Diamond DA 42 Systems Handouts 10 1
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Transcript of Diamond DA 42 Systems Handouts 10 1
7/27/2019 Diamond DA 42 Systems Handouts 10 1
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42Twin Star
Vers. 10.1
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Dimensions and Exterior
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Dimensions
13,42 m
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Dimensions
8,56 m
2,20 m2,49 m
1,74 m
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Dimensions
2,95 m
1,87 m
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Minimum width for 180° turn
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Minimum width for 180° turn
2,95 m
9,5 m
46 cm safety margin
Full nosewheel deflection,no brake
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Minimum width for 180° turn
2,95 m
6,0 m
30cm safety margin
Full nosewheel deflection,max. brake on inner wheel
(wheel blocked)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Attention !
In this program all mass and speedvalues will be for aircraft with a
MTOM 1785 kg
For aircraft not yet certified for thisMTOM (MTOM: 1700 kg) refer tothe AFM!
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
AFM page 1-2
X
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mass
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Mass (Weight)
1700 kgMax LDG
+ 8 kgMax Ramp
1250 kgMin for flight
1650 kgMax Zero Fuel
1785 kgMax TKOF
1250 kgEmpty (typical)
!
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Max Landing Mass
Landing with a mass higher than1700 kg is an „Abnormal OperatingProcedure“
However:
„Hard LDG Check“ only requiredafter a hard LDG, regardless of LDGmass
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Max baggage loads
45 kg
18 kgBaggage extension
45 kgCockpit baggage compartment(behind rear seats)
30 kgNose compartment
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mass (Weight)
Attention!
JET fuel and Diesel are heavier thanAVGAS!
Typical fuel weight:
Diesel:
0,84 kg/ltr
3,2 kg/USG
JET A1:
0,8 kg/ltr
3,03 kg/USG
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Speeds
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Characteristic speeds
126 KIASVA above 1542 kg
120 KIASVA up to 1542 kg
194 KIASVNE
155 KIASVNO
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Characteristic speeds
121-160Vops ice
72 KIASVMCA ice
68 KIASVMCA
64 KIASVS1
57 KIASVSO
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Characteristic speeds
72 KIASVR
82 KIASVSSE
82 KIASVYSE
79 KIASVY
79 KIASVX
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Characteristic speeds
156 KIASEmergency extension
194 KIASVLE (= VNE)
156 KIASVLO R (=~VNO)
194 KIASVLO E (= VNE)
111 KIASVFE (Flaps LDG)
137 KIASVFE (Flaps APP)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Characteristic speeds
82 KIAS
78 KIAS
82 KIAS
86 KIAS
> 1700 kg</= 1700 kg
85 KIASVREF FLAPS UP
82 KIASVGA FLAPS UP
76 KIASVREF FLAPS LDG
82 KIASVREF FLAPS APP *)
*) LDG distance: x 1,4
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Instrument Panel
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Instrument Panel
Garmin 1000
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Instrument Panel
Backup Instruments
Horizon AltimeterAirspeed Compass
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Instrument Panel
Emergency Switch Emergency Battery(non rechargeable)
Flood Lights
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Instrument Panel
ELTLights Circuit breakers
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Instrument Panel
Engine master switches,Engine start
Pitot heat Electric Master,Avionic Master
Alternators + ECU Control
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Instrument Panel
FlapsLanding gear Autopilot
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Alternate Static Valve
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Alternate Static Valve
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Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Garmin 1000Quick overview
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
DA 42 Garmin 1000
PFD MFD
Audio Panel
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Garmin 1000 PFD
Altitude Attitude Airspeed
Vertical speed
DG / HSIOAT Transponder, Time
Skid and Slip
Turn Rate
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Garmin 1000 MFD
EIS / Engine Indication System Multi Function Display
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Default page
Display whenpushing the
SYSTEM button
Engine Indication SystemDisplay whenpushing theFUEL button
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Engine Indication System
SYSTEM FUELDefault
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Garmin 1000
NAV and COM Switching
LH identical RH
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
NAV COM
Garmin 1000
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
MHz tuning
Active: inside Standby: outside
Active: green Standby cursor: boxed
COMvolume/squelch
COM
KHz tuning
COM flip-flop
Cursor toggle Active („green“) is selectedon AUDIO panel
Garmin 1000
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
NAV
Active: insideStandby: outside
Active: greenStandby cursor: boxed
NAV volumeident filter
MHz tuning
KHz tuning
NAV flip-flop
Cursor toggle Active („green“) is on HSI,selected by CDI key
Garmin 1000
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Audio Panel
COM Split Switch
Intercom Isolation
„MIC“ selector; automatically selectscorresponding Audio to headphone
GMA 1347
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Audio Panel
Clearance recorder playback
Intercom volume andsquelch control
• Last 2,5 minutes of communication
• Press MKR/Mute to exit
„MAN Squelch “ key
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Audio Panel
Normal Position: Intercom volume control
VOL
Outer knob:Copilot‘s,
Passengers‘ volume
Inner knob:Pilot‘s volume
MAN SQ off (not lit)
Auto squelch isactive
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Audio Panel
Manual squelch control
VOLPressing inner knob:
toggles between „VOL“ and „SQ“
MAN SQ on(lit)
Outer knob:Copilot‘s,
Passengers‘ squelch
Inner knob:Pilot‘s squelch
SQ
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Hydraulic System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Hydraulic Brakes
Pilot applies brakes
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Hydraulic Brakes
Copilot applies brakes
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Hydraulic Brakes
One-way valve is closed
Parking brake
„Pumping“
Pressure builds up
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Landing Gear
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Hydraulically operated
Electrically powered hydraulic pump
Electrically actuated hydraulic valvesoperated by gear selector switch
„Squat switches“ prevent retraction onground
Warning horn with „gear up“ and „1 throttle in low position“ or „flaps LDG“
Landing gear
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Gear downlock = spring loaded
Downlock released by hydraulicpressure 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
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Landing gear
Landing Gear Warning:
Gear UP
and
one throttle below ~20% or
Flaps LDG
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Landing Gear
Emergency Extension
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Landing gear operation
Extension
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Extended
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Retraction
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Retracted
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Emergency Extension
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Nosewheel steering
Nosewheel steered with rudderpedals
Steering angle:
30° without use of brakes
52° with one wheel fully braked
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Flight Controls
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Flight Control Operation
Rudder:cables
Flaps:electrically by push rods
Ailerons, Elevator:push rods
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Variable elevator backstop
Normal elevator „up“ deflection: 15,5°
Limited to „13° up“ when both throttlesabove 20% (approach power setting) andflaps LDG
Reason: With full elevator deflection in caseof stalling the handling qualities and stall
characteristics are degraded „STICK LIMIT“ caution when variable stop not
in proper position and throttles both low orboth high
Preflight check of this device is mandatory!
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Variable elevator backstop
Flaps
UPor
APP
LDG
Powerlevers
Backstopshall be
If Backstop isCaution
light
Both LOW
Split
Both HIGH
Both LOW
Split
Both HIGH
unlimiting
l imiting unlimiting
limiting STICK LIMIT
STICK LIMIT
unlimiting limiting
STICK LIMIT
STICK LIMIT
inactive
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Trim Tabs
Rudder trim:bowden cable
Elevator trim:bowden cable
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Power Plant
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
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 2300RPM
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
• Throttle selects power (LOAD in %)
• RPM automatically determined by selected power
Power Plant
Recommended Cruise
Power Setting: 70%
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Propeller
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
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Feathering System
No „Auto-feather“
Feathering by „Engine Master OFF“ if RPM above 1300
If RPM below 1300: prop pitch remainsabove high pitch lock
Unfeathering by oil pressure fromaccumulator when Engine Master is ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Power Plant Limitations
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, 83–125 KIAS
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
!
Power plant fluid specifications
Fuel: JET A1 (ASTM 1655)
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: SHELL EP 75W90 API GL-4
Coolant: Destilled water + cooler protection 1:1
(BASF Glysantin Alu Protect Plus/G48)
(freezing point –36 °C)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
AFM page 1-2
X
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
„Diesel“ limitations
Diesel or A1/Diesel mixture notpermitted in AUX tanks
Temperature limits Below -5° C no engine start
Below +5° C no take-off
Be sure that no diesel fuel is in thetanks – otherwise temp limitationsfor diesel ops must be observed
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
When is no more diesel in thetanks?
each tank to be refilled at least twicewith more than 17,2 USG (65 ltrs) of Jet A-1
otherwise
tank must be drained
„Diesel“ limitations
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
JET A-1
-30 +75+70+5-5Fuel temperature
Diesel, Diesel/A-1 blendor unknown Engine start
Take-off
Analogue indication
FUEL page
„Diesel“ limitations
Default page
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fire detection system
Overheat detector in hot area of each engine
Warning above 250°C
Test button:
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Fuel System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
2 Tanks (left and right), eachwith 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
DA 42 Fuel System
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Fuel system
Fuel level sensor
3 chambers Fuel filler
2 ventsDrain
Temperature sensor
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
DA 42 Fuel System
Fuel Valve „ON“Supply
Return flow18-21 USG/hr
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Supply
Return flow
DA 42 Fuel System
X-feed operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fuel Valves Schematic
Supply
Return flow
ONX-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ON X-FON
OFF
X-F
OFF
ON X-F
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Both valves closed
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ON X-FON
OFF
X-F
OFF
ON X-F
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Both engines running
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ON X-FON
OFF
X-F
OFF
ON X-F
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
LH Eng. u/s, RH Eng. X-feed
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ON X-FON
OFF
X-F
OFF
ON X-F
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Both engines from LH Tank
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ON X-FON
OFF
X-F
OFF
ON X-F
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Max unbalance5 USG
76 USG26 USG50 USG
2 x 38 USG2 x 13 USG2 x 25 USG
TotalAUX tanksMain tanks
Optional Auxiliary Fuel Tanks
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Electrical transfer pump feeds fuelfrom the AUX tank to the main tank
Transfer must be initiated manually
Transfer in 2 steps:
First half when main tank 17 USG orless (up to full main tank)
Second half when main tank again 17USG or less
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Transfer pump switched OFFautomatically when:
Main tank is full
AUX tank is empty
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
CAUTION lights
L/R XFER FAIL
AUX pump does not operate
L/R AUX FUEL E
L/R AUX tank empty and fuel transferpump ON
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
L/R XFER FAIL
Use x-feed function to keep fuelbalance
Amend flight plan for reduced amountof available fuel
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Mass and Balance
3.20 AUX tanks
2.63Wing tanks
Lever Arm (m)Item
Optional Auxiliary Fuel Tanks
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fuel quantity check
Verify AUX empty
Electrical Master ON
Fuel transfer ON
L/R AUX FUEL E CHECKED
Verify AUX full Visual check
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fuel quantity between „FULL“ and „EMPTY“ cannot be determined
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Preflight fuel management
If possible transfer all AUX fuel tomain tanks Use external power or one engine running
Electrical Master ON
Fuel transfer ON
until
L/R AUX FUEL E ON(will take max. 10 minutes)
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Remember !
Diesel or A1/Diesel mixture notpermitted in AUX tanks !
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Cooling System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Cooling System
Coolant Temp.
< 80°
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Cooling System
Coolant Temp.
> 80°
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Cooling System
Cabin Heat
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Cabin Heating and Defrosting System
Cabin Heat from RH EngineDefrost from LH Engine
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
TurbochargerSystem
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Exhaust gas drives turbine
Bypass for excess exhaust gas
Turbo Charger
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Compressor compresses intake air
Turbo Charger
Exhaust gas drives turbine
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Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Electrical System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
DA 42 Electrical System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Power sources
LH
Generator
28V 60A
Main Battery
24V 10Ah
Excitation Battery
24V 1,3 Ah
RH
Generator
28V 60A
Emergency Battery
Load balancing
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
DA 42 Electrical System
Power distributionHot Battery Bus
Battery Bus
LH Main Bus
LH ECU Bus
Avionic Bus
RH ECU Bus
RH Main Bus
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Hot Battery Bus
Battery Bus
LH Main Bus
LH ECU Bus
Avionic Bus
RH ECU Bus
RH Main Bus
Main Battery
24V 10Ah
LH
Generator
RH
Generator
Starter Starter
EPU
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Hot Battery Bus
Pilot map / reading light
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Battery Bus
LH / RH Main Bus
LH / RH starter heavy dutypower
LH / RH ECU BUS (via diode)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
LH Main Bus
PFD
Air Data Computer
AHRS
COM 1
GPS/NAV 1
Transponder
EngineInstruments
Fuel transfer
De-icing system
Pitot heating
Oxygen system
Gear control
Gear warning
Map light
Flood light
Taxi light
Anticollisionlights
Variable elevatorbackstop
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
RH Main Bus
Avionic Bus
MFD
Horizon
Starter control
Flap system
Avionic/CDU cooling fan
Stall warning
Autopilotwarning
Landing light
Navigation lights
Instrumentlights
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Avionic Bus
COM 2
GPS/NAV 2
Audio panel
Autopilot
(Data Link)
(WX 500)
(ADF)
DME
(Weather Radar)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Connects Battery Bus to Battery(Battery Bus powers L/R Main Bus)
Enables Alternator Switches
Electric Master
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
DA 42 Electrical System
Connects L/R Generator to L/R MainBus
(In normal operation Alternator switches arealways ON)
L/R Alternator switch
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Enables starter activation
Connects L/R ECU (A+B) to L/R ECU Bus
Provides power for „GLOW“ and unfeatheringaccumulator
Connects L/R generator field to ExcitationBattery
L/R Engine Master
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
DA 42 Electrical System
Connects Avionic Bus to RH Main Bus
Avionic Master Switch
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Excitation BatteryMain Battery
24V 10Ah
Excitation Battery
24V 1,3 Ah
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Electric Master OFF
OFF
OFFOFF
ON
ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Electric Master ON
OFF
ONOFF
ON
ON
Engine Masters still OFF
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
LH Engine Master ON
Preparing Engine Start
ONOFF
ON
ONON
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
LH Engine Start
ONOFF
ON
ON
ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
After LH Engine Start
ONOFF
ON
ON
ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
External power connection
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Ice Protection System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid ice protection system
Product of
CAV Aerospace Ltd(Celtic Aerospace Ventures Ltd)
commonly knows as
„TKS“
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
T
K
S
Tecalemit Ltd.(metering pumps)
Kilfrost Ltd.(deicing chemicals)
Sheepbridge Stokes(porous metals)
Ice protection system
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
„TKS“ Ice ProtectionGeneral
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
How does it work?
Protection fluid acts a „freezing pointdepressant“ (FPD)
Water droplets in the air combine withFPD fluid to form a mixture with a
freezing temperature below thetemperature of the ambient air
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Freezing point of glycol:
-12° C
Freezing point of glycol/watermixture:
-22° C to -40°C
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
„TKS“ Ice ProtectionDA 42
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Ice protection system
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
2 „independent“ systems
2 x 2 pumps
Normally powered from the LH Main Bus
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Operational modes
NORM mode 2 pumps simultaneously, but cycled
30 secs ON and 90 secs OFF
HIGH mode 1 pump continuously
MAX mode 2 pumps simultaneously ON for 2
minutes
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Operational modes
NORM mode
~ 2,5 hrs
HIGH mode
~ 1,0 hr
MAX mode
~ 0,5 hrs
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Windshield ice protection
2 pumps for redundancy
Only one pump operative at a time
Operated for 5 seconds by a pushbutton
Ice protection system
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
NORM
30s ON, 90s OFF
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
HIGH
Continuously ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
MAX
HIGH
+
2 minutes ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Windshield deice
5 seconds
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Main and Windshieldpump selector
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Ice protection system
ALTERNATE switchconnects pump #2
directly toRH main bus
System operates inHIGH mode
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe andProp
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Ice protection system
Annunciator test
DEICE LVL LO light ON
DEIC PRES LO light ONafter 120 seconds
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Ice lights
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Ice protection system
CAUTION lights
DEIC PRES LO
De-icing pressure is low
DEIC PRES HI
De-icing pressure is high
DEICE LVL LO
De-icing fluid level is low (below 10 ltrs) (max 45 mins in NORM mode)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Approved fluids
For use in the system:
AL-5 (DTD 406B)
Aeroshell Compound 07
For de-icing on ground:
AL-5 (DTD 406B)
Aeroshell Compound 07
TKS 80
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Mass and Balance
1.00De-icing fluid tank
Lever Arm(m)
Item
Ice protection system
1 ltr: 1,1 kg
30 ltr: 33,0 kg
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Preflight Check: Electric Master ON
De-ice fluid quantity CHECK
Windshield de-icing CHECK
DE ICE HIGH
Ice lights ON
Porous panels, props CHECK
Ice lights CHECK
DE ICE, Ice lights OFF
Annunciator test PERFORM
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
YES on panels
Water, soap
Isopropyl alcohol
Ethyl alcohol
Methylated spirit
De-icing fluids
AVGAS Jet fuel
NO on panels
Wax
Methyl ethylketone (MEK)
Lacquer thinner
Other thinners and
solvents
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
approved for flight into known icing conditions(„fiki“)
DA42 Ice protection system is NOT a „de-icing“ system but an „anti-ice“ system,
preventing accretion of ice
minimum operating temperature for the iceprotection system: -30°C
Ice protection system
Operational considerations
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Ice protection system
Operational considerations
what defines „icing conditions“?
visually detected ice
visible moisture and OAT +3°C orbelow
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Operational considerations
what indicates conditions thesystem my be unable to cope with?
heavy ice accumulation on windshield
ice on side areas of canopy
rapid formation and shedding of barsthicker than 6mm from porous panels
what to do?
select HIGH/MAX
leave icing conditions
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Ice protection system
Operational considerations
flight in „freezing rain“ or „freezingdrizzle“ is prohibited !
Exit icing conditions immediately
how to detect freezing rain or freezingdrizzle ?
unusually extensive ice where normally notobserved
ice on upper surface of wing aft of protectedarea
ice on spinner further back than normally
observed
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Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Autopilot
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Autopilot Limitations
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
Roll Wrng
AP ON/OFF
HDG select
NAV mode
APR mode
Backbeam
ALT Hold+/- V/S
or+/- Alt
Set Altitude
orBaro
Barodisplay/setting
ALT ARM
Pitch Wrng
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Autopilot
ALTV/S
BARO
display
ALT Alert
Pitch trimannunciator
AP engagedannunciator
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
PitchMode:
VSALT ARM
ALT
GS
Roll Mode:
ROLHDG
NAV ARMNAV
APR ARMAPR
REV ARMREV
GS ARM
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Autopilot
Vertical Speed Mode
Toggles between ALT HLD and V/S
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
Altitude Hold Mode
Toggles between ALT HLD and V/S
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Autopilot
Altitude Preselect
Select Altitude
ALT ARM
Change toV/S
Select V/S
ALT Hold andALERT
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
AP disconnectCWS
Manual Electric Trim
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Performance
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Performance
DA 42 Twin Star according CS 23: Normal, Utility & Aerobatic category
Reciprocating engine Weight < 2722 kg
VSO < 61 kt
„Light Twin“
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Density altitude
No Density Altitudegraph in the DA42 AFM
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
The „DA 42“ and „Density altitude“
Attention! Performance data which are engine-
power dependant cannot bedetermined by just using „DensityAltitude“!
Reason: the engine power output does
not correspond to density altitude butpressure and temperature have theirown, independent influence
This is a feature of the ECU controlled,turbocharged Diesel-engine
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
TOD, TOR tabular format
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
TKOF distance
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Performance diagrams
All diagrams are in duplicate:
1st for mass up to 1700 kg
2nd for mass above 1700 kg
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
TKOF distance (TOM > 1700kg)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Grass Runway
TKOF should not be attempted> 25 cm
+ 25%>10 cm
+ 15%5 - 10 cmadditional+ 10%
+ 10%- 5 cm
Wet grassTKOF rollLength of
grass
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
LD, LR tabular format
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
LD, LR tabular format
Remember: landing mass > 1700kg = „Abnormal Operating Procedure“ !
+ 138 m
710 m1785 kg
572 m1700 kg
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Grass Runway
min + 25%>10 cm
+ 15%5 - 10 cmadditional+ 10%
+ 5%- 5 cm
Wet grassLDG runLength of
grass
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Go around
Required gradient acc. CS 23.77 (a): 3,3% at Sea Level
76 KIAS
78 KIAS
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Accelerate stop distance
824 m
1401 m
+ increment for 0° flaps ?
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Obstacles ?
RWL
TOD
Obst. Dist. „d“
„h“
„d“= (RWL + Obst.Dist.) - TOD
Gradient = („h“ / „d“) * 100
ROC =Gradient x TAS
0.95
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Vöslau RWY 31
950
530
830 m1250
98 ft
„d“= (950 + 830) – 530 = 1250
Gradient = (30 / 1250) * 100 = 2,4%
ROC =2,4 x 85
0.95= 215 fpm
Acc. Performance Graph:@ 1700 kg ~ 220 fpm
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Mass and Balance
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Empty mass
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)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Center of gravity envelope
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Moment envelope
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Moment arms
1.00De-icing fluid
3.20 AUX tanks
4.54Baggage Extension
3.89Cockpit baggage
0.60Nose baggage
2.63Wing tanks
3.25Rear seats
2.30Front seats
Lever Arm (m)Item
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Typical M+B data
2,4333103,81275,5ACFT with AUX tanks
2,4393162,51296,6ACFT with ice-protectionand AUX tanks
CG armMomentEmpty mass
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
EmergencyEquipment
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Emergency Equipment
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Kinds of OperationEquipment List
(KOEL)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Kinds of Operation Equipment List KOEL
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Kinds of Operation Equipment List KOEL
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Kinds of Operation Equipment List KOEL
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Kinds of Operation Equipment List KOEL
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Additional minimum equipment for theintended operationmay be required by
national operating rulesand also depends on the
route to be flown.
Kinds of Operation Equipment List KOEL
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Diamond DA 42 Twin Star
Servicing
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Unscheduled Maintenance
Required after
Hard landings
Propeller strike
Engine fire
Lightning strike
Other malfunctions and damage
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Scheduled maintenance
Every
100 hours
200 hours
1000 hours
2000 hours
Annually
New engine: inspection after 3 – 6 hours
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© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
De-icing
Aproved de-icing fluids:
Kilfrost TKS 80
Aeroshell Compound 07
AL-5 (DTD 406B)
Procedure:
Remove snow with brush Spray de-icing fluid
Wipe dry
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Mooring
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mooring
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitne
Happy landings !