Home

Garmin C90A/GT Airplane Flight Manual Supplement

Contents

1. PRESS NAV verify LOC armed Pressing the NAV button will arm the autopilot flight director to capture Localizer and prevent Glideslope from arming or capturing if the glideslope is inoperative or out of service IF Flying Full Approach Including Transition 3 Airplane cleared to an initial approach fix a ACTIVATE THE APPROACH from the PROC page Or ACTIVATE a DIRECT TO P gt the IAF TIE SELECT GPS Nav Source c Mode Control Panel PRESS NAV GPS Mode Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 58 of 95 NOTE Ensure groundspeed is less than 200 KTS within 1 minute of the IAF Airplane will navigate in GPS mode throughout the intermediate portion of the approach procedure When the airplane is inbound towards the final approach course the CDI will automatically switch from GPS SBAS navigation to LOC navigation Oi MERIBEY neci ette attente Course pointer slews to the front course 4 Established inbound on Final Approach Course FAF Active Waypoint a VERIFY Course Pointer is set to the final approach course b VERIFY LOC is annunciated on the HSI 5 Alfs pedd oriin MAINTAIN 110 KIAS OR GREATER Recommended 6 Atthe EAE S tesis Use desired vertical mode to fly the approach s vertical profile Use Altitude Preselect to level off at intermediate altitudes and at the MDA Reco
2. NOTE IF PILOT S AND COPILOT S ALTITUDE AGREE Airspeed 120 KIAS MINIMUM on slowest indicator 4 Monitor all three airspeed indicators during changes in power or altitude to determine which indicators are inaccurate Indications of inaccurate airspeed include e change in indicated airspeed when power change and altitude maintained Indicated airspeed increases when climbing or decreases when descending 5 Use SENSOR softkey to select most accurate ADC on the affected PFDs 6 RESUME NORMAL SPEEDS IF PILOT S AND COPILOT S ALTITUDE DO NOT AGREE 3 Refer to Abnormal Procedures ALT MISCOMP procedure to determine most accurate ADC PITCH MISCOMPARE This message is displayed when the G1000 detects a difference between the pilot s and copilot s pitch attitude displayed in the upper right of the PFD Refer to GARMIN G1000 Cockpit 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 35 of 95 Reference Guide for additional information 1 2 Refer to STANDBY ATTITUDE indicator to determine which AHRS is providing the most accurate data Use SENSOR softkey to select the most accurate AHRS on the affected PFD ROLL MISCOMPARE This message is displayed when the G1000 detects a difference between the pilot s and copilot s roll attitude displayed in the upper right of the PFD Refer to GARMIN G1000 Cockpit Refe
3. seta cvv we vac oboe eee 81 AFCS AUTOPILOT AND FLIGHT DIRECTOR 81 ELECTRIC ELEVATOR TRIM a a z ceo cava a q q h aa k qun 84 FLIGHT INSTRUMENT S 85 G1000 FLIGHT INSTRUMENTS s ses nasa u 85 STANDBY FLIGHT INSTRUMENTS U amena nh nu snas u n saga 85 ENGINE INSTRUMENTATION 86 PROPELLER SYNCHROPHASER 87 ELECTRICAL SYSTEM 87 IINE 87 POWER DISTRIBUTION u l eae aaa e 87 STANDBY BATTERY POWER 91 LIGHTING SYSTENSS 92 eere oin 92 PITOT AND STATIC SYSTEM 92 92 yp
4. SELECT ACTIVATE VECTORS TO FINAL NOTE SUSP may annunciate on the HSI when Vectors To Final is selected The flight plan will automatically unsuspend when the airplane intercepts and turns inbound on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish Cx ESPODI VERIFY CDI automatically changes to LOC Course pointer slews to the front course d Mode Control PRESS APR Verify LOC and GS armed IF Flying Full Approach Including Transition 3 Airplane cleared to an initial approach fix a ACTIVATE THE APPROACH from the PROC page Or ACTIVATE a DIRECT B gt the IAF nie t oeste us SELECT GPS Nav Source Mode Control Panel enne PRESS NAV GPS Mode Mode Control PRESS APR Verify LOC and GS armed NOTE Ensure groundspeed is less than 200 KTS within 1 minute of the IAF Airplane will navigate in GPS mode throughout the intermediate portion of the approach procedure When the airplane is inbound towards the final approach course the CDI will automatically switch from GPS navigation to LOC navigation VERIFY tay Course pointer slews to the front course 4 Established inbound on Final Approach Course SET Missed Approach Altitud
5. PRESS Yaw damper remains engaged Pitch Trim Switch Pilot s or if installed Copilot s control wheel ACTIVATE Yaw damper remains engaged Go Around GA nennen nene intet enne PRESS AFCS SERVOS Circuit PULL Right circuit breaker panel AUTOPILOT ABNORMAL DISCONNECT Red AP flashing on PFD Continuous high low aural tone 1 A P DISC TRIM INTRPT Button PRESS AND RELEASE to cancel disconnect tone 2 Aircraft MAINTAIN REGAIN AIRCRAFT CONTROL NOTE The autopilot disconnect may be accompanied by a red boxed PTCH pitch ROLL or AFCS on the PFD indicating the axis which has failed or that the automatic flight control system has failed The autopilot cannot be re engaged with any of these annunciations present AUTOPILOT FAILURE Red annunciator on PFD Red AP flashing on PFD Continuous high low aural tone 1 AP YD DISC TRIM INTRPT Button n n nasa PRESS to cancel disconnect tone If red AFCS is displayed the autopilot yaw damper and manual electric pitch trim will be inoperative PITCH AXIS FAILURE Red annunciator on PFD Indicates a failure of the pitch axis of the autopilot The autopilot will be inoperative 190 006
6. m h e N N wu N 9853 03890 1 4805 30 MASON ans UNV 1031409 815 1Nd3QlS YOLON N p EN N KCN N N SL s 8 3 aL u a o as lt _ k N N 2 EP bu X 1331 1331 qud OW JHONS 1531 X NI ds G gt 5 r s s s n s s 5 5 CY DE es 4 l I ea H3MOd 108 02 ONI HOLIND LUYIS N N s gt 4 NY olny 137 14331 Bm Bm S3NIDNI ONINHVM N39 1 N39 iva iva N39 1 N39 iva iva Figure 7 Right Side Circuit Breaker Panel Typical Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 77 of 95 8 H3WOd ASV0N003S 1 91 HOW LEN SN 9 9 9 5 6 94S r 7 1 Dav Sv Nor pel a 3 U3MOd ni oqi 1813 WW u3iH9n fr FON N 1 1 6 16 SL S M 0 5 a G N39 N N N Z N NZ uw uw 815 3008 NIBYO SOINOIAV um
7. eet eee eee er epe eden tette CHECK Activate the copilot s Pitch Trim Switches nose down Verify elevator tab wheel is moving nose down While the tab wheel is moving in the DN direction activate the pilot s Pitch Trim Switches nose up Verify the elevator tab wheel begins to move in the UP direction Release both pilot s and copilot s Pitch Trim switches and reset elevator tab as required e Manually Operate Elevator Tab Wheel VERIFY Pitch Trim Servo is Not Engaged 3 Press GA Button on Left Throttle VERIFY FD Command Bars show Takeoff Attitude TO TO is Annunciated in Mode Window on Both PFDs BEFORE TAKEOFF FINAL ITEMS 1 PFD Attitude and NORMAL 2 GPS sua ent VALID LOI NOT ANNUNCIATED HSI 3 Standby Attitude Indicator ERECT and NORMAL Fail Flag not in view ON TAKEOFF ROLL 1 Verify correspondence of PFD airspeed display and standby airspeed CLIMB CRUISE AND DESCENT Disengage autopilot and yaw damper and retrim the airplane in roll and yaw following a power change change in airspeed or if a slight wing rocking is observed Re engage the autopilot and yaw damper after trimming the airplane SHUTDOWN AND SECURING 1 Standby Battery cece e t eaa eae aa e a a a a ae PRESS OFF a Standby Battery Switch ARMED and ON EXTIN
8. 33 ALTITUDE MISCOMPARE 2 222 33 AIRSPEED NISCONIPARE u ea ccrto erra y ida ev crea dv ob va ve y dans 35 HEADING NISCONPARE UI ccena c rau aurea vera Ur ead 35 ROLL MISCOMPARE Dn ina made n sens 36 HEADING MISCOMPARE cina aer arn u u acra aC rana 36 Display Unit Fallure eda eed cunda euin euin eda euin cuan awas eH an n eH aa eran eua 36 PED EAILURE Rau SN 36 MED lt 00 0 awia 37 DUAL GPS SBAS FAILURE AMBER DR OR LOI ON H9SI 38 GPS APPROACH ALARM LIMITS EXCEEDED u J 39 LOSS OF RADIO TUNING FUNCTIONS U u u u u u 39 FAILED AIRSPEED ALTITUDE AND OR VERTICAL u 40 FAILED ATTITUDE AND OR HEADING 40 ENGINE INDICATION SYSTEM EIS FAILURE U u u
9. Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 4 of 95 Table of Contents Section 1 General Not FAA Approved T 7 Section 2 Limitations FAA Approved T 9 Section Emergency Procedures Not FAA Approved 19 Section Abnormal Procedures Not FAA Approved 27 Section 4 Normal Procedures Not FAA Approved 47 Section 5 Performance Not FAA 67 Section 6 Weight and Balance Not FAA Approved 67 Section 7 Systems Description Not FAA Approved 69 Section 8 Handling Service and Maintenance Not FAA Approved 95 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 5 of 95 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 6 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 installation of the Garmin G1000 Int
10. ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTINGUISHES IF THE ANNUNCIATOR STAYS EXTINGUISHED AND NO OTHER ANNUNCIATIONS ILLUMINATE e Continue to operate the autopilot in a normal manner after the annunciation extinguishes IF THE ANNUNCIATOR REMAINS ILLUMINATED OR REAPPEARS WITH NO CHANGE IN AIRSPEED CONFIGURATION OR ENGINE POWER FROM THE PREVIOUS TRIMMED CONDITION Rudder 25 9 8 HOLD FIRMLY Rudder Tab ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTINGUISHES YD BUTI PRESS on Mode Controller 6 Rudder Tab MANUALLY RETRIM AIRPLANE Yaw Damper should be considered inoperative until the cause of the mistrim has been investigated and corrected The Autopilot can continued to be used normally without the Yaw Damper 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 31 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 selected mode the system will revert to the default mode for the affected axis either ROL or PIT After 10 seconds the new mode PIT or ROL will be annunciated in green Loss of selected vertical mode
11. c CLR all waypoints after the last waypoint in the route to the alternate and the currently loaded instrument approach header 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 65 of 95 d When ready to proceed to the alternate highlight the first enroute waypoint in the route to the alternate airport ACTIVATE a DIRECT TO that waypoint e When enroute to the alternate a new instrument approach can now be loaded into the flight plan Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 66 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 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 67 of 95 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 68 of 95 Section 7 Systems Description Table of contents CS T EE RE 70 G1000 INTEGRATED 5 70 SYSTEM OVERVIEW s u dr acu a s u 70 INSTRUMENT PANEL uy 70 lt
12. Flight Director Mode will automatically change to ROL Course Pointe tis usa ecd tet de ed Haa aote dde Set to inbound course Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 62 of 95 f Mode Control Panel PRESS APR verify VAPP active or armed 4 Established inbound on Final Approach Course a VERIFY Course Pointer is set to the inbound course b VERIFY VOR is annunciated on the HSI NOTE If the Course Deviation Indicator CDI is greater than one dot from center the autopilot will arm the VAPP mode and indicate VAPP in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the APR button is pressed and annunciate VAPP in green on the PFD b cede MAINTAIN 110 KIAS OR GREATER Recommended 6 Atthe FAF Use desired vertical mode to fly the approach s vertical profile Use Altitude Preselect to level off at intermediate altitudes and at the MDA Recommend descending at 1000 ft min or less Descending at a higher rate or reaching MDA too far before the Visual Descent Point VDP could cause TAWS alerts If a TAWS WARNING is issued immediately follow the TAWS WARNING procedure in the EMERGENCY PROCEDURES Section of this AFMS 7 AFTER LEVELING AT MDA SE
13. NY NY NY w ASIS Avuny 3910A SOINOIAV Hv Mo 9 9 6 NZ N SWS 2039 e 2 lt Y X wu viva WHOIS 30 See LON EON ez 17 ND 95 SONOAV SNV3 VIO O3d ZON ZON ZON ZON N A fuk 6 S 9 92 WNOO SO INOIAV om LON ION LON s s s sj NES N SOINOIAY fan for fo S 8 8 8 2 E N L 90v L SHHV Odd SOINOIAV LN A D 5 GL N ed LA H3MOd INGA E sna 3 EN Gi S m S YY N 2 w NY 1331 zm 911792 SNIHSINHnd uv 7OHINOO sna 390130 r 0OHINOO 03318 fu darn 4 S4 Gi 0 5 6 D s N N N Ji suns 39 1391 WLNSWNOYIANS 78 iasa goma 193HION anal si S 0 c r nUi x N N NIBVO uiv L N9IB12313 ACISINO 3105 02 1HOlH 5719 9 QH O 15008 64 s
14. Optional LANDING GEAR Landing Gear Control LIGHTS LIGHTS LIGHTS Cabin Flour Lights Instruments Indirect Lights Navigation Lights Entrance amp Aft Dome Lights Standby Altimeter Internal Lighting Standby Attitude Indicator Internal Lighting Standby Airspeed Indicator Internal Lighting Hawker Beechcraft C90A and C90GT King Air Page 90 of 95 190 00682 02 Rev C TRIPLE FED BUS HOT BATTERY BUS STANDBY BATTERY PROPELLERS Propeller Governor Test WARNING ANNUNCIATORS Annunciator Indicator Annunciator Power L Oil Pressure Warning Landing Gear Position Indicator Landing Gear Warning Horn R Oil Pressure Warning Stall Warning L Fuel Pressure Warning R Fuel Pressure Warning L Auxiliary Fuel Quantity Warning R Auxiliary Fuel Quantity Warning WEATHER L Pitot Heat STANDBY BATTERY POWER SUPPLY The G1000 installation incorporates a 24 vdc 5 Ah JET model PS 835 Standby Battery www that provides electrical power for the standby attitude gyro standby altimeter vibrator and internal lighting for the three standby instruments for a minimum of 30 minutes following a total loss of aircraft power including the aircraft s battery A push button switch located directly below the standby airspeed indicator controls the standby battery power system The switch is a push ON switch latches in push OFF switch pops out type of switch The system has thr
15. ssc 93 Ground Communications 93 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 69 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 the original manual Only topics changed by the installation of the G1000 integrated avionics system will be addressed in this supplement 21000 system is an integrated system that presents flight instrumentation navigation communication weather avoidance engine instrumentation and supplemental flight information to the pilot for enhanced situational awareness through large format displays The G1000 also incorporates an automatic flight control system that includes autopilot and flight director functions Refer to the Garmin Cockpit Reference Guide P N 190 00664 00 Rev A or later FAA approved revision for detailed descriptions of the Garmin G1000 system including its components detailed descriptions of functions and operating instructions G1000 INTEGRATED AVIONICS SYSTEM OVERVIEW The main components of the G1000 Integrated Avionics system consists of 14 Line Replaceable Units LRU s Seven of those LRUs are mounted in the cockpit and interface the pilot to the
16. ALTERNATE position This will connect the alternate static air line to the pilots Air Data Computer ADC1 The alternate line is open to the unpressurized area just aft of the rear pressure bulkhead When the alternate static air source is not needed ensure that PILOT S EMERGENCY STATIC AIR SOURCE valve handle is held in the forward NORMAL position by the spring clip retainer WARNING The pilot s airspeed and altimeter indications change when the alternate static air source is in use Refer to the Airspeed Calibration Alternate System and the Altimeter Correction Alternate System graphs in Section 5 PERFORMANCE of the airplane s original Pilots Operation Handbook and FAA Approved Airplane Flight Manual for operation when the alternate static air source is in use There are three drain petcocks for draining the static air lines located below the side panel on the right sidewall behind an access cover These drain petcocks should be opened to release any trapped moisture at each inspection interval or after exposure to visible moisture on the ground and must be closed after draining Ground Communications Ground communications is provided by the G1000 system by turning ON the airplane s battery and the Avionics Master switch Com1 and the pilot s audio panel will be powered The pilot may use the airplane s speaker and hand microphone or a headset for communication 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King
17. erret tene ero ctr erae dec eer 21 PITCH AXIS FAILURE 21 ROLL AXIS FAILURE anam sa 22 YAW AXIS FAILURE IQ a u a au S aa qaa sansa 22 PITCH TRIM FAILURE ccc 22 AUTOPILOT PRE FLIGHT TEST U U U 22 AUTOPILOT OVERSPEED RECOVERY U U 23 ENGINE FAILURE AUTOPILOT ENGAGED u uuu uu uuu u 23 ELECTBICAL SYSTEM u us SSS Sau aaa qa saa qa 23 DUAL GENERATOR FAILURE L GEN OFF OFF eren 23 sawas T 25 TAWS e 25 DEI EE 25 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 19 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 MALFUNCTION ELEVATOR TRIM RUNAWAY If the airplane deviates unexpectedly from the planned flight path To Conto GRIP FIRMLY 2 AP YD DISC TRIM INTRPT Button PRESS AND HOLD Be prepared for possible high elevator control forces
18. 800 feet AGL 3 Approach GP GS 200 feet AGL 4 Approach FLC VS PIT or ALT Higher of 400 feet AGL or Approach MDA TAWS AND TERRAIN SYSTEM LIMITS Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with TAWS warnings The TAWS databases have an area of coverage as detailed below a The terrain database has an area of coverage from North 75 Latitude to South 60 Latitude in all longitudes b The Airport Terrain Database has an area of coverage that includes airports from North 75 Latitude to South 60 Latitude in all longitudes Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 12 of 95 FAA APPROVED c 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 MAP TAWS page and terrain display is intended to serve as a situational awareness tool only It may not provide either the accuracy or fidelity or both on which to solely base decisions and plan maneuvers to avoid terrain or obstacles To avoid unwanted alerts TAWS should be inhibited when landing at an airport that is not included in the airport database TRAFFIC AVOIDANCE SYSTEM LIMITS Use of the MAP TRAFFIC MAP to maneuver the airplane to avoid traffic without outside visual reference is prohib
19. Automatically Armed if available 259 Right Bank Approach VOR Arm Capture Track APR K 25 Left Bank m 25 Right Bank Approach ILS Arm Capture Track Glideslope Loc 25 Left Bank Mode Automatically Armed 25 Right Bank Takeoff on ground TO Wings Level I GA Switch 5 Go Around in air GA Wings Level annunciation appears in the AFCS Status Box The commandable bank angle range is indicated by a green band along the Roll Scale of the Attitude Indicator The CWS Button does not change lateral references for Heading Select Navigation Backcourse or Approach modes The autopilot guides the aircraft back to the Selected Heading Course upon release of the CWS Button The autopilot is capable of restoring the aircraft to the commanded attitude about the three axes throughout the following minimum ranges Pitch 25 nose up to 20 nose down Roll 45 The Flight Director is not designed to perform unusual attitude recoveries from attitudes outside the following range Pitch 25 nose up to 20 nose down Roll 45 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 83 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 automatically by the autopilot Electric Elevator trim switches are optional on th
20. FLC VS ALT GS 1 Autopilot mode 0 SELECT ANOTHER VERTICAL MODE If on an instrument approach disconnect autopilot and continue manually or execute missed approach 2 AP YD DISC TRIM INTRPT PRESS and RELEASE Loss of selected lateral mode HDG VOR GPS LOC VAPP BC 1 Autopilot mode controls SELECT ANOTHER LATERAL MODE If on an instrument approach disconnect autopilot and continue manually or execute missed approach 2 AP YD DISC TRIM INTRPT PRESS and RELEASE YAW DAMPER AUTOMATIC DISCONNECT Amber Flashing Flashing amber YD in flight indicates that yaw damper has disconnected If the disconnect was not pilot initiated the yaw servo has failed Do not reset the AFCS SERVOS circuit breaker in an effort to reset the yaw servo The autopilot pitch and roll modes will continue to function without the yaw damper engaged Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 32 of 95 G1000 INTEGRATED AVIONICS SYSTEM ALTITUDE 71 This message is displayed when the 21000 detects a difference of 200 feet greater between the pilot s and copilot s altitude information Refer to the G1000 Cockpit Reference Guide for additional information 1 Altimeter 0 VERIFY both pilot and copilot have the correct barometric a
21. G1000 system There are two Primary Flight Displays PFDs that display primary flight information to the pilot such as attitude airspeed altitude heading vertical speed navigation information system information and pilot situational awareness information In the center of the cockpit a 15 inch Multi Function Display MFD displays engine gauges flight plan data various map displays and access to aviation and weather information Information access and data entry through the MFD is via the GCU 475 MFD controller mounted in the pedestal between the pilot s seats Communications is interfaced through the PFD s and two audio panels mounted outside each PFD Radio tuning is through the PFDs and audio from the Com radios Nav radios ADF intercom and XM music is controlled by the two audio panels The G1000 incorporates a fully digital integrated autopilot and flight director Pilot interface to the AFCS is through the GMC 710 Autopilot Mode controller mounted in the center of the cockpit just below the airplane s glareshield In addition to dual Primary Flight Displays the system incorporates dual Air Data Computers GDC Dual AHRS GRS and Dual Integrated Avionics GIA units for system redundancy Each GIA contains a VHF Com radio a VHF Nav radio Glide Slope receiver Marker Beacon receiver and a SBAS augmented GPS receiver Finally the G1000 system includes weather radar and satellite downlinked weather information for weat
22. Indicator and Control Rudder Boost Flap Motor FUEL FUEL R Firewall Valve R Fuel Boost Pump Crossfeed Valve L Firewall Valve L Fuel Boost Pump Crossfeed Valve FURNISHINGS FURNISHINGS Cigarette Lighter Refreshment Bar Optional Electric Toilet Optional LIGHTS LIGHTS LIGHTS Rotating Beacon Lights Tail Taxi Light Ovrhd Subpanel amp Pedestal Lights L Landing Light Icing Light Recognition Lights Optional Center Tail Flood Lights Optional Standby Altimeter Internal Lighting Standby Attitude Indicator Internal Lighting Standby Airspeed Indicator Internal Lighting Recognition Lights Optional Center Bus or Right Gen Bus Bus or Right Gen Bus Side Panel Lights R Landing Light Strobe Lights Optional Cabin Reading Lights amp Sign Chime LANDING GEAR Landing Gear Motor 1 PROPELLERS PROPELLERS Prop Synchrophaser Prop Deice WARNING ANNUNCIATORS NO SMOKING amp FSB Signs WEATHER WEATHER WEATHER L Fuel Vent Heat Pilot Windshield Anti ice 1 Prop Deice Pneumatic Surface Deice Windshield Wiper R Fuel Vent Heat Copilot Windshield Anti ice 1 R Pitot Heat Stall Warning Heat Hawker Beechcraft C90A and C90GT King Air Page 88 of 95 190 00682 02 Rev C LEFT GENERATOR BUS RIGHT GENERATOR BUS GEN No 1 CENTER BUS GEN No 2 1 circuit breaker in this circuit is not accessible to the pilot in flight TRIPLE FED BUS HOT BATT
23. System Normally the pilot s side displays AHRS 1 information and the copilot s side displays AHRS 2 information Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 PFD displaying data from opposite AHRS SENSOR PRESS 2 AHRS 1 or AHRS2 Select on side AHRS AHRS1 for Pilot PFD AHRS2 for copilot PFD 3 PFD Displays CONFIRM BOTH ON AHRS 1 or BOTH ON AHRS 2 message clears on both PFDs BOTHONGPS1 BoTHONGPS2 This message is displayed on both PFDs and indicates that both pilot and copilot PFDs are displaying data from the same GPS SBAS receiver Normally the pilot s side displays GPS 1 and the copilot s side displays GPS 2 and is not pilot selectable This may be caused by operation outside of WAAS satellite coverage in which case the non selected GPS is still available in the event the active GPS fails Refer to GARMIN G1000 Cockpit Reference Guide for additional information 2 GPS SBAS Status aaa Select GPS STATUS page MFD b Select GPS1 then GPS2 softkeys and verify sufficient satellite reception 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 43 of 95 XSIDE ADC LE This message is displayed on bo
24. 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 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 be successfully completed prior to use of the autopilot flight director or manual electric trim Use of the autopilot or manual electric trim system is prohibited if the preflight test is not satisfactorily completed When conducting missed approach procedures autopilot coupled operation is prohibited until the pilot has established a rate of climb that ensures all altitude requirements of the procedure will be met Minimum speed for autopilot operation is 100 KIAS Maximum speed limit for autopilot operation is unchanged from the airplane s maximum airspeed limit Do not use autopilot below the following altitudes 1 On takeoff do not engage the autopilot below 400 feet Above Ground Level 2 een untae e RO EA
25. autopilot yaw damper and electric elevator trim will be inoperative 1 Automatic Autopilot Preflight Test COMPLETE a Red AFCS ILLUMINATED WHILE AHRS ALIGNS b Red AFCS Annunciator EXTINGUISHES When Autopilot Preflight Test Begins c White PFT ILLUMINATED 5 Seconds d White PFT 002222 2 EXTINGUISHES when preflight test complete e Autopilot Disconnect Sta RENN ERAEN KESSE REN ETAS SOUNDS 190 00682 02 Rev C Hawker Beechcraft C90A and 90 King Air Page 49 of 95 2 TAXI Standby Attitude eene nnne nnn nnne CHECK GAGE Knob thiet beate PULL KNOB TO ERECT GYRO b Instrument Fail NOT DISPLAYED IN INSTRUMENT FACE PFD1 PFD2 and Standby Attitude Indicator COMPARE and CROSS CHECK pn cce PA oie ne ee aici ei et a SET and CROSS CHECK PFD 1 PFD 2 Standby Altimeter If barometric pressure settings on the PFD s altimeters differ by more than 0 03 in Hg 1 the baro display on both PFDs will be amber NOTE Taxiing the aircraft before a valid GPS position has been acquired can cause attitude and or heading display to indicate a failed condition Interference from GPS repeaters or magnetic anomalies can cause an intermit
26. 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 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air FAA APPROVED Page 15 of 95 Icing System and or Equipment Conditions Remarks and or Exceptions Removed by G1000 modification Removed by G1000 modification ELECTRICAL POWER Inverter INVERTER Annunciator Standby Battery ENGINE INDICATIONS No Changes Refer to Aircraft Flight Manual ENGINE OIL No Changes Refer to Aircraft Flight Manual ENVIRONMENTAL Temperature limits reduced
27. in the PFD FD mode window and a continuous high low tone However when the Avionics Master Power Switch is turned OFF electrical power is removed from the audio panels preventing the autopilot disconnect tone from being heard NOTE Pressing and holding the CWS control wheel steering switch on the left grip of the pilot s control wheel will disconnect the autopilot servos from the airplane flight controls as long as the CWS switch is depressed Upon release of the CWS switch the system will synchronize to the existing pitch and roll modes selected Review the GFC700 Cockpit Reference Guide for more information The following tables list the available AFCS vertical and lateral modes with their corresponding controls and annunciations The mode reference is displayed next to the active mode annunciation for Altitude Hold Vertical Speed and Flight Level Change modes The NOSE UP DN Wheel can be used to change the vertical mode reference while operating under Pitch Hold Vertical Speed or Flight Level Change Mode Increments of change and acceptable ranges of values for each of these references using the NOSE UP DN Wheel are also listed in the table AFCS VERTICAL MODES e Reference Change Vertical Mode Control Annunciation Reference Range incremant 20 Nose up Pitch Hold default PIT 0 5 poner ea 15 Nose Down Selected Altitude ALTS Capture Altitude Hold ALT Key A
28. of a total loss of aircraft electrical power the standby battery will power the instrument s internal lighting The standby airspeed indicator uses the copilot s static system for its source of static air pressure and the copilot s pitot system for its source of impact air pressure Figure 12 Standby Flight Instruments 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 85 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 replaced At the top the ITT Interstage Turbine Temperature indicators and torquemeters are used to set take off power Climb and cruise power are established with the torquemeters and propeller tachometers while observing ITT limits Gas generator operation is monitored by the gas generator tachometers The lower grouping consists of the fuel flow indicators and the oil pressure temperature indicators The engine transducers send their signals to the Garmin GEA Engine and Airframe LRU where the analog signals are converted to digital signals where the engine parameters are displayed on the MFD There are two GEAs one for each engine The GEAs operate on 28vdc power supplied by the triple fed bus and are protected by circuit breakers normally located on the left side circuit breaker panel labeled ENG INST So
29. on both PFDs FAILED ATTITUDE AND OR HEADING ATTITUDE FAIL AND OR RED X OVER HEADING DISPLAY ON PFD This indicates a loss of pitch roll and or heading information from AHRS Refer to GARMIN G1000 Cockpit Reference Guide for additional information Interference from GPS repeaters operating inside nearby hangars or magnetic anomalies caused by nearby structures can cause an intermittent loss of attitude and heading displays while the aircraft is on the ground This is usually accompanied by a BOTH ON GPS 1 BOTH ON GPS 2 or LOI annunciation Moving the aircraft more than 100 yards away from the source of the interference should alleviate the condition Taxiing the aircraft before a valid GPS position has been acquired can cause attitude and or heading display to indicate a failed condition As soon as the aircraft acquires a valid GPS position attitude and heading should return to normal WARNING DO NOT TAKE OFF WITHOUT VALID NORMAL ATTITUDE AND HEADING DISPLAYS IN FLIGHT IF BOTH SIDES T Attitudes Mere ice qu MONITOR using standby attitude gyro 2 WSHLD ANTI ICE Switches Pilot and Copilot I n n OFF Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 40 of 95 NOTE The magnetic compass is erratic when either windshield anti ice air conditioner or electric heat is on With windshield anti ice OFF windshield may form fog or frost on the inside surfa
30. to 49 C 120 F with inoperative air ir Conditioning System conditioner or air conditioner not 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 Outside Air Temperature G1000 Integrated Avionics Garmin G1000 Cockpit Reference Guide Autopilot Yaw Damper Control Wheel Autopilot Disconnect Trim Interrupt Switches Left side is required Both side required for two crew operation Or as required by operating regulation 1 1 1 1 1 1 0 0 0 0 1 1 0 0 0 0 1 1 1 1 1 0 0 0 0 1 1 1 1 VHF Communications System Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 16 of 95 FAA APPROVED System and or Equipment Audio Control Panel Primary Flight Display Multi Function Display Air Data Computer Attitude Heading Reference System AHRS Standby Attitude Indicator Standby Altimeter Standby Airspeed Indicator ATC Transponder VHF Navigation Receiver GPS SBAS Receiver Automatic Direction Finder ADF Distance Measuring Equipment DME Marker Beacon Receiver Terrain Awareness and Warning System TAWS Weather Radar XM Datalink Weather GDU Cooling Fans 3 total OXYGE
31. to accomplish ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for or GPS is not authorized Use of the G1000 VOR LOC GS receivers to fly approaches not approved for or GPS requires that VOR LOC GS navigation data is selected and presented on the CDI of the pilot flying i e proper CDI source selection NOTE Not all published approaches are in the AVIATION database The flight Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 10 of 95 FAA APPROVED 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 is being flown referenced to GPS SBAS navigation the initial approach fix must be crossed at a ground speed of 200 KT or less 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air FAA APPROVED Page 11 of 95 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 the Earth s poles addition operations are prohibited in the following two regions North of 65 North latitude between longitude 75 W and 120 W Northern Canada South of 55 South latitude between longitude 120 E and 165 E region south of Australia and New Zealand NOTE
32. u u u 42 LOSS OF NAVIGATION cci erar ene cra etae caa adriana arma ara 42 INACCURATE FLIGHT DIRECTOR DISPLAY 42 BOTH ON ADC1 BOTH ON 2 u u uu u u u 43 BOTH ON AHRS 1 BOTH AHRS 2 J U 43 BOTH ON GPS 1 BOTH ON GPS 2 U U 43 XSIDE 44 XSIDE AIRS esd eae T 44 TAWS ABNORMAL PROCEDURES u T J 45 P 45 190 00682 02 Rev Hawker Beechcraft C90A and C90GT King Air Page 27 of 95 TAWS INHIBIT 45 TAWS N A S au u a uma us 45 Hawker Beechcraft C90A C90GT King Air 190 00682 02 Rev C Page 28 of 95 AUTOMATIC FLIGHT CONTROL SYSTEM AILERON MISTRIM amber 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 airspeed engine failure or single engine operation illumination of this message may occur If the autopilot is disconnected while this message is displayed high roll forces are possible The following procedure should be follo
33. will flag the lateral guidance and display a system message ABORT APPROACH loss of navigation Immediately upon viewing the message the unit will revert to Terminal navigation mode alarm limits If the position integrity is within these limits lateral guidance will be restored and the GPS may be used to execute the missed approach otherwise alternate means of navigation must be utilized LOSS OF RADIO TUNING FUNCTIONS 1 COM Frequency Toggle Button PRESS AND HOLD FOR 2 SECONDS NOTE This procedure will tune the active COM field to the emergency frequency 121 5 Certain failures of the tuning system will automatically tune 121 5 without pilot action 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 39 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 gt IF BOTH SIDES 1 Airspeed and Attitude u u MONITOR using standby indicators 2 Land as soon as practical gt IF ONE SIDE ONLY 1 Affected PFD SENSOR PRESS 2 ADC Softkey PRESS the ADC softkey to select the opposite ADC Bothi PFOS e tnn ete CONFIRM BOTH ON ADC1 OR BOTH ON ADC 2 annunciated
34. 190 00682 02 Rev C Page 22 of 95 AUTOPILOT OVERSPEED RECOVERY Yellow MAXSPD MAXSPD PFD 12 MOTUS y RS REDUCE When overspeed condition is corrected 2 SAUTOPIOt aen c e ride RESELECT VERTICAL MODE if necessary NOTE Overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum autopilot operating speed 226 KIAS 0 46 M Overspeed recovery is not active in altitude hold ALT glideslope GS or glidepath GP modes ENGINE FAILURE AUTOPILOT ENGAGED 1 AP YD DISC TRIM INTRPT Button eere PRESS and RELEASE 2 Engine Failure Procedure in EMERGENCY PROCEDURES Section of AFN COMPLETE 3 Trim Tabs MANUALLY ADJUST ELEVATOR AILERON AND RUDDER TABS 4 AUIDDIOL accu sa aciei uD a eee PRESS AP BUTTON if desired to R dder cc MANUALLY ADJUST AS REQUIRED AFTER POWER AND CONFIGURATION CHANGES ELECTRICAL SYSTEM DUAL GENERATOR FAILURE L GEN OFF R GEN OFF 1 and Gen2 Generator OFF ECOUTER T GEN RESET THEN ON 3 Operating DO NOT EXCEED 10096 LOAD If Left Generator Will Not Reset 4 SWIN uu how leiden 5 GeOn2 GEN RESET THEN ON 6 Operatin
35. 3 Aircraft Attitude essere 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 SERVOS Circuit Breaker 4 Elevator etes RETRIM if necessary using Elevator Tab Wheel 5 AFCS SERVOS Circuit PULL Right circuit breaker panel 6 AP YD DISC TRIM INTRPT Button RELEASE WARNING 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 NOTE The maximum altitude lost during malfunction tests was Climb 0 Feet Cruise 50 Feet Descent 320 Feet Maneuvering 0 Feet Approach 54 Feet One engine inoperative approach 45 Feet Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 20 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 PRESS and RELEASE Pilot s or Copilot s control wheel AP Button Autopilot mode control
36. 82 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 21 of 95 ROLL AXIS FAILURE Red MWM annunciator on PFD e Indicates a failure of the roll axis of the autopilot The autopilot will be inoperative YAW AXIS FAILURE Red annunciator on PFD e Indicates a failure of the yaw axis of the autopilot The pitch and roll axes of the autopilot will remain operative DO NOT pull and reset the AFCS SERVOS circuit breaker Resetting the AFCS SERVOS circuit breaker could cause the entire autopilot to become inoperative when no fault exists in the pitch and roll axes PITCH TRIM FAILURE Red annunciator on PFD 1 CONTROL WHEE Les u SS GRIP FIRMLY 2 AP YD DISC TRIM INTRPT PRESS and RELEASE Be prepared for possible high elevator control forces 3 Elevator 4441 1 AS REQUIRED USING ELEVATOR TAB WHEEL If Red Message Clears RE ENGAGE If Red Message Remains 4 AUWWBpII0LL DO NOT RE ENGAGE b Elevator CONTINUE TO USE ELEVATOR TAB WHEEL AUTOPILOT PRE FLIGHT TEST FAIL Red annunciator on PFD e Indicates the AFCS system failed the automatic Pre Flight test The autopilot yaw damper and electric elevator trim is inoperative Flight Director should still function Hawker Beechcraft C90A and C90GT King Air
37. ARNING is issued immediately follow the TAWS WARNING procedure in the EMERGENCY PROCEDURES Section of this AFMS 7 AFTER LEVELING AT SET Missed Approach Altitude In Altitude Preselect Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 64 of 95 GO AROUND GA 6 GoOntrol ea PER GRASP FIRMLY GO AROUND button left throttle PUSH Verify GA GA on PFD in lateral and vertical mode fields Rotate to Go Around attitude Follow Flight Director Command Bars Balked Eandirig e e e in EXECUTE Mode Control PRESS NAV to Fly Published Missed Approach Procedure PRESS HDG to Fly ATC Assigned Missed Approach Heading NOTE The pilot is responsible for initial missed approach guidance in accordance with published procedure The G1000 may not provide correct guidance until the aircraft is established on a defined leg of the procedure Altitude Preselect VERIFY Set to appropriate altitude At an appropriate safe altitude 7 Mode Goritrol Panel adie AP to Engage Autopilot NOTE When the GA button is pressed the autopilot disconnects the Flight Director command bars will command 8 nose up and w
38. Air Page 93 of 95 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 94 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 components 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 95 of 95
39. CATION SYSTEM EIS FAILURE RED X ON ENGINE DISPLAY gt IF ALL ENGINE GAUGES ON ONE ENGINE RED X Indicates failure of the GEA for that engine 1 Check ENG INST circuit breaker RESET once if tripped If unable to restore engine gauges 2 Move both throttles together using the engine with operating engine gauges to set power gt IF ONE OR MORE ENGINE PARAMETER INDICATIONS ARE FLAGGED ON ONLY ONE ENGINE 1 Adjust power using the remaining indications and comparing to the opposite engine LOSS OF NAVIGATION DATA LATERAL DEVIATION BAR NOT PRESENT AND OR GLIDESLOPE INDEX CLEARS This indicates a loss of data from the selected NAV source Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 CDI PRESS TO SELECT ALTERNATE NAVIGATION SOURCE 2 CONFIRM valid navigation source is displayed giving valid navigation guidance INACCURATE FLIGHT DIRECTOR DISPLAY Indicated by one or both flight directors commanding attitude contrary to intended flight path 1 AP YD DISC TRIM INTRPT Button PRESS Pilot s or Copilot s control wheel 25 isch oiim CROSSCHECK BOTH PFDs with the Standby Attitude Indicator 3 Flight Director Modes nennen RESELECT AS DESIRED NOTE If continued use of the flight director is desired it is recommended that
40. ERY BUS STANDBY BATTERY AVIONICS PFD 1 Primary Power AHRS 1 Primary Power ADC 1 Primary Power GIA 1 Primary Power MFD Power PFD 2 Power AHRS 2 Power ADC 2 Power GIA 2 Power MFD Controller Autopilot Mode Controller MFD Cooling Fan STBY Battery Charger Voice Recorder OPT Aural Warnings OPT Avionics Master Power Cabin Audio Avionics No 1 Bus 1 AUDIO 1 XPDR 1 ELECTRICAL ELECTRICAL Bus Tie Control Battery Relay Power Bus Tie Indicator Battery Voltmeter ENVIRONMENTAL Cabin Air Temperature Control Cabin Pressure Control L Bleed Air Control 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 89 of 95 TRIPLE FED BUS HOT BATTERY BUS STANDBY BATTERY ENGINE ENGINE Autofeather Optional Fire Detector Optional L Igniter Power L Start Control R Igniter Power R Starter Control L Engine Fire Extinguisher Optional R Engine Fire Extinguisher Optional FLIGHT INSTRUMENTS FLIGHT INSTRUMENTS Standby Attitude Indicator Gyro Standby Altimeter Vibrator Standby Attitude Indicator Gyro Standby Altimeter Vibrator FUEL FUEL L Fuel Qty Indicator L Fuel Transfer Pump L Firewall Valve L Boost Pump R Fuel Qty Indicator R Fuel Transfer Pump R Firewall Valve R Fuel Boost Pump Fuel Crossfeed Valve L Fuel Boost Pump R Fuel Boost Pump Fuel Crossfeed Valve FURNISHINGS MOD Stereo
41. Flight Level Change FLC MODE estes 53 Altitude Hold ALT Mode Manual 54 VERTICAL NAVIGATION 54 279 2 55 Navigation eset nA EDO 55 Navigation GPS DIRECT TO nosmet Ter tal ete an 55 Navigation GPS OBS s te baute Unt 56 iiie De uelis edel Ei d a deed ise Lr 56 eT 57 ILS Glide Slope 8 58 RNAV GPS LPV or NAVNAN 59 RNAV GPS LNAV LNAV a 60 VOR APPROAGLH tie tieu 62 190 00682 02 Rev Hawker Beechcraft C90A 90 King Air Page 47 of 95 BackeGo rse BO x uen Len ente 63 GO AROUND GA duni acne tn aont a S bA centr DR peeve ate y aun 65 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 48 of 95 COM RADIO COMMUNICATIONS BEFORE STARTING ENGINES To obtain an ATC clearance before starting the engines 1 Switeh M
42. GUISHED b Standby attitude fail flag displayed after BAT MASTER SWITCH is OFF c Standby altimeter vibrator should not be heard BAT MASTER SWITCH OFF Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 52 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 Normal mode transitions will flash inverse video green black for 10 seconds before becoming steady green Abnormal mode transitions will flash amber for 10 seconds before the default mode is annunciated as the active mode Default autopilot flight director modes are Pitch PIT and Roll ROL modes The XFR button on the mode control panel selects the Nav attitude and air data the autopilot flight director uses Pressing the XFR button transfers these selections to the opposite side and causes the autopilot flight director to drop selected lateral and vertical modes and engage the default PIT and ROL modes The pilot must re select the desired modes Vertical Modes Vertical Speed VS MODE 1 Altitude 044 SET to Desired Altitude 2 Press VS GREEN VS White ALTS annunciated on PFD 3 Vertical Speed ADJUST using UP DN Wheel 4 Gr
43. Garmin Ltd or its subsidiaries c o Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 U S A FAA Approved AIRPLANE FLIGHT MANUAL SUPPLEMENT G1000 Integrated Avionics System and GFC 700 AFCS In Hawker Beechcraft C90A and C90GT King Air Aircraft Dwg Number 190 00682 02 Rev This Supplement must be attached to the FAA Approved Airplane Flight Manual when the Garmin G1000 Integrated Avionics System is installed in accordance with STC SA01456WI D The information contained herein supplements the information of the basic Airplane Flight Manual For Limitations Procedures and Performance information not contained in this Supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Only the Limitations Section of this AFMS is FAA APPROVED Airplane Serial Number Airplane Registration Number FAA Approved By Robert G Murray Lead DAS Administrator Garmin International Inc DAS 240087 CE Date 3 13 2206 190 00682 02 Rev Hawker Beechcraft and C90GT King Air Page 1 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 medium for any purpose without the express prior written consent of Garmin Garmin hereby grants permission to download a single copy of this manual a
44. ICS ELECTRICAL EQUIPMENT BUS CONNECTION LEFT GENERATOR BUS GEN No 1 CENTER BUS RIGHT GENERATOR BUS GEN No 2 AVIONICS AVIONICS AVIONICS PFD1 GIA 1 Cooling Fan No 2 Avionics Bus COM 2 AUDIO 2 XPDR 2 RADAR DME AFCS SERVOS Avionics Annunciator PFD 1 Secondary Power AHRS 1 Secondary Power ADC 1 Secondary Power GIA 1 Secondary Power PFD2 GIA 2 Cooling Fan No 3 Avionics Bus Data Link Radio Altimeter OPT ADF WX 500 Stormscope Skywatch Traffic OPT ELECTRICAL ELECTRICAL ELECTRICAL L Gen Bus Bus Tie amp Meter Indication L Generator Control Panel 1 L Generator Field amp Sense 1 L Generator Loadmeter 1 ENGINE L Engine Fuel Control Heater L Chip Detector L Main Anti ice Ice Vane R Standby Ice Vane Generator Reset R Gen Bus Bus Tie amp Meter Indication R Generator Control Panel 1 R Generator Field amp Sense 1 R Generator Loadmeter 1 ENGINE R Engine Fuel Control Heater R Chip Detector R Main Anti ice Ice Vane L Standby Ice Vane 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 87 of 95 LEFT GENERATOR BUS GEN No 1 CENTER BUS RIGHT GENERATOR BUS GEN No 2 ENVIRONMENTAL ENVIRONMENTAL R Bleed Air Control Air Conditioner Motor Vent Blower Normal Heat Electric Max Heat Electric FLIGHT CONTROL FLIGHT CONTROL Flap
45. LT nnnnnFT Vertical Speed VS Key VS nnnn FPM 4000 to 4000 fpm 100 fpm Flight tevel FLC nnn KT 100 to 226 kt 1 kt Change IAS Hold Flight Level FLC Key Change Mach FLC M 0 0 25 to 0 46 0 01 Hold Vertical Path Tracking VNAV Key VETE VNV Target Altitude Capture AETY Glidepath GP Glideslope ARR KOY GS Takeoff on TO ground GA Switch Go Around in air GA ALTS arms automatically when PIT VS FLC TO or GA is active and under VPTH when the Selected Altitude is to be captured instead of the VNV Target Altitude ALTV arms automatically under VPTH when the VNV Target Altitude is to be captured instead of the Selected Altitude Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 82 of 95 AFCS LATERAL MODES Maximum Roll Lateral Mode Control Annunciation Comman d Limit Roll Mode 25 Left Bank default 25 Right Bank Low Bank 15 Left Bank BANK Key 15 Right Bank Heading Select 25 Left Bank 25 Right Bank Navigation GPS Arm Capture Track 25 Left Bank GES 25 Right Bank Navigation VOR Enroute Arm Capture Track 25 Left Bank i NAV Key NOR 25 Right Bank Navigation LOC Arm Capture Track No LOC 25 Left Bank Glideslope 25 Right Bank Backcourse Arm Capture Track 25 Left Bank Be 25 Right Bank Approach GPS Arm Capture Track Glidepath GPS 25 Left Bank Mode
46. N No Changes Refer to Aircraft Flight Manual PROPELLER No Changes Refer to Aircraft Flight Manual VACUUM SYSTEM Gyro Suction Gage Instrument Air System Icing Conditions Remarks and or Exceptions Pilot s audio panel required for single pilot operation Both sides required for two crew operation Or as required by operating regulation Or as required by operating regulation Or as required by operating regulation Or as required by operating regulation Or as required by operating regulation Or as required by operating regulation Or as required by operating regulation Or as required by operating regulation MFD fan is required if OAT is above 33 C 91 F All fans are required if OAT is above 47 C 116 F 190 00682 02 Rev C FAA APPROVED Hawker Beechcraft C90A and C90GT King Air Page 17 of 95 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 18 of 95 FAA APPROVED Section 3 Emergency Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEN 20 AUTOPILOT MALFUNCTION ELEVATOR TRIM RUNAWAY 20 MANUAL AUTOPILOT DISCONNECT 21 AUTOPILOT ABNORMAL 21
47. N if the GPS is the active lateral mode 2 330270 59 NOTE If the Course Deviation Indicator CDI is greater than one dot from center the autopilot will arm the NAV mode and indicate GPS in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the NAV button is pressed and annunciate GPS in green on the PFD APPROACHES The G1000 is capable of performing many tasks for the pilot to reduce pilot workload during the approach and landing phases of flight The G1000 system references the Flight Plan to predict the pilot s intended actions Time permitting the pilot should keep the Flight Plan updated with the destination airport and the instrument approach to be flown This will keep the G1000 from performing tasks associated with the approach procedures entered in the flight plan if the approach plan changes Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 56 of 95 ILS 1 Load the approach into the Active Flight Plan VERIFY the G1000 tunes the proper ILS frequency 2 Approach MINIMUMS siise iieii aee SET on TMR REF page IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control Panel PRESS HDG to fly ATC radar vectors b PROC button on PFDs or MFD
48. OS circuit breaker is reset If the autopilot successfully completes the Pre Flight Test re engage the autopilot reselect the desired autopilot modes and continue to use normally f the Pre Flight Test fails indicated by a red on the PFDs the autopilot yaw damper and electric pitch trim will be inoperative for the remainder of the flight 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 29 of 95 IF STILL INOPERATIVE eo eerta MANUALLY TRIM AIRPLANE IN PITCH Using Elevator Tab Wheel NOTE Autopilot and yaw damper may also be inoperative IF OPERATIVE e Use as required ELEVATOR MISTRIM amber or TELE annunciation PFD Indicates a mistrim of the elevator tab while the autopilot is engaged The autopilot will normally trim the airplane as required However during rapid acceleration deceleration or configuration changes momentary illumination of this message may occur accompanied by minor fluctuations in flight path If the autopilot is disconnected while this message is displayed high elevator control forces are possible In the event of sustained illumination the following procedure should be followed 1 Control Wheel en GRIP FIRMLY 2 Elevator Tab ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTINGUISHES IF THE ANNUNCIATOR STAYS EXTINGUISHED AND NO OTHER ANNUNCIATIONS ILLUMINATE e Con
49. Of Integrity mode LOI The mode is indicated on the HSI by an amber DR or LOI Which mode is active depends on the distance from the destination airport in the active flight plan If the LOI annunciation is displayed revert to an alternate means of navigation appropriate to the route and phase of flight or periodically cross check the GPS guidance to other approved means of navigation In Dead Reckoning mode the MAP NAVIGATION MAP will continue to be displayed with a ghosted aircraft icon in the center and an amber DR overwriting the icon Aircraft position will be based upon the last valid GPS position then estimated by Dead Reckoning methods Changes in true airspeed altitude or winds aloft can affect the estimated position substantially Dead Reckoning is only available in Enroute mode Terminal and Approach modes do not support DR gt IF ALTERNATE NAVIGATION SOURCES ILS LOC VOR DME ADF ARE AVAILABLE 1 Navigation ee dete tte tee USE ALTERNATE SOURCES gt IF NO ALTERNATE NAVIGATION SOURCES ARE AVAILABLE DEAD RECKONING DR MODE ACTIVE WHEN THE AIRPLANE IS GREATER THAN 30 NM FROM THE DESTINATION AIRPORT 1 Navigation Use the airplane symbol and magenta course line on the map display NOTE ALL INFORMATION NORMALLY DERIVED FROM GPS TURNS AMBER ALL OF THIS INFORMATION WILL BECOME LESS ACCURATE OVER TIME e TAWS IS INOPERATIVE e DR mode uses heading t
50. Rev A or later FAA approved revision must be immediately available to the flight crew 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 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air FAA APPROVED Page 9 of 95 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 C 91 F Do not takeoff if PFD1 FAN FAIL or PFD2 FAN FAIL is displayed in the ALERTS window AND the Outside Air Temperature is greater than 47 C 116 F Ground operation of the G1000 system is limited to 25 minutes when the Outside Air Temperature is greater than 49 C 120 F AND air conditioning is inoperative 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 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 t
51. Softkey isses nnne nnns PRESS 5 COPILOT S PFD AHRS2 PRESS 6 Displays CONFIRM BOTH ON AHRS 1 message clears on both PFDs Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 44 of 95 TAWS ABNORMAL PROCEDURES Taws CAUTION TERRAIN 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 available instruments and information TAWS INHIBIT INHB The TAWS Forward Looking Terrain Avoidance FLTA and Premature Descent Alerts PDA functions may be inhibited to stop alerting for acceptable flight conditions Refer to GARMIN G1000 Cockpit Reference Guide for additional information TO INHIBIT TAWS 1 Display the MAP TAWS 2 em ieri adt ee eR e ees PRESS TO ENABLE TAWS IF INHIBITED 1 Display the MAP TAWS 2 ENABLE Softkey eae PRESS TAWS TAWS 1 If the white TAWS N A status annunciator is displayed on the PFD the system will no longer provide TAWS alerting or display relative terrain elevations The crew must maintain compliance with procedures that ensure minimum terrain separation 2 If the red TAWS FAIL status annunciator is displayed on the PFD the system
52. T Missed Approach Altitude In Altitude Preselect Back Course BC 1 Load the approach into the Active Flight VERIFY the G1000 tunes the proper LOC frequency 2 Approach SET ON TMR REF page IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control PRESS HDG to fly radar vectors b PROC button on PFDs or MFD SELECT ACTIVATE VECTORS TO FINAL NOTE SUSP may annunciate on the HSI when Vectors To Final is selected The flight plan will automatically unsuspend when the airplane intercepts and turns inbound on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish pu EE PRESS until LOC Navigation Source to be used for the Approach Displays d VERIFY Course Pointer is Set to the Front Course Mode Control iPaneluu 20 2 ea D eo er PRESS Armed 190 00682 02 Rev Hawker Beechcraft C90A and 90 King Air Page 63 of 95 IF Flying Full Approach Including Transition 3 Airplane cleared to an initial approach fix a ACTIVATE THE APPROACH from the PROC page Or ACTIVATE a DIRECT TO gt the IAF ASI CDI Sr dg itte a i eda d et e oed e a RH e E GPS c Mode Control PRESS NA
53. V GPS Mode NOTE Ensure groundspeed is less than 200 KTS within 1 minute of the IAF d When Established Inbound to the PRESS CDI softkey until LOC navigation source to be used for the approach displays Autopilot Flight Director Mode will automatically change to ROL e uates emt tinte std d Course Pointer is set to the Front Course f Mode Gontrol Pafel etcetera t E te ipay PRESS BC BC Mode Armed or Active 4 Established inbound on Final Approach Course a VERIFY Course Pointer is set to the front course b VERIFY LOC is annunciated on the HSI NOTE If the Course Deviation Indicator CDI is greater than one dot from center the autopilot will arm the BC mode and indicate BC in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the APR button is pressed and annunciate BC in green on the PFD 5 siete MAINTAIN 110 KIAS OR GREATER Recommended 6 Atthe Use desired vertical mode to fly the approach s vertical profile Use Altitude Preselect to level off at intermediate altitudes and at the MDA Recommend descending at 1000 ft min or less Descending at a higher rate or reaching MDA too far before the Visual Descent Point VDP could cause TAWS alerts If a TAWS W
54. Yu ES T 10 660000 OPERATION LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACAROS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS ARE APPROVED THIS AIRPLANE APPROVED FOR VFR IFR DAY amp NIGHT OPERATIONS CAUTION STALL WARNING IS INOPERATIVE WHEN MASTER SWITCH IS OFF STANDBY COMPASS IS ERRATIC WHEN WINDSHIELD ANTI ICE AND OR AIR CONDITIONER AND OR ELECTRIC HEAT IS ON Figure 5 Overhead Light Control Panel 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 75 of 95 045019 3NTVA 1 5 N 15008 55389 MO S s SNYHL HOI s s s MO I1SN Ti IN 3OHd s s s 1331 SIN3W 81SNI WALSAS 1304 N s s s NHVM 0883 NHVM 5354 55060 SSJHd 1331 ALD SNVHL did 15008 3ATVA TIVM 3uld 035019 3ATNA JIOLNHS TivM3ul4 Figure 6 Left Side Circuit Breaker Panel 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 76 of 95 Wve xn Ns ANOOIS 4 8 6 5 4 WS N gt KEA NZ N 2 815 L 90v L SHHV ALI NHVM olanyv HYSLSVW PN gt N 1 CE 9 2 S
55. a se RE ENGAGE and select modes Transponder ucc eh a ade etat e pitt ies SELECT to operating transponder Audio Panels e tee eade tetuer RS SELECT operating COM Radio NOTE Use the operating PFD to control Com frequency selection Com and Nav volume and Altimeter Barometric Pressure setting MFD FAILURE failure is indicated by a complete loss of image on the center display 1 Pilot s Audio Panel DISPLAY BACKUP Button PRESS 2 Copilot s Audio Panel DISPLAY BACKUP PRESS NOTE Engine data will be displayed on both PFDs 3 Electronic Chart Data will not be available following an MFD failure Use the following procedure if a secondary source of aeronautical information is not available in the airplane a Load approaches arrivals and departures into the Active Flight Plan using the PROC button on either PFD The procedure s course can be displayed on either PFD s Inset Map window Navigate using the course pointer and CDI on the PFDs b For instrument approach procedures obtain altitude information from ATC using either COM radio 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 37 of 95 DUAL GPS SBAS FAILURE AMBER DR OR LOI ON HSI LOSS OF GPS SBAS NAVIGATION DATA When both GPS SBAS receivers are inoperative or GPS navigation information is not available or invalid the G1000 system will enter one of two modes Dead Reckoning mode DR or Loss
56. age Or ACTIVATE a DIRECT gt the IAF ISIC ME SELECT GPS Nav Source c Mode Control Panel PRESS APR Verify GPS mode active GP armed NOTE Ensure groundspeed is less than 200 KTS within 1 minute of the IAF VERIFY ete a Course pointer slews to the front course 4 Established inbound on Final Approach Course a VERIFY Course Pointer is set to the final approach course b VERIFY LPV or L VNAV is annunciated on the HSI c VERIFY GP Indicator Displays d VERIFY SUSP is not displayed on HSI e SET Missed Approach Altitude In Altitude Preselect 5 MAINTAIN 110 KIAS OR GREATER Recommended 6 VERIFY Airplane Captures and Tracks GPS Course Captures and tracks GP 7 AT Decision Altitude DA Y D DISC TRIM INTRPT Switch enne PRESS Continue visually for a normal landing Or d GO AROUND button on left throttle PRESS Execute Missed Approach Procedure RNAV GPS LNAV LNAV V 1 Load the approach into the Active Flight Plan 2 Approach SET ON TMR REF page IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control Panel PRESS HDG to fly ATC radar vectors b PROC button on PFDs or SELECT ACTIVATE VECTORS TO FINAL NOTE SUSP may annunciate on the HSI when Vectors To Final is
57. aster e t uysha laiqa ON 2 Avionics Master Pwr aqu n ku Ga t EO un Q MO la a MIQ Qatu S ON Use Pilot s Audio Panel and Com 1 to Obtain ATC Clearance then 3 Avionics Master Pwr Switch OFF 4 Switch Master Switch aaa OFF BEFORE STARTING 1 Standby Battery Switch U en PUSH ON illuminated if Aircraft Battery is OFF ARM illuminated if Aircraft Battery is ON 2 Standby Attitude Gyro Fail Flag NOT DISPLAYED listen for standby altimeter vibrator operation Database REVIEW FOR VALID OPERATING DATES AND CYCLE NUMBER ENT key on the MFD Control PRESS to acknowledge the G1000 database information and activate the selected pilot profile 5 AlX Weight Plarining iiie b dint h Ra E eer ees INPUT LOAD DATA BEFORE TAXI NOTE Autopilot preflight test will not begin until both AHRS have aligned Autopilot Pre Flight test begins when the white PFT message is displayed on each PFD Autopilot Pre Flight test has successfully completed when the white PFT message extinguishes and the autopilot disconnect tone sounds CAUTION A red PFT or AFCS annunciator indicates a malfunction within the autopilot system The
58. ce The windshield anti ice should be turned off only long enough to reference magnetic compass or the pilot should descent to a warmer altitude if terrain fuel and endurance permit 9 ELEC HEAT ete tet OFF 4 CABIN TEMP MODE switch OFF 5 leading ii Ate he diat MONITOR using magnetic compass 6 Land as soon as practical NOTE e autopilot will disconnect and will not re engage e Reference the GPS track on MFD PFD map to improve situational awareness GPS will continue to display correct GPS based map position and track e Magnetic compass is influenced by windshield anti ice air conditioner and electric heat These items must be turned OFF prior to referencing magnetic compass heading Leave these items OFF when maneuvering the aircraft by reference to the magnetic compass IN FLIGHT IF ONE SIDE ONLY 1 MONITOR 2 Affected PFD SENSOR PRESS 3 AHIR S SOMKCY tite etre E PRESS Opposite Side AHRS softkey 4 Both 5 CONFIRM VALID ATTITUDE AND HEADING ARE DISPLAYED CONFIRM BOTH ON AHRS1 BOTH ON AHRS2 annunciated on both PFDs NOTE The autopilot will disconnect and will not re engage 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 41 of 95 ENGINE INDI
59. e In Altitude Preselect AIISDGed adest erem MAINTAIN 110 KIAS OR GREATER Recommended reete Airplane Captures and Tracks LOC captures and tracks GS 190 00682 02 Rev C Hawker Beechcraft C90A and 90 King Air Page 57 of 95 7 AT Decision Altitude DA A P Y D DISC TRIM INTRPT PRESS Continue visually for a normal landing Or b GO AROUND button on left throttle PRESS Execute Missed Approach Procedure ILS Glide Slope INOPERATIVE 1 Load the approach into the Active Flight VERIFY the G1000 tunes the proper ILS frequency 2 Approach MINIMUMS i esL t leche tie tous SET on TMR REF page IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control Panel PRESS HDG to fly ATC radar vectors b PROC button on PFDs or MFD SELECT ACTIVATE VECTORS TO FINAL NOTE SUSP may annunciate on the HSI when Vectors To Final is selected The flight plan will automatically unsuspend when the airplane intercepts and turns inbound on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish Cy c ttes VERIFY CDI automatically changes to LOC Course pointer slews to the front course d Mode Control
60. e copilot s control wheel If pitch trim switches are installed on the copilot s control wheel the pilot s pitch trim inputs override those made by the copilot The ON OFF toggle switch on the pedestal has been removed Electric elevator trim will function if the AFCS circuit breaker right side circuit breaker panel is set and the autopilot has satisfactorily completed a preflight test Pitch trim rocker switches on the pilot s control wheel manually control the electric elevator trim system NOSE DN at the top of the rocker switch when depressed causes the elevator pitch trim servo to move the trim tab in the upward direction resulting in the nose of the airplane pitching downward The control column will move in the forward direction and the pitch trim wheel will move forward in the nose down direction Depressing NOSE UP at the bottom of the rocker switch results in the opposite of the previous motions with the airplane nose pitching up Runaway or malfunctioning trim can be interrupted by pressing and holding the red A P Y D DISC TRIM INTRPT switch on either control wheel Pulling the AFCS circuit breaker on the right side circuit breaker panel will disable the electric elevator trim so it will not move when the TRIM INTRPT switch is released Figure 11 Electric Trim Switches Pilot s Control Wheel Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 84 of 95 FLIGHT INSTRUMENTS G1000 FLIGHT INSTRUMENTS The
61. e pilot determines based on all available information that turning in addition to the escape maneuver is the safest course of action or both TAWS FAIL Red on PFD and MFD Indicates the G1000 will no longer provide TAWS alerting or display relative terrain elevation The crew must maintain compliance with procedures that ensure minimum terrain and obstacle separation 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 25 of 95 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 26 of 95 Section 3A Abnormal Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEMN 29 AILERON MISTRIM lla ik 29 ELECTRIC PITCH TRIM INOPERATIVE U u u u u J 29 ELEVATOR MIS TRIM is i l sone cat seceeveseleacdeccswescasusccevedsawesvandicacSeteseecedudvawesvandsducdesuecerdecdsesvenssocsvenws 30 RUDDER NISTRINu u l l A 31 FLASHING AMBER MODE ANNUNCIATION 32 YAW DAMPER AUTOMATIC DISCONNECT Amber Flashing YD 32 G1000 INTEGRATED AVIONICS SYSTEMN
62. ediction Program Instructions 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 7 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 only one Long Range Navigation sensor NOTE 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 necessarily mean that one GPS has failed Refer to the MFD AUX GPS STATUS page to determine the state of the unused GPS Enroute and Terminal including RNP5 BRNAV and PRNAV RNP 1 In accordance with JAA TGL 10 Rev 1 ACJ 20X4 AC 90 96A and AC 90 100A provided the FMS is receiving usable navigation information from one or more GPS SBAS receivers The G1000 Integrated Avionics system as installed in this is aircraft is eligible for B RNAV in accordance with AMJ20X2 The G1000 Integrated Avionics system as installed in this aircraft is eligible for PRNAV in accordance with PRNAV requirements JAA Administrative amp Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 Airworthiness and Operational Approval for Precessi
63. ee modes OFF ON and ARM OFF ON Amber ARM Green The system is OFF when the Standby Battery switch is popped out There are no internal switch annunciators illuminated in the switch when the system is OFF Illuminates when the standby battery is powering the standby instruments The Standby Battery switch must be latched IN and the airplane has no source of normal electrical power for the standby battery to power the standby instruments When the ON annunciator is illuminated the standby battery will provide electrical power for the three standby instruments for at least 30 minutes The system is ARMed for automatic operation when the Standby Battery switch is latched IN and the airplane is being powered by a normal source of electrical power Normal source of electrical power includes the airplane s battery or at least one generator or external power 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 91 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 panel LIGHTING SYSTEMS COCKPIT An overhead light control panel accessible to both pilots incorporates a functional arrangement of all lighting systems Each light group has its own rheostat switch placarded BRT OFF The MASTER PANEL LIGHTS ON OFF switch i
64. een ALT etie ien tates VERIFY UPON ALTITUDE CAPTURE Flight Level Change FLC MODE Altitude Preselect teer eto SET to Desired Altitude Press Button ii GREEN FLC White ALTS annunciated on PFD AIRSPEED sse ADJUST using UP DN Wheel Green settee erect oe eis hie ete ait eat eee VERIFY UPON ALTITUDE CAPTURE Pu OO i NOTE If the altitude preselect is not changed before selecting FLC the autopilot may re capture the current altitude immediately after entering FLC mode Always ensure that the altitude preselect is adjusted prior to selecting FLC Pressing the SPD button while in FLC Mode toggles the airspeed reference between KIAS and Mach FLC will automatically transition from Mach to KIAS reference during a descent when the current Mach reference equals 220 KIAS FLC will not automatically transition from KIAS to a Mach reference during a climb 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 53 of 95 Altitude Hold ALT Mode Manual Capture At the desired altitude PRESS ALT Button on Mode Controller 2 CIIM TL MET VERIFY on PFD If climbing or descending the aircraft will overshoot the reference altitude and then return to it The amount of overshoot will depend on the vertical speed when the ALT button is pressed VERTICAL NAVIGATION VNAV VNAV Descen
65. egrated 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 the Hawker Beechcraft C90A and C90GT 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 Weather Avoidance and a three axis automatic flight control flight director system OPERATIONAL APPROVALS G1000 GPS SBAS NAVIGATION SYSTEM The Garmin G1000 GPS SBAS receivers incorporating SW version 3 0 or later approved version and Comant Cl 428 410 and Cl 428 200 antennas are approved under TSO C145a Class 3 and installed in accordance with AC 20 138A The Garmin G1000 system has been demonstrated capable of and has been shown to meet the accuracy requirements for the following operations provided it is receiving usable navigation data The G1000 Integrated Avionics system as installed in this aircraft complies with AC 20 138A for navigation using GPS and WAAS within the coverage of a Space Based Augmentation System c
66. er altitude than the VNAV reference altitude This indicates the autopilot flight director will capture the VNAV altitude reference ALTS will be the armed mode during the descent if the altitude preselect is set at or above the VNAV reference altitude indicating that the autopilot flight director will capture the altitude preselect altitude reference Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 54 of 95 Vertical DIRECT TO To descend from the present position to a waypoint Ty Altttude Preseleglu ete mee RESET 2 Button ee etate adt p a t p start ee hae PRESS 3 VNV gt Softkey MFD Flight Plan PRESS 4 ee decerpere SELECT desired waypoint and ACTIVATE Lateral Modes Heading Mode HDG 1 ADG KINOD ee ee PUSH to synch heading bug to current heading 22 HDG ABUT TON o Tu etre re PUSH HDG mode annunciated o KNO D eae Rotate to set heading bug to desired heading Navigation VOR 1 Navigation Source SELECT VOR 1 VOR2 using CDI softkey on PFD 2 Co rse POME sr tee ott ndn o et e oen SET using CRS knob 3 Intercept ESTABLISH in HDG or ROL mode 4 Mode OController enne PRESS NAV on mode controller 5 VOR will be annunciated in WHITE if t
67. escent angle as an aid in flying a stabilized approach These approaches are NOT considered Approaches with Vertical Guidance APV Approaches that are annunciated on the HSI as LNAV or LNAV V are considered Nonprecision Approaches NPA and are flown to an MDA even though vertical glidepath GP information may be provided 6 LADINO FAP uii aie cista Descend via GP if LNAV V approach Use desired vertical mode to fly the approach s vertical profile if LNAV approach Use Altitude Preselect to level off at intermediate altitudes and at the MDA Recommend descending at 1000 ft min or less Descending at a higher rate of descent or reaching MDA too far before the Visual Descent Point VDP could cause TAWS alerts If a TAWS WARNING is issued immediately follow the TAWS WARNING procedure in the EMERGENCY PROCEDURES Section of this AFMS CAUTION Airplane will not capture ALT if descending in GP mode 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 61 of 95 7 Level airplane in ALT mode at 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 LEVELING AT SET Missed Approach Altitude In Altitude Preselect VOR APPROACH 1 Load the approach into the Active Flight Plan VERIFY the G1000 tunes the p
68. flight instruments are an integrated part of the G1000 system For system descriptions operating instructions and abnormal failure indication refer to the Cockpit Reference Guide STANDBY FLIGHT INSTRUMENTS There are three 2 inch standby instruments that are located directly to the right of the pilot s Primary Flight Display arranged vertically standby attitude indicator standby altimeter and standby airspeed indicator A standby attitude indicator located at the top of the stack is normally 22 I M ae powered by the triple fed buss In the event of total loss of aircraft S electrical power there is a standby battery that will power the standby attitude indicator for at least 30 minutes A standby altimeter is the next instrument in the stack It is a mechanical instrument that requires no electrical power to operate Electrical power is used to power an internal vibrator used to minimize indicator pointer sticking and instrument internal lighting The vibrator is normally powered from the triple fed buss the event of total loss of normal aircraft electrical power the vibrator and internal lighting is powered by the standby battery The standby altimeter uses the copilot s static system for its source of static air pressure The bottom instrument is a mechanical airspeed indicator It is a mechanical instrument that requires no electrical power to operate Electrical power is used for internal lighting In the event
69. g 1000 000 DO NOT EXCEED 100 LOAD 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 23 of 95 If Neither Generator Will Reset 7 Avoid IFR conditions if possible and LAND AT THE NEAREST SUITABLE AIRPORT 8 Standby Battery INDICATES ARM or 9 Non essential equipment a b j Left and Right OFF Left and Right TRANS PUMP OFF tte EI TTE EI OFF 1 uuu aie td ctetu ne pei Ed boe de erano aee OFF All Exterior Lights oiii td pence sein UN a In e poa e a Dep ord OFF uy halaq OFF VENT BLOWER uer I AUTO CABIN TEMP MODE 1 mem OFF INSTRUMENT EMERG 5 ON if required INSTRUMENT INDIRECT lights sss HM ON if required 10 The following equipment will be functional while the G1000 is powered from the aircraft s battery power Avionics Master Power Switch is ON and the L GEN TIE OPEN and R GEN TIE OPEN annunciators are illuminated Pilot s Attitude Heading Air Data and Nav CDI Copilot s Attitude Heading Air Data and Nav CDI Engine Gauges Com1 Pilot s Audio Panel GPS 1 GPS 2 VHF Nav1 VHF Nav2 Nav2 Aud
70. he mode is armed or in GREEN if the VOR is the active lateral mode NOTE If the Course Deviation Indicator CDI is greater than one dot from center the autopilot will arm the NAV mode and indicate VOR in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the NAV button is pressed and annunciate VOR in green on the PFD Navigation GPS DIRECT TO 1 Navigation Source SELECT GPS Using the CDI Softkey on PFD 2 Select PRESS the P gt button on the PFDs MFD From the DIRECT TO page activate DIRECT TO a waypoint 3 Mode Controller SELECT NAV on mode controller GPS will be annunciated in GREEN on the PFDs 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 55 of 95 Navigation GPS OBS Mode Navigation Source SELECT GPS using the CDI softkey on PFD Select PRESS the P gt button on the PFDs MFD From the DIRECT TO page activate DIRECT TO a waypoint OBS SofIKoy iid ON PFD PRESS OBS softkey Course tao as SET using CRS knob Intercept Heading rnm ESTABLISH in HDG or ROL mode Mode SELECT NAV on mode controller GPS will be annunciated in WHITE if the mode is armed or in GREE
71. he teardrop segment of the course reversal 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 SafeTaxi and Chartview airport moving map display with own ship position symbol is designed to assist flight crews in orienting themselves on the airport surface to improve pilot positional awareness during taxi operations The airport moving map display function is not to be used as the basis for ground maneuvering G1000 GPS SBAS NAVIGATION SYSTEM SBAS AUGMENTED GPS SYSTEM LIMITATIONS GPS SBAS based IFR enroute oceanic and terminal navigation is prohibited unless the pilot verifies and uses a valid compatible and current Aviation database or verifies each waypoint for accuracy by reference to current approved data GPS or GPS and RNAV GPS instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Aviation database GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Aviation database 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 Use of the Garmin G1000 GPS SBAS receivers
72. her avoidance and situational awareness INSTRUMENT PANEL The G1000 Instrument Panel consists of two 10 inch LCD Primary Flight Displays one 15 inch LCD Multi Function Display two audio panels and autopilot flight director mode control panel an MFD controller and three 2 1 4 inch standby instruments The ADF control head has been relocated from the radio stack location on the instrument panel to the pedestal Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 70 of 95 0 0 lt Figure 1 Instrument Panel Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 71 of 95 Figure 2 Pilot s Control Wheel Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 72 of 95 COPILOT 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 SO Figure 4 Copilot s Control Wheel Without Switches Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 74 of 95 00 NOT OPERATE ON DRY GLASS MAX AIRSPEED KNOTS hic OVERHEAD INSTRUMENT wake INDIRECT GEAR EXTENSION 182 GEAR RETRACT 163 PARK SLOW MASTER GEAR EXTENDED 182 FAST O APPROACH FLAP 184 FULL DOWN FLAP 148 MANEUVERING 169 Kar PANEL me dd STBY OVHD PED SIDE COPILOT amp ore
73. i 109 MOI ISNI H3NOd NNV W39 1803 ona INidOud WOINO 11 NYYM H3MOd 1 sy 5 s s s s G LFA V VU x4 NZ 120 1038 on 131 131 Mis uio SOINOIAV S3NON3 ONNNBYM 190 00682 02 Rev C Figure 8 Right Side Circuit Breaker Panel Optional Configuration Hawker Beechcraft C90A and C90GT King Air Page 78 of 95 Y 9 RANGE om ogoogo 00 FMS ue a Figure 9 Pedestal 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 79 of 95 No 1 GIA 63W AFCS Mode Logic Flight Director Servo Mat Pilot s Control Multi Function GDU 1040A PFD1 GSA 80 Pitch Servo V GSA 80 Roll Servo w w GSA 80 L Yaw Servo lt lt lt NN GSA81 Pitch Trim Servo q lt Figure 10 GFC 700 System Interface GDU 1040A PFD2 No 2 GIA 63W AFCS Mode Logic Flight Director Servo Mat Copilot s Control Hawker Beechcraft C90A and C90GT King Air Page 80 of 95 190 00682 02 Rev C FLIGHT CONTROLS AFCS AUTOPILOT AND FLIGHT DIRECTOR The GFC 700 is a digital Automatic Flight Control System AFCS ful
74. ings level the HSI nav source automatically switches to GPS the flight plan sequences to the first published missed approach leg and automatic leg sequencing resumes The AFCS will fly the published missed approach procedure once the aircraft is established on a segment of the missed approach procedure the autopilot is engaged and NAV mode is selected The flight plan can only contain one approach procedure at a time If the pilot attempts to load another instrument approach at this time the airplane will depart from the missed approach procedure and turn directly towards the first waypoint in the new approach Do not attempt to load or activate a new approach while flying the missed approach procedure until ready to fly the new approach Recommended procedures following a missed approach 1 repeat the instrument approach procedure currently loaded into the flight plan a Activate Vectors To Final if being radar vectored by ATC Or b f flying the entire instrument approach procedure activate a DIRECT TO the desired initial waypoint Follow the appropriate procedure for the instrument approach being flown 2 To proceed to an alternate airport This procedure will allow the pilot to enter the route to the alternate before leaving the missed approach holding fix a Highlight the first enroute waypoint in the flight plan b Begin entering waypoints in the desired route order Do not attempt to load a new approach at this time
75. io Inop MFD Flight Director Transponder 1 NOTE Inoperative G1000 equipment items will be displayed in the ALERTS window on both PFDs The aircraft s battery will continue to power the G1000 equipment for 30 minutes following complete loss of normal electrical power generation Once the aircraft s battery can no longer power the G1000 the standby battery will automatically power the standby attitude indicator altimeter vibrator and the internal lighting of the three standby instruments for an additional 30 minutes 11 Consider a Flaps UP Landing and Landing Gear Manual Extension to conserve battery power for an instrument approach if needed Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 24 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 PULL BACK ON CONTROL WHEEL 3 sei rcd Ra sac eva va DW Sd d ev eua d MAXIMUM ALLOWABLE 4 Airspeed 2 2 BEST ANGLE OF SPEED 5 EE MAXIMUM CONTINUOUS 6 Altil udes u u u u heat CLIMB AND MAINTAIN SAFE ALTITUDE 7 Advise ATC of Altitude Deviation if appropriate NOTE Only vertical maneuvers are recommended unless either operating in visual meteorological conditions VMC or th
76. ion It is the pilot s responsibility to avoid hazardous weather using official weather data sources and the airplane s weather radar 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air FAA APPROVED Page 13 of 95 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 section With the installation of the G1000 these placards are removed and not required On Instrument Panel above the Standby Attitude Indicator STANDBY ALT AS ALTITUDE FEET 5 S L TO 16 000 226 16 000 TO 20 000 209 20 000 TO 25 000 189 25 000 TO 30 000 169 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 14 of 95 FAA APPROVED KINDS OF OPERATION LIMITS The Hawker Beechcraft models C90A and C90GT are 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 VFR Day VFR Night IFR Day IFR Night Icing Conditions arwon KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR day or night IFR and icing
77. ion when System Software Version 0636 01 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 change 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 low speed awareness band is marked on the PFDs in red from 20 78 KIAS While the airplane is on the ground the low speed awareness band is suppressed t displays 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 standby airspeed indicator is not marked with a low speed awareness band POWER PLANT LIMITATIONS AND INDICATOR MARKINGS No change to the airplane s powerplant operating limitations The engine gauges are marked in accordance with the airplane s POH AFM or if an engine modification has been installed in accordance with the AFMS for the engine modification NOTE The gauge indicator pointer and digital display will flash inverse red white video for 5 seconds and then remain steady red if the indicated engine parameter exceeds its established limit G1000 INTEGRATED AVIONICS SYSTEM These limitations apply to Garmin G1000 system software version 0636 00 The Garmin G1000 Cockpit Reference Guide P N 190 00664 00
78. ision Altitude or GPS based approach Minimum Descent Altitude to most accurate altimeter based on FAF crossing WARNING TAWS ALERTS ARE BASED ON GPS ALTITUDE AND POSITION INFORMATION TAWS WARNINGS AND CAUTIONS ARE INDEPENDENT OF ADC DATA IF TAWS WARNING OR CAUTION IS RECEIVED CONSIDER IT ACCURATE AND TAKE IMMEDIATE AVOIDANCE ACTION Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 34 of 95 AIRSPEED MISCOMPARE 2 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 G1000 Cockpit Reference Guide for additional information 1 Pilot s and Copilot s Airspeed COMPARE with Standby Airspeed Indicator WARNING THE STANDBY AIRSPEED INDICATOR USES THE SAME PITOT STATIC SOURCES AS THE COPILOT S SIDE AIR DATA COMPUTER ADC2 DO NOT USE STANDBY AIRSPEED INDICATOR OR STANDBY ALTIMETER AS SOLE SOURCE IN DETERMINING CORRECT AIR DATA INFORMATION gt IF PILOT PFD AND STANDBY AIRSPEED INDICATOR AGREE COPILOT PFD DIFFERS SENSOR Softkey Copilot s PFD n n nunus PRESS ADC ASO CY u Y PRESS 4 PFD Displays CONFIRM BOTH annunciator is displayed both PFDs 2 Pilot and Copilot ALTITUDE
79. ited The Traffic Information System TIS or optional Skywatch HP Traffic Alert Advisory System is 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 DATA LINK WEATHER XM WEATHER Datalink weather information displayed by the G1000 system is limited to supplemental use only XM weather data is not a source of official weather information Use of the NEXRAD and LTNG XM Lightning data on the MAP NAVIGATION MAP and or MAP WEATHER DATA LINK page XM Weather for hazardous weather e g thunderstorm penetration is prohibited NEXRAD and LTNG information on the MAP NAVIGATION or MAP WEATHER DATA LINK page is intended only as an aid to enhance situational awareness of hazardous weather not penetration It is the pilots 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 NAVIGATION MAP and or MAP STORMSCOPE page for hazardous weather thunderstorm penetration is prohibited Stormscope lightning data on the MAP NAVIGATION or MAP STORMSCOPE page is intended only as an aid to enhance situational awareness of hazardous weather not penetrat
80. ltimeter setting 2 Pilot s and Copilot s Altitude COMPARE with Standby Altimeter WARNING THE STANDBY ALTIMETER USES THE SAME STATIC SOURCE AS THE COPILOT S SIDE AIR DATA COMPUTER ADC2 DO NOT USE STANDBY ALTIMETER AS SOLE SOURCE IN DETERMINING CORRECT ALTITUDE gt IF PILOT PFD AND STANDBY ALTIMETER AGREE COPILOT PFD DIFFERS SENSOR Softkey Copilot PED uu uu piti ett PRESS iBIexEceulcy PEE PRESS 5 PFD Displays CONFIRM LLL annunciator is displayed on both PFDs gt IF COPILOT PFD AND STANDBY ALTIMETER AGREE PILOT PFD DIFFERS 3 Pilot s Static Air SELECT ALTERNATE A sudden sustained change in rate of climb indication accompanied by abnormal indicated airspeed and altitude changes beyond normal calibrated differences observed on the Pilot s PFD would indicate a blockage of the pilot s static system f Pilot s PFD and Copilot s PFD agree within normal calibrated differences with Pilot s Alternate Static Air Source in the ALTERNATE position Refer to Section 5 PERFORMANCE in the airplanes AFM for Airspeed Calibration and Altimeter Correction If no change in rate of climb airspeed or altitude is observed 4 Pilot s Static Air Source a nn SELECT NORMAL 5 Compare indicated altitude to GPS altitude on MFD AUX GPS STATUS page to aid in determining which p
81. ly integrated within the G1000 System avionics architecture The GFC 700 is a three axis autopilot and flight director system which provides the pilot with the following features Autopilot AP Autopilot operation occurs within the pitch roll and pitch trim servos It also provides servo monitoring and automatic flight control in response to flight director steering commands AHRS attitude and rate information and airspeed Flight Director FD Two flight directors each operating independently within their respective GIA and referred to as pilot side and copilot side Commands for the selected flight director are displayed on both PFDs The flight director provides e Command Bars showing pitch roll guidance Vertical lateral mode selection and processing e Autopilot communication Yaw Damper YD The yaw servo is self monitoring and provides Dutch roll damping and turn coordination in response to yaw rate roll angle vertical acceleration and airspeed Electric Pitch Trim The pitch trim servo provides manual electric pitch trim capability when the autopilot is not engaged Pilot commands to the AFCS are entered through the GMC 710 Autopilot Mode Controller mounted in the center of the cockpit under the airplane s glareshield The GMC 710 controller also controls the heading bug navigation course selector on each PFD and the altitude preselect Other components of the autopilot include four servos that also contai
82. me configurations will have the ENG INST circuit breakers located on the right side circuit breaker panel The ITT indicator gives a reading of engine gas temperature between the compressor turbine and the power turbines A digital indication combined with the pointer gives a resolution of 19C The torquemeters give an indication in foot pounds of the torque being applied to the propeller A digital indication combined with the pointer gives a resolution of 5 ft lbs The propeller tachometer reads directly in revolutions per minute A digital indication combined with the pointer gives a resolution of 10 rpm The or gas generator tachometer is in percent of rpm based on a figure of 37 500 rpm at 100 Maximum continuous gas generator speed is limited to 38 100 rpm or 101 5 digital indication combined with the pointer gives a resolution of 0 196 rpm The fuel flow indicators give an indication of fuel consumption in pounds of fuel per hour A digital indication combined with the pointer gives a resolution of 1 Ib hr The oil pressure indicator displays oil pressure in PSI digital indication combined with the pointer gives oil pressure a resolution of 1 psi The oil temperature indicator displays oil temperature in Degrees Celsius A digital indication combined with the pointer gives oil temperature a resolution of 19C A propeller synchroscope located above and between the propeller tachometers gives an indication of synch
83. mmend descending at 1000 ft min less Descending at a higher rate or reaching MDA too far before the Visual Descent Point VDP could cause TAWS alerts If a TAWS WARNING is issued immediately follow the TAWS WARNING procedure in the EMERGENCY PROCEDURES Section of this AFMS 7 After Leveling at SET Missed Approach Altitude In Altitude Preselect RNAV GPS LPV or LNAV VNAV 1 Load the approach into the Active Flight Plan 2 Approach 400 SET ON TMR REF page IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control Panel PRESS HDG to fly ATC radar vectors b PROC button on PFDs or MFD SELECT ACTIVATE VECTORS TO FINAL NOTE SUSP may annunciate on the HSI when Vectors To Final is selected The flight plan will automatically unsuspend when the airplane intercepts and turns inbound on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish e VERIFY Lane nons Course pointer slews to the front course d Mode Control PRESS APR Verify GPS and GP armed 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 59 of 95 IF Flying Full Approach Including Transition 3 Airplane cleared to an initial approach fix a ACTIVATE THE APPROACH from the PROC p
84. n autopilot processor control wheel mounted elevator trim switches copilot s side optional control wheel mounted autopilot yaw damper disconnect and trim interrupt switch A P Y D DISC TRIM INTRPT control wheel mounted CWS Control Wheel Steering switch and a go around switch mounted in the left throttle knob The following conditions will cause the autopilot to disconnect e Electrical power failure including pulling the circuit breaker e Electrical power failure to the GMC 710 Autopilot Mode Controller including pulling the CTL circuit breaker e Internal autopilot system failure e Malfunction of either AHRS two fully functional AHRS are required for the autopilot to function e Failure of the on side PFD e Depressing the red A P Y D DISC TRIM INTRPT button on the pilot s or copilot s if installed control wheel e the left section of the manual electric trim split switch pilots and copilot s control wheel e Pushing the AP button on the autopilot mode controller when the autopilot is engaged e Pushing the GO AROUND button on the left throttle e Turning OFF the Avionics Master Power Switch 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 81 of 95 CAUTION Turning OFF the Avionics Master Power Switch will cause the autopilot to abnormally disconnect and the yaw damper to disconnect An abnormal autopilot disconnect is normally annunciated visually by a red flashing AP
85. nd of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 151 Street Olathe KS 66062 USA Telephone 913 397 8200 www garmin com Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 2 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 Aircraft REV PAGE DATE OF FAA APPROVED NO NO S DESCRIPTION APPROVAL A ALL Original Issue 11 08 2007 Robert G Murray DAS Administrator Garmin International Inc DAS 240087 CE Robert G Murray B ALL Repaginated 11 21 2007 DAS Administrator Garmin International Inc DAS 240087 CE C 17 24 Added Non essential equipment See Cover See Cover listto DUAL GENERATOR FAILURE procedure added GDU cooling fans to minimum equipment list editorial updates 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 3 of 95 This page intentionally left blank
86. ng enough to reference magnetic compass or the pilot should descend to a warmer altitude if terrain fuel and endurance permit Display Unit Failure PFD FAILURE PFD failure is indicated by a complete loss of image on a display The pilot should use the cross Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 36 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 display of primary flight information and the engine instruments on the MFD 1 DISPLAY BACKUP Button on audio panel of affected PRESS The DISPLAY BACKUP button can be pressed again to return the MFD to its normal presentation With the MFD in its normal display presentation the pilot has access to functions and pages unique to the MFD that are not accessible when the MFD is in the composite display NOTE The CDI SYNC and BARO SYNC settings must be ON to allow the operating PFD s controls to affect settings on the MFD when the MFD is in the Display Backup mode These settings are accessible on the MFD when in the normal display presentation on the AUX SYSTEM SETUP page Autopilot Mode TRANSFER XFR button to operating PFD AUtOp lots et ee ati TE
87. oa 13 1331 90 ONIHSINENS uv OHINOO sna 30180 r 0HINO0 4 3318 A N N N IEN 5 5 5 9 4 mm St s n o rphl h ar s NEN NN VO CQ P AMIS 240 2007 25867 2039 n ans 30 ong H3HIVaM WIN3ANOH AN3 PT Mw wn 18938 103404 N N s 2 2 2 1 2 Ney Mesh NA 39095 407 viva GN N39 NEO ANS WHOIS 6093 sowas ON m EON Den von 2109000 Pos y s N 4 9 sz 1 6 u es i N ONS NES XZ NZ 54 Nc 503 SOINOIAV me 9953 Nd 8 SNWS 30 JASON Nd ans Wi9 dad 300801 HISNI 71081409 ZON ZON ZON ZON pi 185 HOLON 7 N N 9 s s 1 6 N N Z U NS NS Nod CN NZ N WOdX WAOO 1331 9978 dV SIH9n IH9n3 4 1 ON H ON ON ON PN 1831 ino IHOR ON s s s 5 s s h s rYa Z XZ 52 e 4 SOINOIAY G
88. omplying with ICAO Annex 10 for IFR en route terminal area and non precision approach operations including those approaches titled GPS or GPS and RNAV GPS approaches The G1000 Integrated Avionics system installed in this aircraft is approved for approach procedures with vertical guidance including LPV LNAV VNAV and LNAV V within the U S National Airspace System The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the requirements for GPS as a Primary Means of Navigation for oceanic and remote navigation RNP 10 per FAA AC 20 138A FAA Order 8400 12A and FAA Order 8700 1 when used in conjunction with Garmin WAAS Fault Detection Exclusion WFDE Prediction Program part number 006 A0154 01 or later approved version with Comant Cl 428 200 or Comant Cl 428 410 antennas selected This does not constitute an operational approval Both GPS SBAS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation LRN sensor The G1000 WFDE predication program works in combination with the Garmin AT Inc Route Planning Software version 1 2 or later approved version The route planning and WFDE prediction program can be downloaded from Garmin G1000 website on the internet For information on using the WFDE Prediction Program refer to Garmin WAAS Prediction Program part number 190 00643 01 WFDE Pr
89. on RNAV Operations in Designated European Airspace 7 1 Required Functions 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 ELECTRONIC FLIGHT BAG The G1000 Integrated Avionics System as installed in this aircraft supports approval of AC 120 76A Hardware Class 3 Software Type C Electronic Flight Bag EFB electronic aeronautical chart applications when using current FliteChart or ChartView data Additional operational approvals may be required For operations under 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 aircraft 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 8 of 95 Section 2 Limitations INTRODUCTION G1000 Cockpit Reference Guide for Hawker Beechcraft C90A GT CRG must be immediately available to the flight crew Use the 21000 Cockpit Reference Guide for Hawker Beechcraft C90A GT Garmin part number 190 00664 00 revision C or later approved revis
90. only basic modes 1 ROL and PIT be selected initially If this proves satisfactory HDG and ALT may then be selected Ensure navigation systems are set up correctly prior to attempting to engage NAV mode 4 Autopilot i oem ENGAGE AS DESIRED if flight director commands are appropriate If unable to restore Flight Director 5 PD Button u L net MAS PRESS to remove Flight Director from PFDs Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 42 of 95 BOTH ADC1 BOTHONADC2 ELSE DELL 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 the copilot s side displays ADC 2 information Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 PFD displaying data from opposite ADC SENSOR softkey PRESS 2 OF ADG Z SOTMKCY rer c trt tee SELECT on side ADC ADC1 for Pilot PFD ADC2 for copilot PFD 3 PFD Displays CONFIRM BOTH ON ADC 1 or BOTH ON ADC 2 message clears on both PFDs BOTH AHRS 1 AHRS2 This message is displayed on both PFDs and indicates that both pilot and copilot PFDs displaying data from the same Attitude Heading Reference
91. rence Guide for additional information 1 2 Refer to STANDBY ATTITUDE indicator to determine which AHRS is providing the most accurate data Use SENSOR softkey to select the most accurate AHRS on the affected PFD HEADING MISCOMPARE This message is displayed when the G1000 detects a difference between the pilot s and copilot s heading information displayed in the upper right of the PFD Refer to GARMIN G1000 Cockpit Reference Guide for additional information Te m WSHLD ANTI ICE Switches PILOT CABIN TEMP MODE Selectors rannin a ELECHEAT E OFF Refer to Magnetic Compass to determine which AHRS is providing the most accurate heading information Use SENSOR softkey to select the most accurate AHRS on the affected PFD WSHLD Switches u itte Eee tara AS REQUIRED CABIN TEMP MODE uuu retenti neri eerte tae dta terere ipu qasi AS DESIRED ElEEGTPIEAT ere rere eran etu int EE EE AS REQUIRED NOTE The magnetic compass is affected by windshield anti ice air conditioner and electric heat These items must be turned OFF prior to referencing magnetic compass heading and then may be reselected ON With windshield anti ice OFF windshield may form fog or frost on the inside surface The windshield anti ice should be turned off only lo
92. rimary system is most accurate 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 33 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 with the correct local altimeter setting set GPS altitude will usually be within 600 feet or better of the correct indicated altitude Use the following guidelines to help estimate correct altitude from non standard conditions e Temperatures WARMER than standard can cause GPS altitude to read HIGHER than indicated altitude e Pressures LOWER than standard can cause GPS altitude to read HIGHER than indicated altitude gt IF ABLE TO IDENTIFY ACCURATE ALTITUDE SOURCE 6 Use SENSOR softkey to select most accurate ADC on both PFD s gt IF UNABLE TO IDENTIFY ACCURATE ALTITUDE SOURCE 6 Avoid IFR conditions if possible consider diversion to visual conditions and LAND AS SOON AS PRACTICAL 7 Maintain altitudes based on LOWEST indicated altitude 8 Advise of inability to verify correct altitude 9 If unable to descend into visual conditions an ILS or RNAV GPS LNAV VNAV approach with course intercept well outside the Final Approach Fix FAF 10 Once glideslope or glidepath is captured determine most accurate altitude source when crossing FAF 11 Reference ILS Dec
93. ronization of the propellers When the propellers are operating at the same rpm the display will show stationary diamond symbols As one propeller begins to turn faster than the other propeller the diamonds will begin to move towards the faster turning propeller and transition into an arrowhead pointing towards the faster turning propeller The transition to a full arrowhead is complete when the propeller speed difference is equal to 50 rpm This instrument aids the pilot in obtaining synchronization of the propellers Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 86 of 95 PROPELLER SYNCHROPHASER A push button ON OFF switch is located on the instrument panel below the pilot s PFD that turns the propeller synchrophaser ON and OFF To turn the propeller synchrophaser ON push the PROP SYNC switch A green ON annunciator will illuminate when the system is on To turn the propeller synchrophaser OFF push the PROP SYNC switch Refer to the Systems Description section in the airplane s original Pilot s Operating Handbook and FAA Approved Airplane Flight Manual for a description of the synchrophaser and its operation ELECTRICAL SYSTEM INVERTERS The two solid state inverters are not needed with the G1000 system and have been removed POWER DISTRIBUTION There are no changes to the electrical power generation power feeders control or fault protection Only the Avionics power distribution has changed AVION
94. roper VOR frequency 2 Approach SET ON TMR REF page IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control Panel PRESS HDG to fly ATC radar vectors b PROC button on PFDs or MFD SELECT ACTIVATE VECTORS TO FINAL NOTE SUSP may annunciate on the HSI when Vectors To Final is selected The flight plan will automatically unsuspend when the airplane intercepts and turns inbound on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish ex HSN ED t emet PRESS until VOR navigation source To be used for the approach displays d mtt e Set to inbound course e Mode Control Panel PRESS APR verify VAPP armed IF Flying Full Approach Including Transition 3 Airplane cleared to an initial approach fix a ACTIVATE THE APPROACH from the PROC page Or ACTIVATE a DIRECT gt the IAF tuan SELECT GPS nav source c Mode Control eee PRESS NAV GPS mode NOTE Ensure groundspeed is less than 200 KTS within 1 minute of the IAF d When Established Inbound to the PRESS CDI softkey until VOR navigation source to be used for the approach displays Autopilot
95. rue airspeed last known wind data and the last known GPS position to estimate the airplane s current position e MAP TRAFFIC MAP display is not dependent on GPS information The position of displayed traffic relative to the airplane symbol on the map is still accurate LOSS OF INTEGRITY LOI MODE ACTIVE WHEN THE AIRPLANE IS WITHIN 30NM OF THE DESTINATION OR DEPARTURE AIRPORT AS CALCULATED FROM THE PREVIOUS GPS OR DR POSITION 1 Navigation Fly towards known visual conditions Use ATC or other information sources as possible NOTE e All information derived from GPS or DR will be removed from the displays TAWS IS INOPERATIVE Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 38 of 95 e 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 LNAV VNAV or LNAV V approach if the Horizontal or Vertical alarm limits are exceeded the G1000 System will downgrade the approach This will be annunciated in the ALERTS window and by an annunciation change on the HSI from LPV L VNAV or LNAV V to LNAV GPS glide path vertical guidance will be removed from the PFD The approach may be continued using the LNAV only minimums During any GPS approach in which both precision and non precision alarm limits are exceeded the G1000 System
96. s are powered from the Hot Battery bus PITOT AND STATIC SYSTEM PITOT The pitot heads are the sources of impact air for the operation of the flight instruments A heated pitot mast is located on each side of the lower portion of the nose Tubing from the left pitot mast is connected to the pilot s Air Data Computer ADC1 and tubing from the right pitot mast is connected to the copilot s Air Data Computer ADC2 and the standby airspeed indicator The switch for the PITOT LEFT RIGHT OFF is located in the ICE PROTECTION group on the pilot s right subpanel Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 92 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 standby instruments Each of the normal static air lines opens to the atmosphere through two static air ports one on each side of the aft fuselage four ports total An alternate static air line is also provided for the pilots Air Data Computer ADC1 the event of a failure of the pilot s normal static air source if ice accumulations should obstruct the static air ports the alternate source can be selected by lifting the spring clip retainer off the PILOT S EMERGENCY STATIC AIR SOURCE valve handle located on the right side panel and moving the handle aft to the
97. s the master switch for PILOT PFD STBY INSTR OVHD PED amp SUBPANEL SIDE PANEL CLOCKS and COPILOT PFD PILOT PFD Controls the brightness of the pilot s PFD STBY INSTR Controls the brightness of the internal lighting for the standby attitude indicator standby altimeter and standby airspeed indicator MFD Controls the brightness of the Multi Function Display MFD OVHD PED amp Controls the brightness of the backlighting of the overhead light control panel SUBPANEL and internal lighting of the overhead electrical gauges throttle quadrant backlighting internal lighting for pedestal mounted gauges and the MFD Controller panel backlighting and the subpanel backlighting SIDE PANEL Controls the brightness of the backlighting of the right side circuit breaker panel the left side circuit breaker panel and the fuel gauge panel CLOCKS Controls the brightness of the clocks mounted in the pilot s and copilot s control wheels COPILOT PFD Controls the brightness of the copilot s PFD Separate rheostat switches individually control the instrument indirect lights in the glareshield and overhead map lights An INSTRUMENT EMERG LIGHTS switch is located on the right side of the overhead electrical gauge panel This switch turns on indirect lights under the glareshield These lights are separate from the Instrument Indirect lights The brightness of the Emergency Lights is not controllable These light
98. seconds and then extinguishes e Servos disengaged f PUSH the AP Button on the Mode Control VERIFY Autopilot Engages g Copilot s Control Wheel AP YD DISC TRIM INTRPT Button 55 VERIFY Autopilot Disconnects h Manually Operate Elevator Tab Wheel VERIFY Pitch Trim Servo is Not Engaged 2 Electric Elevator Trim a Pilot s Control Wheel Left and Right Segment sse ACTUATE INDIVIDUALLY Verify there is no elevator tab wheel movement Left and Right Segment ACTUATE TOGETHER Verify proper elevator tab wheel movement e With Elevator Tab Wheel in Motion AP YD DISC TRIM INTRPT 2 44048000 PRESS AND HOLD verify elevator tab wheel motion stops e Manually Operate Elevator Tab Wheel VERIFY Pitch Trim Servo is Not Engaged b Copilot s Control Wheel If Installed Left and Right Segment ACTUATE INDIVIDUALLY Verify there is no elevator tab wheel movement Left and Right Segment sse ACTUATE TOGETHER Verify proper elevator tab wheel movement e With Elevator Tab Wheel in Motion AP YD DISC TRIM INTRPT PRESS AND HOLD verify elevator tab wheel motion stops 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 51 of 95 e Pilots Tiim
99. selected The flight plan will automatically unsuspend when the airplane intercepts and turns inbound on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish VERIFY itt iR ipa Course pointer slews to the inbound course Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 60 of 95 Mode Controllers PRESS APR Button GPS will be the active lateral mode GP will ARM if the procedure provides vertical guidance IF Flying Full Approach Including Transition 3 Airplane cleared to an initial approach fix a ACTIVATE THE APPROACH from the PROC page Or ACTIVATE a DIRECT TO gt the IAF b HISbEGDIzz suite bte dete etae des SELECT GPS Nav Source c Mode Controller 0 PRESS APR Button GPS will be the active lateral mode GP will ARM if the procedure provides vertical guidance NOTE Ensure groundspeed is less than 200 KTS within 1 minute of the IAF 4 Established inbound on Final Approach Course FAF Active Waypoint c VERIFY Course Pointer is set to the final approach course d VERIFY LNAV V or LNAV is annunciated on the HSI e VERIFY GP Deviation Scale Displays if applicable f SET Minimum Descent Altitude MDA Altitude In Altitude Preselect 5 iion tini tes MAINTAIN 110 KIAS OR GREATER Recommended CAUTION Some RNAV GPS approaches provide a vertical d
100. t Vertical navigation will only function when the navigation source is GPS navigation VNAV will not function if the navigation source is VOR Localizer or ADF The airplane s heading must be within 75 of the desired GPS course and within 10 NM cross track error in order of VNAV to function VNAV functions only for enroute and terminal descents Vertical navigation is not available during climbs or descents between the final approach fix FAF and the missed approach point MAP Refer to the G1000 Cockpit Reference Guide for additional information 1 Once clearance from has been received RESET Altitude Preselect to the vertical clearance limit 2 PRESS within 5 minutes of the top of descent TOD NOTE If the VNV button is pressed more than 5 minutes before the TOD or the altitude preselect is not reset to a lower altitude VPTH will begin to flash inverse video white black when the aural alert Vertical Track annunciation sounds Pressing the VNV button and or resetting the altitude preselect to a lower altitude cancels the flashing and the AFCS will capture and track the vertical profile If VNV button is not pressed or the altitude preselect is not reset to a lower altitude VPTH stops flashing at the TOD and the airplane will remain in ALT mode and not descend ALTV will be the armed vertical mode during the descent if the altitude preselect is set to a low
101. tent loss of attitude and heading displays while the aircraft in on the ground cue o eet ei tut pes CHECK a Compare attitude displayed by PFD1 PFD2 and Standby Attitude Indicator b Compare altitude displayed by PFD1 PFD2 and Standby Altimeter c Verify the correct barometric pressure is set in the PFD1 PFD2 and Standby Altimeters d Compare heading displayed by PFD1 PFD2 and Magnetic Compass NOTE The standby compass is erratic when windshield anti ice air conditioner or electric heat is ON Windshield anti ice air conditioner and electric heat must be OFF for heading verification check e Verify turn rate and slip indicator display appropriately Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 50 of 95 BEFORE TAKEOFF RUN UP 1 AUTO 0 ts a PUSH the AP Button on the Mode Control Panel VERIFY Autopilot Engages b Verify ROL AP YD PIT annunciated in green on the PFDs c Control Wheel PULL FULL Verify Elevator Tab Wheel moves in the DN direction d Control Wheel PUSH FULL VERIFY Elevator Tab Wheel moves in the UP direction e Pilot s Control Wheel AP YD DISC TRIM INTRPT Button PRESS VERIFY Autopilot Disconnects e Autopilot Disconnect Tone Sounds e Amber AP and YD flashes for 5
102. th 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 Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 PILOT S PFD SENSOR PRESS 2 PILOT S PFD ADOT Softkey ic scccs ccleccseeccaccihevesacasneedbessbivaeecpheanseetiavaseautaneieshngnnssdtenatenerd PRESS 3 PFD Displays 21 CONFIRM BOTH ADC1 message displayed on both PFDs 4 COPILOT S PFD SENSOR PRESS 5 COPILOT S 2 PRESS 6 PFD Displays CONFIRM BOTH ON ADC 1 message clears on both PFDs XSIDE AHRS EE This message is displayed on both PFDs and indicates that both PFDs are displaying data from the opposite side Attitude Heading Reference System Normally the pilot s side displays AHRS 1 and the copilot s side displays AHRS 2 Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 PILOT S PFD SENSOR Softkey sse PRESS 2 PILOTS PFD AHRS 1 Softkey 1 A nnns PRESS 3 PFD Displays CONFIRM BOTH ON AHRS1 message displayed on both PFDs 4 QCOPILOT S PFD SENSOR
103. tinue to operate the autopilot in a normal manner after the annunciation extinguishes IF THE ANNUNCIATOR REMAINS ILLUMINATED OR REAPPEARS WITH NO CHANGE IN AIRSPEED OR CONFIGURATION FROM THE PREVIOUS TRIMMED CONDITION 39 Control Wheel eot e net i n bec A Rer die a EL ene GRIP FIRMLY 4 Elevator Tab ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTINGUISHES 5 AP YD DISC TRIM INTRPT PRESS and RELEASE Pilot s or Copilot s control wheel 6 Pitch Trim USING ELEVATOR TAB WHEEL MANUALLY RETRIM AIRPLANE Autopilot should be considered inoperative until the cause of the mistrim has been investigated and corrected Yaw damper may be re engaged and used normally Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 30 of 95 RUDDER MISTRIM amber RUD RUDS 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 occur the autopilot is disconnected while this message is displayed high rudder pedal forces and yawing motion are possible The following procedure should be followed 1 Rudder Pedals nde I nadine HOLD FIRMLY 2 Rudder
104. wed Control e tote eit uot edet ee au reer terre eer rer peers GRIP FIRMLY 2 Aileron Tab ROTATE SLOWLY IN DIRECTION OF INDICATED MISTRIM UNTIL THE ANNUNCIATION EXTINGUISHES IF THE ANNUNCIATOR STAYS EXTINGUISHED AND NO OTHER ANNUNCIATIONS ILLUMINATE e Continue to operate the autopilot in a normal manner after the annunciation extinguishes IF THE ANNUNCIATOR REMAINS ILLUMINATED OR REAPPEARS WITH NO CHANGE IN AIRSPEED OR CONFIGURATION FROM THE PREVIOUS TRIMMED CONDITION 3 Gontrol WEG m GRIP FIRMLY 4 Aileron Tab Knob ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTINGUISHES 5 AP YD DISC TRIM INTRPT Button eene PRESS and RELEASE Pilot s or Copilot s control wheel 6 Roll USING AILERON TAB KNOB MANUALLY RETRIM AIRPLANE Autopilot should be considered inoperative until the cause of the mistrim has been investigated and corrected Yaw damper may be re engaged and used normally ELECTRIC PITCH TRIM INOPERATIVE NOTE This condition may be accompanied red or Millis annunciation on the PFDs 1 Move both halves of pilot and copilot pitch trim switches to check for stuck switch 2 AFCS SERVOS Circuit PULL and RESET Right circuit breaker panel The autopilot will enter Pre Flight Test PFT mode when the AFCS SERV
105. will no longer provide TAWS alerting or display relative terrain elevations The crew must maintain compliance with procedures that ensure minimum terrain separation 190 00682 02 Rev C Hawker Beechcraft C90A and C90GT King Air Page 45 of 95 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev C Page 46 of 95 Section 4 Normal Procedures Table of Contents COM RADIO COMMUNICATIONS BEFORE STARTING ENGINES 49 BEFORE STARTING GA LC LER LUE RE 49 BEFORE TAX S a btt bieten idet 49 TAX 50 BEFORE TAKEOFF 51 BEFORE TAKEOFF FINAL ITEMS yin cus et niu adi eu exe evi ndi at obe e CO dE Sad suo d 52 ON TAKEOFF ROL en 52 CLIMB CRUISE AND 201 asu nuda ao card na T 52 SHUTDOWN AND SECURING 5 anres prono o ru rao o ca kr J T 52 AUTOPILOT OPERATION 53 Vertical Modes 53 Vertical Speed VS os can in eae cr ah 53

Download Pdf Manuals

Related Search

Related Contents

Drawing graphs with dot  owner`s manual 18apv read and save these instructions  Philips 6000 series Full HD LED TV 47PFT6309  AudioQuest 1.5m Cinnamon FireWire (IEEE-1394)  3D Connexion Version 6.6 Two  Twist 359 - Help and support  FUNAI CR130TT8 CRT Television User Manual  Retrouvez plus d`infos dans le fichier PDF  POE-SW1616 User Manual - Surveillance System, Security    

Copyright © All rights reserved. Failed to retrieve file