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Garmin C90A/GT Airplane Flight Manual Supplement

1. 47 MED FAILURE ee a ania aada Enaisi 48 DUAL GPS SBAS FAILURE AMBER DR OR LOI ON HSI cernere nnns 49 GPS APPROACH ALARM LIMITS EXCEEDED nnnm nnne nnn nn ann nennen nnn 50 LOSS OF RADIO TUNING FUNCTIONS 50 FAILED AIRSPEED ALTITUDE AND OR VERTICAL SPEED nennen nnns 51 FAILED ATTITUDE AND OR 51 ENGINE INDICATION SYSTEM EIS FAILURE eseeeeeeeeeeeeee eee nnne nnne nn anna n nnne 53 LOSS OF NAVIGATION 2 ice nutre 53 INACCURATE FLIGHT DIRECTOR DISPLAY 53 BOTH ON ADC1 BOTH ON 2 54 BOTH ON AHRS 1 BOTH ON AHRS 2 54 BOTH ON GPS 1 BOTH ON GPS 2 54 ADG 7 55 MSIDE DES 55 SYNTHETIC VISION tarea 55 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air
2. o EUM Kar MIS LPV or L VNAV is annunciated on the HSI Ce GP Indicator Displays 02 VERIFY xxiii dimer ttt eut e E SUSP is not displayed on HSI SET austettuefere e deir e RE Eee Missed Approach Altitude In Altitude Preselect 5 AltSpeed an dide oat MAINTAIN 110 KIAS OR GREATER Recommended 6 VERIFY Airplane Captures and Tracks GPS Course Captures and tracks GP 7 AT Decision Altitude DA c A P Y D DISC TRIM INTRPT 71 PRESS Continue visually for a normal landing Or d GO AROUND button on left PRESS Execute Missed Approach Procedure 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 71 of 117 RNAV GPS LNAV LNAV V 1 Load the approach into the Active Flight Plan 2 Approach 5 SET ON TMR REF page if not already set IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control 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 inbo
3. PRESS APR verify VAPP active or armed 4 Established inbound on Final Approach Course VERIFY ticis e htt eter tentes Course Pointer is set to the inbound course cet A EN ee te 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 Aitspeed ieni ee MAINTAIN 110 KIAS OR GREATER Recommended Atthe EAE iut Use desired vertical mode to fly the approach s vertical profile Use Altitude Preselect to level off at intermediate altitudes and at the MDA It is recommend to descend at 1000 ft min orless 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 SET Missed Approach Altitude In Altitude Preselect Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 74 of 117 BACK COURSE BC 1 Load the approach into the Active
4. ERECT and NORMAL Fail Flag not in view ON TAKEOFF ROLL This procedure should be conducted after brake release during the takeoff roll but before becoming airborne 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 These procedures should be conducted after the Battery and Generator Switches have been turned OFF in the AFM SHUTDOWN AND SECURING checklist and before the flight crew vacates the cockpit 1 Standby Battery PRESS OFF a Standby Battery 5 ARMED and ON EXTINGUISHED 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 D Page 64 of 117 OTHER PROCEDURES 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 s
5. GSA 80 Roll Servo GSA 80 L Yaw Servo lt lt gt GSA 81 Pitch Trim Servo lt Pilot s Control Figure 12 GFC 700 System Interface GDU 1040A PFD2 No 2 GIA 63W AFCS Mode Logic Flight Director Servo Mat Copilot s Control 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 97 of 117 FLIGHT CONTROLS AFCS AUTOPILOT AND FLIGHT DIRECTOR The GFC 700 is a digital Automatic Flight Control System AFCS fully integrated within the G1000 System avionics architecture The GFC 700 is a three axis autopilot and 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 e Vertical lateral mode selection and processing e Autopilot communication Yaw Damper YD The yaw servo is self monitoring and provides Dutch ro
6. VERIFY Elevator Tab Wheel moves in the DN direction d Control Wheel PUSH FULL FORWARD 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 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 PRESS VERIFY Autopilot Disconnects h Manually Operate Elevator Tab Wheel VERIFY Pitch Trim Servo is Not Engaged 2 Electric Elevator Trim Control ssessssssssesesesseee eene nennen nnne nente CHECK a Pilot s Control Wheel Left and Right Segment sse 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 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 IND
7. CONFIRM BOTH ON AHRS1 message displayed on both PFDs 4 COPILOT S PFD SENSOR Softkey sse ener enne PRESS 5 COPILOT S PFD AHRS2 5 PRESS 6 PFD Displays CONFIRM BOTH ON AHRS 1 message clears on both PFDs SYNTHETIC VISION If SVS displays information inconsistent with G1000 primary flight instrumentation On the PFD 1 puc PET PRESS SYN PRESS 9 SYN TERR hve PRESS 4 SVS is removed from both PFD 5 VERIFY Use G1000 primary displays for navigation and aircraft control 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 55 of 117 If G1000 operation in display backup mode is required Select display backup mode on the G1000 system When display backup mode is selected the MFD will initially present a non SVS blue sky over solid brown ground display SVS will be presented on the backup display within 20 seconds if it was enabled on the PFD when display backup was selected 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
8. PRESS CDI softkey until LOC navigation source to be used for the approach displays Autopilot Flight Director Mode will automatically change to ROL tz VERIFY eat Att sta te ttu Course Pointer is set to the Front Course 0 Mode Control 424044 1 10 0000 enne einen ennt sitne PRESS BC Verify BC mode is armed or active 4 Established inbound on Final Approach Course VERIFY anth reet Eo ettet oes Course Pointer is set to the front course Dic VERIFY unii ette eee toit LOC is annunciated on the HSI 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 75 of 117 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 Airspeed uiuere nete MAINTAIN 110 KIAS OR GREATER Recommended Atthe FAT ioannes Use desired vertical mode to fly the approach s vertical profile Use Altitude Preselect to level off at intermediate altitudes and at the MDA It is recommend to descend at 1000 ft min orless Descending at a higher rate or reaching MDA too far before the Visual Descent Po
9. s s s s sys Gee 51 1v8 2 4 Jo NEA EF NY QS NA 1 VIO LSHHY 1054 B i431 1 ii oun TWis H3MOd NEVM SOINOIAY S3NION3 ONINSVAA Figure 9 Right Side Circuit Breaker Panel SN LJ 1063 LJ 1360 amp LJ1362 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 94 of 117 iva XDV H3MOd ABYINOO3S 3 1HOlH s s s 9 9 s St 01 1009 LSHHY 10 sed 19101 ANSA SEP ERE om WIV Sng u31H9r1 Ihe H G 53 US Hee 5 nes E AGLS 3dOW NIB VO SOINOIAV imnoa l 1431 uVOIO TOUNO aL L ONIHSINHhd uv iy HOHINOO sna 3030 r 0HINOO 34 03379 2 4 s s s s SL Ol eS 5 s s 5 sj 249 arise cage RL 301 Ec ah H3HIV3M TWLNAWNOUIANS 58 LIV ANT YOM 1 nee ees z s 4 s s HOlVM 39095 Oldvy viva HISNI ANS WHOIS ONI A cece voona SOAH3S LON ON 1HOlH 1HOlH 1H9lH HO DNIQv3H 54109 3109 00 19008 z s en s GL s s 0 6 5 5051 SOINOWV 1 ner 99894
10. 30 PITCH AXIS FAILURE E DDEL O s 30 ROLL AXIS LT k URE Aaa aa E Saia aa AAS 31 YAW AXIS FAILURE aa aaae ae e aa aa a eA ae A a aa aae a ra a aaraa aiaa 31 PITCH TRIM E T ENT i 31 AUTOPILOT PRE FLIGHT TEST FAIL eere nn nns n nne s nna stria nnns sensns 32 AUTOPILOT OVERSPEED RECOVERY eese enne ener nnne 32 ENGINE FAILURE AUTOPILOT ENGAGED 1 32 ELECTRICAL SYSTEM EUR SR DEP VH 32 DUAL GENERATOR FAILURE L GEN OFF R GEN 32 M 34 TAWS c 34 34 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 27 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 28 of 117 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 unexpe
11. SNv4 H3IJW 4G jog HG 201 INS ON Nd ns SNOYOL any HISNI JOHINOO ZON ZON ZON ZON AGLS BONI HOLOW 8 s s 90 5 5 5 g s 0 ony WWOO SOINOIAY 1431 491 1430 1991 OW do BA SIHON 1HOnd LON LON 10 ON 1531 1HOlH s s s 9 9 5 5 9 8 5 5 SS ony WWOO SOINOIAV GAN AOD SS3Hd ISNI H3MOd JOHINOO NNY 10 VNOIS HOIlINO 1915 NHVM ONIONYI AdVI iHd H3Hlv34 8 9 5 6 5 5 5 5 5 LO v 15 Ladd olny nm TVIS H3MOd NHVM SOINOIAY S3NION3 ONINEWM c N39 NAD iva 1vd c N39 N39 iva on SN LJ 1063 t Breaker Panel Alternate Configurati Figure 10 Right Side C LJ 1360 amp LJ 1362 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 95 of 117 E 8 T B v 9 Figure 11 Pedestal Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 96 of 117 No 1 GIA 63W AFCS Mode Logic Flight Director Servo Mot Multi Function GDU 1040A PFD1 i GSA 80 Pitch Servo 4 amp
12. E AEA 66 LATERAL MODES 67 NAVIGATION EET 67 INAVIGATIONAGBPS DIREGA 67 NAVIGATION amp ds 68 APPROACHES 68 ta e to rtt dedi 68 IES GUDE SLOPE INOPERA TIVE aso cria E Rao eia ERES M whats 69 RNAV GPS LPV or LNAV VNAV ettet ttt ttt ttt ttt ttt ttes 71 RNAV GPS LNAV LNAV V asas tatc 72 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 59 of 117 M M RENE T I 73 BACK GOURBSE BG ste tiun E 75 AROUND m 76 SYNTHETIC VISION Sic 77 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 60 of 117 COM RADIO COMMUNICATIONS BEFORE STARTING ENGINES To obtain an ATC clearance before starting the engines 1 BAT Switeh Master e t cete eee acci ep eme E eda ie iuda ON 2 Avionics Master Pwr 0404 00 0 0 1 1 11 ON
13. 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 Button sss 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 48 of 117 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 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 appropria
14. sei uoce Sonet Exe eat boe ibi ea e IER Ee OFF All Exterior abstain dee OFF CINIS DEED ete OFF VENT BLOWER veter ie tan ca lek date de met AUTO GABIN TEMP MODE Selectric sito toe stu ruit Ed E eL EE E TR ERR ER este OFF INSTRUMENT EMERG ON if required INSTRUMENT INDIRECT lights sss 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 Audio 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 33 of 117 power the G1000 the standby battery will automatically power the standby attitude indicator altimeter vibrat
15. MANUALLY ADJUST ELEVATOR AILERON AND RUDDER TABS 4 AMODIO E etsi esp es eie eio in ie PRESS AP BUTTON if desired to RE ENGAGE 5 Rudder MANUALLY ADJUST AS REQUIRED AFTER POWER AND CONFIGURATION CHANGES ELECTRICAL SYSTEM DUAL GENERATOR FAILURE L GEN OFF R GEN OFF This procedure supersedes the AFM procedure in its entirety 1 Gent and Gen2 Generator SWIitChes ccccccsccceseescecesseeeeeseeeeeeeeseneeeeeseeeseesseneseesseeeaeesseneaeess OFF 2 Gen tret roster kan eto a dcr ne GEN RESET THEN ON 3 Operating DO NOT EXCEED 10096 LOAD Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 32 of 117 If Left Generator Will Not Reset 4 Gen T SWICK nee dete e La E a tva ugs OFF bi KGeOn2 SWIICH oe cta i da re tete ERR HIER ep ae GEN RESET THEN ON 6 Operating Generator DO NOT EXCEED 100 LOAD If Neither Generator Will Reset 7 Avoid FR conditions if possible and LAND AT THE NEAREST SUITABLE AIRPORT 8 Standby Battery INDICATES ARM or ON 9 Non essential equipment a b j Left and Right BOOST OFF Left and Right TRANS PUMP OFF OFF PROP ICE PROTECTION
16. PRESS Pilot s or Copilot s control wheel 2 Altitude CROSSCHECK BOTH PFDs with the Standby Attitude Indicator 3 Flight Director Modes nnn RESELECT AS DESIRED NOTE If continued use of the flight director is desired it is recommended that only basic modes i e 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 2 2 2 ENGAGE AS DESIRED if flight director commands are appropriate If unable to restore Flight Director b JED Buttons ata etie etd e ees PRESS to remove Flight Director from PFDs 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 53 of 117 BOTH ON BOTH ON ance 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 and Pilot s Guide for additional information 1 PFD displaying data from opposite ADC SENSOR PRESS 2 ADC1 or ADC 2 softkey 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 mess
17. 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 If Pilot and Standby Airspeed Indicator Agree Copilot Airspeed Differs 2 SENSOR Softkey Copilot s PFD PRESS 9 ADGCI SoftKey ice rta Cen eigen pity ee de Ete an or RR aa e dd Leap ad PRESS 4 PFD Displays CONFIRM BOTH ON ADCT annunciator is displayed on both PFDs If Copilot and Standby Airspeed Indicator Agree Pilot Airspeed Differs 2 Pilot and Copllot ALTITUDE iet tenia nee aaa Etude rer eed Ea e xad er penal NOTE If Pilot s and Copilot s Altitude Agree 3 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 maint
18. 1 103 PROPELLER SYNCHROPHASER Id 104 ELECTRICAL SYSTEM ccce ccce ce ce veces vete vu ce re cere co vete re co ve ove co vete te rv ve ro ve spe tr vere dear 104 INVERTERS ke DEP 104 POWER DISTRIBUTION 5 1 022 crc retur Input ratore rati dene stteevencrentceestas repecerbeseesedeevsectesteereente 104 STANDBY BATTERY POWER 0 nn anita natnm nnn tn nuni nn assa s anneanne nna 108 LIGHTING SYSTEMS 109 d pp PL T 109 AND STATIC SYSTEM 110 PITO Tine LI arts MI IM I El 110 m 110 GROUND 6 2 02 2 1 1 n nnn nnn n nnn nnn nnn nnns 110 SYNTHETIC VISION denial aAa A aea anA aeiaai adaha ienai 111 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 83 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 84 of 117 GENERAL This section supplements the Systems Description chapter in the airplanes original Pilot s Operating Handbook and FAA Approved Airplane Fligh
19. 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 35 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 36 of 117 Section 3A Abnormal Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEM 1 nnna 39 AILERON anime 39 ELECTRIC PITCH TRIM INOPERATIVE 39 ERE VAT OR dupl ec EE 40 RUDDER gni 41 FLASHING AMBER MODE ANNUNCIATION 42 YAW DAMPER AUTOMATIC DISCONNECT Amber Flashing 42 G1000 INTEGRATED AVIONICS SYSTEM cernens 43 ALTITUDE MISCOMPARE 11er rere eas eer Ee aaee aaa ee aa a a aa s raaa oeiee 43 2 DD iaiaaeaia a pee iaiaeiaeiaa 45 PITGH Eee ili aa dasa iai uadui eaea 46 ROLL MISCOMPARE Ier cotta ierit epe raaa ao e aa eren teg deseas 46 HEADING MISCOMPARE 5 1 12 Cerne accen aaa 46 DISPLAY UNIT FAILURE cce ccccccc ciere ceo ce cete coe cete cen ecce ecce cese cec 47 PFD FAILURE 5
20. Page 37 of 117 TAWS ABNORMAL 5 2 2 222 56 CAUT O N es eee a 56 I EXIIT 56 WAVERTPEnRREAVUEATOUEO 56 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 38 of 117 AUTOMATIC FLIGHT CONTROL SYSTEM AILERON MISTRIM amber or annunciation on PFD Indicates a mistrim of the ailerons while the autopilot is engaged The autopilot cannot trim the airplane in roll During large changes in 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 followed je EMT GRIP FIRMLY 2 Aileron Tab Knob 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 changes in airspeed or configuration from the previous trimmed condition m GRIP FIRMLY 4 Aileron Tab Knob ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTI
21. ON 915 7 305 p ONI is s Y fro Y s s SL 5 s s CeO ee VY NS 4 b uu bu pu NS uv oiany AV nm 1331 1331 dvi4 SHON HONS 1 LON LON LON LON 1531 me 1HO9iH va ONI yx PN FN s s 5 sz s ss Ho a s a ANOO SONOAY GaN AOD Hi DM EM 108INOO lo 9 HOLINO LUVIS ON ONT Ava H3HIV34 1 N3 ae 8 5 S O Om Om O a as a a a UBP d _ 120 SHHV olny on on on in Tis Nav SOINOIAV S3NION3 z N39 N39 iva z N39 N39 ive 1v8 t Breaker Panel SN LJ 1361 LJ 1363 and Subsequent Figure 8 Right Side C Page 93 of 117 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D ive 48004 AHYONOO3S 34 s s s s si y Z N35 NY 7 VE aad Woy bm id bu AS IW 1 Sav 10 uaMOd NN au 901 sna PM 1 19 ps x Hon iA 4 f t L 5 5 2 Z Iw Ns Nh pis ub No AGLS NISVO SOINOIAY wamog 13 1391 Bv9IO 3OuINOO SNIHSINHO3 uv Liv TE OHINO
22. TRIM INTRPT Button 2 2 PRESS and RELEASE Be prepared for possible high elevator control forces 3 AS REQUIRED USING ELEVATOR TAB WHEEL If Red Message Clears SABODIIDE ero hens eem Renan ENSE ELI IU RE ENGAGE If Red Message Hemains 4 eem M DO NOT RE ENGAGE 5 Elevator Trim CONTINUE TO USE ELEVATOR TAB WHEEL 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 31 of 117 AUTOPILOT PRE FLIGHT TEST FAIL Red ERER 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 AUTOPILOT OVERSPEED RECOVERY Yellow MAXSPD MAXSPD on PFD LE ecc REDUCE When overspeed condition is corrected 2 Autopllot Rede ele euius 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 22 2 PRESS and RELEASE 2 Engine Failure Procedure in EMERGENCY PROCEDURES Section of COMPLETE 3 Trim
23. 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 Hawker Beechcraft C90A and C90GT King Air Page 100 of 117 190 00682 02 Rev D 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 the copilot s control wheel f 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 prev
24. displayed in the upper right of the PFD Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 WSHLD ANTI ICE Switches PILOT and OFF 2 CABIN TEMP MODE nennen nnne nnne rennes OFF 3 eiim med ue MM eee OFF 4 Refer to Magnetic Compass to determine which AHRS is providing the most accurate heading information 5 Use SENSOR softkey to select the most accurate AHRS on the affected PFD 6 WSHLD Switches 2 2 00006 0000 00 enne nns AS REQUIRED 7 CABIN TEMP MODE d er o etra e ra tren AS DESIRED ELEG HEAT RAI uie eee 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 long enough to reference magnetic compass or the pilot should descend to a warmer altitude if terrain fuel and endurance permit Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 46 of 117 DISPLAY UNIT FAILURE PFD FAILURE PFD failure is indicated by a complete loss of image on a display The pilot should use the cross side PFD and the standby flight instrum
25. D Page 80 of 117 This page intentionally left blank 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 81 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 82 of 117 Section 7 Systems Description Table of contents 31000 INTEGRATED AVIONICS rien rapa nara ua aan aua nara annua gna nana naga aud 85 Ei cand Rejd2dlidl 85 INSTRUMENT PANEL 2 tree rennen sp concede Euren 85 EBIGHIE GONTBOLS uds aaO Ces cV REN ERIS 98 AFCS AUTOPILOT AND FLIGHT nnn 98 ELECTRIC ELEVATOR TRIM 2 2 a 101 FLIGHT INSTRUMENTS cicer 102 1000 FLIGHT INSTRUMENTS 1 7 tenere reciente nentur erint neuen 102 STANDBY FLIGHT 102 ENGINE 4 22 4 422222111 11
26. ENGINE ENGINE L Engine Fire Extinguisher Optional R Engine Fire Extinguisher Optional Autofeather Optional Fire Detector Optional L Igniter Power L Start Control L Torque L Signal Conditioner VMI L Engine Instrument GEA L Fuel Flow L Oil Pressure R Igniter Power R Starter Control R Torque R Signal Conditioner VMI R Engine Instrument GEA R Fuel Flow R Oil Pressure FLIGHT INSTRUMENTS Standby Attitude Indicator Gyro Standby Altimeter Vibrator FLIGHT INSTRUMENTS 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 Optional LANDING GEAR Landing Gear Control 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 107 of 117 TRIPLE FED BUS HOT BATTERY BUS STANDBY BATTERY LIGHTS LIGHTS LIGHTS Standby Altimeter Internal Lighting Standby Attitude Indicator Internal Lighting Standby Airspeed Indicator Internal Lighting Entrance amp Aft Dome Lights Cabin Flour Lights Instruments Indirect Lights Navigation Lights PROPELLERS Propeller Governor Test WARNING ANNUNCIATORS Annunciator Indicator Annunciator Power L Oil Pres
27. 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 D Page 42 of 117 G1000 INTEGRATED AVIONICS SYSTEM ALTITUDE 171 This message is displayed when the G1000 detects a difference of 200 feet or greater between the pilot s and copilot s altitude information Refer to the G1000 Cockpit Reference Guide for additional information 1 Altimeter 0 VERIFY both pilot and copilot have the correct barometric altimeter 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 If Pilot and Standby Altimeter Agree Copilot Altimeter Differs 3 SENSOR Softkey Copilot PED iita tie itti t teli ent taedet nien doses ente e PRESS 4 ADOT SOMKCY mm PRESS 5 PFD Displays CONFIRM LLL annunciator is displayed on both PFDs If Copilot and Standby Altimeter Agree Pilot Altimeter Differs 3 Pilot s Static Air Source n
28. Flight VERIFY the G1000 tunes the proper LOC frequency 2 Approach SET ON TMR REF page if not already set 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 Cx HS CD lia PRESS until LOC Navigation Source to be used for the Approach Displays NERIFY etd Course Pointer is Set to the Front Course Mode Control Panel ee dee tree ri i Ph daa E in PRESS BC Verify BC mode is 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 TO P gt the IAF ae nies SELECT GPS c Mode Control PRESS NAV GPS Mode dz ne UE AS DESIRED e When Established Inbound to the FAF
29. 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 prohibited 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 pilot s responsibility to avoid hazardous weather using official weather data sources and the airplane s in flight weather radar Display of XM NEXRAD data is prohibited if XM ICING or XM TURBULENCE are displ
30. 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 abs ea 15 Nose Down Selected Altitude ALTS Capture Altitude Hold ALT Key ALT nnnnnFT Vertical Speed VS Key VS nnnn FPM 4000 to 4000 fpm 100 fpm Flight tevel FLC nnn KT 100 to 226 kt ik Change IAS Hold Flight Level FLC Key Change Mach FLC M M 0 25 to 0 46 0 01 Hold Vertical Path Tracking VNAV VNV 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 99 of 117 AFCS LATERAL MODES Maximum Roll Lateral Mode Control Annunciati
31. Or b GOAROUND button on left 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 SET on TMR REF page if not already set IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control PRESS HDG to fly ATC radar vectors b PROC button on PFDs or MFD SELECT ACTIVATE VECTORS TO FINAL 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 69 of 117 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 Co RSOB ui E e VERIFY CDI automatically changes to LOC Course pointer slews to the front course d Mode Control 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 cle
32. Red annunciator PFD e Indicates a failure of the pitch axis of the autopilot The autopilot will be inoperative NOTE If the red annunciator illuminates without the autopilot engaged it may indicate a faulted AHRS Monitor both PFDs and the standby attitude indicator for abnormal attitude indications Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 30 of 117 ROLL AXIS FAILURE Red annunciator on PFD e Indicates a failure of the roll axis of the autopilot The autopilot will be inoperative NOTE If the red WAM annunciator illuminates without the autopilot engaged it may indicate a faulted AHRS Monitor both PFDs and the standby attitude indicator for abnormal attitude indications 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 NOTE If the red annunciator illuminates without the autopilot engaged it may indicate a faulted AHRS Monitor both PFDs and the standby attitude indicator for abnormal attitude indications PITCH TRIM FAILURE Red annunciator on PFD 1 CONTROL WHEEL tette teer ir tee tet ec et vetet GRIP FIRMLY 2 AP YD DISC
33. TAWS TEMP TIS TMR TO TOD TSO VAPP Vde VDP VFR VHF VMC VMI VNAV VNV VOR VPTH VS WAAS WFDE WGS 84 WSHLD XFR XM XPDR XSIDE YD Standard Terminal Arrival Route Standby Supplemental Type Certificate Suspend Synthetic Vision System Software Synthetic Terrain softkey Synthetic Vision softkey Terrain Awareness and Warning System Temperature Traffic Information System Timer Take off Top of Descent Technical Standard Order AFCS VOR Approach Mode Volts DC Visual Descent Point Visual Flight Rules Very High Frequency Visual Meteorological Conditions Vibro meter Inc Maximum operation limit speed in knots Vertical Navigation Vertical Navigation button on the GMC 710 AFCS Mode Controller VHF Omni directional Range Vertical path Vertical Speed Wide Area Augmentation System WAAS Fault Detection Exclusion World Geodetic System 1984 Windshield Transfer button on the GMC 710 AFCS Mode Controller XM satellite system Transponder Cross Side Yaw Damper Hawker Beechcraft C90A and C90GT King Air Page 14 of 117 190 00682 02 Rev D Section 2 Limitations INTRODUCTION The G1000 Cockpit Reference Guide for Hawker Beechcraft C90A GT CRG must be immediately available to the flight crew Use the G1000 Cockpit Reference Guide for Hawker Beechcraft C90A GT Garmin part number 190 00664 01 revision A or later approved revision when System Software Version 0636 02 is installed The S
34. 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 Continue to operate the autopilot in a normal manner after the annunciation extinguishes If the annunciator remains illuminated or reappears with no changes in airspeed or configuration from the previous trimmed condition 3 Control Wheel aee es ane Ite nl Ra a en P Rer die 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 USING ELEVATOR TAB WHEEL MANUALLY RETRIM AIRPLANE Autopilot should be
35. Use Pilot s Audio Panel and Com 1 to Obtain ATC Clearance then 3 Avionics Master Pwr Switch OFF 4 BAT Switch Master Switch 4 1 OFF BEFORE STARTING These procedures should be conducted after completing the airplane s AFM BEFORE ENGINE STARTING checklist items 1 Standby Battery eseeee enne ra Ae aai PUSH ON illuminated if Aircraft Battery is OFF ARM illuminated if Aircraft Battery is ON 2 Standby Attitude Gyro Fail NOT DISPLAYED listen for standby altimeter vibrator operation REVIEW FOR VALID OPERATING DATES AND CYCLE NUMBER ENT key on the MFD Control PRESS to acknowledge the G 1000 database information and activate the selected pilot profile 5 AUX Weight Planning nennen nennen nnns INPUT LOAD DATA BEFORE TAXI These procedures should be conducted after completing the airplane s AFM BEFORE TAXI checklist items 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 AFC
36. around Garmin Control Unit Garmin Air Data Computer Garmin Display Unit Garmin Engine Airframe Unit Generator Geographic Garmin Flight Control Garmin Integrated Avionics Unit Garmin Audio Panel Garmin Mode Control Unit GPS Glide Path Global Positioning System Garmin Reference System AHRS 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 11 of 117 GS GSA HDG HITS HPa HSI IAF IAS ICAO IFR ILS IMC in Hg INOP INST ITT KIAS Kt s L LCD LDA LNAV V LNAV VNAV LOC LOI LPV LRN LRU LTNG M MAP MAXSPD MDA MEL MFD Glide Slope Garmin Servo Actuator AFCS heading mode or the HDG button on the GMC 710 AFCS Mode Controller Highway in the Sky Hectopascal Horizontal Situation Indicator Initial Approach Fix Indicated Airspeed International Civil Aviation Organization Instrument Flight Rules Instrument Landing System Instrument Meteorological Conditions inches of mercury Inoperative Instrument Interstage Turbine Temperature Knots Indicated Air Speed Knot s Left Liquid Crystal Display Localizer Type Directional Aid Lateral Navigation Lateral Navigation with Advisory Vertical Guidance Lateral Navigation Vertical Navigation Localizer Loss of Integrity GPS Localizer Performance with Vertical Guidance Long Range Navigation Line Replaceable Unit Lightning XM Weather Product Mach Missed Approach Point Maximum Speed AFCS Overspeed Pro
37. location on the instrument panel to the pedestal 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 85 of 117 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 86 of 117 Figure 1 Instrument Panel PILOT Figure 2 Pilot s Control Wheel 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 87 of 117 COPILOT Figure 3 Copilot s Control Wheel With Trim Switches Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 88 of 117 Ex py Figure 4 Copilot s Control Wheel Without Trim Switches 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 89 of 117 DO NOT OPERATE ON DRY GLASS MAX AIRSPEED KNOTS br un OVERHEAD INSTRUMENT INDIRECT GEAR EXTENSION 182 GEAR RETRACT 163 PARK SLOW MASTER GEAR EXTENDED 182 FAST APPROACH FLAP 184 FULL DOWN FLAP 148 MANEUVERING 169 er oa PANEL ur e E STBY OVHD PED SIDE ar ld amp Er ES TE 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 PLACARDS 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 SWITC
38. on the G1000 FMS the Pathway to the Missed Approach Holding Point will be displayed just as described for the departure segment The pilot must assure that the aircraft path will at all times comply with the requirements of the published missed approach procedure If the initial missed approach leg is heading to altitude or a leg defined by other than a GPS course the Pathway will not be displayed for that segment If the course to the Missed Approach Holding Point is out of the SVS field of view during the initial missed approach climb the Pathway will not be visible on the PFD until the aircraft is turned toward the course The Pathway will be displayed at the published missed approach altitude OR the altitude set on the G1000 altitude selector WHICHEVER IS HIGHER If the G1000 altitude selector is set to MDA on the final approach segment and not reset during the initial missed approach the Pathway will still be displayed at the published missed approach altitude FAF MAP ALTITUDE Pathway NOT displayed on heading and turn segments Missed Approach Pathway Display 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 79 of 117 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev
39. the G1000 Cockpit Reference Guide and Pilot s Guide for additional information 1 Once clearance from has been received RESET Altitude Preselect to the vertical clearance limit 2 VNV 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 lower 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 D Page 66 of 117 Vertical DIRECT TO To descend f
40. 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 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 essen SELECT NAV on mode controller GPS will be annunciated in GREEN on the PFDs 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 67 of 117 NAVIGATION GPS OBS MODE OV Navigation SELECT GPS using the CDI softkey on PFD Select PRESS the B gt button on the PFDs MFD From the DIRECT TO page activate DIRECT TO a waypoint OBS SofIKoy iid et etate ret e etre ON PFD PRESS OBS softkey Course PL SET using CRS knob Intercept Heading rnm ESTABLISH in HDG or ROL mode Mode 4 4 00 nnn SELECT mode controller GPS will be annunciated in WHITE if the mode is armed or in GREEN if the GPS 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 GPS in white on the PFD The pilot must ensure that the current heading will re
41. 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 9v 3 0 m KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR day or night IFR and icing conditions when the required systems and equipment are installed and operable The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated The system and equipment listed must be installed and operable for the particular kind of operation indicated unless The airplane is approved to be operated in accordance with a current Minimum Equipment List MEL issued by the FAA Or An alternate procedure is provided in the Pilots Operating Handbook and FAA Approved Flight Manual for the inoperative state of the listed system or equipment and all limitations are complied with 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 21 of 117 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 oper
42. 0A and C90GT King Air 190 00682 02 Rev D Page 6 of 117 Section 1 General The information in this supplement is FAA approved material and must be attached to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual POH AFM when the airplane has been modified by installation of the Garmin G1000 Integrated Avionics System and GFC 700 Digital Automatic Flight Guidance System in accordance with Garmin International Inc approved data The information in this supplement supersedes or adds to the basic POH AFM only as set forth below Users of the manual are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of the airplane The Garmin G1000 system installed in the Hawker Beechcraft 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 Class B Weather Avoidance and a three axis automatic flight control flight director system USE OF THE HANDBOOK The following definitions apply to WARNINGS CAUTIONS and NOTES found throughout the handbook WARNING Operating procedures techniques etc which could result in personal injury or loss of life if not carefully followed CAUTION Operating procedures techniques etc which could result in
43. 4 CONFIRM VALID ATTITUDE AND HEADING ARE DISPLAYED CONFIRM BOTH ON AHRS1 or BOTH ON 52 annunciated on both PFDs NOTE The autopilot will disconnect and will not re engage Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 52 of 117 ENGINE INDICATION SYSTEM EIS FAILURE RED X ON ENGINE DISPLAY If All Engine Gauges One Engine Red xX Indicates failure of the GEA for that engine 1 Check ENG INST circuit 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 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 a 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
44. 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 D This Supplement is Applicable to the Following Manuals 90 590024 5 90 590024 43 90 590024 23 90 590024 61 90 590024 35 90 590024 69 90 590024 163 4 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 Airplane Serial Number Airplane Registration Number FAA Approved By Robert G Murray Lead ODA Administrator Garmin International Inc ODA 240087 CE Date 2 3 20 0 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 1 of 117 Copyright 2007 2010 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
45. H 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev B Page 90 of 117 045019 3NTVA 5 TivAul3 N N3dO 59999 MO s s s JAVA did INA 15008 SNVuL ALD s s s s 15 HOVL 1804 ON3 LN dOHd EE 5 5 5 5 141 S1N3IACIBLSNI 3NION3 NASAS 1814 i s s s s s m s NHVM a334 NHVM did 3ATVA SSdHd SSOHO SSuHd ALD SNVHL 15008 IM 035019 3NTVA 5 TivM3ul4 Figure 6 Left Side Circuit Breaker Panel SN LJ 1361 LJ 1363 and Subsequent Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 91 of 117 9 3unss3ud ISNI ONOO 19 ON3 370801 m 1331 SINAWNYISNI 3NION3 WALSAS 1304 ob P 13m 345538 AWA Pew ony ee wd EAS 4 5 Qui 8 ANA ASOLNHS N N N Fa S NC 2 Xe ASOLNHS TYM TYM ANWA dWnd ATA TyM 15008 SNVHL 85354 556080 5644 SNVHL 15009 TYM N3dO 190 00682 02 Rev D and Subsequent Figure 7 Left Side Circuit Breaker Panel Alternate Configuration SN LJ 1361 LJ 1363 Ha
46. IVIDUALLY 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 Button PRESS AND HOLD verify elevator tab wheel motion stops 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 63 of 117 e Pilots Tiim Override eii eet eee eee er epe eden tette EE inh ea pe 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 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 is Annunciated in Mode Window on Both PFDs BEFORE TAKEOFF FINAL ITEMS These procedures should be conducted after completing the airplane s AFM BEFORE TAKEOFF FINAL ITEMS checklist 1 PFD Attitude and Heading NORMAL 2 GBS POSIUOD n eese temet VALID LOI NOT ANNUNCIATED on HSI 3 Standby Attitude
47. N group on the pilot s right subpanel 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 pilot s Air Data Computer ADC1 the event of a failure of the pilot s normal static air source e g 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 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
48. NGUISHES 5 AP YD DISC TRIM INTRPT Button 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 by a red 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 SERVOS 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 If 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 D Hawker Beechcraft C90A and C90GT King Air Page 39 of 117 If still inoperative 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
49. O sna r OHINOO 4 03318 fe fc eu MEE m 2 6 S8 6 6 Dan Om Onn Ss 6 9 g S NU NL A MZ ed 7 Nau 815 cVIO 200 ZzSBHv di sung 1 301 di im I H3HIV3M 3 WIN3ANOHIAN3 S8 i393 I EN 01 10380N i 6 2 2 6 1 Ms 90 42 aS 4 2 7 s LZ 39095 dOv OlOvd HISNI AS WHOLS ON 9 songas LON T BON IM rea me TOSNO 13098 5 2 6 Se ty 6 ls Hoas ans 2 7 uw 224 LA NF uw 3 SO3v HvOvH SOINOWV 764 TNd diae GHAO H313 4g 321 MNS ON Nd 8nS 4 30080l nn ous TOHLNOO LE ED E A LA o s s s s 1 5 820 4 5 5 SL 02 N39 5 V7 9 ME NP 27 NS 5 Xe v ony WOO SOINOIAY 1331 im um 133 40914 dvi SHON 1H9N4 LON LON LON 1531 JHOI a 9 lon PEN N Y N s 5 5 se s ss 9 eS eS Daa GO aa 8 es 2 M NC _ VS ae YY H dX Oldnv WOO SOINOIAY dOHd SS3Hd 15 HOWL 3Ou NOO NNW 7130 NHYM m 3 MOd
50. ORMATION WILL BECOME LESS ACCURATE OVER TIME e TAWS IS INOPERATIVE e DR mode uses heading true airspeed last known wind data and the last known GPS position to estimate the airplane s current position DR information will be available for a maximum of 20 minutes 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 49 of 117 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 e TAWS IS INOPERATIVE 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 usi
51. 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 110 of 117 SYNTHETIC VISION General The SVS sub system is dependent upon terrain data provided by the underlying G1000 system If for some reason the terrain data is not available from the G1000 all of the components of the SVS system will be unavailable The flight path marker horizon heading and airport signs are all sub components of the Synthetic Terrain display and are only available when Synthetic Terrain is enabled Those features are selected or de selected using the PFD softkeys on the SVS menu Synthetic Terrain The synthetic 3D terrain display on the PFD provides a perspective vi
52. PRESS on Mode Controller 6 Rudder Tab Knob sees 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 D Hawker Beechcraft C90A and C90GT King Air Page 41 of 117 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 FLC VS VPTH ALT GS GP 1 Autopilot mode 8 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 sse 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
53. 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 105 of 117 LEFT GENERATOR BUS GEN No 1 CENTER BUS RIGHT GENERATOR BUS GEN No 2 TRIPLE FED BUS HOT BATTERY BUS 1 The circuit breaker in this circuit is not accessible to the pilot in flight 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 Hawker Beechcraft C90A and C90GT King Air Page 106 of 117 190 00682 02 Rev D TRIPLE FED BUS HOT BATTERY BUS STANDBY BATTERY
54. S annunciator indicates a malfunction within the autopilot system The autopilot yaw damper and electric elevator trim will be inoperative 1 Automatic Autopilot Preflight Test nennen COMPLETE a Red AFCS ILLUMINATED WHILE AHRS ALIGNS b Red AFCS Annunciator EXTINGUISHES When Autopilot Preflight Test Begins 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 61 of 117 c White PFT ILLUMINATED 5 Seconds d White PFT 22222 2 EXTINGUISHES when preflight test complete e Autopilot Disconnect 2 1 1 11 0 SOUNDS 2 Standby Attitude Indicator nennen nennen nnne nettes CHECK a PULL TO CAGE PULL KNOB TO ERECT GYRO b Instrument Fail Flag NOT DISPLAYED IN INSTRUMENT FACE c PFD1 PFD2 and Standby Attitude Indicator COMPARE and CROSS CHECK 3 ete delen ute eiie tes RUNE RR SET and CROSS CHECK PFD 1 PFD 2 Standby Altimeter If barometric pressure settings on the PFD1 and PFD2 altimeters differ by more than 0 03 in Hg 1 HPa the baro display on both PFDs will be amber TAXI The following procedure should be accomplished while the aircraft is taxiing and prior to conducting the airplane s AFM BEFORE TAKEOFF RUNUP checklist NOTE Taxiing the aircraft before a
55. YD DISC TRIM INTRPT Button sess PRESS and RELEASE Pilot s or Copilot s control wheel 2 AP Button Autopilot mode control panel PRESS Yaw damper remains engaged 3 Pitch Trim Switch Pilot s or if installed Copilot s control ACTIVATE Yaw damper remains engaged 4 GA switch sssssssssssssseseeeee ener enne nnn nennen nns PRESS 5 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 PRESS AND RELEASE to cancel disconnect tone 2 gt Aircraft At tude niunt ta Rea tede cnr 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 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
56. abase or verifies each waypoint for accuracy by reference to current approved data Discrepancies that invalidate a procedure must be reported to Garmin International The affected procedure is prohibited from being flown using data from the Navigation database until a new Navigation database is installed in the aircraft and verified that the discrepancy has been corrected Contact Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 16 of 117 information to report Navigation database discrepancies can be found at www Garmin com Support Contact Garmin Support gt Aviation Pilots and operators can view navigation data base alerts at www Garmin com In the Air NavData Alerts For flight planning purposes in areas where SBAS coverage is not available the pilot must check RAIM availability Within the United States RAIM availability can be determined using the G1000 WFDE Prediction program part number 006 A0154 01 010 G1000 00 or later approved version with Comant Cl 428 410 and Cl 428 200 antennas selected or the FAA s en route and terminal RAIM prediction website www raimprediction net or by contacting a Flight Service Station Within Europe RAIM availability can be determined using the G1000 WFDE Prediction program or Europe s AUGER GPS RAIM Prediction Tool at http augur ecacnav com augur app home For other areas use the G1000 WFDE Prediction program This requirement is not necessary if SBAS coverage is confi
57. ach operations S00 Display NOTE 1 Some operations require two Comant 428 410 antenna functioning GPS SBAS receivers Comant CI 428 200 antenna NOTE 2 If only one is required and only one is operative it must be 1 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 23 of 117 Icing System and or Equipment Conditions Remarks and or Exceptions OXYGEN No Changes Refer to Aircraft Flight Manual PROPELLER No Changes Refer to Aircraft Flight Manual VACUUM SYSTEM Gyro Suction Gage Instrument Air System Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 24 of 117 This page intentionally left blank 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 25 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 26 of 117 Section 3 Emergency Procedures Table of Contents AUTOMATIC FLIGHT CONTROL SYSTEM 29 AUTOPILOT MALFUNCTION ELEVATOR TRIM 1 nnne 29 MANUAL AUTOPILOT DISCONNECT eerte enne nn in thin tras euneun ennnen nennen ne 30 AUTOPILOT ABNORMAL DISCONNECT eese eene ennemi nin intr intr intr santa sn nennen 30 erronee drei oerte eo eme ero ctr
58. age clears on both PFDs BOTH AHRS 1 52 This message is displayed on both PFDs and indicates that both pilot and copilot PFDs are displaying data from the same Attitude Heading Reference 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 GPs 1 2 LU This message is displayed 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 1 GPS SBAS Stats sene et a CHECK a Select AUX GPS STATUS page on MFD b Select GPS1 the
59. ages on the specified route that would prevent the G1000 to provide primary means of Class II navigation in oceanic and remote areas of operation that requires RNP 10 or RNP 4 capability If the G1000 WFDE Prediction program indicates fault exclusion FDE availability will exceed 34 minutes in accordance with FAA Order 8400 12A for RNP 10 requirements or 25 minutes in accordance with FAA Order 8400 33 for RNP 4 requirements then the operation must be rescheduled when FDE is available Both GIA 63Ws GPS navigation receivers must be operating and providing GPS navigation guidance to their respective PFD for operations requiring RNP 4 performance North Atlantic NAT Minimum Navigational Performance Specifications MNPS Airspace operations per AC 91 49 and AC 120 33 require both GPS SBAS receivers to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor Each display computes an independent navigation solution based on the on side GPS sensor However either display will automatically revert to the cross side sensor if the on side sensor fails or if the cross side sensor is determined to be more accurate A BOTH ON GPS1 or BOTH GPS2 message does not necessarily mean that one GPS has failed Refer to the MFD AUX GPS STATUS page to determine the state of the unused GPS Whenever possible RNP and RNAV routes including Standard Instrument Departures SIDs and Obstacle Departure Proc
60. ained Indicated increases when climbing or decreases when descending 5 Use SENSOR softkey to select most accurate ADC on the affected PFDs 6 AIS POO 2 ened RESUME NORMAL SPEEDS If Pilot s and Copilot s Altitude Do Not Agree 1 Refer to Abnormal Procedures ALT MISCOMP procedure to determine most accurate ADC 190 00682 02 Rev D Hawker Beechcraft C90A and 90 King Air Page 45 of 117 PITCH MISCOMPARE LES 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 Reference Guide for additional information 1 Referto STANDBY ATTITUDE indicator to determine which AHRS is providing the most accurate data 2 Use SENSOR softkey to select the most accurate AHRS on the affected PFD ROLL 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 Reference Guide for additional information 1 Referto STANDBY ATTITUDE indicator to determine which AHRS is providing the most accurate data 2 Use SENSOR softkey to select the most accurate AHRS on the affected PFD HEADING MISCOMPARE This message is displayed when the G1000 detects a difference between the pilot s and copilot s heading information
61. ared to an initial approach fix a ACTIVATE THE APPROACH from the PROC page Or ACTIVATE a DIRECT B gt the IAF bz SEIS ODE cote Deas cesso 17 SELECT GPS Nav Source c Mode Control Panel PRESS NAV GPS Mode NOTE 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 dc MERIEY e Echt atio titius Course pointer slews to the front course 4 Established inbound on Final Approach Course FAF Active Waypoint WERIEY Course Pointer is set to the final approach course b Xue ete Uses th t se et eet LOC is annunciated on the HSI 5 MAINTAIN 110 KIAS OR GREATER Recommended Atthe EAE iiu Use desired vertical mode to fly the approach s vertical profile Use Altitude Preselect to level off at intermediate altitudes and at the MDA NOTE It is 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 SET Missed Approach Altitude In Altitude Preselect Hawker Beechcraf
62. ating rules It also does not include components obviously required for the airplane to be airworthy such as wings empennage engines etc System and or Equipment 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 Air Conditioning System 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 Conditions Remarks and or Exceptions Removed by G1000 modification Removed by G1000 modification Temperature limits reduced to 49 C 120 F with inoperative air conditioner or air conditioner not Left side is required Both side required for two crew operation Hawker Beechcraft C90A and C90GT King Air Page 22 of 117 190 00682 02 Rev D Icing System and or Equipment Conditions Remarks and or Remarks VHF Communications System Or as required by
63. ayed on the MFD MAP WEATHER DATA LINK page XM ICING and XM TURBULENCE data must be turned off in order to display XM NEXRAD data OPTIONAL L3 COMMUNICATIONS AVIONICS SYSTEM WX 500 STORMSCOPE Stormscope lightning information displayed by the G1000 system is limited to supplemental use only The use of the Stormscope lightning data on the MAP NAVIGATION MAP and or MAP STORMSCOPE page for hazardous weather thunderstorm penetration is prohibited Stormscope lightning data on the MAP NAVIGATION or MAP STORMSCOPE page is intended only as an aid to enhance situational awareness of hazardous weather not penetration It is the pilot s responsibility to avoid hazardous weather using official weather data sources and the airplane s weather radar Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 20 of 117 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 KINDS OF OPERATION LIMITS The Hawker Beechcraft models C90A and C90GT are approved for the following types of operations
64. 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 D Page 40 of 117 RUDDER MISTRIM amber RUD or 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 If 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 endet M M ERA HOLD FIRMLY 2 Rudder Tab 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 changes in airspeed or configuration from the previous trimmed condition Rudder Pedals 0 0 cccccccccccceeececccecseeaeececeseesseaueaseeeseeeuseaueaeaceeeeeeuauauaeeeeeseuaeaueaseeeeess HOLD FIRMLY Rudder Tab ROTATE SLOWLY IN THE DIRECTION OF INDICATED MISTRIM UNTIL ANNUNCIATION EXTINGUISHES b YD BttOrziii ie eee cei Bes
65. ctedly from the planned flight path Dey Conto M ee DE GRIP FIRMLY 2 AP YD DISC TRIM INTRPT 2222 PRESS AND HOLD Be prepared for possible high elevator control forces 9 Atrcraft Attitude tes ic er rette te ku enr anions 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 Breaker esten ntis nnns 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 29 of 117 MANUAL AUTOPILOT DISCONNECT If necessary the autopilot can be manually disconnected using any one of the following methods 1 AP
66. damage to equipment if not carefully followed NOTE Operating procedures techniques etc which is considered essential to emphasize 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 7 of 117 G1000 GNSS GPS SBAS NAVIGATION SYSTEM EQUIPMENT APPROVALS The Garmin G1000 Integrated Avionics GNSS navigation system installed in this aircraft is a GPS system with a Satellite Based Augmentation System SBAS comprised of two TSO C145a Class 3 approved Garmin GIA 63Ws TSO C146a Class 3 approved Garmin GDU 104X Display Units Comant Cl 428 410 and Cl 428 200 antennas and GPS software version 3 0 or later approved version The G1000 GNSS navigation system in this aircraft is installed in accordance with AC 20 1384 The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the requirements of AC 20 138A and is approved for navigation using GPS and SBAS within the coverage of a Satellite Based Augmentation System complying 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 GNSS navigation system installed in this aircraft is approved for approach procedures with vertical guidance including LPV and LNAV VNAV within the U S National Airspace System The Garmin G1000 Integrated Avionics GNSS navigation system as installed in t
67. de Control Panel sss 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 C tee ttr tentata PRESS until VOR navigation source To be used for the approach displays d Course Pointer Set to inbound course if not already set e Mode Control PRESS APR verify VAPP armed 190 00682 02 Rev D Hawker Beechcraft C90A and 90 King Air Page 73 of 117 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 P gt the IAF eM Ier PE SELECT GPS nav source Mode Control Pariel ui eer e oret e PRESS NAV GPS mode When Established Inbound to the FAF PRESS CDI softkey until VOR navigation source to be used for the approach displays Autopilot Flight Director Mode will automatically change to ROL Course Poner tas uinci dae erano eh ast eR ORT d Set to inbound course f Mode Control
68. e 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 ALI EAE S i dde teet 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 NOTE It is recommend to descend 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 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 MDA SET Missed Approach Altitude In Altitude Preselect VOR APPROACH 1 Load the approach into the Active Flight VERIFY the G1000 tunes the proper VOR frequency 2 Approach 5 SET ON TMR REF page if not already set IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mo
69. e display until the aircraft has turned toward the course e The Pathway will be displayed at either the altitude selected on the G1000 selector OR the altitude published for the procedure e g SID WHICHEVER IS HIGHER After departure the primary aircraft control must be by reference to the primary aircraft instruments The SVS and Pathway displays should be used to aid in awareness of the terrain and programmed flight path 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 77 of 117 Prior to intercepting the programmed course the Pathway will be displayed as a series of magenta boxes with pointers at each corner that point in the direction of the programmed course The Pathway boxes will not be displayed on portions of the course line that would lead the pilot to intercept the course in the wrong direction As the aircraft approaches the center of the programmed course and altitude the number of Pathway boxes will decrease to a minimum of four Enroute When enroute the Pathway will be displayed along the lateral path defined by the flight plan at the altitude selected on the G1000 altitude selector Flight plan changes in altitude that require a climb will be indicated by the Pathway being displayed as a level path at the altitude entered for the current flight plan leg Because the G1000 system does not have information available to it about aircraft performance climb profiles are not displayed by the Path
70. e 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 15 of 117 Do not take off with any of the following messages displayed in the ALERTS window GPS1 FAIL and GPS2 FAIL simultaneously PFD1 SERVICE GPS NAV LOST PFD2 SERVICE GIA1 SERVICE GMA1 SERVICE GIA2 SERVICE GMA2 SERVICE MFD SERVICE GEO LIMITS 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 20 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 the teardrop segment of the course reversal The fuel quantity fuel required fuel remaining a
71. ection 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 98 of 117 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 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
72. edures ODPs Standard Terminal Arrival STAR and enroute RNAV Q and RNAV T routes should be loaded into the flight plan from the database in their entirety rather than loading route waypoints from the database into the flight plan individually Selecting and inserting individual named fixes from the database is permitted provided all fixes along the published route to be flown are inserted Manual entry of waypoints using latitude longitude or place bearing is prohibited 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 17 of 117 GPS or GPS and RNAV GPS instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Navigation database GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Navigation database Not all published Instrument Approach Procedures IAP are in the Navigation database Pilots planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must be loaded from the Navigation database into the FMS flight plan by its name IFR non precision approach approval using the GPS SBAS sensor is limited to published approaches within the U S National Airspace System Approaches to airports in other airspace are not approved unless authorized by the appropriate gove
73. ennen 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 e 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 essei entente nentes tents SELECT NORMAL 5 Compare indicated altitude to GPS altitude on MFD AUX GPS STATUS page to aid in determining which primary system is most accurate 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 43 of 117 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 Pre
74. ents 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 2 Autopilot Mode TRANSFER XFR button to operating PFD reo o Meet ED RE ENGAGE and select modes 4 Transponder er nete eer eerte robe rct SELECT operating transponder 5 Audio Panels osni de ae aged a ido dede picea de ded SELECT operating COM Radio NOTE Use the operating PFD to control Com frequency selection Com and Nav volume and Altimeter Barometric Pressure setting 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 47 of 117 MFD FAILURE
75. ew of the terrain ahead of the aircraft showing ground features up to 30 degrees left and 35 degrees right of the airplane heading The terrain display is derived from the same terrain data contained in the G1000 system that is optionally used to display terrain on the MFD map display The terrain data has a resolution of 9 arc seconds this means that the terrain elevation contours in the database are stored broken down into squares 9 arc seconds on each side That data is processed and smoothed by the G1000 system to provide the synthetic terrain display In some instances terrain features such as lakes in mountainous areas may be presented by the SVS system as if the lake water extends somewhat up the mountainside This is due to the limitations of the terrain database resolution but is not significant for the approved uses of the SVS system The SVS terrain display will show land contours large water features and towers and other obstacles over 200 ft AGL including buildings that are included in the G1000 obstacle database n order to provide a clean uncluttered PFD display cultural features on the ground such as roads and highways railroad tracks cities and political boundaries state county lines are not displayed on the PFD even if those features are selected for display on the MFD The colors used to display the terrain elevation contours are similar to those used on the MFD map The terrain display also includes a north south east
76. h Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 68 of 117 dr iae eain 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 TO P gt the IAF HS GDI teat ues SELECT GPS Nav Source Mode Control Panel sse PRESS NAV GPS Mode Mode Control PRESS APR Verify LOC and GS armed NOTE 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 i t en ge Ave du d dE Course pointer slews to the front course 4 Established inbound on Final Approach Course SET Missed Approach Altitude In Altitude Preselect 5p jJ AIrSDeed iuuat Leet MAINTAIN 110 KIAS OR GREATER Recommended MERIEY a aeu Airplane Captures and Tracks LOC captures and tracks GS 7 AT Decision Altitude DA a A P Y D DISC TRIM INTRPT Switch 20 2 400 0 00 enne PRESS Continue visually for a normal landing
77. he last waypoint in the route to the alternate and the currently loaded instrument approach header 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 SYNTHETIC VISION Use of Pathways If Synthetic Terrain is displayed on the PFD the Pathways may be used to assist the pilot s awareness of the programmed lateral and vertical navigation path The following sections describe the basic use of the Pathways in various flight segments For more detailed information consult the G1000 Pilot s Guide Departure Prior to departure load and activate the desired flight plan into the G1000 FMS set the initial altitude on the G1000 altitude selector and select GPS on the HSI display just as you would without the SVS system The programmed flight path will be displayed as a series of magenta boxes along the path at the flight plan altitude subject to the following conditions e If the first segment of the flight plan is a heading to altitude leg the Pathway will not be displayed for that segment first Pathway segment displayed will be the first GPS course leg e Pathway must be within the SVS field of view of 30 degrees left and 35 degrees right If the programmed path is outside that field of view the Pathways will not be visible on th
78. his aircraft complies with the equipment requirements of AC 90 105 and meets the equipment performance and functional requirements to conduct RNP terminal departure and arrival procedures and RNP approach procedures without RF radius to fix legs Part 91 subpart K 121 125 129 and 135 operators require a Letter of Authorization for operational approval from the FAA The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the equipment requirements of AC 90 100A for RNAV 2 and RNAV 1 operations In accordance with AC 90 100A Part 91 operators except subpart K following the aircraft and training guidance in AC 90 100A are authorized to fly RNAV 2 and RNAV 1 procedures Part 91 subpart K 121 125 129 and 135 operators require a Letter of Authorization for operational approval from the FAA The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft has been found to comply with the requirements for primary means of Class navigation in oceanic and remote navigation RNP 10 without time limitations in accordance with AC 20 138A and FAA Order 8400 12A The G1000 can be used without reliance on other long range navigation systems This does not constitute an operational approval The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft has been found to comply with the navigation requirements for primary means of Class navigation i
79. ill provide electrical power for the three standby instruments for at least 30 minutes ARM Green 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 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 is the master switch for PILOT PFD STBY INSTR MFD 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 ligh
80. information TAWS INHIBIT TAWS INH 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 page 2 INHIBIT 50 REDEEM PRESS 3 Verify LTAWS annunciation displays on both PFDs and in the lower right corner of the MFD To Enable TAWS lf Inhibited 1 Display the MAP TAWS page PME Scc ERE PRESS 3 Verify the TAWS INH annunciations displays are removed both PFDs and the TAWS N A and TAWS 5 TAWS 1 the amber TAWS N A status annunciator is displayed on the PFDs and MFD the system will no longer provide TAWS alerting or display relative terrain and obstacle elevations The crew must maintain compliance with procedures that ensure minimum terrain and obstacle separation 2 Ifthe amber TAWS FAIL status annunciator is displayed on the PFDs and MFD the system will no longer provide TAWS alerting or display relative terrain and obstacle elevations The crew must maintain compliance with procedures that ensure minimum terrain and obstacle separation Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 56 of 117 This page intentionally left blank 190 00682 02 Rev D Ha
81. int 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 SET Missed Approach Altitude In Altitude Preselect GO AROUND GA 1 Control Wheel 2 REP tal oe e GRASP FIRMLY 2 GO AROUND button left PUSH Verify GA GA on PFD in lateral and vertical mode fields Rotate to Go Around Follow Flight Director Command Bars Balked Eandilng is exa om etu mu NAE EXECUTE 5 Mode Control Panel 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 6 Altitude VERIFY Set to appropriate altitude At an appropriate safe altitude 7 Mode Control Panel esses 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 wings level the HSI nav source automatically switches to GPS the flight plan sequences to the first published mis
82. ious 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 13 Electric Trim Switches Pilot s Control Wheel 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 101 of 117 FLIGHT INSTRUMENTS G1000 FLIGHT INSTRUMENTS The flight instruments are an integrated part of the G1000 system For system descriptions operating instructions and abnormal failure indication refer to the Cockpit Reference Guide STANDBY ALT AS ALTITUDE FEET Vwe S L TO 16 000 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 Mo powered by the triple fed buss In the event of total loss of aircraft electrical power there is a standby battery that will power the standby ME E attitude indicator for at least 30 minutes 2 A standby altimeter is the next instrument in the stack It is a o mechanical instrument tha
83. l path through space is not defined by them a Pathway is not displayed for heading legs VOR LOC BC or ADF segments When the Pathway is displayed the color of the boxes indicates the sensor generating the path If the GPS sensor is in use the boxes will be magenta colored If the LOC sensor is defining the path in use the boxes will be green The Pathway boxes are 100 ft in vertical dimension and approximately 4 380 ft horizontally from the center of the box The Pathway presentation is intended only to aid the pilot in awareness of the programmed flight path location relative to the airplane s current position The pathway is not intended for use as a primary reference in tracking the navigation path If a GPS based descent profile has been programmed either on the G1000 flight plan page or as part of an approach or STAR the descent will be displayed by the Pathway Climb paths are never displayed by the Pathway If a profile requires a climb the Pathway will be displayed as a level segment at the higher of the altitude defined by the programmed path or the G1000 altitude selector Traffic If traffic that is within the SVS field of view is detected by the G1000 system a symbol will be displayed on the PFD indicating the direction and relative altitude of the traffic The traffic will be displayed as a white diamond unless it generates a traffic alert Traffic that causes an alert will be displayed as a solid yellow circle accompanied b
84. ll 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 contain 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 s
85. n GPS2 softkeys and verify sufficient satellite reception Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 54 of 117 XSIDE ADC This message is displayed on both PFDs and indicates that both PFDs are displaying data from the opposite side Air Data Computer Normally the pilot s side displays ADC 1 and the copilot s side displays ADC 2 Refer to GARMIN G1000 Cockpit Reference Guide for additional information 1 PILOT S PFD SENSOR PRESS 2 PILOT S PFD ADOT Soflkey de ke Ee PRESS 3 PFD Displays CONFIRM BOTH ON ADC1 message displayed on both PFDs 4 COPILOT S PFD SENSOR Softkey sse ene ennennnenneenrnn n nns PRESS 5 COPILOT S PFD ADC2 Softkey PRESS 6 PFD Displays CONFIRM BOTH ON ADC 1 message clears on both PFDs XSIDE AHRS E 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 nnns PRESS 2 PILOTS PFD AHRS1 Softkey ire ttr ER Re EE PRESS 3 PFD Displays
86. n oceanic and remote navigation RNP 4 in accordance with AC 20 138A and FAA Order 8400 33 The G1000 can be used without reliance on other long range navigation systems Additional equipment may be required to obtain operational approval to utilize RNP 4 performance This does not constitute an operational approval The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the accuracy integrity and continuity of function and contains the minimum system functions required for PRNAV operations in accordance with JAA Administrative amp Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 JAA TGL 10 Rev 1 The GNSS navigation system has two ETSO 145 TSO C145a Class 3 approved Garmin GIA 63Ws and ETSO 146 TSO C146a Class 3 approved Garmin GDU 104X Display Units The G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the equipment requirements for PRNAV and BRNAV operations in accordance with AC 90 96A and JAA TGL 10 Rev 1 This does not constitute an operational approval Garmin International holds an FAA Type 2 Letter of Acceptance LOA in accordance with AC 20 153 for database Integrity quality and database management practices for the Navigation database Pilots and operators can view the LOA status at www Garmin com gt Aviation Databases gt Type 2 LOA Status Navigation information is referenced to WGS 84 refe
87. nd Heading Reference System Altitude or AFCS altitude hold mode or ALT button on the GMC 710 AFCS Mode Controller AFCS altitude capture using the altitude in the altitude preselect window AFCS altitude capture using the altitude from the VNAV profile vertical constraint Airport Moving Map Display Autopilot AFCS Approach mode or APR button of GMC 710 AFCS mode controller Airport Signs SVS softkey on the PFD Approach with Vertical Guidance Airspeed Air Traffic Control Auxiliary Low bank mode of the AFCS Barometric Setting Battery Back Course Basic Area Navigation Bright Celsius Course Deviation Indicator Clear Communication radio Cockpit Reference Guide Course Control Wheel Steering Hawker Beechcraft C90A and C90GT King Air Page 10 of 117 190 00682 02 Rev D DA DC DME DN DR EFB EIS ELEC EMERG ENG ENT F FAF FD FLC FLTA FMS FPM FSB ft ft lbs ft min GA GCU GDC GDU GEA GEN GEO GFC GIA GMA GMC GP GPS GRS Decision Altitude Direct Current Distance Measuring Equipment Down Dead Reckoning Electronic Flight Bag Engine Indication System Electrical Emergency Engine Enter Fahrenheit Final Approach Fix Flight Director AFCS Flight Level Change mode or FLC button on the GMC 710 AFCS mode controller Forward Looking Terrain Awareness Flight Management System Flight Path Marker or Feet Per Minute Fasten Seat Belts Feet Foot Pounds Feet Minute Go
88. nd gross weight estimate functions of the G1000 are supplemental information only and must be verified by the flight crew Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering SafeTaxi and Chartview functions do not comply with the requirements of AC 20 159 and are not qualified to be used as an airport moving map display AMMD SafeTaxi and Chartview are to be used by the flight crew to orient themselves on the airport surface to improve pilot situational awareness during ground operations The use of the colors red and amber within the checklist function has not been evaluated or approved by this STC Use of the colors red and or amber within user created checklists may require separate evaluation and approval by the FAA G1000 GNSS GPS SBAS NAVIGATION SYSTEM LIMITATIONS The pilot must confirm at system initialization that the Navigation database is current Navigation database is expected to be current for the duration of the flight If the AIRAC cycle will change during flight the pilot must ensure the accuracy of navigation data including suitability of navigation facilities used to define the routes and procedures for flight If an amended chart affecting navigation data is published for the procedure the database must not be used to conduct the procedure GPS SBAS based IFR enroute oceanic and terminal navigation is prohibited unless the pilot verifies and uses a valid compatible and current Navigation dat
89. nerates a terrain alert or warning the terrain feature displayed on the PFD will be colored yellow for an alert or red for a warning for as long as the alert remains valid Because the area monitored by the Terrain or TAWS system can be wider than the field of view that can be displayed by the SVS system it is possible to receive an obstacle or terrain audible alert for an obstacle or terrain that is not shown on the SVS display those cases the object generating the alert will be left or right of the aircraft Refer to the other displays in the aircraft to determine the cause of the message Flight Path Marker 5 The SVS display includes a green circular barbed symbol called the Flight Path Marker FPM that represents the current path of the airplane relative to the terrain display The FPM is always displayed when synthetic terrain is displayed and the aircraft ground speed exceeds 30 kt The FPM indicates the current lateral and vertical path of the airplane as determined by the GPS sensor If the FPM is above the horizon line the airplane is climbing and similarly if the FPM is below the horizon line the airplane is descending f the airplane is flying in a crosswind the FPM will be offset from the center of the display In that case the center of the PFD airplane reference symbol indicates the airplane heading and the FPM indicates the direction that the airplane is actually moving taking into account the crosswind The FPM indicate
90. nfOUtO iii be inMein 800 feet AGL 3 Approach GP or GS 200 feet AGL 4 Approach FLC VS PIT or ALT Mode Higher of 400 feet AGL or Approach MDA SYNTHETIC VISION Use of the Synthetic Vision system display elements alone for aircraft control without reference to the G1000 primary flight instruments or the aircraft standby instruments is prohibited Use of the Synthetic Vision system alone for navigation or obstacle or terrain avoidance is prohibited Use of the SVS traffic display alone to avoid other aircraft is prohibited 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 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 19 of 117 NOTE The MAP TAWS page and terrain display is intended to serve as a situational awareness tool only
91. ng Air Page 51 of 117 9 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 surface 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 ELEG HEAT orrai e idet e a N M pt A cit edt t ea ri etes OFF ic e ete ico doeet eu det OFF Fleading dat Ret i MONITOR using magnetic compass Land as soon as practical NOTE The autopilot will disconnect and will not re engage Reference the GPS track on MFD PFD map to improve situational awareness GPS will continue to display correct GPS based map position and track 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 T Standby Attitude 3yr0 en n eoe re aie a e p metet MONITOR 2 Affected PFD SENSOR enne PRESS 3 AEIRS SOfIKOy tite etre PRESS Opposite Side AHRS softkey
92. ng the LNAV only minimums During any GPS approach in which both precision and non precision alarm limits are exceeded the G1000 System 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 50 of 117 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 If Both Sides 1 Airspeed MONITOR using standby indicators 2 Land as soon as practical If One Side Only 1 Autopilot ALT Mode rera te d er an do p d ets DISENGAGED 2 Affected PFD SENSOR 5 PRESS 3 ADC Softkey PRESS the ADC s
93. of Garmin Garmin hereby grants permission to download a single copy of this manual and 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 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 www garmin com Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 2 of 117 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 DESCBIPTHON APPROVAL e Robert G Murray A ALL Original Issue 11 08 2007 DAS Administrator Garmin International Inc DAS 240087 CE Robert G M B ALL Repaginated 11 21 2007 DAS Adminisirator Garmin International Inc DAS 240087 CE 17 24 Added Non essential equipment See Cover See Cover list to DUAL GENERATOR FAILURE procedure added GDU cooling fans to minimum equipment list editorial updates D All Updated System Software See Cover See C
94. oftkey to select the functional ADC ADC1 or ADC2 4 amp ales nta CONFIRM BOTH ON ADC1 OR BOTH ON ADC 2 annunciated on both PFDs 5 Autopilot ALT Mode FAILED ATTITUDE AND OR HEADING RESELECT AS DESIRED 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 and Pilot s 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 Vee Attt de oec Et ED CROIRE d D di MONITOR using standby attitude gyro 2 WSHLD ANTI ICE Switches Pilot and OFF 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT Ki
95. on Comman d Limit Roll Mode 25 Left Bank default ot 25 Right Bank Low Bank 15 Left Bank BANK Key 15 Right Bank Heading Select 25 Left Bank PIG 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 BOK Be 25 Right Bank Approach GPS Arm Capture Track Glidepath GPS 25 Left Bank Mode Automatically Armed if available 259 Right Bank Approach VOR Arm Capture Track APR 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 l GA Switch Go Around in air GA Wings Level No 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
96. operating regulation Pilot s audio panel required for single Audio Control Panel pilot operation Both sides required for two crew operation Primary Flight Display Multi Function Display Air Data Computer Attitude Heading Reference System AHRS Standby Attitude Indicator Standby Altimeter Standby Airspeed Indicator Or as required by operating regulation Or as required by operating regulation ATC Transponder VHF Navigation Receiver Or as required by operating Automatic Direction Finder ADF regulation Distance Measuring Equipment Or as required by operating DME regulation Marker Beacon Receiver Or as required by operating regulation Terrain Awareness and Warning Or as required by operating System TAWS regulation Or as required by operating Weather Radar regulation XM Datalink Weather MFD fan is required if OAT is above 33 C 91 F GDU Cooling Fans 3 total All fans are if OAT is above Equipment and components required for RNAV Operations Equipment and RNAV 2 RNAV 1 B RNAV P RNAV Class II Components navigation RNP and RNAV routes including 3 Standard Instrument Departures SIDs and GPS SBAS receiver with GPS Obstacle Departure Procedures ODPs Software 3 2 or later approved Standard Terminal Arrival STAR and version Note 1 2 enroute RNAV Q and RNAV T routes and GPS or GPS and RNAV GPS GDU 104X Display instrument appro
97. or 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 TAWS TAWS WARNING Red on PFD and aural PULL UP 1 AP YD DISC TRIM INTRPT Button eese enne PRESS and RELEASE To disconnect the autopilot 2 Aircraft 22 42 2 PULL BACK ON CONTROL WHEEL Ki MAXIMUM ALLOWABLE 4 Airspeed E ence score cra seca sacs BEST ANGLE OF CLIMB SPEED b PoOWel ou runi E MAXIMUM CONTINUOUS Altitude ertet ine eas CLIMB AND MAINTAIN SAFE ALTITUDE Advise ATC of Altitude Deviation if appropriate NOTE Only vertical maneuvers are recommended unless either operating in visual meteorological conditions VMC or the 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 34 of 117 This page intentionally left blank
98. over Version from 0636 01 to 0636 02 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 3 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 4 of 117 Table of Contents S ction 1 ninh 7 Section 2 Limitations cron s Ea dx LER Haa E o d e 15 Section 3 Emergency Procedures 27 Section Abnormal Procedures 37 Section 4 Normal QU 59 Section 5 Performante 80 Section 6 Weight and 80 Section 7 Systems 83 Section 8 Handling Service and Maintenance 117 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 5 of 117 This page intentionally left blank Hawker Beechcraft C9
99. rence system Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 8 of 117 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 9 of 117 ABBREVIATIONS AND TERMINOLOGY The following glossary is applicable within the airplane flight manual supplement AC ADC ADF AFCS AFM AFMS AGL Ah AHRS ALT ALTS ALTV AMMD AP APR APTSIGNS APV AS ATC AUX BANK BARO BAT BC BRNAV BRT CDI CLR COM CRG CRS CWS Advisory Circular Air Data Computer Automatic Direction Finder Automatic Flight Control System Airplane Flight Manual Airplane Flight Manual Supplement Above Ground Level Amp hour Attitude a
100. rmed to be available along the entire route of flight The route planning and WFDE prediction program may be downloaded from the GARMIN G1000 website on the internet For information on using the WFDE Prediction Program refer to GARMIN WAAS FDE Prediction Program part number 190 00643 01 WFDE Prediction Program Instructions For flight planning purposes operations within the U S National Airspace System on RNP and RNAV procedures when SBAS signals are not available the availability of GPS integrity RAIM shall be confirmed for the intended route of flight In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended route of flight the flight should be delayed canceled or re routed on a track where RAIM requirements can be met For flight planning purposes for operations within European B RNAV and P RNAV airspace if more than one satellite is scheduled to be out of service then the availability of GPS integrity RAIM shall be confirmed for the intended flight route and time In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended flight the flight should be delayed canceled or re routed on a track where RAIM requirements can be met For flight planning purposes operations where the route requires Class navigation the aircraft s operator or pilot in command must use the G1000 WFDE Prediction program to demonstrate that there are no out
101. rmin 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 18 of 117 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 E
102. rning authority The navigation equipment required to join and fly an instrument approach procedure is indicated by the title of the procedure and notes on the IAP chart Use of the GARMIN G1000 GPS SBAS receivers to provide navigation guidance during the final approach segment of an ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for or GPS navigation is prohibited When using the G1000 VOR LOC GS receivers to fly the final approach segment VOR LOC GS navigation data is must be selected and presented on the CDI of the pilot flying 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 AHRS AREAS OF OPERATION Flight operations with the G1000 Integrated Avionics installed are prohibited in the following regions due to unsuitability of the magnetic fields near the Earth s poles 1 North of 72 North latitude at all longitudes 2 South of 70 South latitude at all longitudes 3 North of 65 North latitude between longitude 75 W and 120 W Northern Canada 4 North of 70 North latitude between longitude 70 W and 128 W Northern Canada 5 North of 70 North latitude between longitude 85 E and 114 E Northern Russia 6 South of 55 South latitude between longitude 120 E and 165 E Region south of Australia and New Zealand NOTE The Ga
103. rom the present position to a waypoint Altitude Presel amp ct e eie em e p trim RESET 25 MNMBUIIOT me oed ad n a ar et o erede ees PRESS 8 MaypOlni accueil gusce rad dica dou ta de ea de SELECT desired waypoint 4 VNV gt Softkey MFD Flight Plan PRESS 5 Wert ical iDIBEG TI Que ide ooa fete atom detiene etat Pe ACTIVATE LATERAL MODES HEADING MODE HDG Ta HD GFKNOD iai tp tiere tp eds PUSH to synch heading bug to current heading 2 IHDG BUTTON tt tore e eer Pep c reri Pe n den PUSH HDG mode annunciated 3 HDG Knob une RS Rotate to set heading bug to desired heading NAVIGATION VOR 1 Navigation SELECT VOR 1 or VOR2 using CDI softkey on PFD 22 de RU ee daa do e ue Ae odd SET using CRS knob 3 Intercept ESTABLISH in HDG or ROL mode 4 Mode Controller esses PRESS NAV on mode controller 5 VOR will be annunciated in WHITE if the 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
104. roximately 4 5 nm from the airport the airport sign will be removed but the runways presentation will remain If an approach to a specific runway has been loaded and activated that runway will be highlighted on the SVS display When on an approach the highlight for the approach runway will be considerably larger than normal to assist in visually acquiring the runway The oversized highlight will automatically shrink around the runway depiction so that the runway is proportionally displayed when the aircraft is within approximately Ve nm of the threshold Runway highlighting is displayed even if APTSIGNS are turned off Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 114 of 117 This page intentionally left blank 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 115 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 116 of 117 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 D Hawker Beechcraft C90A and C90GT King Air Page 117 of 117
105. s the current path of the airplane but does not predict the future path If aircraft attitude power setting airspeed crosswind etc are changed the FPM will move to indicate the new path resulting from those changes If the FPM is below the terrain or obstacle displayed behind it on the PFD the current aircraft path will not clear that terrain or obstacle If the FPM is above that terrain or obstacle the aircraft will clear the terrain or obstacle IF AND ONLY IF THE CURRENT AIRCRAFT CONFIGURATION IS MAINTAINED AND THE AIRCRAFT PERFORMANCE WILL PERMIT YOU TO MAINTAIN THE CURRENT VERTICAL CLIMB GRADIENT UNTIL PAST THE TERRAIN OR OBSTACLE Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 112 of 117 Pathway BE If PATHWAY is enabled on the SVS menu of the PFD and a defined navigation path has been entered on the G1000 the SVS system will display a pathway sometimes called a highway in the sky or HITS The pathway is a perspective representation of the programmed flight path When the aircraft is well off course the pathway will be displayed as a number boxes floating in the sky along the programmed lateral and vertical path As the aircraft intercepts the programmed flight path the number of boxes displayed will be reduced to a maximum of four to avoid cluttering the PFD display The pathway is only displayed for navigation paths that are fully defined by the sensor in use Because a fully defined lateral and vertica
106. sed 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 Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 76 of 117 Recommended procedures following a missed approach 1 To 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 c all waypoints after t
107. ssures LOWER than standard can cause GPS altitude to read HIGHER than indicated altitude If Able to Identify Accurate Altitude Source Autopilot ALT Mode rete rende tre Len DISENGAGED Use SENSOR softkey to select most accurate ADC on both PFD s Confirm DI or BOTH ON ADC2 annunciators are displayed on both PFDs Autopilot ALT Mode essen ener nnne ENGAGE AS DESIRED 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 plan an ILS LPV 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 Decision 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 A 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 D Page 44 of 117 AIRSPEED
108. sult 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 ILS 2 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 Load the approach into the Active Flight VERIFY the G1000 tunes the proper ILS frequency Approach 5 SET on TMR REF page if not already set IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control 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 extinguis
109. sure 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 24 vdc 5 Ah JET model PS 835 Standby Battery 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 three modes OFF ON and ARM Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 108 of 117 OFF 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 ON Amber 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 w
110. t 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 AVIONICS ELECTRICAL EQUIPMENT BUS CONNECTION LEFT GENERATOR BUS RIGHT GENERATOR BUS GEN No 1 CENTERIBUS GEN No 2 AVIONICS AVIONICS AVIONICS PFD1 GIA 1 Cooling Fan Avionics Annunciator PFD2 GIA 2 Cooling Fan No 2 Avionics Bus PFD 1 Secondary Power No 3 Avionics Bus COM 2 AHRS 1 Secondary Power Data Link AUDIO 2 ADC 1 Secondary Power Radio Altimeter OPT XPDR 2 GIA 1 Secondary Power ADF RADAR WX 500 Stormscope OPT DME Skywatch Traffic OPT AFCS SERVOS ELECTRICAL ELECTRICAL ELECTRICAL L Gen Bus Bus Tie amp Meter R Gen Bus Bus Tie amp Meter Generator Reset Indication Indication L Generator Control Panel 1 L Generator Field amp Sense 1 L Generator Loadme
111. t C90A and C90GT King Air 190 00682 02 Rev D Page 70 of 117 RNAV GPS LPV or LNAV VNAV 1 Load the approach into the Active Flight Plan 2 Approach 5 SET ON TMR REF page if not already set IF Flying Vectors To Final 3 Airplane on Vectors To Final a Mode Control 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 Lote nue iiio ns Course pointer slews to the front course d Mode Control PRESS APR Verify GPS and GP 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 HSPOBI at cett de tc tse SELECT GPS Nav Source c Mode Control Panel PRESS APR Verify GPS mode active GP armed d VERIFY ex Course pointer slews to the front course 4 Established inbound on Final Approach Course VERIFY tat Course Pointer is set to the final approach course
112. t 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 The G1000 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 Pilot s Guide and Cockpit Reference Guide P N 190 00663 01 and 190 00664 01 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 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
113. t 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 n the event of total loss 5 of normal aircraft electrical power the vibrator and internal lighting is 2 powered by the standby battery The standby altimeter uses the 52 copilot s static system for its source of static air pressure dem The bottom instrument is a mechanical airspeed indicator It is mechanical instrument that requires electrical power to operate Electrical power is used for internal lighting the event 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 STANDBY BATTERY ARM ON Figure 14 Standby Flight Instruments Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 102 of 117 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
114. te 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 Course deviation information will be displayed as an amber CDI on both PFDs and will remain for up to 20 minutes after GPS position data has been lost The autopilot and or flight director may be coupled in GPS mode while the system is in Dead Reckoning mode Refer to the G1000 Cockpit Reference Guide for further information Revert to an alternate means of navigation appropriate to the route and phase of flight If Alternate Navigation Sources ILS LOC VOR DME ADF Are Available 13 Navigationi ir ate edi c te meo nia eie E ER a USE ALTERNATE SOURCES If No Alternate Navigation Sources Are Available DEAD RECKONING DR MODE ACTIVE WHEN THE AIRPLANE IS GREATER THAN 30 NM FROM THE DESTINATION AIRPORT 2 Navigation Use the airplane symbol and magenta course line on the map display NOTE e ALL INFORMATION NORMALLY DERIVED FROM GPS TURNS AMBER ALL OF THIS INF
115. teady 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 navigation attitude and air data inputs 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 Preselect iie eR Reed eden SET to Desired Altitude 2 Press VS GREEN VS White ALTS annunciated on PFD 3 Vertical Speed ADJUST using UP DN Wheel 4 Green ALT 3 ade dete enit ts VERIFY UPON ALTITUDE CAPTURE FLIGHT LEVEL CHANGE FLC MODE Altitude in tee beth s SET to Desired Altitude Press Button eese GREEN FLC White ALTS annunciated on PFD AIRSPEED Reference sse ADJUST using UP DN Wheel Green ALT i a Tb ord VERIFY UPON ALTITUDE CAPTURE Pi ORO ce NOTE If the altitude preselect is not changed before selecting FLC the autopilot may re capture the current altitude immediately af
116. tection mode barometric minimum descent altitude Minimum Equipment List Multi Function Display Hawker Beechcraft C90A and C90GT King Air Page 12 of 117 190 00682 02 Rev D MLS 5 NAV NEXRAD NM NPA OAT OBS OPT OVHD P N PDA PED PFD PFT PIT POH PRNAV PROC PROP PSI PTCH PWR R REF RNAV RNP ROL RPM SBAS SDF SID SPD Microwave Landing System Maximum operation limit speed in mach Minimum Navigational Performance Specifications North Atlantic Track Navigation or AFCS navigation mode or NAV button on the GMC710 AFCS Mode Controller Next Generation Radar XM Weather Product Nautical Mile Non precision Approaches Outside Air Temperature Omni Bearing Selector Optional Overhead Part Number Premature Descent Alert Pedestal Primary Flight Display Pre Flight Test AFCS pitch mode Pilot s Operating Handbook Precision Area Navigation Procedure button on the GDU or GCU 477 Propeller Pounds per Square Inch Pitch Power Right Reference Area Navigation Required Navigation Performance AFCS roll mode Revolutions per Minute Satellite Based Augmentation System Simplified Directional Facility Standard Instrument Departure Speed button on the GMC 710 AFCS Mode Controller Toggles the FLC speed between Mach and IAS references 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 13 of 117 STAR STBY STC SUSP SVS SW SYN TERR SYN VIS
117. ter 1 ENGINE L Engine Fuel Control Heater L Chip Detector L Main Anti ice Ice Vane R Standby Anti Ice Ice Vane 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 Anti Ice Ice Vane Hawker Beechcraft C90A and C90GT King Air Page 104 of 117 190 00682 02 Rev D 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 Indicator and Control Rudder Boost Flap Motor FUEL FUEL L Firewall Valve L Fuel Boost Pump Crossfeed Valve R Firewall Valve R 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
118. ter 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 D Hawker Beechcraft C90A and C90GT King Air Page 65 of 117 ALTITUDE HOLD ALT MODE MANUAL CAPTURE At the desired PRESS ALT Button on Mode Controller 2 Greens ce hedera Ir aco cd aah cra 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 Descent 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
119. ting 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 lights are powered from the Hot Battery bus 190 00682 02 Rev D Hawker Beechcraft C90A and 90 King Air Page 109 of 117 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 pilots 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 PROTECTIO
120. 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 Some 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 Ma
121. und on the final approach course When automatic flight plan waypoint sequencing resumes SUSP will extinguish 6 VERIFY uinea ette Course pointer slews to the inbound course Mode Controler d d dea dde aded ee Oe 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 P gt the IAF Bs AST OLD EEATT SELECT GPS Nav Source CG Mode Gontroller oreet Leite teret eb oec cete ema etel PRESS APR Button GPS will be the active lateral mode GP will ARM if the procedure provides vertical guidance 4 Established inbound on Final Approach Course FAF Active Waypoint VERIFY Antes ui Course Pointer is set to the final approach course b MERIEXY e etra LNAV V or LNAV is annunciated on the HSI Ce VERIFY Ascot stet tta GP Deviation Scale Displays if applicable d Minimum Descent Altitude MDA Altitude In Altitude Preselect 5 MAINTAIN 110 KIAS OR GREATER Recommended Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 72 of 117 NOTE Some RNAV GPS approaches provide a vertical descent angle as an aid in flying a stabilized approach These approaches ar
122. 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 intermittent loss of attitude and heading displays while the aircraft in on the ground 1 Flhght Instr ments tocco iy dct tap c cea ucc ge dg cs CHECK Compare attitude displayed by PFD1 PFD2 and Standby Attitude Indicator Compare altitude displayed by PFD1 PFD2 and Standby Altimeter Verify the correct barometric pressure is set in the PFD1 PFD2 and Standby Altimeters 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 D Page 62 of 117 BEFORE TAKEOFF RUN UP These procedures should be conducted after completing the airplane s AFM BEFORE TAKEOFF RUNUP checklist items 1 CHECK THEN OFF 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 AFT
123. 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 weather 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
124. way If the programmed flight plan includes one or more defined VNAV descent segments the descent path s will be displayed by the Pathway as prompted by the Gi1000 FMS If the flight plan includes a significant change in course at a waypoint the Pathway boxes toward the currently active waypoint will be magenta in color The boxes defining the next flight plan segment may be visible but will be displayed in a white color displayed by Pathway Climb NOT displayed by Pathway Enroute Pathway Altitude Display Approach During an approach transition with the GPS CDI active the Pathway will be displayed along the lateral path defined by the flight plan at the altitude selected on the G1000 altitude selector Pathway will be displayed at least up to the Final Approach Fix on all instrument approach procedures For ILS LNAV VNAV LNAV V and LPV approaches the Pathway will display the lateral and vertical descent segments from the glideslope or glidepath intercept altitude down to the Decision Altitude For all other non precision approaches Pathway will not display beyond the Final Approach Fix until the missed approach segment become active In all cases the pilot must still ensure that the aircraft complies with the requirements of the published instrument approach procedure Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 78 of 117 Missed approach When the missed approach is selected
125. west grid to assist in orientation relative to the terrain The terrain display is intended to serve as an 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 Navigation must not be predicated solely upon the use of the TAWS Terrain or Obstacle data displayed by the G1000 SVS system 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 111 of 117 The Terrain Obstacle Airport databases have an area of coverage as detailed below e The Terrain Database has an area of coverage from North 75 Latitude to South 60 Latitude in all longitudes e The Airport Terrain Database has an area of coverage that includes the United States Canada Mexico Latin America and South America e The Obstacle Database has an area of coverage that includes the United States NOTE The area of coverage may be modified as additional terrain data sources become available Obstacle and Terrain Alerts and Warnings Obstacles and terrain displayed on the SVS system may be highlighted if an alert or warning is generated by the G1000 Terrain or TAWS system If an obstacle alert is presented for an obstacle that is in the SVS field of view the obstacle symbol on the PFD will turn yellow in color an obstacle warning is generated by the G1000 system the obstacle symbol on the PFD will turn red If the G1000 Terrain or TAWS system ge
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127. wker Beechcraft C90A and C90GT King Air Page 57 of 117 This page intentionally left blank Hawker Beechcraft C90A and C90GT King Air 190 00682 02 Rev D Page 58 of 117 Section 4 Normal Procedures Table of Contents COM RADIO COMMUNICATIONS BEFORE STARTING ENGINES 61 BEFORE STARING poco Kuga c Qu Cad od oU on anc an 61 rem E 61 62 BEFORE TAKEOFF RUN U PD isissesskessuuu ka abo cR Ry LASER NE EP EA MM 63 BEFORE EM FPIFM HEAD ERO EM E M 64 ON TAKEOFF ROLL iti dud EID UU LN RUDI 64 CLIMB CRUISE AND DESGCENT 2n nins on inu rrr xi tuta n vo nk Ya dau tao n 64 SHUTDOWN AND SECURING 2 5 cranii nu ain ada dai o ga ck dk dun nnmnnn nne 64 OTHER PROCEDURES ein S titan E gU pibe BM cu op n Cre 65 AUTOPILOT OPERATION ccs occhi iia c nen GU dA xen 65 VERTICAL MODES cR 65 VERTICAL SPEED VS eee inti eee 65 FLIGHT LEVEL CHANGE PEG MODE cete 65 ALTITUDE HOLD ALT MODE MANUAL CAPTURE ticae 66 VERDIGAILINAVIGUATIONIMINEM
128. ximum continuous gas generator speed is limited to 38 100 rpm or 101 5 A 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 synchronization 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 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 103 of 117 PROPELLER SYNCHROPHASER A push button ON OFF switch is located on the instrument panel below the pilot s PFD tha
129. y a yellow TRAFFIC annunciator to the right of top of the airspeed display tape The SVS display includes an always visible white horizon line that represents the true horizon Terrain will be presented behind the horizon line and terrain shown above the horizon line is above the current aircraft altitude Terrain that is shown below the horizon line is below the aircraft altitude Horizon Heading A heading scale may be displayed on the PFD horizon line if selected by the pilot The heading marks are spaced in even 30 degree increments and are presented just above the horizon line with tic marks that intersect the horizon line The horizon heading will correspond to that presented by the HSI Because the horizon heading is only displayed in 30 degree increments it should only be used for general heading awareness and not be used to establish the aircraft heading Horizon line 190 00682 02 Rev D Hawker Beechcraft C90A and C90GT King Air Page 113 of 117 Airport Signs and runway highlight If APTSIGNS is selected a sign post along with a representation of the runways will be plotted on the SVS display for nearby airports that are contained in the G1000 airport database The signpost will become visible when you are within approximately 15nm of the airport The text identifier for the airport will be displayed inside the airport sign when the aircraft reaches approximately 8 nm from the airport Once the aircraft reaches app
130. ystem 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 The 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 02 The Garmin G1000 Cockpit Reference Guide P N 190 00664 01 Rev A or later FAA approved revision must be immediately availabl

Garmin C90A/GT Airplane Flight Manual Supplement

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