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

Garmin G1000: Diamond DA40/DA40F Airplane Flight Manual Supplement (EASA)
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Garmin Ltd. Or its subsidiaries
c/o Garmin International
1200 E. 151st Street
Olathe, KS 66062 USA
EASA 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)
1
All
190-00303-81 Rev 1
Description
Initial Release
EASA
Approved
AW
Date of
Approval
Aug 11 06
Diamond Aircraft DA 40
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190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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 EASA Approved)
SECTION II
LIMITATIONS................................................................................... 9
(EASA Approved)
SECTION III
EMERGENCY PROCEDURES....................................................... 18
(Not EASA Approved)
SECTION IVA
NORMAL PROCEDURES .............................................................. 26
(Not EASA Approved)
SECTION IVB
ABNORMAL PROCEDURES......................................................... 38
(Not EASA Approved)
SECTION V
PERFORMANCE ............................................................................. 38
(Not EASA Approved)
SECTION VI
WEIGHT AND BALANCE ............................................................. 38
(Not EASA Approved)
SECTION VII
SYSTEM DESCRIPTIONS.............................................................. 39
(Not EASA Approved)
190-00303-81 Rev 1
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190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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 20-138A.
•
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.
•
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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
(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, and FAA Order
8110.60 for oceanic and remote airspace operations, provided it is
receiving usable navigation information from the GPS receiver.
The system meets the accuracy requirements of EASA AMC 20-4
for Basic RNAV.
•
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.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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.
2.
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.
System Software
Version
Garmin G1000 Cockpit Reference Guide (CRG)
revision
0369.11
P/N 190-00324-05, Revision A or later appropriate
revision.
The G1000 installation in the DA 40 /DA 40F requires the following or
later EASA approved LRU software versions. Approved LRU software
versions are referenced to the System Software Version number.
LRU
LRU Software Version
0369.11
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
7.00
2.05
2.04
4.30
2.08
2.01
3.01
2.03
3.00
4.01
6.12
4.00
6.12
GDL
DME
ADF
2.14
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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 sub-page 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) RNAV (GPS) approaches must be conducted utilizing the GPS sensor.
(f) 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.
(g) RNP RNAV operations are not authorized, except as noted in item 4 of
Section I of this AFMS.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
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”)
(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 degreeminutes)
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 Terrain or Obstacle
data displayed by the G1000.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
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.
12. 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.
13. The ADF aural identifier must be monitored any time the ADF is used as
the primary source of navigation.
14. Display of NEXRAD information on the NAVIGATION map of the MFD,
and the inset map on the PFD, is prohibited for ranges of 30 NM or less,
except in North Up display mode.
2.3 AIRSPEED MARKINGS
Marking
IAS
Red band
20 KIAS – 53 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
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.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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*
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 – 17
--
--
0
--
<0 – 16
19 – 24
--
--
RPM
Oil Temp
°F
Cylinder Head
Temp
°F
Fuel Press PSI
(DA 40)
Oil Press
PSI
Fuel flow
Gal/hr
Voltage
Volts
Amperage
Amps
Fuel quantity
US gal
Standard
Tanks
Fuel quantity
US gal
Long Range
Tanks
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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.
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
190-00303-81 Rev 1
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
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EASA 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 25.0 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)
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
2.15 Limitation Placard
Instead of the Original Limitation Placard for the Fuel Quantity Indication
the following placards apply. 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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
2.16 Required Equipment List
Airplanes approved by EASA must contain System Software Version 0369.11
or later FAA approved software. In addition, these airplanes must contain the
following equipment and part numbers or later approved versions:
Description
LRU Part Number
Software
Version
GDU 1040 Display Unit, PFD
011-00972-03
6.12
GDU 1040 Display Unit, MFD
011-00972-03
6.12
GIA 63 Avionics Integration Unit No.1
011-00781-01
4.30
GIA 63Avionics Integration Unit No. 2
011-00781-01
4.30
GRS 77 Attitude Heading Reference
Unit
011-00868-10
2.03
GMA 1347 Audio Panel
011-00809-00
2.08
GMU 44 Magnetometer
011-00870-00
2.01
GDC 74A Air Data Computer
011-00882-00
2.05
GEA 71 Engine Airframe Unit
011-00831-00
2.04
GTX 33 Mode S Transponder
011-00779-00 or
4.01
011-00779-10
GDL69 Data Link
011-00987-00
Honeywell DME
066-1070-01
Becker RA3502 ADF
0505.757-912
(Receiver)
2.14
0856.010-912 (RMI
Converter)
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Diamond Aircraft DA 40
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EASA 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.
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.
The following warnings and cautions appear in various locations on the
PFD or MFD.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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:
7.
8.
BATtery switch.............................................................................................. ON
ESS BUS switch ............................................................................................ ON
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
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.
If smoke or fumes decrease:
9.
Land at the nearest suitable airport as soon as possible
If smoke or fumes persist:
10. ALTernator switch......................................................................................... ON
11. ESS BUS switch ...........................................................................................OFF
12. 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.
13. Use standby instruments for attitude, airspeed and altitude
14. Refer to Section 3.7.2 (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 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
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Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
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.
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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Diamond Aircraft DA 40
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EASA 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 (message extinguishes and ammeter
indication greater than zero):
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 30-minute 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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EASA 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
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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
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.
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.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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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Diamond Aircraft DA 40
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EASA 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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Diamond Aircraft DA 40
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EASA 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 (Diamond Industries 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.
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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.
When engine starts:
6.
7.
8.
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.
9.
10.
11.
12.
ALTernator switch......................................................................................... ON
Ammeter .................................................................................................... Check
Fuel pressure......................................................Check no messages illuminated
Annunciator section of PFD ...................................................................... Check
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA 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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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
190-00303-81 Rev 1
Diamond Aircraft DA 40
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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
190-00303-81 Rev 1
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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
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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EASA 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
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Diamond Aircraft DA 40
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EASA 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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EASA 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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Diamond Aircraft DA 40
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EASA 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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Diamond Aircraft DA 40
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EASA 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
P/N 190-00324-04, Revision A or later appropriate
revision.
Garmin G1000 Cockpit Reference Guide (CRG)
0369.11
190-00303-81 Rev 1
P/N 190-00324-05, Revision A or later appropriate
revision.
Diamond Aircraft DA 40
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EASA 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 25 US gal
(95 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 24 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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EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GARMIN G1000 INTEGRATED AVIONICS SYSTEM
DIAMOND MODEL DA 40
DIAMOND MODEL DA 40 F
G1000 Wiring Diagram
ADF
BECKER
ADF
DME
HONEYWELL
DME
WX-500
HORIZON EMERGENCY SWITCH
L3
WX-500
STORMSCOPE
DATA LINK
GDL 69
DATA LINK
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Diamond Aircraft DA 40
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