Garmin | G1000: Diamond DA40/DA40F | Garmin G1000: Diamond DA40/DA40F Airplane Flight Manual Supplement

Garmin G1000: Diamond DA40/DA40F Airplane Flight Manual Supplement
This page is intentionally blank.
Garmin Ltd. Or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
LOG OF REVISIONS
Revision
Number
Page
Number(s)
FAA
Approved
Date of
Approval
1
All
Initial Release
--
--
All
Updated doc. To reflect
current processes.
Updated header/footer to
current format.
2
--
--
3
All
Revised to reflect FAA
Approval of Limitations
Section only.
--
--
4
All
Initial FAA Approval
GMB 1
6/25/2004
5
All
Make KAP 140 autopilot
an optional equipment
installation
GMB 1
9/20/2004
6
All
Amendment 1 revision
and administrative
corrections.
GMB1
3/30/05
7
All
DA 40 F revision and
administrative
corrections
GMB1
6/27/05
8
All
Amendment 2 revision
and administrative
corrections.
GMB1
9/16/05
9
All
Amendment 3 revision
GMB1
11/03/05
Description
Log of Revisions continued on next page
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 3 of 42
Garmin Ltd. Or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
LOG OF REVISIONS
Revision
Number
Page
Number(s)
10
All
11
12
13
FAA
Approved
Date of
Approval
Amendment 5 revision
WCS1
8/03/06
All
TAWS limitation added
and administrative
corrections
GMB1
10/27/06
All
Revised by Garmin
DAS. Modified Autoreversion procedure.
Clarified Alternator Fail
procedure. Added
limitation for Arrival and
departure procedures.
RGM
07/05/07
All
Revised by Garmin
ODA. Administrative
corrections to fuel
quantity indication range
markings.
See Cover
See Cover
Description
1
For Margaret Kline, Manager
Wichita Aircraft Certification Office
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 4 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
Table of Contents
SECTION I
GENERAL .......................................................................................... 7
(Not FAA Approved)
SECTION II
LIMITATIONS ................................................................................... 9
(FAA Approved)
SECTION III
EMERGENCY PROCEDURES ....................................................... 17
(Not FAA Approved)
SECTION IVA
NORMAL PROCEDURES .............................................................. 26
(Not FAA Approved)
SECTION IVB
ABNORMAL PROCEDURES ......................................................... 38
(Not FAA Approved)
SECTION V
PERFORMANCE ............................................................................. 38
(Not FAA Approved)
SECTION VI
WEIGHT AND BALANCE ............................................................. 38
(Not FAA Approved)
SECTION VII
SYSTEM DESCRIPTIONS.............................................................. 39
(Not FAA Approved)
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 5 of 42
This page is intentionally blank.
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 6 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
SECTION I
GENERAL
1.
The G1000 Integrated Avionics System is a fully integrated flight, engine,
communication, navigation and surveillance instrumentation system. The
system consists of a Primary Flight Display (PFD), Multi-Function Display
(MFD), audio panel, Air Data Computer (ADC), Attitude and Heading
Reference System (AHRS), engine sensors and processing unit (GEA), and
integrated avionics (GIA) containing VHF communications, VHF
navigation, and GPS (Global Positioning System).
2.
The primary function 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 information, mapping, terrain information, and for flight planning.
The audio panel is used for selection of radios for transmitting and
listening, intercom functions, and marker beacon functions.
3.
The primary function of the VHF Communication portion of the G1000 is
to enable external radio communication. The primary function of the
VOR/ILS Receiver portion of the equipment is to receive and demodulate
VOR, Localizer, and Glide Slope signals. The primary function of the GPS
portion of the system is to acquire signals from the GPS system satellites,
recover orbital data, make range and Doppler measurements, and process
this information in real-time to obtain the user's position, velocity, and time.
4.
Provided a Garmin G1000 GPS receiver is receiving adequate usable
signals, it has been demonstrated capable of and has been shown to meet
the accuracy specifications for:
•
VFR/IFR enroute, oceanic, terminal, and non-precision
instrument approach (GPS, Loran-C, VOR, VOR-DME,
TACAN, NDB, NDB-DME, RNAV) operation within the
U.S. National Airspace System in accordance with AC 20138A.
•
Oceanic/Remote per FAA Notice 8110.60 – Two FMSs are
required to be installed, operating and receiving usable signals
from independent GPS sensors (one GPS sensor for those
routes requiring only one Long Range Navigation (LRN)
sensor. This does not constitute operational approval.
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 7 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
•
North Atlantic (NAT) Minimum Navigation Performance
Specifications (MNPS) Airspace as defined in AC 91-49 and
AC 91-70 – Provided two FMSs are installed, operating and
are receiving usable signals from any two GPS navigation
sensors (one GPS sensor for those routes requiring only one
Long Range Navigation (LRN) sensor). The GPS sensor
meets the requirements of FAA Notice 8110.60 for primary
navigation sensors. This does not constitute operational
approval.
•
RNAV (GPS) Approaches – The G1000 GPS meets the
requirements of AC 20-138(A) for GPS based RNAV
approaches. This includes RNAV approaches labeled as
RNAV (GPS), provided GPS sensor data is valid.
•
The systems meets RNP5 airspace (BRNAV) requirements of
AC 90-96 and in accordance with AC 20-138A, JAA GAI-20
ACJ 20X4, and FAA Order 8110.60 for oceanic and remote
airspace operations, provided it is receiving usable navigation
information from the GPS receiver.
Navigation is accomplished using the WGS-84 (NAD-83) coordinate reference
datum. GPS navigation data is based upon use of only the GPS operated by the
United States of America.
5.
If the optional TAWS function is installed in the G1000, the pilot will
receive appropriate aural warnings and cautions for terrain and obstacles.
The pilot should refer to the DA40/DA40F Pilot’s Guide (Garmin doc. 19000324-05 Revision A or later) for the terrain warning and caution messages
and system information.
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 8 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
SECTION II
LIMITATIONS
2.1 INTRODUCTION
General Limitations:
1.
The Garmin G1000 Cockpit Reference Guide (CRG) must be immediately available
to the flight crew. The required CRG is referenced to the System Software Version
number. The System Software Version number is displayed at the top right side of
the MFD Power-up page. DA 40 F requires System Software Version 0369.07 or
later FAA approved software.
System Software
Version
0369.04
P/N 190-00324-00, dated November, 2003 or later
appropriate revision.
0369.06
P/N 190-00324-01, dated February, 2005 or later
appropriate revision.
0369.07
0369.08
P/N 190-00324-03, dated June, 2005 or later appropriate
revision.
0369.09
P/N 190-00324-04, Revision A or later appropriate
revision.
0369.11
P/N 190-00324-06, Revision A or later appropriate
revision.
0369.12
2.
Garmin G1000 Cockpit Reference Guide (CRG)
revision
The G1000 installation in the DA 40 requires the following or later FAA approved
LRU software versions. Approved LRU software versions are referenced to the
System Software Version number. DA 40 F requires System Software Version
0369.07 or later FAA approved software.
LRU
COM 1 & 2
GDC 1
GEA 1
GIA 1 & 2
GMA 1
GMU 1
GPS 1 & 2
GRS 1
GS 1 & 2
GTX 1
MFD1
NAV 1 & 2
PFD 1
GDL
190-00303-02 Rev 13
FAA APPROVED
0369.04
0369.06
7.00
2.02
2.02
2.01
2.03
2.01
3.01
2.01
3.00
3.06
2.02
4.00
2.02
7.00
2.05
2.04
2.06
2.07
2.01
2.01
2.03
3.00
4.01
4.04
4.00
4.04
LRU Software Version
0369.07 0369.08/
0369.09
7.00
2.05
2.04
2.06
2.07
2.01
3.01
2.03
3.00
4.01
4.06
4.00
4.06
0369.11
0369.12
7.00
2.05
2.04
3.01
2.08
2.01
3.01
2.03
3.00
4.01
5.02
4.00
5.02
7.00
2.05
2.04
4.30
2.08
2.01
3.01
2.03
3.00
4.01
6.13
4.00
6.13
7.00
2.05
2.04
4.30
2.11
2.01
3.01
2.03
3.00
4.01
6.13
4.00
6.13
2.14
2.14
2.14
Diamond Aircraft DA 40
Page 9 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
The system’s databases and System Software Version number are displayed on the
MFD Power-up page immediately after system power-up and must be
acknowledged. The LRU software versions can be verified on the AUX group subpage 5, “AUX - SYSTEM STATUS” along with the system’s databases.
3.
IFR enroute, oceanic and terminal navigation predicated upon the G1000 GPS
Receiver is prohibited unless the pilot verifies the currency of the database or
verifies each selected waypoint for accuracy by reference to current approved data.
4.
Instrument approach navigation predicated upon the G1000 GPS Receiver must be
accomplished in accordance with approved instrument approach procedures that are
retrieved from the GPS equipment database. The GPS equipment database must
incorporate the current update cycle.
NOTE
Not all published approaches are in the FMS database. The pilot must ensure that the
planned approach is in the database.
(a) Instrument approaches utilizing the GPS receiver must be conducted in the
approach mode and Receiver Autonomous Integrity Monitoring (RAIM) must
be available at the Final Approach Fix.
(b) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of
approach not approved for GPS overlay with the G1000 GPS receiver is not
authorized.
(c) Use of the G1000 VOR/ILS receiver to fly approaches not approved for GPS
require VOR/ILS navigation data to be present on the display.
(d) Vertical Navigation information may be utilized for advisory information only.
Use of Vertical Navigation information for Instrument Approach Procedures
does not guarantee step-down fix altitude protection, or arrival at approach
minimums in normal position to land.
(e) IFR non-precision approach approval is limited to published approaches within
the U.S. National Airspace System. Approaches to airports in other airspace are
not approved unless authorized by the appropriate governing authority.
(f) RNAV (GPS) approaches must be conducted utilizing the GPS sensor.
(g) When conducting missed approach procedures, autopilot (if installed) coupled
operation is prohibited until the pilot has established a rate of climb that ensures
all altitude requirements of the procedure will be met.
(h) RNP RNAV operations are not authorized, except as noted in item 4 of Section
I of this AFMS.
5.
If not previously defined, the following default settings must be made in the
“SYSTEM SETUP” menu of the G1000 prior to operation (refer to Pilot's Guide for
procedure if necessary):
(a) DIS, SPD ........... kt (sets navigation units to “nautical miles” and “knots”)
190-00303-02 Rev 13
FAA APPROVED
Diamond Aircraft DA 40
Page 10 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
(b) ALT, VS ............ft fpm (sets altitude units to “feet” and “feet per minute”)
(c) MAP DATUM ..WGS 84 (sets map datum to WGS-84, see note below)
(d) POSITION .........deg-min (sets navigation grid units to degree-minutes)
NOTE
In some areas outside the United States, datums other than WGS-84 or NAD-83 may
be used. If the G1000 is authorized for use by the appropriate Airworthiness
authority, the required geodetic datum must be set in the G1000 prior to its use for
navigation.
6.
Operation is prohibited north of 70°N and south 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.
7.
CDI sequencing of the ILS must be set to manual for instrument approaches
conducted with the autopilot coupled (if installed). If the CDI source is changed
when the autopilot is engaged in NAV mode, the autopilot lateral mode will revert to
ROLL ATTITUDE mode and NAV mode must be manually reselected by the pilot.
8.
The fuel quantity, fuel required, and fuel remaining functions of the FMS are
supplemental information only and must be verified by the flight crew.
9.
The pilot’s altimeter is the primary altitude reference during all operations using
advisory vertical navigation information.
10. If a KAP 140 autopilot is installed, autopilot-coupled ILS, LOC, LDA, and Back
Course approaches are prohibited with direct crosswinds greater than 15 knots with
greater than light turbulence.
11. Navigation must not be predicated upon the use of the TAWS, Terrain or Obstacle
data displayed by the G1000.
12. TAWS must be inhibited prior to the Final Approach Fix (FAF) when conducting an
instrument approach that terminates in a circling to land or side step maneuver.
NOTE: The terrain display is intended to serve as a situational awareness
tool only. It may not provide either the accuracy or fidelity, or both, on
which to solely base decisions and plan maneuvers to avoid terrain or
obstacles.
190-00303-02 Rev 13
FAA APPROVED
Diamond Aircraft DA 40
Page 11 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
13. Pilots are authorized to deviate from their ATC clearance to the extent necessary to
comply with terrain / obstacle warnings from TAWS.
14. The Terrain/Obstacle/Airport 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 the United
States, Canada, Mexico, Latin America, and South America.
(c) 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.
15. To avoid giving unwanted alerts, TAWS must be inhibited when landing at an
airport that is not included in the airport database.
16. The ADF aural identifier must be monitored any time the ADF is used as the primary
source of navigation.
17. For airplanes with system software 0369.08 or 0369.09, display of NEXRAD
information on the NAVIGATION map on the MFD, or on the inset map on the
PFD is prohibited for map ranges of 30 NM or less, except in the North Up display
mode.
18. Do not load a new arrival or departure procedure in the flight plan if one currently
exists without first removing the existing arrival or departure procedure. Failing to
remove an existing arrival or departure procedure from the flight plan prior to
loading a new arrival or departure procedure can cause erroneous course deviation
indications, loss of GPS navigation information and other display anomalies.
2.3 AIRSPEED MARKINGS
Marking
IAS
Red band
20 KIAS – 53 KIAS
Yellow band
53 KIAS – 58 KIAS
White band
58 KIAS – 91 KIAS
Green band
Yellow band
58 KIAS – 129 KIAS
129 KIAS – 178 KIAS
Red band
178 KIAS and greater
Significance
Low speed awareness – stall is
imminent
Low speed awareness – reduced
airspeed margin to stall
Operating range with flaps fully
extended
Normal operating range
Caution range – smooth air only
Lower limit of 178 KIAS is the
maximum speed for all operations
The airspeed indicator is marked in IAS values.
190-00303-02 Rev 13
FAA APPROVED
Diamond Aircraft DA 40
Page 12 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
2.5 ENGINE INSTRUMENT MARKINGS
Engine instrument markings and their color code significance are shown in the table
below.
NOTE
When an indication lies in the upper or lower prohibited range, the legend for that
display will change to the color of the prohibited range and will begin flashing as
well.
Indication
Manifold
Pressure
In. – Hg
*Note 2*
RPM
Oil Temp
°F
Cylinder Head
Temp
°F
Fuel Press PSI
(DA 40)
*Note 4*
Oil Press
PSI
Fuel flow
Gal/hr
Voltage
Volts
Amperage
Amps
Fuel quantity
US gal
Standard
Tanks
Fuel quantity
US gal
Long Range
Tanks
190-00303-02 Rev 13
FAA APPROVED
Red arc
or bar
=
Lower
prohibite
d range
Yellow
arc or
bar
=
Caution
range
Green arc
or bar
=
Normal
operating
range
Yellow
arc or
bar
=
Caution
range
Red arc
or bar
=
Upper
prohibite
d range
--
--
13 – 30
--
--
--
--
500 – 2700
--
>2700
*Note 3*
--
--
149 – 230
231 245
>245
--
--
150 – 475
476 –
500
>500
0 – 14
--
14 – 35
--
>35
0 – 25
25 - 55
56 – 95
96 - 97
>97
--
--
1 – 20
--
>20
0 – 24.1
24.1 – 25
25.1 – 30
30.1 – 32
>32
--
--
2 – 75
--
--
0
>0 - 3
>3 – 17
--
--
0
>0 - 3
>3 – 16
>19 – 24
--
--
Diamond Aircraft DA 40
Page 13 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
Note 2: Not applicable to DA 40 F. Manifold Pressure gauge is not installed in the DA
40 F.
Note 3: To prevent nuisance alerts during normal takeoffs, the legend “RPM” and digits
will not turn red or flash until the RPM exceeds 2780.
Note 4: Fuel Pressure Gauge is optional for DA 40 aircraft.
2.6 WARNING, CAUTION AND STATUS MESSAGES
The following tables show the color and significance of the warning, caution, and
advisory messages which may appear on the G1000 displays.
NOTE
The G1000 Cockpit Reference Guide and the G1000 Pilot’s Guide contain detailed
descriptions of the annunciator system and all warnings, cautions and advisories.
Warning annunciations – Red
Annunciation
OIL PRES LO
FUEL PRES LO (DA40 Only)
FUEL PRES HI (DA 40 Only)
ALTERNATOR
STARTER ENGD
DOOR OPEN
TRIM FAIL
Cause
Oil pressure is less than 25 psi
Fuel pressure is less than 14 psi
Fuel pressure is greater than 35 psi
Alternator failure
Operation of the starter without the key in
the start position, or failure of the starter
motor to disengage from the engine after
starting
Front canopy and/or rear door not
completely closed and locked
Failure of the automatic trim system of the
autopilot (if installed)
Caution annunciations – Yellow
Annunciation
PITOT OFF
PITOT FAIL
L FUEL LOW
R FUEL LOW
LOW VOLTS
190-00303-02 Rev 13
FAA APPROVED
Cause
Pitot heat is not switched on
Fault in the pitot heating system
Fuel quantity in the left tank is less than 3
US gal (+1 US gal)
Fuel quantity in the right tank is less than 3
US gal (+1 US gal)
On-board voltage below 24 volts
Diamond Aircraft DA 40
Page 14 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
Advisory annunciations – White
Annunciation
PFD FAN FAIL
MFD FAN FAIL
GIA FAN FAIL
Cause
The cooling fan for the PFD is inoperative.
The cooling fan for the MFD is inoperative.
The cooling fan for the GIA is inoperative.
2.13 KINDS OF OPERATION
Minimum operational equipment (serviceable)
Equipment
Primary Flight Display
Multi-Function Display
Audio panel
Air data computer
Attitude and Heading Reference
System
Static dischargers
GPS
Number
installed
1
1
1
1
VFR
Day
1
1
1
1
VFR
Night
1
1
1
1
IFR
1
1
1
1
1
-
1
1
7
2
-
1
7
2
2.14 FUEL
Fuel Quantity: Total fuel quantity:
Standard Tanks:
Long Range Tanks:
Unusable fuel:
2 x 20.6 US gal (approx. 156 liters)
2 x 25.5 US gal (approx. 193 liters)
2 x 0.5 US gal (approx. 3.8 liters)
Max. Indicated Fuel Quantity:
Standard Tanks:
17 US gal per tank
Long Range Tanks:
24.0 US gal per tank
Max. permissible difference
between right and left tank:
Standard Tanks:
10 US gal (approx. 38 liters)
Long Range Tanks:
8 US gal (approx. 30.3 liters)
190-00303-02 Rev 13
FAA APPROVED
Diamond Aircraft DA 40
Page 15 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
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 use of max. tank capacity see AFM
Long Range Tanks
Fuel qty. Indication: max 24 US gal
Refer to AFM to use entire tank capacity
Max. difference LH/RH tank: 8 US gal
190-00303-02 Rev 13
FAA APPROVED
Diamond Aircraft DA 40
Page 16 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
SECTION III
EMERGENCY PROCEDURES
GENERAL
1.
If Garmin G1000 GPS navigation information is not available or invalid, utilize
remaining operational navigation equipment as required. If the TAWS option is
installed, it will not be available. A white ‘TAWS N/A’ or red ‘TAWS FAIL’
annunciator will be displayed on the PFD (left of selected altitude) or on the MFD
TAWS page (lower right hand corner).
2.
If the "POSN ERROR" 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 means of navigation other than the
G1000 GPS receivers.
3.
If the "RAIM UNAVAIL" annunciation is displayed in the enroute, oceanic,
terminal, or initial approach phase of flight, continue to navigate using the GPS
equipment or revert to an alternate means of navigation other than the G1000 GPS
receiver appropriate to the route and phase of flight. When continuing to use GPS
navigation, position must be verified every 15 minutes using the G1000 VOR/ILS
receiver or another IFR-approved navigation system.
4.
If the "RAIM UNAVAIL" annunciation is displayed while on the final approach
segment, GPS based navigation will continue for up to 5 minutes with approach
CDI sensitivity (0.3 nautical mile). After 5 minutes the system will flag and no
longer provide course guidance with approach sensitivity. Missed approach course
guidance may still be available with 1 nautical mile CDI sensitivity and integrity
by executing the missed approach.
5.
In an in-flight emergency, depressing and holding the Com transfer button for 2
seconds will tune the emergency frequency of 121.500 MHz. If the display is
available, it will also show it in the "Active" frequency window.
6.
If the white ‘TAWS N/A’ status annunciator is displayed on the PFD or MFD
TAWS page, the system will no longer provide TAWS alerting or display relative
terrain elevations. The crew must maintain compliance with procedures that
ensure minimum terrain separation.
7.
If the red ‘TAWS FAIL’ status annunciator is displayed on the PFD or MFD
TAWS page, the system will no longer provide TAWS alerting or display relative
terrain elevations. The crew must maintain compliance with procedures that
ensure minimum terrain separation.
8.
The following warnings and cautions appear in various locations on the PFD or
MFD.
190-00303-02 Rev 13
Diamond Aircraft DA 40
Page 17 of 42
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
Annunciation
AHRS Aligning – Keep
Wings Level
ATTITUDE FAIL
AIRSPEED FAIL
ALTITUDE FAIL
VERT SPEED FAIL
HDG
Red X
INTEG
WARN
Cause
Attitude and Heading Reference System is aligning.
Keep wings level using standby attitude indicator.
Display system is not receiving attitude reference
information from the AHRS; accompanied by the
removal of sky/ground presentation and a red X over
the attitude area.
Display system is not receiving airspeed input from
the air data computer; accompanied by a red X
through the airspeed display
Display system is not receiving altitude input from the
air data computer; accompanied by a red X through
the altimeter display
Display system is not receiving vertical speed input
from the air data computer; accompanied by a red X
through the vertical speed display
Display system is not receiving valid heading input
from the AHRS; accompanied by a red X through the
digital heading display
A red X through any display field, such as com
frequencies, nav frequencies, or engine data, indicates
that display field is not receiving valid data.
RAIM is not available.
RAIM position warning – nav deviation bar removed
3.2.3 ENGINE PROBLEMS IN FLIGHT
(h) High Fuel Flow – (DA 40 only)
Fuel flow in red sector
1.
Fuel pressure ............................. check for red FUEL PRESS LO message
•
If fuel pressure is low (FUEL PRESS LO message), there is possibly a leak
(between the injection system and the injectors). Land at the nearest available
airport.
•
If there is no FUEL PRESS LO message, there is no leak; the likely cause is a
defective fuel flow indication, which should thus be ignored (the airplane
should be serviced). Fuel flow data should be taken from the engine
performance table in Chapter 5 of the AFM.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
(g) High Fuel Flow – (DA 40 F only)
1.
Fuel Quantity ..................................................................Check and Monitor
2.
Power Setting ...................................................................................... Check
Land as soon as practical. Consider the reduced range and endurance due to possible
loss of fuel.
NOTE
Have the airplane inspected before next flight.
3.3.3 SMOKE AND FIRE IN FLIGHT
(b) Electrical fire with smoke in flight
3.
Emergency switch ......................................................................... ON if installed
CAUTION
Switching OFF the master switch (ALT/BAT) will lead to total loss of all
electronic and electric equipment, including the AHRS and attitude display.
However, by switching the HORIZON EMERGENCY switch ON, the emergency
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 partially open, in order to improve ventilation. The canopy
will remain open in this position. Flight characteristics will not be affected
significantly.
4.
5.
6.
7.
8.
Master switch (ALT/BAT) ........................................................................... OFF
Cabin heat ..................................................................................................... OFF
Emergency window(s) ............................................................................... OPEN
Use standby instruments for airspeed, altitude and attitude reference, if necessary
Land at the nearest suitable airport as soon as possible
If electronic or avionics equipment is required for continued flight, the following
procedure may be used to isolate the source of the smoke or fumes:
9. BATtery switch .............................................................................................. ON
10. ESS BUS switch ............................................................................................ ON
NOTE
This removes power from the main and avionics busses, but does not allow
alternator operation. See the table at the end of this section for the equipment
which is still available.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
If smoke or fumes decrease:
11. Land at the nearest suitable airport as soon as possible
If smoke or fumes persist:
12. ALTernator switch ......................................................................................... ON
13. ESS BUS switch ........................................................................................... OFF
14. BATT and ESS TIE circuit breakers ......................................................... PULL
This removes power from the essential bus and restores
power to the main and avionics busses. See the table at the
end of this section for the equipment which will still be
available.
15. Use standby instruments for attitude, airspeed and altitude
16. Refer to Section 3.7.2 (b) of this Supplement, Alternator Failure
17. 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 switch selected) is:
Air Data Computer (airspeed, altitude, vertical speed, OAT, TAS)
Attitude and Heading Reference System (attitude, heading)
PFD (in composite mode)
Pitot Heat
Flaps
Com 1
GPS/Nav 1
Transponder
Landing light
Instrument flood lights
Engine instruments
Starter
Refer to the “Essential Bus” area of the circuit breaker panel for a quick reference to
equipment on the Essential Bus.
Equipment available on the Main and Avionics Busses only:
Com 2
GPS/Nav 2
MFD
Electric fuel pump
Instrument lights
Strobe lights
Position lights
Taxi light
Refer to the “Main Bus” and “Avionics Bus” areas of the circuit breaker panel for a
quick reference to equipment on those busses.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
3.7.1 ICING
Unintentional flight into icing conditions
1.
Leave the icing area (by changing altitude or turning back, in order to reach zones
with a higher ambient temperature).
2. Pitot heating ................................................................................................... ON
3. 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 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.
8.
ATC .............................................................. advise if an emergency is expected
CAUTION
When the pitot heating fails (yellow PITOT FAIL annunciation), and the alternate
static valve is installed:
9.
10.
Alternate static valve............................................................................... OPEN
Emergency window(s) .............................................................................. close
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
3.7.2 FAILURES IN THE ELECTRICAL SYSTEM
(b) Alternator failure
An alternator failure is indicated by a red ALTERNATOR message and an ammeter
indication of 0 Amps.
1. Circuit breakers ...................................................................................... Check in
2. ALTernator switch ........................................................................ OFF, then ON
If alternator does not come back on line, proceed to step 3.
NOTE
If the alternator has come back on line, the red ALTERNATOR message will
extinguish and the ammeter indication will be greater than zero amps.
3.
4.
5.
ESS BUS switch ............................................................................................ ON
Switch off any non-essential electrical loads.
Land within 30 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 1
• Attitude and Heading Reference System (AHRS)
• Air Data Computer
• Pitot heat
• Engine instruments
• Transponder
• Flood light
• Landing light
Refer to the ESSENTIAL BUS area of the circuit breaker panel for a quick
reference to equipment on those busses. These items of equipment can be
supplied with power by the battery for at least 30 minutes. During this 30minute period, the airplane must be landed at a suitable airport. Economical
use of electrical equipment, in particular of pitot heat, and switching off
equipment that is not needed extends the time during which the other
equipment remains available.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
For cases in which the battery capacity is not sufficient to reach a suitable
airport, an emergency battery is installed to power the standby attitude gyro and
floodlight. This battery is switched on with the HORIZON EMERGENCY
Switch. It provides power for 1 hour and 30 minutes when the floodlight is
switched on.
3.8 AVIONICS EMERGENCIES
3.8.1 PFD OR MFD DISPLAY FAILURE
a)
DISPLAY BACKUP button on audio panel…..PUSH (button will be OUT)
3.8.1.1 AUTOMATIC ENTRY OF DISPLAY 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 will be OUT)
NOTE
After automatic entry of reversionary mode, it is required to press the DISPLAY
BACKUP button on the audio panel. With the DISPLAY BACKUP button pushed, if
the problem causing the automatic entry of reversionary mode is resolved, the system
will remain in reversionary mode. A maximum of one attempt to return to normal
mode is approved using the following procedure.
b) DISPLAY BACKUP button on audio panel…..PUSH (button will be IN)
•
If the system returns to normal mode, leave the DISPLAY BACKUP button in
and continue.
•
If the system remains in reversionary mode or abnormal display behavior such
as display flashing occurs, then return the DISPLAY BACKUP button to the
OUT position.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
3.8.2 AHRS FAILURE
NOTE
A failure of the Attitude and Heading Reference System (AHRS) is indicated by
removal of the sky/ground presentation and a red X and a yellow “AHRS
FAILURE” shown on the PFD. The digital heading presentation will be replaced
with a yellow “HDG” and the compass rose digits will be removed. The course
pointer will indicate straight up and course may be set using the digital window.
1.
2.
Use Standby Attitude Indicator, magnetic compass and Navigation Map
Course .......................................................................... Set using digital window
3.8.3 AIR DATA COMPUTER (ADC) FAILURE
NOTE
Complete loss of the Air Data Computer is indicated 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.
2.
Use Standby Airspeed Indicator and Altimeter
Land as soon as practical at a suitable airport
3.8.4 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS
NOTE
Loss of an engine parameter is indicated by a red X through the data field.
Erroneous information may be identified by indications that do not agree with
other system information. Erroneous indications may be determined by
comparing a display with other displays and other system information.
1.
Set power based on throttle lever position, engine noise, and speed.
2.
Monitor other indications to determine the health of the engine.
3.
Use known power settings from Table 5.3.2 (DA 40) or Charts 5.3.8 (DA 40 F) of
AFM for approximate fuel flow values.
4.
Use other system information, such as annunciator messages, ENGINE SYSTEM
page, and AUX – TRIP PLANNING page to safely complete the flight.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
3.8.5 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS
NOTE
Loss of an annunciator may be indicated when engine or fuel displays show an
abnormal or emergency situation and the annunciator is not present. An
erroneous annunciator may be identified when an annunciator 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 procedures contained in this AFMS.
2.
If a display indicates an abnormal condition but no annunciator is present, use
other system information, such as engine displays, ENGINE SYSTEM page, GAL
REM and FFLOW GPH displays, to determine if the condition exists. If it cannot
be determined that the condition does not exist, treat the situation as if the
condition exists. Refer to the AFM Emergency or Abnormal procedures or the
procedures contained in this AFMS.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
SECTION IVA
NORMAL PROCEDURES
WARNING
The G1000 altitude references (digits and altimeter bug) are included to increase
altitude awareness, and are not connected in any way to the KAP 140 autopilot (if
installed). Altitude alerter and autopilot functions are accomplished with the
altitude set function of the KAP 140 autopilot if installed.
NOTE
Readability of the PFD and MFD displays may be degraded when wearing
polarized sunglasses.
1.
DETAILED OPERATING PROCEDURES
Normal operating procedures for the G1000 are described in the Garmin G1000
Cockpit Reference Guide and the Garmin G1000 Pilot's Guide.
PRE-FLIGHT INSPECTION
I. Cabin check
a)
b)
c)
d)
e)
f)
g)
MET, NAV, Mass & CG ............................................. flight planning complete
Airplane documents ...................................................... complete and up-to-date
Ignition key .......................................................................................... pulled out
Front canopy & rear door ....................................................... clean, undamaged
All electrical equipment ................................................................................ OFF
Circuit breakers .............................. set in (if one has been pulled, check reason)
Engine control levers ............................ check condition, freedom of movement
Full travel of throttle,
Full Travel of RPM (DA 40 only)
Full Travel of mixture lever
h) Throttle ....................................................................................................... IDLE
i) Mixture control lever ................................................................................ LEAN
j) RPM lever (DA 40 only) .................................................................. HIGH RPM
k) Carburetor Heat (DA 40 F only) .............................................................. COLD
l) Master switch (BAT) ..................................................................................... ON
m) Fuel Quantity ....................................................................check fuel qty. on EIS
check with fuel qty. measuring device
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
NOTE
FOR STANDARD TANKS, when the fuel quantity indicator reads 17
US gal the correct fuel quantity must be determined with the fuel quantity
measuring device. If this measurement is not carried out, the fuel quantity
available for flight planning is 17 US gal.
FOR LONG RANGE TANKS, when the fuel indicator reads 16 US
gal the correct fuel quantity must be determined with the fuel quantity
measuring device. There are 3 US gal of ungauged fuel from 16 to 19 US gal.
If this measurement is not carried out, the fuel quantity available for flight
planning is 16 US gal.
n)
o)
p)
q)
r)
Position lights, strobe light (ACL’s) ........................................................... check
Master switch (BAT) .................................................................................... OFF
Check for loose items ............................................................................complete
Flight controls and trim................................................. free to move and correct
Baggage .................................................................................. stowed and secure
NOTE
Refer to DA 40 and DA 40 F AFMs to complete the Walk-around check, visual
inspection
BEFORE STARTING ENGINE
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
Preflight inspection ............................................................................... Complete
Rudder pedals ..................................................................... Adjusted and locked
Passengers ............................................................................................ Instructed
Safety Harnesses ................................................................... All on and fastened
Rear door ................................................................................ Closed and locked
Door lock (if installed)................................................. Unblocked, key removed
Front canopy ....................................................... Position 1 or 2 (“cooling gap”)
Canopy lock (if installed) ............................................ Unblocked, key removed
Parking brake .................................................................................................. Set
Flight controls .................................Freedom of movement and proper direction
Trim wheel ..................................................................................................... T/O
Friction device, throttle quadrant ........................................................... Adjusted
Throttle ....................................................................................................... IDLE
Mixture control lever ................................................................................ LEAN
RPM lever (DA 40 only) ................................................................. HIGH RPM
Carburetor heat (DA 40 F only) ............................................................... COLD
Alternate air (DA 40 only) ....................................................................CLOSED
Alternate Static Valve ........................................................ CLOSED, if installed
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
19. Avionics master 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. BATtery switch ............................................................................................. ON
22. Fuel tank selector .......................................................................... on fullest tank
WARNING
Never move the propeller by hand while the ignition is switched on, as it may
result in serious personal injury.
Never try to start the engine by hand.
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
STARTING ENGINE (DA 40 only)
(a) Cold engine
1.
2.
3.
4.
5.
Strobe light (ACL) ......................................................................................... ON
Electrical fuel pump ........................................................... ON, note pump noise
(=functional check of pump)
Throttle ........................................................... 3 cm (1.2 in) forward from IDLE
(measured from rear of slot)
Mixture control lever ........................................ RICH for 3 – 5 sec, then LEAN
Throttle1 cm (0.4 in) forward from ........................................................... IDLE
(measured from rear of slot)
WARNING
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 more than
10 seconds. After operating the starter motor, let it cool off for 20 seconds. After
6 attempts to 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 at ambient temperatures below 0°C (32°F), to
reduce wear and abuse to the engine and electrical system. Pre-heat will thaw the
oil trapped in the oil cooler, which can be congealed in extremely cold
temperatures. After a warm-up period of approximately 2 to 5 minutes (depending
on the ambient temperature) at 1500 RPM, the engine is ready for takeoff if it
accelerates smoothly and the oil pressure is normal and steady.
6.
Ignition switch ......................................................................................... START
When engine starts:
7.
8.
9.
Mixture control lever ........................................................ rapidly move to RICH
Oil pressure ...................................................................... green arc within 15 sec
Electrical fuel pump ...................................................................................... OFF
WARNING
If the oil pressure has not moved into the green arc within 15 seconds after
starting, SWITCH OFF ENGINE and investigate problem.
10.
11.
12.
13.
ALTernator switch ......................................................................................... ON
Ammeter .................................................................................................... Check
Fuel pressure ...................................................... Check no messages illuminated
Annunciator section of PFD ...................................................................... Check
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
(b) Warm engine
1.
2.
3.
4.
Strobe light (ACL) ......................................................................................... ON
Electrical fuel pump ........................................................... ON, note pump noise
(=functional check of pump)
Throttle ........................................................... 3 cm (1.2 in) forward from IDLE
(measured from rear of slot)
Mixture control lever ......................................... RICH for 1 - 3 sec, then LEAN
WARNING
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 more than
10 seconds. After operating the starter motor, let it cool off for 20 seconds. After
6 attempts to start the engine, let the starter cool for 30 minutes before further start
attempts.
5.
Ignition switch ........................................................................................ START
When engine starts:
6.
7.
Mixture control lever ........................................................ rapidly move to RICH
Oil pressure ...................................................................... green arc within 15 sec
WARNING
If the oil pressure has not moved into the green arc within 15 seconds after
starting, SWITCH OFF ENGINE and investigate problem.
8.
9.
10.
11.
12.
Electrical fuel pump ...................................................................................... OFF
ALTernator switch ......................................................................................... ON
Ammeter .................................................................................................... Check
Fuel pressure ...................................................... Check no messages illuminated
Annunciator section of PFD ...................................................................... Check
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
(c) Engine will not start after injection (”flooded engine”) Warm engine
1.
2.
3.
4.
Strobe light (ACL) ......................................................................................... ON
Electrical fuel pump ........................................................... ON, note pump noise
(=Functional check of pump)
Mixture control lever .................................................................. LEAN, fully aft
Throttle ........................................................................................ at mid position
WARNING
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 more than
10 seconds. After operating the starter motor, let it cool off for 20 seconds. After
6 attempts to start the engine, let the starter cool for 30 minutes before further start
attempts.
5.
6.
Ignition switch ........................................................................................ START
Throttle ........................................... pull back towards IDLE when engine starts
When engine starts:
7.
8.
Mixture control lever ........................................................ rapidly move to RICH
Oil pressure ...................................................................... green arc within 15 sec
WARNING
If the oil pressure has not moved into the green arc within 15 seconds after
starting, SWITCH OFF ENGINE and investigate problem.
9.
10.
11.
12.
ALTernator switch ......................................................................................... ON
Ammeter .................................................................................................... Check
Fuel pressure ...................................................... Check no messages illuminated
Annunciator section of PFD ...................................................................... Check
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
STARTING ENGINE (DA 40 F only)
(a) Cold engine
1.
2.
3.
4.
5.
Strobe light (ACL) ......................................................................................... ON
Mixture ............................................................................................. fully RICH
Electrical fuel pump ........................................................... ON, note pump noise
(=functional check of pump)
Throttle ................................................................... ¼ travel forward from IDLE
Prime ..................................................................... 1 – 4 seconds (electric pump)
WARNING
Use the primer system to prepare the engine for a starting attempt. Do not use the
throttle to pump fuel through the carburetor to the engine for priming since this
may lead to carburetor fire. The primer system delivers fuel to the cylinders
directly.
CAUTION
The priming system is not intended for operation in flight.
WARNING
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 more than
10 seconds. After operating the starter motor, let it cool off for 20 seconds. After
6 attempts to 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 at ambient temperatures below 0°C (32°F), to
reduce wear and abuse to the engine and electrical system. Pre-heat will thaw the
oil trapped in the oil cooler, which can be congealed in extremely cold
temperatures. After a warm-up period of approximately 2 to 5 minutes (depending
on the ambient temperature) at 1500 RPM, the engine is ready for takeoff if it
accelerates smoothly and the oil pressure is normal and steady.
6.
Starter ........................................................................................................ engage
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
When engine starts:
7. Oil pressure ...................................................................... green arc within 15 sec
8. Throttle .......................................................................................... set 1000 RPM
9. Electrical fuel pump ...................................................................................... OFF
WARNING
If the oil pressure has not moved into the green arc within 15 seconds after
starting, SWITCH OFF THE ENGINE and investigate problem.
10. ALTernator switch ......................................................................................... ON
11. Ammeter .................................................................................................... Check
12. Annunciator section of PFD ...................................................................... Check
(b) Warm engine
1.
2.
3.
4.
Strobe light (ACL) ......................................................................................... ON
Mixture ............................................................................................. fully RICH
Electrical fuel pump ........................................................... ON, note pump noise
(=functional check of pump)
Throttle ................................................................... ¼ 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
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 engine, let the starter cool for 30 minutes before further start
attempts.
5.
Starter ........................................................................................................ engage
When engine starts:
6.
7.
8.
Oil pressure ...................................................................... green arc within 15 sec
Throttle .......................................................................................... set 1000 RPM
Electrical fuel pump ...................................................................................... OFF
WARNING
If the oil pressure has not moved into the green arc within 15 seconds after
starting, SWITCH OFF THE ENGINE and investigate problem.
9. ALTernator switch ......................................................................................... ON
10. Ammeter .................................................................................................... Check
11. Annunciator section of PFD ...................................................................... Check
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
(c) Engine will not start after priming (”flooded engine”)
1.
2.
3.
4.
Strobe light (ACL) ......................................................................................... ON
Electrical fuel pump ...................................................................................... OFF
Mixture ...................................................................................... LEAN, fully aft
Throttle ............................................................................................. MAX PWR
WARNING
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 more than
10 seconds. After operating the starter motor, let it cool off for 20 seconds. After
6 attempts to start the engine, let the starter cool for 30 minutes before further start
attempts.
5.
Starter ........................................................................................................ engage
When engine starts:
6.
7.
Throttle ............................................. pull back towards IDLE when engine fires
Oil pressure ...................................................................... green arc within 15 sec
WARNING
If the oil pressure has not moved into the green arc within 15 seconds after
starting, SWITCH OFF THE ENGINE and investigate problem.
8.
9.
10.
11.
Throttle ......................................................................................... set 1000 RPM
ALTernator switch ......................................................................................... ON
Ammeter .................................................................................................... Check
Annunciator section of PFD ...................................................................... Check
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
BEFORE TAXIING
1.
2.
3.
Avionics master switch .................................................................................. ON
Electrical equipment .....................................................................On as required
Flaps............................................................................... UP – T/O – LDG – T/O
(indicator and visual check)
4. Flight instruments and avionics ............................. set, test function, as required
5. (set both altimeters)
6. Flood light ............................................................. ON, test function, as required
7. Ammeter ........................................................... check, if required increase RPM
8. Fuel tank selector ........................................... change tanks, confirm that engine
also runs on other tank (at least 1
minute at 1500 RPM)
9. Pitot heating ...........................................................................ON, test function –
no yellow PITOT FAIL annunciation
10. Pitot heating ............................................................. OFF if not required (yellow
PITOT OFF annunciation)
11. Strobe lights (ACLs) ..................................................... check ON, test function,
as required
12. Position lights, landing and taxi lights .................. ON, test function, as required
CAUTION
When taxiing at close range to other aircraft, or during night flight in clouds,
fog or haze, the strobe lights should be switched OFF. The position lights
must always be switched ON during night flight.
13. Throttle .......................................................................... check, 600 to 800 RPM
BEFORE TAKE-OFF
1.
2.
3.
4.
5.
Position airplane into wind if possible
Parking brake ................................................................................................... set
Safety harnesses .......................................................................... on and fastened
Rear door ...................................................................... check closed and locked
Front canopy ............................................................................closed and locked
CAUTION
When operating the canopy, pilots / operators must ensure that there are no
obstructions between the canopy and the mating frame, for example seat
belts, clothing, etc. When operating the locking handle do NOT apply undue
force.
A slight downward pressure on the canopy may be required to ease the
handle operation.
6.
Door warning light (DOOR OPEN) .................. Check no messages illuminated
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GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
7.
8.
9.
10.
11.
12.
Fuel tank selector ............................................................................... fullest tank
Engine instruments ....................................................................... in green sector
Circuit breakers .................................................................................... pressed in
Fuel pressure ...................................................... Check no messages illuminated
Electric fuel pump .......................................................................................... ON
Mixture control lever ........................................................ RICH (below 5000 ft)
NOTE
At a density altitude of 5000 ft or above or at high ambient
temperatures, a fully rich mixture can cause rough running of the
engine or a loss of performance. The mixture should be set for
smooth running engine.
13.
14.
15.
16.
Flaps.................................................................................................... check T/O
Trim .................................................................................................... check T/O
Flight controls ........................................................free movement, correct sense
Throttle ................................................................................ 2000 RPM (DA 40)
1800 RPM (DA 40 F)
17. Magneto check ...................................................................... L-BOTH-R-BOTH
Max. RPM drop ..........175 RPM
Max. difference .............50 RPM
CAUTION
The lack of an RPM drop suggests a faulty ground or incorrect ignition
timing. In case of doubt the magneto check can be repeated with a leaner
mixture, in order to confirm a problem. Even when running on only one
magneto the engine should not run unduly roughly.
18. RPM lever (DA 40 only) ...................................... pull back until a drop of max.
500 RPM is reached – HIGH RPM;
Cycle 3 times
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
18a Carburetor Heat (DA 40 F only) ...................................................check function
18b Throttle (DA 40 F only) ................................ MAX PWR, minimum 2200 RPM
NOTE (DA 40 F only)
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
higher RPM than tailwind.
19.
20.
21.
22.
23.
Throttle....................................................................................... set 1000 RPM
Carburetor Heat (DA 40 F only) .................................................. check COLD
Alternate Air (DA 40 only) ..................................................... check CLOSED
Parking brake ......................................................................................... release
Landing light ............................................................................. ON as required
TAWS CAUTION
When a TAWS CAUTION occurs, take positive corrective action until the alert ceases.
Stop descending or initiate either a climb or a turn, or both, as necessary, based on
analysis of all 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 similar approved vertical terrain escape
maneuver, until all alerts cease. 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 INHIBIT
The TAWS Forward Looking Terrain Avoidance (FLTA) and Premature Descent
Alerts (PDA) functions may be inhibited to stop alerting for acceptable flight
conditions (such as below glideslope maneuvers). For detailed operating instructions
regarding the G1000 TAWS Option, refer to the Garmin DA40/DA40F Pilot’s Guide
P/N 190-00324-05 Revision A, or later subsequent revision.
190-00303-02 Rev 13
Diamond Aircraft DA 40
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
SECTION IVB
ABNORMAL PROCEDURES
4B.3 FAILURES IN THE ELECTRICAL SYSTEM
(a) Low voltage caution (LOW VOLTS)
This caution is indicated when the normal on-board (bus) voltage (28V) drops below
24V.
Possible reasons are:
-A fault in the power supply
-RPM is too low
(i) Low voltage on the ground:
1.
2.
3.
Engine speed ....................................................................................... 1200 RPM
Electrical equipment ..................................................................................... OFF
Ammeter and voltmeter .............................................................................. check
If the caution message does not extinguish, and the ammeter legend flashes and reads
zero, discontinue the flight.
(ii) Low voltage caution during flight:
1.
2.
Electrical equipment ............................................................... OFF if not needed
Ammeter and Voltmeter ............................................................................. check
If the caution message does not go out, and the ammeter legend flashes and reads zero,
follow procedure 3.7.2(b) – Alternator Failure, in this Supplement.
(iii) Low voltage caution during landing:
-Follow (i) after landing
SECTION V
PERFORMANCE
No change.
SECTION VI
WEIGHT AND BALANCE
See current weight and balance data.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
SECTION VII
SYSTEM DESCRIPTIONS
The Garmin G1000 Integrated Avionics System consists of a Primary Flight Display
(PFD), a Multi-Function Display (MFD), an Audio Panel, and Attitude and Heading
Reference System (AHRS), an Air Data Computer (ADC), and the sensors and
computers to process flight and engine information for display to the pilot. The system
contains dual GPS receivers, dual VOR/ILS receivers, dual VHF communications
transceivers, a transponder, an Automatic Direction Finder (ADF) receiver, Distance
Measuring Equipment (DME), and an integrated annunciation system to alert the pilot
of certain abnormal conditions.
The Primary Flight Display (PFD) typically displays airspeed, attitude, altitude, and
heading information in a traditional format. Slip information is shown as a trapezoid
under the bank pointer. One width of the trapezoid 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 the
PFD (clockwise from top right):
•
•
•
•
•
•
•
•
•
•
•
•
•
Communications frequency volume and squelch knob
Communications frequency set knobs
Communications frequency transfer button
Altimeter setting knob (baro set)
Course knob
Map range knob and cursor control
FMS control buttons and knob
PFD softkey buttons, including master warning/caution acknowledgement
Altitude reference set knob
Heading bug control
Navigation frequency transfer button
Navigation frequency set knobs
Navigation frequency volume and Identifier knob
The PFD displays the crew alerting (annunciator) system. When a warning or caution
message is received, a warning or caution annunciator will flash on the PFD,
accompanied by an aural tone. A warning is accompanied by a repeating tone, and a
caution is accompanied by a single tone. Acknowledging the alert will cancel the
flashing and provide a text description of the message. Refer to the Emergency or
Abnormal Procedures Sections of the AFM or this Supplement for the appropriate
procedure to follow for each message.
Advisory messages related to G1000 system status are shown in white and are
accompanied by a white flashing ADVISORY alert. Refer to the G1000 Pilot’s Guide
and Cockpit Reference Guide for descriptions of the messages and recommended
actions (if applicable).
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
Trend vectors are shown on the airspeed and altimeter displays as a magenta line
predicting 6 seconds at the current rate. The turn rate indicator also functions as a
trend indicator on the compass scale.
The PFD can be displayed in a composite format for emergency use by pressing the
DISPLAY BACKUP button on the audio panel. In the composite mode, the full crew
alerting function remains, but no map functions are available.
The Multi-Function Display (MFD) typically displays engine data, maps, terrain,
traffic and topography displays, and flight planning and progress information. The
display unit is identical to the PFD and contains the same controls as previously listed.
The audio panel contains traditional transmitter and 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 ½ minutes of received audio.
Lights above the selections indicate what selections are active. Pressing the red
DISPLAY BACKUP button on the audio panel causes both the PFD and MFD to
display a composite mode.
The Attitude and Heading Reference System (AHRS) uses GPS, rate sensors, air data,
and magnetic variation to determine pitch and roll attitude, sideslip and heading.
Operation is possible in a degraded mode if the system loses any of these inputs.
Status messages alert the crew of the loss of any of these inputs. The AHRS will align
while the aircraft is in motion, but will align more quickly if the wings are kept level
during the alignment process.
The Air Data Computer (ADC) provides airspeed, altitude, vertical speed, and air
temperature to the display system. In addition to the primary displays, this information
is used by the FMS and TIS systems.
Engine instruments are displayed on the MFD. Discrete engine sensor information is
processed by the Garmin Engine Airframe (GEA) sub-system. When an engine sensor
indicates a value outside the normal operating range, the legend will turn yellow for
caution range, and turn red and flash for warning range.
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
Refer to the Garmin G1000 Cockpit Reference Guide for descriptions of the G1000
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 MFD Power-up page. DA 40 F requires System Software Version 0369.07
or later FAA approved software.
System Software
Version
Pilot’s Guides
Garmin G1000 Cockpit Reference Guide (CRG)
0369.04
P/N 190-00324-00, dated May, 2004 or later
appropriate revision
Garmin G1000 Cockpit Reference Guide (CRG)
0369.06
P/N 190-00324-01, dated February, 2005 or later
appropriate revision
0369.07
Garmin G1000 Cockpit Reference Guide (CRG)
0369.08
P/N 190-00324-03, dated June, 2005 or later
appropriate revision
Garmin G1000 Cockpit Reference Guide (CRG)
0369.09
0369.11
0369.12
190-00303-02 Rev 13
P/N 190-00324-04, Revision A or later appropriate
revision.
Garmin G1000 Cockpit Reference Guide (CRG)
P/N 190-00324-06, Revision A or later appropriate
revision.
Diamond Aircraft DA 40
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FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
7.10 FUEL SYSTEM
Fuel Quantity Indication
Each fuel tank has a capacity probe that ascertains fuel quantity in that tank. Standard
Tank configurations have two fuel probes, one in each wing. Long Range Tank
configurations have four fuel probes, two in each wing, an outboard tank and an
inboard tank. When the fuel quantity indicator reads zero, only unusable fuel remains
in the tank. Usable capacity of each tank for the Standard Tank configuration is 20 US
gal (76 liters). Usable capacity of an outboard and inboard tank for the Long Range
Tank configuration is 24 US gal (91 liters).
Fuel quantity:
Fuel quantity indicating for the Standard Tank configuration functions as described in
the DA 40 AFM. Also, refer to the ‘G1000 Pilot's Guide for the Diamond DA 40’ for
additional information about the functionality of the G1000’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
quantity. The fuel quantity gauge is marked in five gallon increments starting at zero
to 25 US gal. The break in the green band between 16 and 19 US gal shows the
ungauged portion of the fuel tanks usable fuel.
When a fuel tank is completely full, the quantity pointer will indicate 24 US gallons.
As fuel is consumed from the tank, the pointer will move to the left. Once there is no
more measurable fuel in the outboard tank, the pointer migrates over a 30 second
period to the 16 US gal position. The pointer will remain at 16 US gallons while the
ungauged fuel quantity is consumed. Once the quantity of fuel remaining in the
inboard tank is less than 16 gallons, the pointer will begin moving left towards zero.
When either pointer enters the amber portion of the scale, the pointer and the gauge
title, ‘FUEL QTY GAL’, will turn amber. When either pointer enters the red portion of
the gauge, the pointer will turn red, and the gauge title, ‘FUEL QTY GAL’, will turn
red and flash continuously in inverse video.
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