Airplane
DA 40 NG AFM
Description
7.4 INSTRUMENT PANEL
|
ENGINE |
|
|
|
VOTER |
ECU |
MASTER |
|
|
ECU A |
TEST |
ON |
|
|
|
|
|
|
|
AUTO |
|
|
H |
|
|
|
OFF |
OFF |
|
ECU B |
|
O |
||
|
FUEL |
|
R |
|
|
|
I |
|
|
|
PUMPS |
|
|
|
|
ON |
|
Z |
|
|
|
|
O |
|
|
OFF |
|
N |
ON |
EMERGENCY
EM ER GE N CY
Ess Bus not for normal operation SeeAFM
|
|
|
|
|
|
P |
R |
|
|
|
|
|
|
|
|
|
A |
|
D |
ON |
|
|
|
|
|
|
|
R |
E |
|
E |
|
|
ESS |
AVIONIC |
|
|
|
K |
L |
|
F |
|
|
|
|
|
I |
E |
|
R |
|
||
|
BUS |
MASTER |
|
|
ON |
N |
A |
|
C |
|
Ess Bus |
|
|
|
|
|
G |
S |
|
S |
A |
ON |
|
|
|
|
|
E |
|
T |
B |
|
not for |
|
|
|
|
B |
|
|
|
I |
|
|
|
|
|
|
|
|
F |
N |
||
normal |
|
|
|
|
|
R |
O |
|
|
|
|
|
|
|
|
A |
|
O |
|
||
operation |
|
|
|
|
|
E |
L |
|
L |
|
|
|
|
|
|
C |
|
O |
|
||
|
|
|
|
|
|
K |
|
|
|
|
See AFM OFF |
|
|
ALTERNATE AIR |
|
|
K |
|
R |
OF F |
|
|
|
|
|
|
|
|
||||
|
|
|
|
|
|
|
100% |
|
|
|
|
|
|
(if installed) |
GO- |
|
|
GO- |
|
|
|
' |
|
|
|
AROUND |
|
|
|
|||
|
|
AROUND |
|
|
0% |
|
|
|
||
|
|
|
|
|
|
|
FUEL VALVE |
|
||
|
|
|
|
|
|
NORMAL |
EMERGENCY |
|||
|
|
|
|
|
|
|
|
C AU TION interm ittent use |
||
|
|
|
|
|
|
|
|
only (see AFM) |
|
|
|
|
|
|
|
|
|
|
|
ELOFF |
|
|
|
|
|
|
|
|
|
U |
|
|
|
|
|
|
|
|
|
|
F |
|
|
EECU BUS
|
|
|
|
FUEL |
FUEL |
|
|
|
EECU A |
EECU B |
EECU A |
EECU B |
PUMP A |
PUMP B |
|
|
|
20 |
|
20 |
20 |
|
|
|
|
|
|
ESSENTIAL BUS |
|
|
|
|
|
||
HORIZON |
AHRS |
ADC |
COM1 |
GPS/NAV1 |
|
|
|
|
3 |
5 |
5 |
5 |
5 |
|
|
|
|
5 |
5 |
5 |
10 |
3 |
|
|
|
|
|
|
MASTER |
|
|
|
|
|
|
|
|
CONTROL |
|
|
|
|
|
|
5 |
5 |
2 |
30 |
30 |
|
|
|
|
|
|
MAIN BUS |
|
|
|
AVIONICS BUS |
|
|
|
|
|
|
|
|
|
||
60 |
5 |
5 |
5 |
25 |
5 |
5 |
5 |
2 |
3 |
10 |
5 |
3 |
5 |
5 |
|
3 |
|
P |
R |
|
|
|
A |
D |
ON |
||
R |
E |
|||
E |
|
|||
K |
L |
|
||
F |
|
|||
I |
E |
|
||
R |
|
|||
N |
A |
C |
||
O |
||||
G |
S |
|||
S |
A |
|||
|
E |
|||
|
T |
B |
||
B |
|
|
I |
|
|
F |
N |
||
R |
L |
L |
|
|
A |
|
|||
O |
O |
|
||
K |
|
|||
C |
O |
|
||
E |
|
|||
K |
R |
OFF |
||
|
||||
|
|
|
100%
0%
FUEL VALVE
NORMAL EMERGENCY
CAU TION interm ittent use only (s ee AF M)
' |
Instrument Panel with G1000 |
OFF
Page 7 - 8 |
Rev. 1 |
15-Mar-2011 |
|
Doc. # 6.01.15-E |
|
|
|
|
|
2011-Mar-15 1 .Rev E-15.01.6 # .Doc
9 - 7 Page
'
G1000 with Panel Instrument
24 |
10 |
11 |
12 |
17 |
25 |
18 |
19 |
20 |
26 |
21 |
AFM NG 40 DA |
|||||||||
|
||||||||||||||||||||
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
13 |
16 |
|
|
|
|
|
|
|
16 |
9 |
|
|
|
|
|
|
|
|
7 |
|
|
|
|
|
|
|
|
8 |
|
|
|
|
|
|
|
|
6 |
Manouveringspeed: |
|
|
|
|
|
Limitations for GFC 70 0Autopilot Sy ste m: |
|
=111KIAS(above 1036upto1200kg/ above2284upto2646 lb) |
Ess Bus |
|
|
|
|
Do not us eAP if “Alte rnate Static ”is open. |
||
=94KIAS (780to1036 kg / 1 720to2284lb) |
|
|
|
|
Co nduct AP andtrim che ck prior to each flight (see AFM). |
|||
This airplane may onlybe operatedinaccordance withtheAirplaneFlight |
not for |
|
|
|
|
|||
|
Manual. It can be operated inthe "Normal"and"Utility"categories in |
|
|
|
|
Aut opilo t OFF during take-o ff and land ing. |
|
|
|
non-icing conditions. Providedthat national operational requirements |
normal |
|
|
|
|
Maximum speed for autopilot operat ionis 165 KIAS. |
|
|
aremet and theappropriateequipment is installed, thisairplaneis ap- |
operation |
|
|
|
|
Minimum spe ed for au topilo t o perationis 70 KI AS. |
|
|
provedforthefollowingkinds of operation: day VFR, night VFR and |
See AFM |
|
|
|
|
Minimum altitude for autopilot operatio n: |
|
|
IFR. All aerobaticsmaneuvers includingspinningareprohibited. For |
|
|
|
|
|
Cruise, Climb, Descen t a nd Maneuvering: 800 fe et AGL |
|
|
furtheroperationallimitations refer tothe AirplaneFlight Manual. |
|
|
|
|
|
Approach: |
2 00 feet AGL |
|
No smoking |
|
|
|
|
|
||
|
15 |
5 |
4 |
1 |
2 |
3 |
14 |
22 |
Description |
Airplane |
Airplane
DA 40 NG AFM
Description
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'Instrument Panel with SED, MED and White Wire Annunciator Panel
Page 7 - 10 |
Rev. 1 |
15-Mar-2011 |
|
Doc. # 6.01.15-E |
|
|
|
|
|
|
DA 40 NG AFM |
|
|
|
Airplane |
||
|
|
|
|
Description |
|||
|
|
|
|
|
|
|
|
|
|
|
|
|
|
||
|
|
|
|
|
|||
|
|
|
Major Instruments and Controls |
||||
|
|
|
|
|
|
||
|
1 |
Electric Master key switch |
|
21 |
ELT control unit |
||
|
|
|
|
|
|
||
|
2 |
Fuel Transfer switch |
|
22 |
Accessory power socket |
||
|
|
|
|
|
|
|
|
|
3 |
Pitot Heat switch |
|
|
|
|
|
|
|
|
|
|
|
||
|
4 |
Avionics Master switch |
|
24 |
Primary Flight Display (PFD) |
||
|
|
|
|
|
|
||
|
5 |
Essential Bus switch |
|
25 |
Audio amplifier / Intercom / |
||
|
|
|
|
|
|
Marker beacon receiver |
|
|
|
|
|
|
|
||
|
6 |
Fuel pumps switch |
|
26 |
Multi Function Display (MFD) |
||
|
|
|
|
|
|
||
' |
7 |
ECU Test button |
|
27 |
Airspeed Indicator |
||
|
|
|
|
|
|
||
' |
8 |
ECU Voter switch |
|
28 |
Attitude Gyro (artificial horizon) |
||
|
|
|
|
|
|
||
' |
9 |
Engine Master switch |
|
29 |
Altimeter |
||
|
|
|
|
|
|
||
' |
10 |
Rotary buttons for instrument |
|
30 |
Vertical Speed Indicator (VSI) |
||
|
|
lighting and flood light |
|
|
|
|
|
|
|
|
|
|
|
||
' |
11 |
Light switches |
|
31 |
Directional Gyro |
||
|
|
|
|
|
|
||
' |
12 |
Emergency switch |
|
32 |
Turn & Bank indicator |
||
|
|
|
|
|
|
||
' |
13 |
Circuit breakers* |
|
33 |
Intercom |
||
' |
14 |
Flap selector switch |
|
34 |
Annunciator panel |
||
|
|
|
|
|
|
||
' |
15 |
Alternate static valve |
|
35 |
Main Engine Display (MED) |
||
|
|
|
|
|
|
||
' |
16 |
Ventilation nozzles |
|
36 |
Secondary Engine Display (SED) |
||
|
|
|
|
|
|
||
' |
17 |
Backup airspeed indicator |
|
37 |
Chronometer with OAT Indicator |
||
|
|
|
|
|
|
||
' |
18 |
Backup artificial horizon |
|
38 |
COM/NAV |
||
|
|
|
|
|
|
||
' |
19 |
Backup altimeter |
|
39 |
Transponder |
||
|
|
|
|
|
|
|
|
|
20 |
Emergency compass |
|
|
|
|
|
|
*) Designations and abbreviations used to identify the circuit breakers are explained in |
||||||
|
Section 1.5 - DEFINITIONS AND ABBREVIATIONS of the AFM. |
||||||
|
|
|
|
NOTE |
|
|
|
' |
|
The figures on previous pages show the typical DA 40 NG |
|||||
|
|
installation position for the equipment. The actual installation |
|||||
|
|
may vary due to the approved equipment version. |
|||||
Doc. # 6.01.15-E |
Rev. 1 |
15-Mar-2011 |
Page 7 - 11 |
|
|
|
|
Airplane
DA 40 NG AFM
Description
Cockpit Ventilation
Ventilation in the front is provided by the movable ventilation over nozzles (16) in the instrument panel. Furthermore there are spherical nozzles in the roll bar on the left and right side next to the front seats as well as on the central console above the passengers’ heads. The spherical nozzles are opened and closed by twisting.
Unconditioned ambient air is supplied to the interior through an inlet on the bottom surface of the left wing. To increase cabin temperatures when operating at low outside air temperatures, a ventilation inlet baffle may be installed at the inlet. With the baffle installed, the rear cabin ventilation nozzles on the left and right hand side and in the central console above the passengers' heads will be inoperative.
The ventilation inlet baffle consists of a metal plate with rubber edging and is attached to the bottom LH wing by a camloc.
Heating
Heating is operated using two levers located on the small center console under the instrument panel.
Right lever: |
up |
= |
heating ON |
|
down |
= |
heating OFF |
Central lever (air distribution lever): |
|
|
|
|
up |
= airflow to canopy (DEFROST) |
|
|
down |
= airflow to floor (FLOOR) |
|
Page 7 - 12 |
Rev. 1 |
15-Mar-2011 |
|
Doc. # 6.01.15-E |
|
|
|
|
|
DA 40 NG AFM
Airplane
Description
Cabin Air Control
NACA Air Inlet
Sealed
Cabin Air Control RH |
Cover plate |
Rear Cabin Air Control
Sealed
Cabin Air Control LH
Cover plate
NACA Air Inlet
Cabin Air
Exhaust
Cabin Air
Exhaust
Doc. # 6.01.15-E |
Rev. 1 |
15-Mar-2011 |
Page 7 - 13 |
|
|
|
|