Robin DR400 Series, DR400/140B, DR400/120D, DR400/200R, DR400/180R Pilot Operating Handbook
...
PILOT’S OPERATING HANDBOOK
SUPPLEMENT
DR400/135CDI
Document n° 1001639GB
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Pilot´s Operating Handbook
Supplement
for the
DR400/120D
DR400/140B
DR400/180R
DR400/200R
DR400/RP
Equipped with TAE 125 Installation
TYPE ................................ DR 400
MODEL No. ......................
SERIAL No. ......................
REGISTER No. ................
This supplement must be attached to the EASA approved Pilot´s
Operating Handbook of the DR400/120D, DR400/140B, DR400/180R,
DR400/200R or DR400/RP when the TAE 125-01 or TAE 125-02-99
installation has been installed in accordance with EASA.A.S.01380 or
EASA STC 10014219.
The information contained in this supplement supersedes or adds to the
information published in the EASA approved Pilot´s Operating Handbook
only as set forth herein.
For limitations, procedures, performance and loading information not
contained in this supplement, consult the EASA approved Pilot´s
Operating Handbook.
This supplement Pilot‘s Operating Handbook is approved with EASA
STC 10014219.
Doc.Nr.: 1001639GB
Issue 3 – July 2014 Page i
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Page - ii Issue 3 - July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Issue/
Rev.
Section
Description
Approval
D
at
Endorsed
2/1
2
New fuel,
new gearbox oil
M
ar
c
h
1
6
2
0
Revision No. 1 to AFM
supplement ref 60-0310-
60022 is approved under
the authority of DOA ref.
EASA.21J.010.
Date: March 16 ,2012
Office of Airworthiness
4
Procedures updated
3/0
all
Change of TC holder
Initial issue C.E.A.P.R
Numbering of CEAPR
documents
J
ul
y
2
0
EASA STC 10014219
transfer
APPROVAL
Issue 2:
The content of approved sections is approved by EASA. All other content
is approved by TAE under the authority of EASA DOA No.
EASA.21J.010 in accordance with Part 21.
Issue 3:
The content of approved sections is approved by EASA, transfer of STC
10014219. C.E.A.P.R is TC holder.
LOG OF REVISIONS
The parts of the text which changed are marked with a vertical line on
the margin of the page.
Issue 3 – July 2014 Page iii
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Section
Issue/ Revision
Date
0
3/0
July 2014
1
3/0
July 2014
2
3/0
July 2014
3
3/0
July 2014
4
3/0
July 2014
5
3/0
July 2014
6
3/0
July 2014
7
3/0
July 2014
LIST OF EFFECTIVE SECTIONS
Page - iv Issue 3 - July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
TABLE OF CONTENTS
APPROVAL .............................................................................................. iii
LOG OF REVISIONS ............................................................................... iii
LIST OF EFFECTIVE SECTIONS ........................................................... iii
ABBREVIATIONS .................................................................................... xi
SECTION 0
GENERAL
CONVENTIONS IN THIS HANDBOOK ................................................. 0-1
FOR DR400 AIRCRAFT FROM SERIAL NUMBER 2500 AND UP ...... 0-1
UPDATE AND REVISION OF THE MANUAL ....................................... 0-1
SECTION 1
DESCRIPTION
OVERALL DIMENSIONS ...................................................................... 1-1
ENGINE ................................................................................................. 1-1
PROPELLER.......................................................................................... 1-2
NOISE LIMITATION ............................................................................... 1-2
ELECTRICAL SYSTEM ......................................................................... 1-3
FADEC-RESET ...................................................................................... 1-6
FUELS, OILS and LIQUIDS ................................................................... 1-6
ENGINE OIL........................................................................................... 1-7
FUEL SYSTEM ...................................................................................... 1-7
OPTIONAL EXTENDED RANGE TANK ............................................... 1-8
INSTRUMENT PANEL.........................................................................1-11
HEATING AND VENTILATION ............................................................1-20
Issue 3 – July 2014 Page v
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
SECTION 2
LIMITATIONS
APPROVED OPERATION .................................................................... 2-1
MAXIMUM ALTITUDE........................................................................... 2-1
FLIGHT LOAD FACTOR LIMITS AT MAXIMUM WEIGHT .................. 2-2
MAXIMUM AUTHORIZED WEIGHTS .................................................. 2-2
WEIGHT AND BALANCE ..................................................................... 2-2
LOAD PLANNING ................................................................................. 2-3
ENGINE OPERATING LIMITS .............................................................. 2-3
ENGINE INSTRUMENT MARKINGS ................................................... 2-6
GROUNDING (EARTHING) BEFORE AND DURING FUELING ......... 2-6
PERMISSIBLE FUEL GRADES ............................................................ 2-7
MAXIMUM FUEL QUANTITIES ............................................................ 2-7
PERMISSIBLE OIL GRADES ............................................................... 2-7
PERMISSIBLE COOLING LIQUID ....................................................... 2-8
LOAD LIMITS ........................................................................................ 2-8
OPERATIONAL LIMITATIONS IN THE “U” CATEGORY .................... 2-8
PLACARDS ........................................................................................... 2-9
Page - vi Issue 3 - July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
SECTION 3
EMERGENCY PROCEDURES
ENGINE FAILURE OR LOSS OF POWER ........................................... 3-2
During takeoff roll ................................................................................... 3-2
Immediately after takeoff ....................................................................... 3-2
During flight ............................................................................................ 3-3
LANDING WITHOUT ENGINE POWER ............................................... 3-4
Restart after engine failure .................................................................... 3-5
FADEC malfunction in flight ................................................................... 3-6
ENGINE SHUT-DOWN IN FLIGHT ....................................................... 3-8
FIRE ....................................................................................................... 3-9
Engine fire on the ground, during starting ............................................. 3-9
Engine fire in flight ................................................................................ 3-9
Electrical fire ........................................................................................3-10
ROUGH ENGINE OPERATION ..........................................................3-11
Oil pressure too low .............................................................................3-11
Oil temperature too high ......................................................................3-12
Coolant temperature too high ..............................................................3-12
“Cool level” light illuminates .................................................................3-13
Gearbox temperature too high .............................................................3-13
Fuel temperature too low .....................................................................3-13
Propeller RPM too high ........................................................................3-14
Fluctuations in propeller RPM ..............................................................3-14
ICING ...................................................................................................3-14
ELECTRICAL POWER SUPPLY MALFUNCTION .............................3-16
If the “ALT” light is lit or the ammeter shows battery discharge during
normal engine operation for more than 5 minutes ...............................3-17
INADVERTENT SPIN ..........................................................................3-18
LOSS OF ELEVATOR CONTROL ......................................................3-18
Issue 3 – July 2014 Page vii
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
SECTION 4
NORMAL PROCEDURES
NORMAL OPERATING SPEEDS ......................................................... 4-1
Best rate of climb speed ........................................................................ 4-1
Maximum operating speed in turbulent air ............................................ 4-1
Never Exceed speed ............................................................................. 4-1
Maximum speed .................................................................................... 4-1
Landing speed, final approach .............................................................. 4-1
PRE-FLIGHT INSPECTION .................................................................. 4-2
CABIN INTERIOR CHECK BEFORE START-UP ................................ 4-5
STARTING THE ENGINE ..................................................................... 4-6
AFTER ENGINE START ....................................................................... 4-7
FADEC BACKUP BATTERY TEST ...................................................... 4-7
WARM UP ............................................................................................. 4-8
TAXIING ................................................................................................ 4-8
BEFORE TAKEOFF .............................................................................. 4-8
TAKEOFF ............................................................................................ 4-11
Short takeoff ....................................................................................... 4-11
Crosswind takeoff ................................................................................ 4-11
CLIMB .................................................................................................. 4-12
Normal climb (flaps up) ....................................................................... 4-12
CRUISE ............................................................................................... 4-12
DESCENT ........................................................................................... 4-13
Approach or downwind ........................................................................ 4-13
Final ..................................................................................................... 4-13
LANDING ............................................................................................. 4-14
Short landing ....................................................................................... 4-14
Overshoot procedure........................................................................... 4-14
AFTER LANDING ................................................................................ 4-14
ENGINE SHUT-DOWN ....................................................................... 4-14
After the engine stops ......................................................................... 4-14
PARKING BRAKE USE ...................................................................... 4-15
Brake on .............................................................................................. 4-15
Brake off .............................................................................................. 4-15
Page - viii Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
SECTION 5
PERFORMANCE
AIRSPEED INSTALLATION CALIBARTION ......................................... 5-1
STALL SPEEDS .................................................................................... 5-1
TAKEOFF PERFORMANCE ................................................................. 5-2
Takeoff distance, 1100 kg ...................................................................... 5-3
Takeoff distance, 1000 kg ...................................................................... 5-4
CLIMB PERFORMANCE ....................................................................... 5-5
Climb speeds ......................................................................................... 5-5
Rate of climb, Flaps retracted, 1100 kg ................................................. 5-6
Rate of climb, Flaps retracted, 1000 kg ................................................. 5-7
Time, fuel and distance to climb, Flaps retracted, 1100kg .................... 5-8
Time, fuel and distance to climb, Flaps retracted, 1000kg .................... 5-9
Maximum angle of climb in takeoff position .........................................5-10
Glide performance ...............................................................................5-10
CRUISE PERFORMANCE ..................................................................5-11
At maximum take-off weight, 1100 kg .................................................5-12
At take-off weight 980 kg .....................................................................5-15
LANDING PERFORMANCE ................................................................5-18
SECTION 6
WEIGHT AND BALANCE
USE OF WEIGHT AND BALANCE DIAGRAM ..................................... 6-3
Example of loading problem (dashed line on the diagram) ................... 6-3
SECTION 7
SUPPLEMENTS
No supplements
Issue 3 – July 2014 Page ix
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Page -x Issue 3 - July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
ABBREVIATIONS
TAE Thielert Aircraft Engines GmbH, developing and
manufacturing company of the Centurion 2.0 S engine, (since
July 2013, Technify Motors GmbH).
FADEC Full Authority Digital Engine Control
CED 125 Compact Engine Display. Multifunctional instrument for
indication of engine data of the TAE 125-01 and TAE 125-02-
99 engine.
Issue 3 – July 2014 Page xi
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Page -xii Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
SECTION 0
GENERAL
CONVENTION IN THIS HANDBOOK
This manual contains the following convention and warnings. They
should be strictly followed to rule out personal injury, property damage,
and impairment to the aircraft´s operating safety or damage to it as a
result of improper functioning.
▲ WARNING: Non-compliance with these safety rules could lead to
injury or even death.
CAUTION: Non-compliance with these special notes
and safety measures could cause damage to the engine
or to the other components.
Note: Information added for a better understanding of an
instruction.
FOR DR400 AIRCRAFT FROM SERIAL NUMBER 2500 AND UP
This supplement is valid if the TAE 125-01 or TAE 125-02-99 aircraft
engine is installed.
UPDATE AND REVISION OF THE MANUAL
▲ WARNING: A safe operation is only assured with an up to date POH
supplement.
Note: The document number of this POH supplement is
published on the cover sheet of this supplement.
Issue 3 – July 2014 Page 0 - 1
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Page 0 - 2 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
SECTION 1
DESCRIPTION
OVERALL DIMENSIONS
Wing span ................................................................ (28 ft 7.3 in) 8.72 m
Overall length ...............................................................(23 ft 8 in) 7.20 m
Overall height ........................................................... (7 ft 3.79 in) 2.23 m
Propeller ground clearance ............................................... (9.5 in) 0.26 m
ENGINE
Engine manufacturer ........................................... Technify Motors GmbH
Engine models ........................................ TAE 125-01 or TAE 125-02-99
The TAE 125-02-99 is the successor of the TAE 125-01. Both engine
variants have the same power output and the same propeller speeds but
different displacement. While the TAE 125-01 has 1689 ccm, the TAE
125-02-99 has 1991 ccm.
Both engine variants are liquid cooled in-line four-stroke 4-cylinder
engines with DOHC (double overhead camshaft) and are direct Diesel
injection engines with common-rail technology and turbocharging. Both
engine variants are controlled by a FADEC system. The propeller is
driven by a built-in gearbox (i = 1.69) with mechanical vibration damping
and overload release. The engine variants have an electrical self-starter
and an alternator.
▲ WARNING: The engine requires an electrical power source for
operation. If the main battery and alternator fail
simultaneously, the engine will operate for a very limited
time on FADEC backup battery power (TAE 125-02-99
installation).
Therefore, it is important to pay attention to indications of
alternator failure.
Issue 3 – July 2014 Page 1 - 1
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Due to the specific characteristic of the TAE 125 engine, all of the
information from the original DR400 flight manual recognized by EASA
are no longer valid with the reference to:
carburetor and carburetor pre-heating,
ignition magnetos and spark plugs, and
mixture control and priming system.
PROPELLER
Manufacturer ....................................... MT Propeller Entwicklung GmbH
Model ........................................................................... MTV-6-A/187-129
Number of blades ................................................................................... 3
Diameter ......................................................................................... 1.87m
Type ................................................................................ Constant Speed
NOISE LIMITATION
In compliance with the regulation ICAO, annex 16, Volume I, Part II,
Chapter X, the maximum acceptable noise level for the DR400/120D,
DR400/140B, DR400/180R, DR400/200R, DR400/RP at a certified max.
take-off weight of 980 kg (2161 lb) is 78.4 dB(A).
For the TAE 125-01 installation:
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with "Akrapovic type for TAE 125" muffler, is 70.9 dB(A).
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with no installed muffler, is 74.4 dB(A).
For the TAE 125-02-99 installation:
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with "Akrapovic type for TAE 125" muffler, is 70.2 dB(A).
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with “Langer LA 44” muffler, is 69.1 dB(A).
ELECTRICAL SYSTEM
The electrical system of the TAE 125 installation differs from the previous
Page 1 - 2 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
installation and is equipped with the following operating and display
elements:
1. Rocker Switch "Battery"
The battery must be switched ON in normal operation.
2. The circuit breaker below the Rocker Switch "Battery" disables the
alternator. The alternator can be left ON always.
3. Key Switch "Starter"
This switch controls the starter motor only.
4. Voltmeter
5. Warning lamp "Alternator".
Illuminates when the power output of the alternator is too low or the
circuit breaker “Alternator” (Switch resp.) is switched off. Normally, this
warning lamp always illuminates when the “Engine Master” (“IGN” resp.)
is switched on without revolution and extinguished immediately after
starting the engine.
6. Switch "Engine Master"
The Engine Master switch controls the two redundant FADEC
components, and the back-up alternator excitation battery, with three
independent contacts. It is protected against unintentional switching with
a pull-to-actuate mechanism and a guard. The alternator excitation
battery is used to ensure that the alternator continues to function in any
circumstances even if the main battery fails.
7. Switch "FORCE B"
If the FADEC does not automatically switch from A-FADEC to the BFADEC in case of an emergency despite of obvious necessity, this
switch allows to switch manually to the B-FADEC.
8. FADEC Backup Battery (TAE 125-02-99 installation)
The backup battery ensures power supply to A-FADEC only when supply
from main battery and alternator is interrupted. This allows continued
engine operation for limited time only.
Issue 3 – July 2014 Page 1 - 3
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
STARTER
PITOT HEAT
(optional)
ALTERNATOR
BATTERY
EXTERNAL POWER
PLUG
SWITCH TYPE
CIRCUIT BREAKER
TRIP FREE
CIRCUIT BREAKER
SWITCH
PUSH
BUTTON
WARNING
LIGHT
FADEC
PULL TO
FORCE B
ENGINE MASTER
ALTERNATOR
BATTERY
TEST
START
(key)
GLOW
CED
COMPACT ENGINE DISPLAY
TEST / ACK
TURN INDICATOR
VOLTMETER
STROBE
LIGHT
NAVIGATION
LIGHT
TAXI
LIGHT
LANDING
LIGHT
ELECT.
PUMP
FUEL
TEMPERATURE
PITOT
HEAT
DIMMERS
AVIONICS
STALL WARNING
FUEL GAUGE
ANNUNCIATOR PANEL
FUEL
TEMPERATURE
ICE ZONE
ELECTRONICS INTERNATIONAL
C
RDO & inst.
Cabin
Figure 1-1 Simplified block diagram
Page 1 - 4 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Figure 1-2 Simplified Block Diagram with FADEC backup battery installed
Issue 3 – July 2014 Page 1 - 5
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
FADEC-RESET
In case of a FADEC-warning, one or both FADEC warning lamps are
flashing. If then the "FADEC" Test Knob is pressed for at least 2
seconds:
a) the active warning lamps will extinguish if it was a LOW category
warning.
b) the active warning lamps will be illuminated steady if it was a
HIGH category warning.
CAUTION: If a FADEC-warning occurred, contact your
service center. Next flight is not permitted.
When a high category warning occurs the pilot should land as soon as
practical, since the affected FADEC ECU has diagnosed a severe fault.
A low category fault has no significant impact on engine operation.
Refer also to the engine manual OM-02-01 or OM-02-02 for additional
information.
FUELS, OILS and LIQUIDS
Approved fuels, oil and liquids are published in Section 2 - Limitations of
this POH Supplement.
▲ WARNING: The engine must not be started if the oil or coolant level is
too low.
CAUTION: Use of unapproved fuels, oil and coolant may result in
damage to the engine and fuel system components,
resulting in possible engine failure.
CAUTION: Normally it is not necessary to fill the cooling liquid or
gearbox oil between maintenance intervals. If the level is
too low, please notify the service department
immediately.
Page 1 - 6 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
ENGINE OIL
Oil quantity between dipstick min and max indication: .................. 1 liter
Total engine capacity including filters and coolers: .................. 6.7 liters
Approved grades: .................................. Refer to Section 2 – Limitations
CAUTION: Use the approved oil with exact declaration only!
FUEL SYSTEM
The fuel system of the TAE 125 installation includes a variant of the
original standard tank of the DR400, plus a level sender and display, and
an independent low-level warning light. An additional sensor and display
for fuel temperature is installed.
The fuel flows out of the tank to the Fuel Selector Valve which has
positions ON and OFF.
The electrically driven fuel pump supports the fuel flow to the filter
module if required. Upstream to the fuel filter module a thermostatcontrolled fuel pre-heater is installed. Then, the engine-driven feed pump
and the high-pressure pump supply the rail, from where the fuel is
injected into the cylinders depending upon the position of the thrust lever
and regulation by the FADEC.
Surplus fuel flows to the filter module and then through the fuel selector
valve back into the tank. A temperature sensor in the filter module
controls the heat exchange between the fuel feed and return. Since
Diesel fuel tends to form paraffin at low temperatures, the information in
Section 2 “Limitations“ pertaining to fuel temperature have to be
observed. The fuel return ensures a quicker warm up of the fuel in the
tank.
Issue 3 – July 2014 Page 1 - 7
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Fuel capacity
Tank
Total usable
fuel
Total unusable fuel
Total capacity
109 liters
28.7 US gal
24 imp gal
1 liter
0.26 US gal
0.22 imp gal
110 liters
29 US gal
24.2 imp gal
If Diesel fuel is used, Diesel fuel according DIN EN 590 has to be used
exclusively.
Note: There are differences in the national
supplements to EN 590. Approved are Diesel fuels with
the addition DIN EN 590.
Table 1-1 Fuel Capacity
OPTIONAL EXTENDED RANGE TANK
▲ WARNING: The optional tank is only approved for Jet-A1
The total fuel capacity can be increased to 160 l / 35.2 Imp gal / 42.24
US gal (159 l / 35 Imp gal / 42 US gal usable) by installing an optional
fuel tank of 50 l / 11 Imp gal / 13.2 US gal.
The optional tank is located in the fuselage, aft of the rear seat. The fuel
from the optional tank can be transferred into the main tank by pulling the
transfer valve control, located on the instrument panel. The fuel
temperature and the fuel level of the optional tank are displayed either on
the triple indicator or on the quad indicator (depending on the instrument
panel model) when a momentary switch is pushed (warning LED signal).
Note: The main fuel tank must be empty enough
to receive full quantity from the optional fuel tank.
Since the optional fuel tank is not heated, it is limited to the use of
JET A-1 only to prevent a potential clogging of Diesel Fuel to low
temperature.
Page 1 - 8 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Fuel shut-off
with fuel filter
and
drain-valve
Electric
fuel pump,
Switch
Fire-wall
Fuel quantity
transmitter
Vent/overflow line
Filler
port
Drain valve
Strainer
Power lever
Fuel
quantity
ON
OFF
Option.fuel
quantity
CED
6
8
10 12 14
16
FUEL
F
½EFUEL
2
1
3WESTACH
Fuel
low-level
Fuel
temperature
Optional
switch
Optional tank
50 litres
Engine-driven
fuel pump
FU EL
FIL T E R
Excess from
fuel injectors
Excess from
fuel pump
ENGINE
VOLTSFUEL
F
½
½
EEFUEL
FUEL
2
1
3
4
WESTACH
F
FADEC
Figure 1-3/1 fuel system simplified diagram (Instrument panel models #1
and #2)
Issue 3 – July 2014 Page 1 - 9
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Fuel shut-off
with fuel filter
and
drain-valve
Electric
fuel pump,
Switch
Engine-driven
fuel pump
Fire-wall
Fuel quantity
transmitter
Vent/overflow line
Filler
port
Drain valve
Strainer
Power lever
Fuel
quantity
ON
OFF
Option.fuel
quantity
FU EL
FIL T ER
CED
Excess from
fuel injectors
Excess from
fuel pump
6
8
10 12
14
16
FUEL
F
½EFUEL
2
1 3WESTACH
Fuel
low-level
Fuel
temperature
Optional
switch
Optional tank
50 litres
VOLTS
FUEL
°C
½
E
OAT
FUEL
2
1 3
4
WESTACH
F
ENGINE
FADEC
Figure 1-2 Fuel system simplified diagram (Instrument panel model #3)
Page 1 - 10 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
G
M
A
3
4
0
K
M
D
1
5
0
V
H
F
/
V
O
R
K
X
1
5
5
-
4
2
1
5
6
8
1
0
1
1
1
2
1
3
1
5
2
7
9
1
6
1
7
1
8
1
9
2
9
2
8
2
7
2
6
2
5
2
4
2
4
3
0
3
1
3
2
3
4
3
6
3
5
3
7
4
2
3
9
2
0
2
2
2
2
2
3
2
3
3
3
3
4
3
8
4
0
4
1
4
3
4
4
R
P
M
OPO
T
2
3
6
5
0
1
4
0
b
arC
L
O
A
D
%
t
r
/
m
i
n
2
3
0
0
6
0
1
0
5
1
2
0
C
C
CTG
T
1
0
0
O
F
F
L
R
B
O
T
H
S
T
2
0
707
070707060
4
0
4
0
2
0
2
1
1
4
5
1
4
5
Q
U
A
R
T
Z
-
C
H
R
O
N
O
M
E
T
E
R
L
C
-
2
R
S
T
S
T
/
S
P
M
O
D
E
S
E
T
D
T
/
V
T
I
M
E
R
C
L
O
C
K
3
6
3
6
Figure 1-5 Instrument panel model #1
Note: The avionics instrument panel is shown as an example
only.
Issue 3 – July 2014 Page 1 - 11
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Instrument panel model #1
Pos
Fonction
Pos
Fonction
Pos
Fonction
1
Airspeed indicator
16
Warning lights
31
Fuel tank valve
2
Gyro horizon
17
Lights test &
day/night dimmer
switch
32
Elevator trim control
valve
3
Altimeter
18
Instrument panel
light
33
Elevator trim
position indicator
4
Turn coordinator
19
Safety switches:
landing light, taxi
light, strobe light,
navigation light,
pitot heat
34
Cabin heat /
windshield defrost
control
5
Directional gyro
20
Circuit breakers
35
Cabin heat
6
Rate of climb
indicator
21
Electric throttle
control
36
Instrument cut-off
7
Vacuum gauge
22
ANR jacks
37
VOR/LOC indicator
8
Engine indicator
CED-125
23
Mike and headset
jacks
38
Hourmeter
9
Parking brake
control knob
24
Fresh air vent
39
Outside air
temperature (OAT)
10
Westach triple
indicator
25
Battery safety
switch
40
Clock / chronometer
11
FADEC & alternator
excitation battery
26
Key starter
41
Stall warning
12
Electrical fuel pump
control
27
Glow light
42
Music jack
13
Alt. Induction air
28
FADEC test button
43
Auxiliary 12V
14
Force FADEC B
29
CED test / warning
switch off
44
Avionics Master
switch
15
Magnetic compass
30
CED-125 lighting
knob
45
Alternator relay
breaker
Table 1-2 Instrument panel #1 description
Page 1 - 12 Issue 3 – July 2014
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
1
5
6
8
1
0
1
1
1
2
1
3
1
4
1
5
2
7
9
1
6
1
7
1
8
1
9
2
9
2
8
2
7
2
6
2
5
2
4
2
4
3
0
3
1
3
2
3
4
3
6
3
5
3
7
4
2
3
9
2
0
2
2
2
2
2
3
2
3
3
3
3
4
3
8
4
0
4
1
4
3
4
4
R
P
M
O
POT
2
3
6
5
0
1
4
0
b
a
r
C
L
O
A
D
%
t
r
/
m
i
n
2
3
0
0
6
0
1
0
5
1
2
0
C
C
CTG
T
1
0
0
O
F
F
L
R
B
O
T
H
S
T
2
0
707
0
707
0
706
0
4
0
4
0
2
0
2
1
4
5
5
C
H
R
O
N
O
M
E
T
E
R
L
C
-
6
R
S
T
S
T
/
S
P
M
O
D
E
S
E
T
A
D
V
4
6
4
7
G
M
A
3
4
0
K
M
D
1
5
0
K
X
1
5
5
-
3
8
E
L
T
A
U
T
O
M
A
N
U
A
L
4
6
Note: The avionics instrument panel is shown as an example
Figure 1-6 Instrument panel model #2
only.
Issue 3 – July 2014 Page 1 - 13
Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Instrument panel model #2
Pos
Fonction
Pos
Fonction
Pos
Fonction
1
Airspeed indicator
17
Lights test &
day/night dimmer
switch
33
Elevator trim
position indicator
2
Gyro horizon
18
Instrument panel
light
34
Cabin heat /
windshield defrost
control
3
Altimeter
19
Safety switches:
landing light, taxi
light, strobe light,
navigation light,
pitot heat
35
Cabin heat
4
Turn coordinator
20
Circuit breakers
36
Interphone on board
5
Directional gyro
21
Electric throttle
control
37
VOR/LOC indicator
6
Rate of climb
indicator
22
ANR jacks
38
Hourmeter
7
Vacuum gauge
23
Mike and headset
jacks
39
Outside air
temperature (OAT)
8
Engine indicator
CED-125
24
Fresh air vent
40
Clock / chronometer
9
Parking brake
control knob
25
Battery safety
switch
41
Instrument cut-off
10
Westach triple
indicator
26
Key starter
42
Instrument cut-off
11
FADEC & alternator
excitation battery
27
Glow light
43
Auxiliary 12V
12
Electrical fuel pump
control
28
FADEC test button
44
Avionics Master
switch
13
Alt. Induction air
29
CED test / warning
switch off
45
Alternator relay
breaker
14
Force FADEC B
30
CED-125 lighting
knob
46
ELT control
15
Magnetic compass
31
Fuel tank valve
47
Music jack
16
Warning lights
32
Elevator trim control
valve
Table 1-3 Instrument panel #2 description
Page 1 - 14 Issue 3 – July 2014
Loading...