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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT

GARMIN G1000 INTEGRATED AVIONICS SYSTEM

DIAMOND MODEL DA 40

DIAMOND MODEL DA 40 F

190-00492-10 Rev 5

Diamond DA 40 / DA 40F

Page 35 of 65

3.7.1 ICING

Unintentional flight into icing conditions

Leave the icing area (by changing altitude or turning back, in order to reach
zones with a higher ambient temperature).

Pitot heating ............................................................................................. ON

Cabin heat ................................................................................................. ON

Air distribution lever............................................................................

(UP)

RPM.............................................................. increase, in order to prevent ice

build-up on the propeller blades

Alternate Air (

DA 40 only

) ..................................................................OPEN

Carburetor Heat (

DA 40 F only

) ........................................................... HOT

Emergency window(s) ...........................................................open if required

CAUTION

Ice build-up increases the stalling speed. If required for safety reasons,
engine speeds up to 2700 RPM are permissible without time limit.

ATC .........................................................advise if an emergency is expected

CAUTION

When the pitot heating fails (yellow PITOT FAIL annunciation), and the
alternate static valve is installed:

Alternate static valve ............................................................................OPEN

10.

Emergency window(s) ............................................................................ close

Содержание Cessna Caravan G1000

Страница 1: ......

Страница 2: ...190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 2 of 65 This page is intentionally blank...

Страница 3: ...WITH GFC 700 AUTOMATIC FLIGHT CONTROL SYSTEM DIAMOND MODEL DA 40 DIAMOND MODEL DA 40 F LOG OF REVISIONS Revision Number Page Number s Description FAA Approved Date of Approval 1 All Initial Release R...

Страница 4: ...190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 4 of 65 This page is intentionally blank...

Страница 5: ...ND MODEL DA 40 F Table of Contents SECTION I GENERAL 7 NOT FAA APPROVED SECTION II LIMITATIONS 14 FAA APPROVED SECTION III EMERGENCY PROCEDURES 26 NOT FAA APPROVED SECTION IVA NORMAL PROCEDURES 40 NOT...

Страница 6: ...190 00492 10 Rev 5 Diamond DA 40 DA 40F Page 6 of 65 This page is intentionally blank...

Страница 7: ...n of the PFD is to provide attitude heading air data navigation and alerting information to the pilot The PFD may also be used for flight planning The primary function of the MFD is to provide engine...

Страница 8: ...AA Order 8700 1 Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor This does not constitute operational appr...

Страница 9: ...rdance with PRNAV requirements JAA Administrative Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 Airworthiness and Operational Approval for Precession RNAV Oper...

Страница 10: ...NAV and LNAV V within the U S National Airspace System The G1000 Integrated Avionics system as installed in this aircraft has been found to comply with the requirements for GPS as a Primary Means of N...

Страница 11: ...s JAA Administrative Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 Airworthiness and Operational Approval for Precession RNAV Operations in Designated European...

Страница 12: ...signals except for routes requiring only one Long Range Navigation LRN sensor This does not constitute an operational approval North Atlantic NAT Minimum Navigational Performance Specifications MNPS...

Страница 13: ...onform to WGS 84 or equivalent ELECTRONIC FLIGHT BAG The G1000 Integrated Avionics System as installed in this aircraft has been approved as a Hardware Class 3 Software Type C Electronic Flight Bag EF...

Страница 14: ...00324 09 Revision A or later appropriate revision 2 The G1000 installation in the DA 40 requires the following or later FAA approved LRU software versions Approved LRU software versions are referenced...

Страница 15: ...h of 70 S latitudes In addition operation is prohibited in the following two regions 1 north of 65 N between 75 W and 120 W longitude and 2 south of 55 S between 120 E and 165 E longitude 4 The fuel q...

Страница 16: ...data 2 GPS or GPS and RNAV GPS instrument approaches using the G1000 System are prohibited unless the pilot verifies and uses the current Aviation database GPS based instrument approaches must be flo...

Страница 17: ...t the planned approach is in the database 6 Use of the G1000 VOR ILS receiver to fly approaches not approved for GPS requires VOR ILS navigation data to be present on the display 7 When conducting mis...

Страница 18: ...ate to the flight with the exception of oceanic and remote operations For flight planning purposes if an alternate airport is required the alternate airport must have an approved instrument approach p...

Страница 19: ...em is prohibited if the preflight test is not satisfactorily completed 2 A pilot with the seat belt fastened must occupy the left pilot s seat during all autopilot operations 3 The autopilot must be o...

Страница 20: ...of position information on all terminal charts for airports within 1 5 either side of zero degrees latitude or longitude The list of affected airports below is subject to change by Jeppesen This list...

Страница 21: ...band 20 KIAS 53 KIAS Low speed awareness stall is imminent Yellow band 53 KIAS 58 KIAS Low speed awareness reduced airspeed margin to stall White band 58 KIAS 91 KIAS Operating range with flaps fully...

Страница 22: ...or of the prohibited range and will flash Indication Red arc or bar Lower prohibited range Yellow arc or bar Caution range Green arc or bar Normal operating range Yellow arc or bar Caution range Red a...

Страница 23: ...e G1000 Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories Warning annunciations Red Annunciation Cause OIL PRES LO Oil pressure is less tha...

Страница 24: ...e Equipment Number installed VFR Day VFR Night IFR Primary Flight Display 1 1 1 1 Multi Function Display 1 1 1 1 Audio panel 1 1 1 1 Air data computer 1 1 1 1 Attitude and Heading Reference System 1 0...

Страница 25: ...0 DA 40F FAA Approved Page 25 of 65 2 15 Limitation Placard Below the MFD next to the fuel quantity indication Standard Tanks Fuel qty Indication max 17 US gal Max difference LH RH tank 10 US gal For...

Страница 26: ...corner 4 If the GPS NAV LOST annunciation is displayed the system will flag and no longer provide GPS based navigational guidance The crew should revert to the G1000 VOR ILS receivers or an alternate...

Страница 27: ...s appear in various locations on the PFD or MFD Annunciation Cause AHRS Aligning Keep Wings Level Attitude and Heading Reference System is aligning Keep wings level using standby attitude indicator AT...

Страница 28: ...ellow CHECK ATTITUDE on the PFD The autopilot and AHRS monitors normally detect failures and automatically disconnect the autopilot Failure of the electric pitch trim indicated by a red boxed PTRM ind...

Страница 29: ...PFD 1 Throttle REDUCE When overspeed condition is corrected 2 Autopilot RESELECT VERTICAL MODE if necessary NOTE Overspeed recovery mode provides a pitch up command to decelerate the airplane at or be...

Страница 30: ...nt sustained control forces in the direction of the annunciation arrow For example an arrow pointing down indicates nose down control stick force will be required upon autopilot disconnect NOTE Moment...

Страница 31: ...RE ENGAGE if lateral trim re established FLASHING YELLOW MODE ANNUNCIATION NOTE Abnormal mode transitions those not initiated by the pilot or by normal sequencing of the autopilot will be annunciated...

Страница 32: ...rcuit breaker unless the airplane is on the ground MAXIMUM ALTITUDE LOSS DUE TO AUTOPILOT FLIGHT DIRECTOR OR AHRS MALFUNCTIONS MANEUVER ALTITUDE LOSS Climb Cruise Descent 200 feet Maneuvering 115 feet...

Страница 33: ...cy battery will supply power to the standby attitude gyro artificial horizon and the flood light In case of extreme smoke development the front canopy may be unlatched during flight This allows it to...

Страница 34: ...b of this Supplement Alternator Failure 15 Land at the nearest suitable airport as soon as possible The equipment available on Essential Bus only operating on battery only and the Essential Bus switc...

Страница 35: ...Cabin heat ON 4 Air distribution lever f UP 5 RPM increase in order to prevent ice build up on the propeller blades 6 Alternate Air DA 40 only OPEN 6a Carburetor Heat DA 40 F only HOT 7 Emergency wind...

Страница 36: ...minutes If PFD attitude information is lost prior to landing 6 HORIZON EMERGENCY Switch ON CAUTION The following items are available on the Essential Bus PFD in composite backup format NAV COM 1 GPS...

Страница 37: ...Y REVERSIONARY MODE If the PFD and MFD have automatically entered reversionary mode use the following procedure a DISPLAY BACKUP button on audio panel PUSH button shall be OUT NOTE After automatic ent...

Страница 38: ...ndicated by a red X and yellow text over the airspeed altimeter vertical speed TAS and OAT displays Some FMS functions such as true airspeed and wind calculations will also be lost 1 Use Standby Airsp...

Страница 39: ...ator appears which does not agree with other displays or system information 1 If an annunciator appears treat it as if the condition exists Refer to the AFM Emergency or Abnormal procedures or the pro...

Страница 40: ...d the Garmin G1000 Pilot s Guide PRE FLIGHT INSPECTION I Cabin check a MET NAV Mass CG flight planning complete b Airplane documents complete and up to date c Ignition key pulled out d Front canopy re...

Страница 41: ...gal n Position lights strobe light ACL s check o BAT battery switch OFF p Check for loose items complete q Flight controls and trim free to move and correct r Baggage stowed and secure NOTE Refer to...

Страница 42: ...r switch OFF 20 Essential Bus switch OFF CAUTION When the essential bus is switched ON the battery will not be charged unless the essential tie relay bypass OAM 40 126 is installed 21 BAT battery swit...

Страница 43: ...o start the engine let the starter cool for 30 minutes before further start attempts CAUTION The use of an external pre heater and external power source is recommended whenever possible in particular...

Страница 44: ...ns can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attemp...

Страница 45: ...angered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start t...

Страница 46: ...ARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION Do not overheat the starter motor Do not operate the starter motor for...

Страница 47: ...ump noise functional check of pump 4 Throttle travel forward from IDLE WARNING Before starting the engine the pilot must ensure that the propeller area is free and no persons can be endangered CAUTION...

Страница 48: ...gered CAUTION Do not overheat the starter motor Do not operate the starter motor for more than 10 seconds After operating the starter motor let it cool off for 20 seconds After 6 attempts to start the...

Страница 49: ...ciation 9 Pitot heating OFF if not required yellow PITOT OFF annunciation 10 Strobe lights ACLs check ON test function as required 11 Position lights landing and taxi lights ON test function as requir...

Страница 50: ...essages illuminated 7 Fuel tank selector fullest tank 8 Engine instruments in green sector 9 Circuit breakers pressed in 10 Fuel pressure Check no messages illuminated 11 Electric fuel pump ON 12 Mixt...

Страница 51: ...The result of the ground check at full throttle depends on a number of environmental factors e g temperature ambient air pressure and in particular head or tailwind components Headwind will cause a h...

Страница 52: ...MODES AND PROPER ENGINE POWER SETTINGS TO ENSURE THAT AIRCRAFT SPEED IS MAINTAINED BETWEEN 70 KIAS AND 165 KIAS IT WILL BE NECESSARY TO CHANGE ENGINE POWER TO MAINTAIN THE DESIRED RATE OF DESCENT WHE...

Страница 53: ...o desired altitude 2 Mode Controller SELECT FLC on mode controller 3 Airspeed Reference ADJUST using NOSE UP and NOSE DN buttons 4 White ALT altitude preselect armed NOTE on PFD 5 Green ALT VERIFY UPO...

Страница 54: ...VNV on mode controller 5 White VPTH Vertical Path armed NOTE on PFD 6 Green VPTH VERIFY UPON VERTICAL PATH CAPTURE NOTE If VNV is pressed and VPTH is armed prior to 5 minutes time to top of descent V...

Страница 55: ...capture mode when the VAPP button is pressed and annunciate VAPP in green on the PFD ILS LOC 1 Navigation Source SELECT LOC using CDI button on PFD 2 Course Bearing Pointer SET using course knob 3 Int...

Страница 56: ...S front course using course knob 3 Intercept Heading ESTABLISH in HDG or ROL mode if required 4 Mode Controller SELECT NAV on mode controller 5 Green or White BC annunciation NOTE on PFD NOTE The cour...

Страница 57: ...based on analysis of all available instruments and information TAWS WARNING If a TAWS WARNING occurs immediately initiate and continue a climb that will provide maximum terrain clearance or any simil...

Страница 58: ...age on the ground 1 Engine speed 1200 RPM 2 Electrical equipment OFF 3 Ammeter and voltmeter check If the caution message does not extinguish and the ammeter legend flashes and reads zero discontinue...

Страница 59: ...d is equal to a one ball width slip Rate of turn information is shown on the scale above the compass rose full scale deflection is equal to a standard rate turn The following controls are available on...

Страница 60: ...receiver selectors as well as an integral intercom and marker beacon system The marker beacon lights appear on the PFD In addition a clearance recorder records the last 2 minutes of received audio Lig...

Страница 61: ...nnect switch on both sides a left control stick mounted CWS Control Wheel Steering switch a throttle mounted GA Go Around switch and PFD MFD mounted altitude preselect heading and course knobs Flight...

Страница 62: ...ormation The GFC 700 may be manually disconnected by any of the following means Depressing the red AP DISC button on either control stick Moving the left outboard side of the manual electric trim swit...

Страница 63: ...ual electric trim will be inoperative Loss of GIA 2 will also prevent autopilot and manual electric trim operation but flight director will be available Loss of the standby airspeed indicator standby...

Страница 64: ...of the G1000 and GFC 700 system and operating procedures Refer to the following table to determine the appropriate guide The System Software Version number is displayed at the top right side of the MF...

Страница 65: ...00 s fuel quantity gauge For the Long Range Tank configuration dual pointers on a linear scale a top pointer for the left fuel quantity and a bottom pointer for the right fuel quantity indicate fuel q...

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