Aircraft Attitude ..........................
Page 27 - Section 3A - Abnormal Procedures
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 27 of 95 Section 3A - Abnormal Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEM ................................................................ 29 AILERON MISTRIM ............................................................
Page 29 - AILERON MISTRIM; or; ELECTRIC PITCH TRIM INOPERATIVE
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 29 of 95 AUTOMATIC FLIGHT CONTROL SYSTEM AILERON MISTRIM (amber or annunciation on PFD) Indicates a mistrim of the ailerons while the autopilot is engaged. The autopilot cannot trim the airplane in roll. During large changes in airsp...
Page 30 - IF STILL INOPERATIVE; IF OPERATIVE; ELEVATOR MISTRIM
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 30 of 95 IF STILL INOPERATIVE • Pitch Trim ............................................................. MANUALLY TRIM AIRPLANE IN PITCH (Using Elevator Tab Wheel) NOTE Autopilot and yaw damper may also be inoperative. IF OPERATIVE •...
Page 31 - RUDDER MISTRIM
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 31 of 95 RUDDER MISTRIM (amber or annunciation on PFD) Indicates a mistrim of the rudder while the autopilot is engaged. During large changes in airspeed, engine failure, or single engine operation, illumination of this message may o...
Page 32 - FLASHING AMBER MODE ANNUNCIATION; mode; YAW DAMPER AUTOMATIC DISCONNECT
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 32 of 95 FLASHING AMBER MODE ANNUNCIATION NOTE Abnormal mode transitions (those not initiated by the pilot or by normal sequencing of the AFCS) will be annunciated by flashing the disengaged mode in amber on the PFD. Upon loss of a s...
Page 33 - G1000 INTEGRATED AVIONICS SYSTEM; ALTITUDE MISCOMPARE; correct barometric altimeter setting.; IF PILOT PFD AND STANDBY ALTIMETER AGREE (COPILOT PFD DIFFERS); Softkey; IF COPILOT PFD AND STANDBY ALTIMETER AGREE (PILOT PFD DIFFERS); determining which primary system is most accurate.; WARNING
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 33 of 95 G1000 INTEGRATED AVIONICS SYSTEM ALTITUDE MISCOMPARE This message is displayed when the G1000 detects a difference of 200 feet or greater between the pilot’s and copilot’s altitude information. Refer to the G1000 Cockpit Ref...
Page 34 - IF ABLE TO IDENTIFY ACCURATE ALTITUDE SOURCE; Use SENSOR softkey to select most accurate ADC on both PFD’s; IF UNABLE TO IDENTIFY ACCURATE ALTITUDE SOURCE; Maintain altitudes based on LOWEST indicated altitude.
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 34 of 95 NOTE When comparing indicated altitude to GPS altitude, deviations from standard temperature or pressure can cause indicated altitude to deviate from GPS altitude. These errors are largest at high altitude. Below 10,000 feet...
Page 35 - AIRSPEED MISCOMPARE; annunciator is displayed on both PFDs.; IF PILOT’S AND COPILOT’S ALTITUDE AGREE; Airspeed 120 KIAS MINIMUM on slowest indicator; IF PILOT’S AND COPILOT’S ALTITUDE DO NOT AGREE; PITCH MISCOMPARE
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 35 of 95 AIRSPEED MISCOMPARE This message is displayed when the G1000 detects a difference of 7 KIAS or greater between the pilot’s and copilot’s airspeed indicators (10 KIAS difference during takeoff or landing roll). Refer to the G...
Page 36 - ROLL MISCOMPARE; TEMP; Display Unit Failure; PFD FAILURE
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 36 of 95 Reference Guide for additional information. 1. Refer to STANDBY ATTITUDE indicator to determine which AHRS is providing the most accurate data. 2. Use SENSOR softkey to select the most accurate AHRS on the affected PFD. ROLL...
Page 37 - Audio; Engine data will be displayed on both PFDs
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 37 of 95 side PFD and the standby flight instruments for information to fly the airplane. If only individual elements of the display are failed, refer to appropriate procedures for the individual failures. To display a composite disp...
Page 39 - GPS APPROACH ALARM LIMITS EXCEEDED
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 39 of 95 • The airplane symbol is removed from all maps. The map will remain centered at the last known position. “NO GPS POSITION” will be annunciated in the center of the map. GPS APPROACH ALARM LIMITS EXCEEDED During a GPS LPV, LN...
Page 40 - IF BOTH SIDES; Land as soon as practical; IF ONE SIDE ONLY; “BOTH ON ADC 2” annunciated on both PFDs.; FAILED ATTITUDE AND/OR HEADING
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 40 of 95 FAILED AIRSPEED, ALTITUDE, AND/OR VERTICAL SPEED (RED "X" ON PFD AIRSPEED, ALTITUDE, AND/OR VERTICAL SPEED INDICATORS) This indicates a loss of valid air data computer information to the respective system. ¾ IF BOTH ...
Page 42 - ENGINE INDICATION SYSTEM (EIS) FAILURE; IF ALL ENGINE GAUGES ON ONE ENGINE RED ‘X’:; Indicates failure of the GEA for that engine; INACCURATE FLIGHT DIRECTOR DISPLAY; If unable to restore Flight Director:
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 42 of 95 ENGINE INDICATION SYSTEM (EIS) FAILURE (RED 'X' ON ENGINE DISPLAY) ¾ IF ALL ENGINE GAUGES ON ONE ENGINE RED ‘X’: Indicates failure of the GEA for that engine 1. Check ENG INST circuit breaker ...................................
Page 43 - BOTH ON ADC1, BOTH ON ADC2; message clears on both PFDs.; BOTH ON AHRS 1, BOTH ON AHRS 2; message clears on both PFDs; BOTH ON GPS 1, BOTH ON GPS 2
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 43 of 95 BOTH ON ADC1, BOTH ON ADC2 This message is displayed on both PFDs and indicates that both pilot and copilot PFDs are displaying data from the same Air Data Computer. Normally the pilot’s side displays ADC 1 information and t...
Page 44 - XSIDE ADC; XSIDE AHRS; PFD
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 44 of 95 XSIDE ADC This message is displayed on both PFDs and indicates that both PFDs are displaying data from the opposite side Air Data Computer. Normally the pilot’s side displays ADC 1 and the copilot’s side displays ADC 2. Refe...
Page 45 - TAWS ABNORMAL PROCEDURES; TAWS CAUTION; TO ENABLE TAWS IF INHIBITED:; Display the MAP – TAWS page
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 45 of 95 TAWS ABNORMAL PROCEDURES TAWS CAUTION When a TAWS CAUTION occurs, take positive corrective action until the alert ceases. Stop descending or initiate either a climb or a turn, or both, as necessary, based on analysis of all ...
Page 47 - Section 4 - Normal Procedures
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 47 of 95 Section 4 - Normal Procedures Table of Contents COM RADIO COMMUNICATIONS BEFORE STARTING ENGINES........................... 49 BEFORE STARTING ....................................................................................
Page 52 - ON TAKEOFF ROLL
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 52 of 95 • Pilot’s Trim Override.................................................................................................... CHECK Activate the copilot’s Pitch Trim Switches nose down. Verify elevator tab wheel is moving nose...
Page 53 - AUTOPILOT OPERATION
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 53 of 95 AUTOPILOT OPERATION Autopilot/Flight Director mode annunciations on the PFDs displayed in green indicate active autopilot/flight director modes. Annunciations displayed in white indicate armed autopilot/flight director modes...
Page 54 - VNAV Descent; to the vertical clearance limit.
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 54 of 95 Altitude Hold (ALT) Mode, Manual Capture: 1. At the desired altitude ................................................... PRESS ALT Button on Mode Controller 2. Green ‘ALT’........................................................
Page 55 - Vertical DIRECT TO; To descend from the present position to a waypoint:; Lateral Modes; From the DIRECT TO page, activate DIRECT TO a waypoint.
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 55 of 95 Vertical DIRECT TO To descend from the present position to a waypoint: 1. Altitude Preselect............................................................................................................. RESET 2. VNV Button .....
Page 57 - ILS; IF Flying Full Approach Including Transition; Or
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 57 of 95 ILS 1. Load the approach into the Active Flight Plan .................................... VERIFY the G1000 tunes the proper ILS frequency 2. Approach Minimums ....................................................................
Page 62 - VOR APPROACH
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 62 of 95 7. Level airplane in ALT mode at MDA.............................. PRESS NAV button 200 ft above MDA If airplane is descending via GP, GP will extinguish and PIT mode will be active and airplane will capture MDA. 8. AFTER LE...
Page 65 - At an appropriate safe altitude:; Recommended procedures following a missed approach
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 65 of 95 GO AROUND (GA) 1. Control Wheel ................................................................................................... GRASP FIRMLY 2. GO AROUND button (left throttle) .......................................... ...
Page 67 - Section 5 - Performance
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 67 of 95 Section 5 - Performance No Change. Refer to basic Aircraft Flight Manual or appropriate supplement. Section 6 - Weight and Balance No Change. Refer to basic Aircraft Flight Manual or appropriate supplement
Page 69 - Section 7 - Systems Description; Table of contents
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 69 of 95 Section 7 - Systems Description Table of contents GENERAL..................................................................................................................... 70 G1000 INTEGRATED AVIONICS .......................
Page 70 - GENERAL; SYSTEM OVERVIEW
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 70 of 95 GENERAL This section supplements the Systems Description chapter in the airplanes original Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. This section will follow the format and layout of the chapter in ...
Page 71 - Figure 1, Instrument Panel
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 71 of 95 Figure 1, Instrument Panel
Page 73 - Figure 3, Copilot's Control Wheel With Trim Switches
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 73 of 95 Figure 3, Copilot's Control Wheel With Trim Switches
Page 74 - Figure 4, Copilot's Control Wheel Without Trim Switches
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 74 of 95 Figure 4, Copilot's Control Wheel Without Trim Switches
Page 75 - Figure 5, Overhead Light Control Panel
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 75 of 95 Figure 5, Overhead Light Control Panel
Page 76 - Figure 6, Left Side Circuit Breaker Panel
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 76 of 95 Figure 6, Left Side Circuit Breaker Panel
Page 80 - Figure 10, GFC 700 System Interface
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 80 of 95 Figure 10, GFC 700 System Interface
Page 81 - FLIGHT CONTROLS; AFCS, AUTOPILOT AND FLIGHT DIRECTOR
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 81 of 95 FLIGHT CONTROLS AFCS, AUTOPILOT AND FLIGHT DIRECTOR The GFC 700 is a digital Automatic Flight Control System (AFCS), fully integrated within the G1000 System avionics architecture. The GFC 700 is a three axis autopilot and f...
Page 83 - AFCS LATERAL MODES
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 83 of 95 AFCS LATERAL MODES Lateral Mode Control Annunciation Maximum Roll Command Limit Roll Mode (default) ROL 25 O Left Bank 25 O Right Bank Low Bank BANK Key * 15 O Left Bank 15 O Right Bank Heading Select HDG Key HDG 25 O Left B...
Page 84 - ELECTRIC ELEVATOR TRIM
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 84 of 95 ELECTRIC ELEVATOR TRIM The electric elevator trim is standard with the G1000 system installation. The electric elevator trim can be operated manually by the pilot using the pitch trim switches on the control wheel, or, autom...
Page 85 - FLIGHT INSTRUMENTS; STANDBY FLIGHT INSTRUMENTS; Figure 12, Standby Flight Instruments
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 85 of 95 FLIGHT INSTRUMENTS G1000 FLIGHT INSTRUMENTS The flight instruments are an integrated part of the G1000 system. For system descriptions, operating instructions, and abnormal failure indication refer to the Cockpit Reference G...
Page 86 - ENGINE INSTRUMENTATION; ) operation is monitored by the gas generator
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 86 of 95 ENGINE INSTRUMENTATION Engine instruments, located in a window on the left side of the MFD, are grouped according to their function. The G1000 engine gauges are constructed and arranged to emulate the mechanical gauges they ...
Page 92 - LIGHTING SYSTEMS; COCKPIT; PITOT AND STATIC SYSTEM; PITOT
Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. C Page 92 of 95 During normal operations, the standby battery is kept in a fully charged state by its own trickle charger powered from the triple-fed bus through the STBY AUX BAT circuit breaker located on the right side circuit breaker pan...
Page 93 - STATIC; Ground Communications
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 93 of 95 STATIC The normal static system has two separate sources of static air, one source is connected to the pilot ’ s Air Data Computer (ADC1), and the other source is connected to the copilot ’ s Air Data Computer (ADC2) and the...
Page 95 - Section 8 – Handling, Service, and Maintenance
190-00682-02 Rev. C Hawker Beechcraft C90A and C90GT King Air Page 95 of 95 Section 8 – Handling, Service, and Maintenance Refer to Garmin G1000 Instructions For Continued Airworthiness, P/N 190-00682-01 Rev. A or later FAA approved revision for maintenance requirements for the G1000 system and comp...
