Handout DA42 Systems - JetAgejetage.sk/project/files/pages/123/da42systems-handouts.pdfDA42 Systems...

Handout

DA42 Systems

Flight Training Division

1

© Peter SchmidleitnerCompiled by Peter SchmidleitnerCompiled by Peter Schmidleitner

Diamond DA 42 Twin Star

Vers. 11.2


Dimensions and Exterior


Dimensions

13,42 m


Dimensions

8,56 m

2,20 m2,49 m

1,74 m


Dimensions

2,95 m

1,87 m


Minimum width for 180° turn

2



2,95 m

9,5 m

46 cm safety margin

Full nosewheel deflection,no brake



2,95 m

6,0 m

30cm safety margin

Full nosewheel deflection,max. brake on inner wheel

(wheel blocked)


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!


AFM page 1-2

X


Mass


Mass (Weight)

1700 kgMax LDG

+ 8 kgMax Ramp

1250 kgMin for flight

1650 kg Max Zero Fuel

1785 kgMax TKOF

1250 kgEmpty (typical)

!

3


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


Max baggage loads

45 kg18 kgBaggage extension

45 kgCockpit baggage compartment(behind rear seats)

30 kgNose compartment


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


Speeds


Characteristic speeds

126 KIASVA above 1542 kg

120 KIASVA up to 1542 kg

194 KIASVNE

155 KIASVNO



121-160Vops ice

72 KIASVMCA ice

68 KIASVMCA

64 KIASVS1

57 KIASVSO

4



72 KIASVR

82 KIASVSSE

82 KIASVYSE

79 KIASVY

79 KIASVX



156 KIASEmergency extension

194 KIASVLE (= VNE)

156 KIASVLO R (=~VNO)

194 KIASVLO E (= VNE)

111 KIASVFE (Flaps LDG)

137 KIASVFE (Flaps APP)



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


Instrument Panel


Instrument Panel

Garmin 1000


Instrument Panel

Backup Instruments

Horizon AltimeterAirspeed Compass

5


Instrument Panel

Emergency Switch Emergency Battery(non rechargeable)

Flood Lights


Instrument Panel

ELTLights Circuit breakers


Instrument Panel

Engine master switches, Engine start

Pitot heat Electric Master,Avionic Master

Alternators + ECU Control


Instrument Panel

FlapsLanding gear Autopilot


Alternate Static Valve


Alternate Static Valve

6



Garmin 1000Quick overview


DA 42 Garmin 1000

MFDAudio Panel

PFD


PFDAltitudeAttitudeAirspeed

Vertical speed

DG / HSIOAT Transponder, Time

Skid and Slip

Turn Rate


Garmin 1000 MFDEIS / Engine Indication System Multi Function Display


Default page

Display whenpushing the

SYSTEM button

Engine Indication SystemDisplay whenpushing theFUEL button


Engine Indication SystemSYSTEM FUELDefault

7


NAV and COM Tuning

LH identical RH


NAV COM

NAV and COM Tuning


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


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


Audio Panel

COM Split Switch

Intercom Isolation

„MIC“ selector; automatically selectscorresponding Audio to headphone

GMA 1347


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


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


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



Hydraulic System


Hydraulic Brakes

Pilot applies brakes


Hydraulic Brakes

Copilot applies brakes


Hydraulic Brakes

One-way valve is closed

Parking brake

„Pumping“

Pressure builds up

9


Landing Gear


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


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


Landing gear

Landing Gear Warning:Gear UP

and

one throttle below ~20%or

Flaps LDG


Landing Gear

Emergency Extension


Landing gear operation

Extension

10


Extended



Retraction



Retracted



Emergency Extension



Nosewheel steering

Nosewheel steered with rudderpedalsSteering angle:

30° without use of brakes52° with one wheel fully braked



Flight Controls

11


Flight Control Operation

Rudder:cables

Flaps:electrically by push rods

Ailerons, Elevator:push rods


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!


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


Trim Tabs

Rudder trim:bowden cable

Elevator trim:bowden cable



Power Plant


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


• Power lever selects power (LOAD in %)

• RPM automatically determined by selected power

Power Plant

Recommended Cruise Power Setting: 70%


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


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


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


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


AFM page 1-2

X

13


„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


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



JET A-1

-30 +75+70+5-5Fuel temperature

Diesel, Diesel/A-1 blend or unknown Engine start

Take-off

Analogue indication

FUEL page


Default page


Fire detection system

Overheat detector in hot area of each engineWarning above 250°CTest button:



Fuel System


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


DA 42 Fuel system

Fuel level sensor

3 chambers Fuel filler

2 ventsDrain

Temperature sensor


DA 42 Fuel System

Fuel Valve „ON“Supply

Return flow18-21 USG/hr


Supply

Return flow

DA 42 Fuel System

X-feed operation


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


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


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


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


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



Optional Auxiliary Fuel Tanks




One tank in each nacelleCapacity: 13,7 USG per sideUseable: 13,2 USG per sideFor practical purposes (placarded):

13,0 USG per side



Max unbalance5 USG

76 USG26 USG50 USG

2 x 38 USG2 x 13 USG 2 x 25 USG

TotalAUX tanksMain tanks


16


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





Transfer pump switched OFF automatically when:

Main tank is fullAUX tank is empty



CAUTION light

L/R AUX FUEL EL/R AUX tank empty and fuel transferpump ON



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



Mass and Balance

3.20AUX tanks

2.63Wing tanks

Lever Arm (m)Item


17


Fuel quantity checkVerify AUX empty

Electrical Master ONFuel transfer ONL/R AUX FUEL E CHECKED

Verify AUX fullVisual check



Fuel quantity between „FULL“ and „EMPTY“ cannot be determined



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)



Remember !

Diesel or A1/Diesel mixture notpermitted in AUX tanks !



Cooling System


Cooling System

Coolant Temp.< 80°

18


Cooling System

Coolant Temp.> 80°


Cooling System

Cabin Heat


Cabin Heating and Defrosting System

Cabin Heat from RH EngineDefrost from LH Engine



TurbochargerSystem


Exhaust gas drives turbine

Bypass for excess exhaust gas

Turbo Charger


Compressor compresses intake air

Turbo Charger

Exhaust gas drives turbine

19



Electrical System


DA 42 Electrical System



Power sources

LH Generator28V 60A

Main Battery24V 10Ah

Excitation Battery24V 1,3 Ah

RH Generator28V 60A

Emergency Battery

Load balancing



Power distribution Hot Battery Bus

Battery Bus

LH Main Bus

LH ECU Bus

Avionic Bus

RH ECU Bus

RH Main Bus



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


Hot Battery Bus

Pilot map / reading light

20


Battery Bus

LH / RH Main BusLH / RH starter heavy dutypowerLH / RH ECU BUS (via diode)


LH Main Bus

PFDAir Data ComputerAHRSCOM 1GPS/NAV 1TransponderEngineInstrumentsFuel transferDe-icing system

Pitot heatingOxygen systemGear controlGear warningMap light Flood lightTaxi light AnticollisionlightsVariable elevatorbackstop


RH Main Bus

Avionic BusMFDHorizonStarter controlFlap systemAvionic/CDU cooling fan

Stall warningAutopilot warningLanding lightNavigation lightsInstrument lights


Avionic Bus

COM 2GPS/NAV 2Audio panelAutopilot(Data Link)(WX 500)(ADF)DME(Weather Radar)



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

Electric Master



Connects L/R Generator to L/R Main Bus

(In normal operation Alternator switches arealways ON)

L/R Alternator switch

21



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



Connects Avionic Bus to RH Main BusAvionic Master Switch



Excitation BatteryMain Battery

24V 10Ah

Excitation Battery24V 1,3 Ah


Electric Master OFF

OFF

OFFOFF

ON

ON


Electric Master ON

OFF

ONOFF

ON

ON

Engine Masters still OFF


LH Engine Master ON

Preparing Engine Start

ONOFF

ON

ONON

22


LH Engine Start

ONOFF

ON

ON

ON


After LH Engine Start

ONOFF

ON

ONON


External power connection



Oxygen System


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


Oxygen system

23


Oxygen system

Oxygen cylinder

Oxygen outlets


Oxygen system


Oxygen system


Oxygen system


Oxygen system

Quick connect

Adjustable flow valve


Oxygen systemFlowmeter

Scale for maskScale for cannula

24



Ice Protection System


Fluid ice protection system

Product of

CAV Aerospace Ltd(Celtic Aerospace Ventures Ltd)

commonly knows as

„TKS“

Ice protection system


TKS

Tecalemit Ltd.(metering pumps)

Kilfrost Ltd.(deicing chemicals)

Sheepbridge Stokes(porous metals)



„TKS“ Ice ProtectionGeneral


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



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


25


Freezing point of glycol:-12° C

Freezing point of glycol/watermixture:

-22° C to -40°C



„TKS“ Ice ProtectionDA 42






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



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


26


Operational modes

NORM mode~ 2,5 hrs

HIGH mode~ 1,0 hr

MAX mode~ 0,5 hrs



Windshield ice protection

2 pumps for redundancyOnly one pump operative at a timeOperated for 5 seconds by a push button




NORM

30s ON, 90s OFF


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE


cycling



HIGH

Continuously ON


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE


27



MAX

HIGH

+

2 minutes ON


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




Windshield deice

5 seconds


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




Main and Windshieldpump selector


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE


28


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




ALTERNATE switchconnects pump #2

directly to RH main bus

System operates in HIGH mode


Fluid tank

Airframe and Prop

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




Annunciator test

DEICE LVL LO light ON

DEIC PRES LO light ON after 120 seconds



Ice lights



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


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



Mass and Balance

1.00De-icing fluid tank

Lever Arm (m)Item


1 ltr: 1,1 kg

30 ltr: 33,0 kg


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



YES on panelsWater, soapIsopropyl alcoholEthyl alcoholMethylated spiritDe-icing fluidsAVGASJet fuel

NO on panelsWaxMethyl ethylketone (MEK)Lacquer thinnerOther thinners and solvents



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


Operational considerations




what defines „icing conditions“?visually detected icevisible moisture and OAT +3°C orbelow

30




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




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




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




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




Airspeeds with ice on unprotected areas

+ 4 KIASStalling speeds

121 – 160 KIASContinuous operation in icingconditions (except TKOF, LDG and maneuvers)

72 KIASVMCA




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




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


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


Technical considerations



Autopilot


Autopilot Limitations


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


Autopilot

ALTV/S

BARO

display

ALT Alert

Pitch trimannunciator

AP engagedannunciator

32


Autopilot

PitchMode:

VSALT ARM

ALTGS

Roll Mode:

ROLHDG

NAV ARMNAV

APR ARMAPR

REV ARMREV

GS ARM


Autopilot

Vertical Speed Mode

Toggles between ALT HLD and V/S


Autopilot

Altitude Hold Mode

Toggles between ALT HLD and V/S


AutopilotAltitude Preselect

Select Altitude

ALT ARM

Change to V/S

Select V/S

ALT Hold and ALERT


Autopilot

AP disconnectCWS

Manual Electric Trim



Performance

33


Performance

DA 42 Twin Star according CS 23:Normal, Utility & Aerobatic category

Reciprocating engineWeight < 2722 kg

VSO < 61 kt

„Light Twin“


Density altitude

No Density Altitudegraph in the DA42 AFM


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


TOD, TOR tabular format


TKOF distance


Performance diagrams

All diagrams are in duplicate:1st for mass up to 1700 kg2nd for mass above 1700 kg

34


TKOF distance (TOM > 1700kg)


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


LD, LR tabular format


LD, LR tabular format

Remember: landing mass > 1700kg = „Abnormal Operating Procedure“ !

+ 138 m

710 m1785 kg

572 m1700 kg


Grass Runway

min + 25%>10 cm

+ 15%5 - 10 cmadditional+ 10%

+ 5%- 5 cm

Wet grassLDG runLength of grass


Go around

Required gradient acc. CS 23.77 (a): 3,3% at Sea Level

76 KIAS

78 KIAS

35


Accelerate stop distance

824 m

1401 m

+ increment for 0° flaps ?


Obstacles ?

RWLTOD

Obst. Dist.„d“

„h“

„d“= (RWL + Obst.Dist.) - TOD

Gradient = („h“ / „d“) * 100

ROC =Gradient x TAS

0.95


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



Mass and Balance


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)


Center of gravity envelope

36


Moment envelope


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


Typical M+B data

2,4333103,81275,5ACFT with AUX tanks

2,4393162,51296,6ACFT with ice-protectionand AUX tanks

CG armMomentEmpty mass



EmergencyEquipment


Emergency Equipment



Kinds of Operation Equipment List

(KOEL)

37


Kinds of Operation Equipment List KOEL








Additional minimum equipment for theintended operationmay be required by

national operating rulesand also depends on the

route to be flown.




Servicing

38


Unscheduled Maintenance

Required afterHard landingsPropeller strikeEngine fireLightning strikeOther malfunctions and damage


Scheduled maintenance

Every100 hours200 hours1000 hours2000 hours

Annually

New engine: inspection after 3 – 6 hours


De-icing

Aproved de-icing fluids:Kilfrost TKS 80Aeroshell Compound 07AL-5 (DTD 406B)

Procedure:Remove snow with brushSpray de-icing fluidWipe dry


Mooring


Mooring


Happy landings !

Handout DA42 Systems - JetAgejetage.sk/project/files/pages/123/da42systems-handouts.pdfDA42 Systems...

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