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Transcript of Handout DA42 Systems - JetAgejetage.sk/project/files/pages/123/da42systems-handouts.pdfDA42 Systems...
1
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Vers. 11.2
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Dimensions and Exterior
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Dimensions
13,42 m
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Minimum width for 180° turn
2
© 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 Schmidleitner
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 kgFor aircraft not yet certified for thisMTOM (MTOM: 1700 kg) refer to the AFM!
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
AFM page 1-2
X
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mass
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mass (Weight)
1700 kgMax LDG
+ 8 kgMax Ramp
1250 kgMin for flight
1650 kg Max Zero Fuel
1785 kgMax TKOF
1250 kgEmpty (typical)
!
3
© 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 LDG mass
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Max baggage loads
45 kg18 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/ltr3,2 kg/USG
JET A1: 0,8 kg/ltr3,03 kg/USG
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Characteristic speeds
121-160Vops ice
72 KIASVMCA ice
68 KIASVMCA
64 KIASVS1
57 KIASVSO
4
© 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 Schmidleitner
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 Schmidleitner
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 Schmidleitner
Instrument Panel
Backup Instruments
Horizon AltimeterAirspeed Compass
5
© 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 Schmidleitner
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 Schmidleitner
Instrument Panel
FlapsLanding gear Autopilot
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Alternate Static Valve
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Alternate Static Valve
6
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Garmin 1000Quick overview
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Garmin 1000
MFDAudio Panel
PFD
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
PFDAltitudeAttitudeAirspeed
Vertical speed
DG / HSIOAT Transponder, Time
Skid and Slip
Turn Rate
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Garmin 1000 MFDEIS / 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 Schmidleitner
Engine Indication SystemSYSTEM FUELDefault
7
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
NAV and COM Tuning
LH identical RH
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
NAV COM
NAV and COM Tuning
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
MHz tuning
Active: inside Standby: outside
Active: green Standby cursor: boxed
COM volume/squelch
COM
KHz tuning
COM flip-flop
Cursor toggleActive („green“) is selectedon AUDIO panel
Garmin 1000
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
NAV
Active: insideStandby: outside
Active: greenStandby cursor: boxedNAV 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 Schmidleitner
Audio Panel
Clearance recorder playback
Intercom volume and squelch control
• Last 2,5 minutes of communication
• Press MKR/Mute to exit
„MAN Squelch“ key
8
© 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 Schmidleitner
Audio Panel
Manual squelch control
VOL Pressing 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 Schmidleitner
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 Schmidleitner
Hydraulic Brakes
One-way valve is closed
Parking brake
„Pumping“
Pressure builds up
9
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Landing Gear
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Hydraulically operatedElectrically powered hydraulic pumpElectrically actuated hydraulic valvesoperated by gear selector switch„Squat switches“ prevent retraction on groundWarning 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 loadedDownlock released by hydraulicpressure for retractionGreen lights = gear down and lockedRed lights = gear neither down nor upGear held up hydraulicallyEmergency operation = free fall (by releasing hydraulic pressure)
Landing Gear
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Landing gear operation
Extension
10
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Extended
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Retraction
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Retracted
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Emergency Extension
Landing gear operation
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Nosewheel steering
Nosewheel steered with rudderpedalsSteering angle:
30° without use of brakes52° with one wheel fully braked
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Flight Controls
11
© 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 Schmidleitner
Variable elevator backstop
Normal elevator „up“ deflection: 15,5°Limited to „13° up“ when both throttlesabove 20% (approach power setting) and flaps LDGReason: With full elevator deflection in caseof stalling the handling qualities and stall characteristics are degraded„STICK LIMIT“ caution when variable stop notin proper position and throttles both low orboth highPreflight check of this device is mandatory!
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Variable elevator backstop
Flaps
UP or
APP
LDG
Power levers
Backstopshall be If Backstop is Caution
light
Both LOW
Split
Both HIGH
Both LOW
Split
Both HIGH
unlimiting
limiting unlimiting
limiting STICK LIMIT
STICK LIMIT
unlimiting limiting
STICK LIMIT
STICK LIMIT
inactive
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Power Plant
2 Thielert Aircraft Engines TAE125Four cylinders, liquid-cooled, 1689 ccmCommon-rail direct injectionReduction gear 1:1,69Dual digital engine controlTurbochargerMax. power 99kW (135 HP) at 2300 RPMMax cont. power 99kW (135 hp) at 2300 RPM
12
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
• Power lever selects power (LOAD in %)
• RPM automatically determined by selected power
Power Plant
Recommended Cruise Power Setting: 70%
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Propeller
3-blade wooden propellerConstant speed, featheringPitch control integrated into enginePitch control by gearbox oilGovernor valve controlled by ECU
Oil pressure up = pitch down = RPM upOil pressure down = pitch up = RPM down
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Feathering System
No „Auto-feather“Feathering by „Engine Master OFF“ ifRPM above 1300If RPM below 1300: prop pitch remainsabove high pitch lockUnfeathering by oil pressure fromaccumulator when Engine Master is ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Power plant limitations
Max overspeed: 2500 RPM, max 20 sec.Oil pressure: 1.0 – 6.5 barOil quantity (per engine): 4.5 – 6.0 litersMax. oil consumption: 0.1 liters/hrOil temperature: -32 °C – 140 °CGearbox temperature: max. 120 °CCoolant temperature: -32 °C – 105 °CMax. restart altitude: 6000 ft, 80–120 KIAS
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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/CFSHELL Helix Ultra 5W40 synth. API SL/CFAERO 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)
!
Power plant fluid specifications
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
AFM page 1-2
X
13
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
„Diesel“ limitations
Diesel or JET/Diesel mixture notpermitted in AUX tanksTemperature limits
Below -5° C no engine startBelow +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 Schmidleitner
When is no more diesel in thetanks?
each tank to be refilled at least twicewith more than 17,2 USG (65 ltrs) of Jet fuel
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 blend or unknown Engine start
Take-off
Analogue indication
FUEL page
„Diesel“ limitations
Default page
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fire detection system
Overheat detector in hot area of each engineWarning above 250°CTest button:
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Fuel System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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/hrMax unbalance: 5 USG
DA 42 Fuel System
14
© 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 Schmidleitner
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 Schmidleitner
Fuel Valves Schematic
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ONX-FON
OFF
X-F
OFF
ONX-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
ONX-FON
OFF
X-F
OFF
ONX-F
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Both engines running
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ONX-FON
OFF
X-F
OFF
ONX-F
15
© 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
ONX-FON
OFF
X-F
OFF
ONX-F
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Both engines from LH Tank
Supply
Return flow
ON
X-FEED
OFF
ON
X-FEED
OFF
ON
OFF
X-F
OFF
ONX-FON
OFF
X-F
OFF
ONX-F
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
One tank in each nacelleCapacity: 13,7 USG per sideUseable: 13,2 USG per sideFor practical purposes (placarded):
13,0 USG per side
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Max unbalance5 USG
76 USG26 USG50 USG
2 x 38 USG2 x 13 USG 2 x 25 USG
TotalAUX tanksMain tanks
Optional Auxiliary Fuel Tanks
16
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Electrical transfer pump feeds fuelfrom the AUX tank to the main tankTransfer must be initiated manuallyTransfer in 2 steps:
First half when main tank 17 USG orless (up to full main tank)Second half when main tank again 17 USG or less
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Transfer pump switched OFF automatically when:
Main tank is fullAUX tank is empty
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
CAUTION light
L/R AUX FUEL EL/R AUX tank empty and fuel transferpump ON
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
In case of a L or R XFER pump failure:(AUX pump does not operate)
Use x-feed function to keep fuel balanceAmend flight plan for reduced amountof available fuel
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mass and Balance
3.20AUX tanks
2.63Wing tanks
Lever Arm (m)Item
Optional Auxiliary Fuel Tanks
17
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fuel quantity checkVerify AUX empty
Electrical Master ONFuel transfer ONL/R AUX FUEL E CHECKED
Verify AUX fullVisual check
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fuel quantity between „FULL“ and „EMPTY“ cannot be determined
Optional Auxiliary Fuel Tanks
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Preflight fuel managementIf possible transfer all AUX fuel to main tanks
Use external power or one engine running
Electrical Master ONFuel 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 Schmidleitner
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 Schmidleitner
Cooling System
Coolant Temp.< 80°
18
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Cooling System
Coolant Temp.> 80°
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
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 Schmidleitner
Compressor compresses intake air
Turbo Charger
Exhaust gas drives turbine
19
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Electrical System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Power sources
LH Generator28V 60A
Main Battery24V 10Ah
Excitation Battery24V 1,3 Ah
RH Generator28V 60A
Emergency Battery
Load balancing
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Power distribution Hot 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 Battery24V 10Ah
LH Generator
RH Generator
Starter Starter
EPU
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Hot Battery Bus
Pilot map / reading light
20
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Battery Bus
LH / RH Main BusLH / RH starter heavy dutypowerLH / RH ECU BUS (via diode)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
LH Main Bus
PFDAir Data ComputerAHRSCOM 1GPS/NAV 1TransponderEngineInstrumentsFuel transferDe-icing system
Pitot heatingOxygen systemGear controlGear warningMap light Flood lightTaxi light AnticollisionlightsVariable elevatorbackstop
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
RH Main Bus
Avionic BusMFDHorizonStarter controlFlap systemAvionic/CDU cooling fan
Stall warningAutopilot warningLanding lightNavigation lightsInstrument lights
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Avionic Bus
COM 2GPS/NAV 2Audio panelAutopilot(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 Schmidleitner
DA 42 Electrical System
Connects L/R Generator to L/R Main Bus
(In normal operation Alternator switches arealways ON)
L/R Alternator switch
21
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Enables starter activationConnects L/R ECU (A+B) to L/R ECU BusProvides power for „GLOW“ and unfeatheringaccumulatorConnects L/R generator field to ExcitationBattery
L/R Engine Master
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Connects Avionic Bus to RH Main BusAvionic Master Switch
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
DA 42 Electrical System
Excitation BatteryMain Battery
24V 10Ah
Excitation Battery24V 1,3 Ah
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
LH Engine Master ON
Preparing Engine Start
ONOFF
ON
ONON
22
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
LH Engine Start
ONOFF
ON
ON
ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
After LH Engine Start
ONOFF
ON
ONON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
External power connection
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Oxygen System
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
Continous Flow SystemOperation up to 18.000 ftOxygen cylinder pressure MAX 1850 psi4 cannulas plus 1 maskAcc. AFM to be used above 12.500 ft
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
23
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
Oxygen cylinder
Oxygen outlets
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen system
Quick connect
Adjustable flow valve
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Oxygen systemFlowmeter
Scale for maskScale for cannula
24
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
TKS
Tecalemit Ltd.(metering pumps)
Kilfrost Ltd.(deicing chemicals)
Sheepbridge Stokes(porous metals)
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
„TKS“ Ice ProtectionGeneral
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
How does it work?Protection fluid acts a „freezing point depressant“ (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
25
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
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 Schmidleitner
Operational modes
NORM mode2 pumps simultaneously, but cycled30 secs ON and 90 secs OFF
HIGH mode1 pump continuously
MAX mode2 pumps simultaneously ON for 2 minutes
Ice protection system
26
© 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 Schmidleitner
Windshield ice protection
2 pumps for redundancyOnly one pump operative at a timeOperated for 5 seconds by a push button
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
NORM
30s ON, 90s OFF
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
cycling
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
HIGH
Continuously ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
27
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
MAX
HIGH
+
2 minutes ON
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
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
Windshield deice
5 seconds
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
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 Schmidleitner
Fluid tank
Airframe and Prop
Windshield
LH Main BUS
RH Main BUS
MAX
HIGH
NORM
PUMP 1 PUMP 2
ALTERNATE
Ice protection system
28
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
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
ALTERNATE switchconnects pump #2
directly to RH main bus
System operates in HIGH mode
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Fluid tank
Airframe and Prop
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
Annunciator test
DEICE LVL LO light ON
DEIC PRES LO light ON after 120 seconds
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Ice lights
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
CAUTION lightsDEIC PRES LO
De-icing pressure is low
DEIC PRES HIDe-icing pressure is high
DEICE LVL LODe-icing fluid level is low (below 10 ltrs)
(max 45 mins in NORM mode)
29
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Approved fluidsFor use in the system:
AL-5 (DTD 406B)Aeroshell Compound 07
For de-icing on ground:AL-5 (DTD 406B)Aeroshell Compound 07TKS 80
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Preflight Check:Electric Master ONDe-ice fluid quantity CHECKWindshield de-icing CHECKDE ICE HIGHIce lights ONPorous panels, props CHECKIce lights CHECKDE ICE, Ice lights OFFAnnunciator test PERFORM
Ice protection system
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
YES on panelsWater, soapIsopropyl alcoholEthyl alcoholMethylated spiritDe-icing fluidsAVGASJet fuel
NO on panelsWaxMethyl ethylketone (MEK)Lacquer thinnerOther 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“ systembut 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 Schmidleitner
Ice protection system
Operational considerations
what defines „icing conditions“?visually detected icevisible moisture and OAT +3°C orbelow
30
© 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 windshieldice on side areas of canopyrapid formation and shedding of barsthicker than 6mm from porous panels
what to do?select HIGH/MAXleave icing conditions
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 notobservedice on upper surface of wing aft of protectedareaice on spinner further back than normallyobserved
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Operational considerations
how to detect possible freezing rain orfreezing drizzle conditions?
visible rain in OAT below +5°Cdroplets that splash on impact in OAT below+5°Cperformance loss larger than normallyexperienced in icing conditions
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Operational considerations
Autopilotmay be used in icing conditions, but:
disconnect every 10 – 15 minutes to detect out of trim conditions
PROHIBITED withice aft of protected areaunusual lateral trimautopilot trim warning
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Operational considerations
Airspeeds with ice on unprotected areas
+ 4 KIASStalling speeds
121 – 160 KIASContinuous operation in icingconditions (except TKOF, LDG and maneuvers)
72 KIASVMCA
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Operational considerations
Performance with ice on unprotected areas
above 2000ft PA positive ROC may not be achieved
reduced by
15%Cruise performance
up to 150 fpm1-engine ROC
up to 150 fpmRate of climb
31
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Ice protection system
Operational considerations
Approach, landing in icing conditions:Gear down, flaps APPVa min 82 KIASLDG distance: x 1,4 !
Go aroundwith Flaps APP, gear down, 82 KIAS:
5,83%, 529 fpm climb
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Priming of the system:main pumps:
primed by windshield pumpsporous panels:
not to be primed in icing conditions !!shall be primed in climb or descentup to 4°CMAX mode in intervals of 5 minutes untilfluid dissipates from all panelsabove 4°C priming by special maintenanceonly
Ice protection system
Technical considerations
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Autopilot
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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/Sor
+/- Alt
SetAltitude
orBaro
Barodisplay/setting
ALT ARM
Pitch Wrng
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
ALTV/S
BARO
display
ALT Alert
Pitch trimannunciator
AP engagedannunciator
32
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
PitchMode:
VSALT ARM
ALTGS
Roll Mode:
ROLHDG
NAV ARMNAV
APR ARMAPR
REV ARMREV
GS ARM
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
Vertical Speed Mode
Toggles between ALT HLD and V/S
© 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 Schmidleitner
AutopilotAltitude Preselect
Select Altitude
ALT ARM
Change to V/S
Select V/S
ALT Hold and ALERT
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Autopilot
AP disconnectCWS
Manual Electric Trim
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Performance
33
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Performance
DA 42 Twin Star according CS 23:Normal, Utility & Aerobatic category
Reciprocating engineWeight < 2722 kg
VSO < 61 kt
„Light Twin“
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Density altitude
No Density Altitudegraph in the DA42 AFM
© 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 doesnot correspond to density altitude butpressure and temperature have theirown, independent influenceThis is a feature of the ECU controlled, turbocharged Diesel-engine
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
TOD, TOR tabular format
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
TKOF distance
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Performance diagrams
All diagrams are in duplicate:1st for mass up to 1700 kg2nd for mass above 1700 kg
34
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
TKOF distance (TOM > 1700kg)
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
LD, LR tabular format
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Go around
Required gradient acc. CS 23.77 (a): 3,3% at Sea Level
76 KIAS
78 KIAS
35
© 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 Schmidleitner
Obstacles ?
RWLTOD
Obst. Dist.„d“
„h“
„d“= (RWL + Obst.Dist.) - TOD
Gradient = („h“ / „d“) * 100
ROC =Gradient x TAS
0.95
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Vöslau RWY 31
950530
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 Schmidleitner
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 InventoryBrake fluidHydraulic fluidEngine 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 Schmidleitner
Center of gravity envelope
36
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Moment envelope
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Moment arms
1.00De-icing fluid
3.20AUX tanks
4.54Baggage Extension
3.89Cockpit baggage
0.60Nose baggage
2.63Wing tanks
3.25Rear seats
2.30Front seats
Lever Arm (m)Item
© 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 Schmidleitner
Diamond DA 42 Twin Star
EmergencyEquipment
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Emergency Equipment
Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Diamond DA 42 Twin Star
Kinds of Operation Equipment List
(KOEL)
37
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Kinds of Operation Equipment List KOEL
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Kinds of Operation Equipment List KOEL
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Kinds of Operation Equipment List KOEL
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
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 Schmidleitner
Diamond DA 42 Twin Star
Servicing
38
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Unscheduled Maintenance
Required afterHard landingsPropeller strikeEngine fireLightning strikeOther malfunctions and damage
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Scheduled maintenance
Every100 hours200 hours1000 hours2000 hours
Annually
New engine: inspection after 3 – 6 hours
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
De-icing
Aproved de-icing fluids:Kilfrost TKS 80Aeroshell Compound 07AL-5 (DTD 406B)
Procedure:Remove snow with brushSpray de-icing fluidWipe dry
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mooring
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Mooring
© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner
Happy landings !