Handout DA42 Systems

Transcription

Flight Training Division
Handout
DA42 Systems
Diamond DA 42
Twin Star
Dimensions and Exterior
Vers. 11.2
© Peter Schmidleitner
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Dimensions
Dimensions
13,42 m
2,49 m
2,20 m
8,56 m
1,74 m
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Dimensions
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Minimum width for 180° turn
1,87 m
2,95 m
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Full nosewheel deflection,
no brake
Full nosewheel deflection,
max. brake on inner wheel
(wheel blocked)
2,95 m
2,95 m
9,5 m
6,0 m
46 cm safety margin
30cm safety margin
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Attention !

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AFM page 1-2
In this program all mass and speed
values will be for aircraft with a
MTOM 1785 kg
For aircraft not yet certified for this
MTOM (MTOM: 1700 kg) refer to
the AFM!
X
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Mass (Weight)
Mass
Empty (typical)
1250 kg
Max TKOF
1785 kg
Max Ramp
+ 8 kg
Max Zero Fuel
1650 kg
Max LDG
1700 kg
Min for flight
1250 kg
!
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Max Landing Mass

Max baggage loads
Landing with a mass higher than
1700 kg is an „Abnormal Operating
Procedure“
However:
„Hard LDG Check“ only required
after a hard LDG, regardless of LDG
mass
Nose compartment
30 kg
Cockpit baggage compartment
45 kg
Baggage extension
18 kg
(behind rear seats)
45 kg
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Mass (Weight)
Attention!
JET fuel and Diesel are heavier than
AVGAS!
Speeds
Typical fuel weight:
JET A1:
0,8 kg/ltr
3,03 kg/USG
Diesel:
0,84 kg/ltr
3,2 kg/USG
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Characteristic speeds
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VNO
155
KIAS
VSO
57
KIAS
VNE
194
KIAS
VS1
64
KIAS
VA
up to 1542 kg
120
KIAS
VMCA
68
KIAS
VA
above 1542 kg
126
KIAS
VMCA ice
72 KIAS
Vops ice
121-160
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VFE (Flaps APP)
137
KIAS
VFE (Flaps LDG)
111
KIAS
VLO E
194
KIAS
VR
72 KIAS
VX
79
KIAS
VY
79
KIAS
VYSE
82
KIAS
VLO R (=~VNO)
156
KIAS
VSSE
82
KIAS
VLE
194
KIAS
(= VNE)
Emergency extension
(= VNE)
156 KIAS
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Diamond DA 42 Twin Star
</= 1700 kg
> 1700 kg
VREF FLAPS UP
85 KIAS
86 KIAS
VREF FLAPS APP
82
KIAS
82
KIAS
VREF FLAPS LDG
76
KIAS
78
KIAS
VGA
82
KIAS
82
KIAS
FLAPS
UP
*) LDG distance:
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Instrument Panel
*)
x 1,4
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Instrument Panel
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Instrument Panel
Airspeed
Garmin 1000
Horizon
Altimeter
Compass
Backup Instruments
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Instrument Panel
Instrument Panel
Flood Lights
Emergency Switch
Emergency Battery
(non rechargeable)
Lights
ELT
Circuit breakers
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Instrument Panel
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Instrument Panel
Alternators + ECU Control
Pitot heat
Engine master switches,
Engine start
Electric Master,
Avionic Master
Landing gear
Autopilot
Flaps
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Alternate Static Valve
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Alternate Static Valve
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DA 42 Garmin 1000
Garmin 1000
Quick overview
Audio Panel
PFD
MFD
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PFD
Airspeed
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Garmin 1000 MFD
Attitude
Altitude
Skid and Slip
EIS / Engine Indication System
Multi Function Display
Vertical speed
Turn Rate
OAT
DG / HSI
Transponder, Time
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Engine Indication System
Default page
Display when
pushing the
SYSTEM button
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Engine Indication System
Display when
pushing the
FUEL button
Default
SYSTEM
FUEL
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NAV and COM Tuning
NAV and COM Tuning
NAV
LH
identical
COM
RH
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Garmin 1000
Garmin 1000
Active: inside
Standby: outside
Active: green
Standby cursor: boxed
COM
volume/squelch
COM
Active („green“) is selected
on AUDIO panel
NAV volume
ident filter
Active: inside
Active: green
NAV
COM flip-flop
NAV flip-flop
Cursor toggle
Cursor toggle
MHz tuning
MHz tuning
KHz tuning
KHz tuning
Standby: outside
Standby cursor: boxed
Active („green“) is on HSI,
selected by CDI key
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Audio Panel
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Audio Panel
„MIC“ selector; automatically selects
corresponding Audio to headphone
COM Split Switch
Clearance recorder playback
• Last 2,5 minutes of communication
GMA 1347
• Press MKR/Mute to exit
„MAN Squelch“ key
Intercom Isolation
Intercom volume and
squelch control
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Audio Panel
Audio Panel
Normal Position: Intercom volume control
Manual squelch control
MAN SQ off
(not lit)
MAN SQ on
(lit)
Auto squelch is
active
VOL
Inner knob:
Pilot‘s volume
VOL
Outer knob:
Copilot‘s,
Passengers‘ volume
SQ
Pressing inner knob:
toggles between
„VOL“ and „SQ“
Outer knob:
Copilot‘s,
Passengers‘ squelch
Inner knob:
Pilot‘s squelch
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Hydraulic Brakes
Hydraulic System
Pilot applies brakes
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Hydraulic Brakes
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Hydraulic Brakes
Parking brake
„Pumping“
Copilot applies brakes
One-way valve is closed
Pressure builds up
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Landing Gear
Landing gear

Hydraulically operated
Electrically powered hydraulic pump
Electrically actuated hydraulic valves
operated by gear selector switch
„Squat switches“ prevent retraction on
ground
Warning horn with „gear up“ and
„1 throttle in low position“ or
„flaps LDG“
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Landing Gear

Landing gear
Gear downlock = spring loaded
Downlock released by hydraulic
pressure for retraction
Green lights = gear down and locked
Red lights = gear neither down nor up
Gear held up hydraulically
Emergency operation = free fall
(by releasing hydraulic pressure)

Landing Gear Warning:

Gear UP

one throttle below ~20%

Flaps LDG

and

or
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Landing Gear
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Landing gear operation
Extension
Emergency Extension
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Extended
Retraction
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Retracted
Emergency Extension
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Nosewheel steering

Nosewheel steered with rudder
pedals
Steering angle:

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Flight Controls
30° without use of brakes
52° with one wheel fully braked
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Flight Control Operation
Variable elevator backstop

Ailerons, Elevator:
push rods

Flaps:
electrically by push rods

Rudder:
cables

Normal elevator „up“ deflection: 15,5°
Limited to „13° up“ when both throttles
above 20% (approach power setting) and
flaps LDG
Reason: With full elevator deflection in case
of stalling the handling qualities and stall
characteristics are degraded
„STICK LIMIT“ caution when variable stop not
in proper position and throttles both low or
both high
Preflight check of this device is mandatory!
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Variable elevator backstop
Flaps
UP
or
APP
Power
levers
Backstop
shall be
Trim Tabs
Caution
light
If Backstop is
Both LOW
unlimiting
Split
Rudder trim:
bowden cable
limiting
Both HIGH
LDG
Elevator trim:
bowden cable
STICK LIMIT
STICK LIMIT
Both LOW
unlimiting
Split
inactive
Both HIGH
limiting
limiting
unlimiting
STICK LIMIT
STICK LIMIT
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Power Plant
Power Plant

2 Thielert Aircraft Engines TAE125
Four cylinders, liquid-cooled, 1689 ccm
Common-rail direct injection
Reduction gear 1:1,69
Dual digital engine control
Turbocharger
Max. power 99kW (135 HP) at 2300 RPM
Max cont. power 99kW (135 hp) at 2300
RPM
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Power Plant
Propeller
• Power lever selects power (LOAD in %)
• RPM automatically determined by selected power

Recommended Cruise
Power Setting: 70%

3-blade wooden propeller
Constant speed, feathering
Pitch control integrated into engine
Pitch control by gearbox oil
Governor valve controlled by ECU

Oil pressure up = pitch down = RPM up
Oil pressure down = pitch up = RPM down
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Feathering System

Power plant limitations
No „Auto-feather“
Feathering by „Engine Master OFF“ if
RPM above 1300
If RPM below 1300: prop pitch remains
above high pitch lock
Unfeathering by oil pressure from
accumulator when Engine Master is ON

Max overspeed: 2500 RPM, max 20 sec.
Oil pressure: 1.0 – 6.5 bar
Oil quantity (per engine): 4.5 – 6.0 liters
Max. oil consumption: 0.1 liters/hr
Oil temperature: -32 °C – 140 °C
Gearbox temperature: max. 120 °C
Coolant temperature: -32 °C – 105 °C
Max. restart altitude: 6000 ft, 80–120 KIAS
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Power plant fluid specifications
AFM page 1-2

Fuel:
JET A-1 or JET A (ASTM 1655)
JET No. 3 (GB6537-94)
Diesel (EN 590)

Oil:
SHELL Helix Ultra 5W30 synth. API SL/CF
SHELL Helix Ultra 5W40 synth. API SL/CF
AERO SHELL Diesel 10W-40
Gearbox oil:
Coolant:
SHELL EP 75W90 API GL-4

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!
X
Destilled water + cooler protection 1:1
(BASF Glysantin Alu Protect Plus/G48)
(freezing point –36 °C)
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„Diesel“ limitations

Diesel or JET/Diesel mixture not
permitted in AUX tanks
Temperature limits

Below -5° C
Below +5° C

When is no more diesel in the
tanks?

no engine start
no take-off
Be sure that no diesel fuel is in the
tanks – otherwise temp limitations
for diesel ops must be observed
each tank to be refilled at least twice
with more than 17,2 USG (65 ltrs) of
Jet fuel

otherwise
tank must be drained
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Fuel temperature
-30
-5
Fire detection system
+5
+70
+75

JET A-1
Take-off
Diesel, Diesel/A-1 blend
or unknown

Engine start

Overheat detector in hot area of
each engine
Warning above 250°C
Test button:
Analogue indication
Default page
FUEL page
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DA 42 Fuel System
Fuel System

2 Tanks (left and right), each
with 3 chambers:
2 x 25 USG usable
= 50 USG (189 ltr)
= 152 kg (at 0,80 kg/ltr)
At 70% power: 10,5 USG/hr
Max unbalance: 5 USG
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DA 42 Fuel system
DA 42 Fuel System
Fuel filler
3 chambers
Fuel Valve „ON“
Supply
Temperature sensor
Drain
Return flow
18-21 USG/hr
Fuel level sensor
2 vents
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DA 42 Fuel System
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Fuel Valves Schematic
Supply
X-feed operation
Return flow
ON
X-F
ON
OFF
ON
ON
X-FEED
OFF
OFF
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Both valves closed
X-F
ON
OFF
X-F
ON
OFF
OFF
OFF
ON
X-F
ON
X-FEED
Supply
Return flow
X-F
X-F
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Both engines running
Supply
Supply
Return flow
Return flow
X-F
ON
X-F
OFF
OFF
OFF
ON
ON
X-F
ON
OFF
X-F
X-F
ON
X-F
OFF
OFF
OFF
ON
ON
ON
ON
ON
X-FEED
X-FEED
X-FEED
X-FEED
OFF
OFF
OFF
OFF
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LH Eng. u/s, RH Eng. X-feed
ON
X-F
ON
OFF
X-F
Both engines from LH Tank
Supply
Supply
Return flow
Return flow
X-F
ON
X-F
OFF
OFF
OFF
ON
ON
X-F
ON
OFF
X-F
X-F
X-F
ON
OFF
OFF
OFF
ON
ON
ON
ON
X-FEED
X-FEED
X-FEED
X-FEED
OFF
OFF
OFF
OFF
ON
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Optional Auxiliary Fuel Tanks
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One tank in each nacelle
Capacity: 13,7 USG per side
Useable:
13,2 USG per side
For practical purposes (placarded):
13,0 USG per side
Main tanks
AUX tanks
Total
2 x 25 USG
2 x 13 USG
2 x 38 USG
50 USG
26 USG
76 USG
5 USG
Max unbalance
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Electrical transfer pump feeds fuel
from the AUX tank to the main tank
Transfer must be initiated manually
Transfer in 2 steps:

First half when main tank 17 USG or
less (up to full main tank)
Second half when main tank again 17
USG or less
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CAUTION light
Transfer pump switched OFF
automatically when:

Main tank is full
AUX tank is empty
L/R AUX FUEL E

L/R AUX tank empty and fuel transfer
pump ON
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In case of a L or R XFER pump failure:
(AUX pump does not operate)
Use x-feed function to keep fuel balance
Amend flight plan for reduced amount
of available fuel
Mass and Balance
Item
Lever Arm (m)
Wing tanks
2.63
AUX tanks
3.20
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Fuel quantity check
Verify AUX empty

Electrical Master
Fuel transfer
L/R AUX FUEL E
ON
ON
CHECKED

Fuel quantity between „FULL“ and
„EMPTY“ cannot be determined
Verify AUX full

Visual check
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Remember !

Preflight fuel management
If possible transfer all AUX fuel to
main tanks

Use external power or one engine running
Electrical Master
Fuel transfer

Diesel or A1/Diesel mixture not
permitted in AUX tanks !
ON
ON
until

L/R AUX FUEL E
(will take max. 10 minutes)
ON
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Cooling System
Cooling System
Coolant Temp.
< 80°
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Cooling System
Cooling System
Coolant Temp.
Cabin Heat
> 80°
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Cabin Heating and Defrosting System
Defrost from LH Engine
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Cabin Heat from RH Engine
Turbocharger
System
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Turbo Charger
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Turbo Charger
Compressor compresses intake air
Bypass for excess exhaust gas
Exhaust gas drives turbine
Exhaust gas drives turbine
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DA 42 Electrical System
Electrical System
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Power sources
Power distribution
Main Battery
24V 10Ah
LH
Generator
28V 60A
Hot Battery Bus
Battery Bus
RH Main Bus
LH Main Bus
Load balancing
RH
Generator
28V 60A
RH ECU Bus
LH ECU Bus
Excitation Battery
24V 1,3 Ah
Emergency Battery
Avionic Bus
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Hot Battery Bus
Battery Bus
Starter
Starter

LH
Generator
EPU
Pilot map / reading light
RH
Generator
Main Battery
24V 10Ah
Avionic Bus
Hot Battery Bus
RH ECU Bus
LH ECU Bus
LH Main Bus
RH Main Bus
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Battery Bus
LH Main Bus

LH / RH Main Bus
LH / RH starter heavy duty
power
LH / RH ECU BUS (via diode)

PFD
Air Data Computer
AHRS
COM 1
GPS/NAV 1
Transponder
Engine
Instruments
Fuel transfer
De-icing system

Pitot heating
Oxygen system
Gear control
Gear warning
Map light
Flood light
Taxi light
Anticollision
lights
Variable elevator
backstop
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RH Main Bus

Avionic Bus
MFD
Horizon
Starter control
Flap system
Avionic/
CDU cooling fan
Avionic Bus

Stall warning
Autopilot
warning
Landing light
Navigation lights
Instrument
lights

COM 2
GPS/NAV 2
Audio panel
Autopilot
(Data Link)
(WX 500)
(ADF)
DME
(Weather Radar)
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Electric Master

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L/R Alternator switch
Connects Battery Bus to Battery
(Battery Bus powers L/R Main Bus)
Enables Alternator Switches

Connects L/R Generator to L/R Main
Bus
(In normal operation Alternator switches are
always ON)
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L/R Engine Master

Avionic Master Switch
Enables starter activation
Connects L/R ECU (A+B) to L/R ECU Bus
Provides power for „GLOW“ and unfeathering
accumulator
Connects L/R generator field to Excitation
Battery

Connects Avionic Bus to RH Main Bus
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Excitation Battery
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Electric Master OFF
Main Battery
24V 10Ah
OFF
OFF
ON
OFF
ON
Excitation Battery
24V 1,3 Ah
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Electric Master ON
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LH Engine Master ON
Preparing Engine Start
Engine Masters still OFF
ON
OFF
ON
ON
OFF
ON
OFF
ON
ON
ON
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LH Engine Start
ON
After LH Engine Start
OFF
ON
ON
OFF
ON
ON
ON
ON
ON
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External power connection
Oxygen System
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Oxygen system

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Oxygen system
Continous Flow System
Operation up to 18.000 ft
Oxygen cylinder pressure MAX 1850 psi
4 cannulas plus 1 mask
Acc. AFM to be used above 12.500 ft
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Oxygen system
Oxygen system
Oxygen cylinder
Oxygen outlets
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Oxygen system
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Oxygen system
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Oxygen system
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Oxygen system
Flowmeter
Quick connect
Adjustable flow valve
Scale for cannula
Scale for mask
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Ice protection system
Ice Protection System
Fluid ice protection system
Product of
CAV Aerospace Ltd
(Celtic Aerospace Ventures Ltd)
commonly knows as
„TKS“
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T
K
S

Tecalemit Ltd.
(metering pumps)
„TKS“ Ice Protection
General
Kilfrost Ltd.
(deicing chemicals)
Sheepbridge Stokes
(porous metals)
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How does it work?

Protection fluid acts a „freezing point
depressant“ (FPD)
Water droplets in the air combine with
FPD fluid to form a mixture with a
freezing temperature below the
temperature of the ambient air

Two means of FPD fluid application:

Spray nozzles (windshield, propeller)
Porous skin panels
Propeller:

Feeding into a „slinger ring“
Feeder tube to (rubber) leading edge
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Freezing point of glycol:

-12° C
Freezing point of glycol/water
mixture:

-22° C
to
„TKS“ Ice Protection
DA 42
-40°C
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Operational modes
2 „independent“ systems
Airframe and
Prop
Windshield

MAX
HIGH
NORM mode

NORM
PUMP 1
PUMP 2
2 x 2 pumps

HIGH mode
ALTERNATE

LH Main BUS
RH Main BUS
Normally powered from the LH Main Bus
Fluid tank

2 pumps simultaneously, but cycled
30 secs ON and 90 secs OFF
1 pump continuously
MAX mode

2 pumps simultaneously ON for 2
minutes
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Operational modes

NORM mode

~ 2,5 hrs

HIGH mode

Windshield ice protection

~ 1,0 hr
MAX mode

2 pumps for redundancy
Only one pump operative at a time
Operated for 5 seconds by a push
button
~ 0,5 hrs
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Airframe and
Prop
Windshield
MAX
cycling
HIGH
NORM
NORM
PUMP 1
PUMP 2
ALTERNATE
30s ON, 90s OFF
LH Main BUS
RH Main BUS
Fluid tank
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Airframe and
Prop
Continuously ON
Windshield
MAX
HIGH
HIGH
NORM
PUMP 1
PUMP 2
ALTERNATE
LH Main BUS
RH Main BUS
Fluid tank
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2 minutes ON
Airframe and
Prop
MAX
Windshield
MAX
+
HIGH
HIGH
NORM
PUMP 1
PUMP 2
ALTERNATE
LH Main BUS
RH Main BUS
Fluid tank
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Airframe and
Prop
Windshield
MAX
HIGH
NORM
PUMP 1
PUMP 2
ALTERNATE
5 seconds
LH Main BUS
Windshield deice
RH Main BUS
Fluid tank
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Airframe and
Prop
Windshield
MAX
HIGH
NORM
PUMP 1
PUMP 2
ALTERNATE
Main and Windshield
pump selector
LH Main BUS
RH Main BUS
Fluid tank
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Airframe and
Prop
Windshield
MAX
ALTERNATE switch
connects pump #2
directly to
RH main bus
HIGH
NORM
PUMP 1
PUMP 2
ALTERNATE
LH Main BUS
RH Main BUS
System operates in
HIGH mode
Fluid tank
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Airframe and
Prop
Windshield
MAX
HIGH
NORM
PUMP 1
DEICE LVL LO light ON
PUMP 2
DEIC PRES LO light ON
after 120 seconds
ALTERNATE
LH Main BUS
RH Main BUS
Annunciator test
Fluid tank
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CAUTION lights

DEIC PRES LO

DEIC PRES HI

Ice lights
De-icing pressure is low
De-icing pressure is high
DEICE LVL LO

De-icing fluid level is low (below 10 ltrs)

(max 45 mins in NORM mode)
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Approved fluids
For use in the system:

Mass and Balance
AL-5 (DTD 406B)
Aeroshell Compound 07
For de-icing on ground:

Lever Arm
(m)
1.00
Item
De-icing fluid tank
AL-5 (DTD 406B)
TKS 80
1 ltr: 1,1 kg
30 ltr: 33,0 kg
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Preflight Check:

Electric Master
De-ice fluid quantity
Windshield de-icing
DE ICE
Ice lights
Porous panels, props
Ice lights
DE ICE, Ice lights
Annunciator test

ON
CHECK
CHECK
HIGH
ON
CHECK
CHECK
OFF
PERFORM
YES on panels

Water, soap
Isopropyl alcohol
Ethyl alcohol
Methylated spirit
De-icing fluids
AVGAS
Jet fuel

NO on panels

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Operational considerations
approved for flight into known icing conditions
(„fiki“)
DA42 Ice protection system is

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Wax
Methyl ethyl
ketone (MEK)
Lacquer thinner
Other thinners and
solvents
NOT a „de-icing“ system
but an „anti-ice“ system,
preventing accretion of ice

what defines „icing conditions“?

visually detected ice
visible moisture and OAT +3°C or
below
minimum operating temperature for the ice
protection system: -30°C
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what indicates conditions the
system my be unable to cope with?

heavy ice accumulation on windshield
ice on side areas of canopy
rapid formation and shedding of bars
thicker than 6mm from porous panels

select HIGH/MAX
leave icing conditions
Exit icing conditions immediately
how to detect freezing rain or freezing
drizzle ?

what to do?

flight in „freezing rain“ or „freezing
drizzle“ is prohibited !

unusually extensive ice where normally not
observed
ice on upper surface of wing aft of protected
area
ice on spinner further back than normally
observed
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how to detect possible freezing rain or
freezing drizzle conditions?

visible rain in OAT below +5°C
droplets that splash on impact in OAT below
+5°C
performance loss larger than normally
experienced in icing conditions
Autopilot

may be used in icing conditions, but:

disconnect every 10 – 15 minutes to
detect out of trim conditions
PROHIBITED with

ice aft of protected area
unusual lateral trim
autopilot trim warning
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Airspeeds with ice on unprotected areas
VMCA
72 KIAS
Continuous operation in icing
conditions (except TKOF, LDG and
maneuvers)
Stalling speeds
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121 – 160 KIAS
+ 4 KIAS
Performance with ice on unprotected areas
reduced by
Rate of climb
up to 150 fpm
1-engine ROC
up to 150 fpm
above 2000ft PA positive ROC may not be achieved
Cruise performance
15%
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Technical considerations

Approach, landing in icing conditions:
Gear down, flaps APP
Va min 82 KIAS
LDG distance: x 1,4 !
Go around
with Flaps APP, gear down, 82 KIAS:

5,83%, 529 fpm climb
Priming of the system:

main pumps:

porous panels:

primed by windshield pumps
not to be primed in icing conditions !!
shall be primed in climb or descent
up to 4°C
MAX mode in intervals of 5 minutes until
fluid dissipates from all panels
above 4°C priming by special maintenance
only
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Autopilot Limitations
Autopilot
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Autopilot
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Autopilot
AP engaged
annunciator
Pitch trim
annunciator
ALT Alert
ALT ARM
Baro
display/
setting
Pitch Wrng
AP ON/OFF
Roll Wrng
ALT
V/S
BARO
Set
Altitude
or
Baro
HDG select
APR mode
NAV mode
ALT Hold
Backbeam
display
+/- V/S
or
+/- Alt
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Autopilot
Autopilot
Roll Mode:
ROL
HDG
NAV ARM
NAV
APR ARM
APR
REV ARM
REV
GS ARM
Vertical Speed Mode
Pitch
Mode:
VS
ALT ARM
ALT
GS
Toggles between ALT HLD and V/S
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Autopilot
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Autopilot
Altitude Preselect
Altitude Hold Mode
Select Altitude
ALT ARM
Select V/S
Change to
V/S
Toggles between ALT HLD and V/S
ALT Hold and
ALERT
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Autopilot
CWS
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AP disconnect
Performance
Manual Electric Trim
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Performance

DA 42 Twin Star according CS 23:

No Density Altitude
graph in the DA42 AFM
Normal, Utility & Aerobatic category

Reciprocating engine

Density altitude
Weight < 2722 kg
VSO < 61 kt
„Light Twin“
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TOD, TOR tabular format
The „DA 42“ and „Density altitude“

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Attention!

Performance data which are enginepower dependant cannot be
determined by just using „Density
Altitude“!
Reason: the engine power output does
not correspond to density altitude but
pressure and temperature have their
own, independent influence
This is a feature of the ECU controlled,
turbocharged Diesel-engine
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Performance diagrams
TKOF distance

All diagrams are in duplicate:

1st for mass up to 1700 kg
2nd for mass above 1700 kg
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TKOF distance
Grass Runway
(TOM > 1700kg)
Length of
grass
- 5 cm
+ 10%
5 - 10 cm
+ 15%
>10 cm
+ 25%
> 25 cm
TKOF roll
Wet grass
additional
+ 10%
TKOF should not be attempted
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LD, LR tabular format
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LD, LR tabular format
Remember: landing mass > 1700kg =
„Abnormal Operating Procedure“ !
1700 kg
1785 kg
572 m
710 m
+ 138 m
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Grass Runway
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Go around
76 KIAS
Length of
grass
- 5 cm
5 - 10 cm
>10 cm
LDG run
Wet grass
78 KIAS
+ 5%
+ 15%
additional
+ 10%
min + 25%
Required gradient acc. CS 23.77 (a): 3,3% at Sea Level
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Accelerate stop distance
Obstacles ?
„d“= (RWL + Obst.Dist.) - TOD
Gradient = („h“ / „d“) * 100
ROC =
Gradient x TAS
0.95
824 m
„h“
1401 m
+ increment for 0° flaps ?
„d“
Obst. Dist.
TOD
RWL
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Vöslau RWY 31
Mass and Balance
„d“= (950 + 830) – 530 = 1250
Gradient = (30 / 1250) * 100 = 2,4%
ROC =
2,4 x 85
0.95
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= 215 fpm
Acc. Performance Graph:
@ 1700 kg ~ 220 fpm
98 ft
1250
830 m
530
950
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Empty mass

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Center of gravity envelope
Empty Mass includes:

Equipment as per Equipment Inventory
Brake fluid
Hydraulic fluid
Engine oil (2 x 6.0 liters)
Coolant (2 x 6.0 liters)
Gearbox oil (2 x 0.9 liters)
Unusable fuel in main tanks (2 USG)
Unusable fuel in AUX tanks (1 USG)
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Moment envelope
Moment arms
Item
Lever Arm (m)
Front seats
2.30
Rear seats
3.25
Wing tanks
2.63
AUX tanks
3.20
De-icing fluid
1.00
Nose baggage
0.60
Cockpit baggage
3.89
Baggage Extension
4.54
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Typical M+B data
Empty mass
Moment
CG arm
ACFT with ice-protection
and AUX tanks
1296,6
3162,5
2,439
ACFT with AUX tanks
1275,5
3103,8
2,433
Emergency
Equipment
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Emergency Equipment
Kinds of Operation
Equipment List
(KOEL)
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Kinds of Operation Equipment List
KOEL
KOEL
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KOEL
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KOEL
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KOEL
Additional minimum equipment for the
intended operation
may be required by
national operating rules
and also depends on the
route to be flown.
Servicing
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Unscheduled Maintenance

Scheduled maintenance

Required after

Hard landings
Propeller strike
Engine fire
Lightning strike
Other malfunctions and damage
Every
100 hours
200 hours
1000 hours
2000 hours

Annually
New engine: inspection after 3 – 6 hours
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De-icing

Mooring
Aproved de-icing fluids:

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Kilfrost TKS 80
AL-5 (DTD 406B)
Procedure:

Remove snow with brush
Spray de-icing fluid
Wipe dry
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Happy landings !
Mooring
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