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


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





2,95 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 kg

For aircraft not yet certified for thisMTOM (MTOM: 1700 kg) refer tothe AFM!


AFM page 1-2

X


Mass


Mass (Weight)

1700 kgMax LDG

+ 8 kgMax Ramp

1250 kgMin for flight

1650 kgMax Zero Fuel

1785 kgMax TKOF

1250 kgEmpty (typical)

!




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


Max baggage loads

45 kg

18 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/ltr

3,2 kg/USG

JET A1:

0,8 kg/ltr

3,03 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





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 Schmidleitne

Diamond DA 42 Twin Star

Instrument Panel


Instrument Panel

Garmin 1000


Instrument Panel

Backup Instruments

Horizon AltimeterAirspeed Compass




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



Compiled by Peter SchmidleitnerCompiled by Peter Schmidleitner


Garmin 1000Quick overview


DA 42 Garmin 1000

PFD MFD

Audio Panel


Garmin 1000 PFD

Altitude Attitude Airspeed

Vertical speed

DG / HSIOAT Transponder, Time

Skid and Slip

Turn Rate


Garmin 1000 MFD

EIS / Engine Indication System Multi Function Display


Default page

Display whenpushing the

SYSTEM button

Engine Indication SystemDisplay whenpushing theFUEL button


Engine Indication System

SYSTEM FUELDefault




Garmin 1000

NAV and COM Switching

LH identical RH


NAV COM

Garmin 1000


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


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


Audio Panel

COM Split Switch

Intercom Isolation

„MIC“ selector; automatically selectscorresponding Audio to headphone

GMA 1347


Audio Panel

Clearance recorder playback

Intercom volume andsquelch control

• Last 2,5 minutes of communication

• Press MKR/Mute to exit

„MAN Squelch “ key




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

VOLPressing 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




Landing Gear


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


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


Landing gear

Landing Gear Warning:

Gear UP

and

one throttle below ~20% or

Flaps LDG


Landing Gear

Emergency Extension


Landing gear operation

Extension




Extended



Retraction



Retracted



Emergency Extension



Nosewheel steering

Nosewheel steered with rudderpedals

Steering angle:

30° without use of brakes

52° with one wheel fully braked



Flight Controls




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) 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!


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


Trim Tabs

Rudder trim:bowden cable

Elevator trim:bowden cable



Power Plant


Power Plant

2 Thielert Aircraft Engines TAE125

Four cylinders, liquid-cooled, 1689 ccm

Common-rail direct injection

Reduction gear 1:1,69

Dual digital engine control

Turbocharger

Max. power 99kW (135 HP) at 2300 RPM

Max cont. power 99kW (135 hp) at 2300RPM




• Throttle selects power (LOAD in %)

• RPM automatically determined by selected power

Power Plant

Recommended Cruise

Power Setting: 70%


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


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


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


!

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)


AFM page 1-2

X




„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


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



JET A-1

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

Diesel, Diesel/A-1 blendor unknown Engine start

Take-off

Analogue indication

FUEL page


Default page


Fire detection system

Overheat detector in hot area of each engine

Warning above 250°C

Test 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/hr

Max unbalance: 5 USG

DA 42 Fuel System




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

ONX-FEED

OFF

ON

X-FEED

OFF

ON

OFF

X-F

OFF

ON X-FON

OFF

X-F

OFF

ON X-F


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


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




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


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



Optional Auxiliary Fuel Tanks




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



Max unbalance5 USG

76 USG26 USG50 USG

2 x 38 USG2 x 13 USG2 x 25 USG

TotalAUX tanksMain tanks





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





Transfer pump switched OFFautomatically when:

Main tank is full

AUX tank is empty



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



L/R XFER FAIL

Use x-feed function to keep fuelbalance

Amend flight plan for reduced amountof available fuel



Mass and Balance

3.20 AUX tanks

2.63Wing tanks

Lever Arm (m)Item





Fuel quantity check

Verify AUX empty

Electrical Master ON

Fuel transfer ON

L/R AUX FUEL E CHECKED

Verify AUX full Visual check



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



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)



Remember !

Diesel or A1/Diesel mixture notpermitted in AUX tanks !



Cooling System


Cooling System

Coolant Temp.

< 80°




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





Electrical System


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



Power distributionHot 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 Battery

24V 10Ah

LH

Generator

RH

Generator

Starter Starter

EPU


Hot Battery Bus

Pilot map / reading light




Battery Bus

LH / RH Main Bus

LH / RH starter heavy dutypower

LH / RH ECU BUS (via diode)


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


RH Main Bus

Avionic Bus

MFD

Horizon

Starter control

Flap system

Avionic/CDU cooling fan

Stall warning

Autopilotwarning

Landing light

Navigation lights

Instrumentlights


Avionic Bus

COM 2

GPS/NAV 2

Audio panel

Autopilot

(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 MainBus

(In normal operation Alternator switches arealways ON)

L/R Alternator switch





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



Connects Avionic Bus to RH Main Bus

Avionic Master Switch



Excitation BatteryMain Battery

24V 10Ah

Excitation Battery

24V 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




LH Engine Start

ONOFF

ON

ON

ON


After LH Engine Start

ONOFF

ON

ON

ON


External power connection



Ice Protection System


Fluid ice protection system

Product of

CAV Aerospace Ltd(Celtic Aerospace Ventures Ltd)

commonly knows as

„TKS“

Ice protection system


T

K

S

Tecalemit Ltd.(metering pumps)

Kilfrost Ltd.(deicing chemicals)

Sheepbridge Stokes(porous metals)





„TKS“ Ice ProtectionGeneral


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



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



Freezing point of glycol:

-12° C

Freezing point of glycol/watermixture:

-22° C to -40°C



„TKS“ Ice ProtectionDA 42








Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE



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



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



Operational modes

NORM mode

~ 2,5 hrs

HIGH mode

~ 1,0 hr

MAX mode

~ 0,5 hrs



Windshield ice protection

2 pumps for redundancy

Only one pump operative at a time

Operated for 5 seconds by a pushbutton






NORM

30s ON, 90s OFF


Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




HIGH

Continuously ON


Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




MAX

HIGH

+

2 minutes ON


Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE






Windshield deice

5 seconds


Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




Main and Windshieldpump selector


Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE



Fluid tank

Airframe andProp

Windshield

LH Main BUS

RH Main BUS

MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE




ALTERNATE switchconnects pump #2

directly toRH main bus

System operates inHIGH mode




Fluid tank

Airframe andProp

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 ONafter 120 seconds



Ice lights



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)


Approved fluids

For use in the system:

AL-5 (DTD 406B)

Aeroshell Compound 07

For de-icing on ground:

AL-5 (DTD 406B)


TKS 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 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



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



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


Operational considerations




what defines „icing conditions“?

visually detected ice

visible moisture and OAT +3°C orbelow




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




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





Autopilot


Autopilot Limitations


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


Autopilot

ALTV/S

BARO

display

ALT Alert

Pitch trimannunciator

AP engagedannunciator


Autopilot

PitchMode:

VSALT ARM

ALT

GS

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


Autopilot

Altitude Preselect

Select Altitude

ALT ARM

Change toV/S

Select V/S

ALT Hold andALERT


Autopilot

AP disconnectCWS

Manual Electric Trim



Performance


Performance

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

Reciprocating engine Weight < 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 does

not correspond to density altitude butpressure and temperature have theirown, independent influence

This 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 kg

2nd for mass above 1700 kg


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


Accelerate stop distance

824 m

1401 m

+ increment for 0° flaps ?


Obstacles ?

RWL

TOD

Obst. Dist. „d“

„h“

„d“= (RWL + Obst.Dist.) - TOD

Gradient = („h“ / „d“) * 100

ROC =Gradient x TAS

0.95




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



Mass and Balance


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)


Center of gravity envelope


Moment envelope


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




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 OperationEquipment List

(KOEL)


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


Unscheduled Maintenance

Required after

Hard landings

Propeller strike

Engine fire

Lightning strike

Other malfunctions and damage


Scheduled maintenance

Every

100 hours

200 hours

1000 hours

2000 hours

Annually

New engine: inspection after 3 – 6 hours




De-icing

Aproved de-icing fluids:

Kilfrost TKS 80


AL-5 (DTD 406B)

Procedure:

Remove snow with brush Spray de-icing fluid

Wipe dry


Mooring


Mooring


Happy landings !

Diamond DA 42 Systems Handouts 10 1

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Transcript of Diamond DA 42 Systems Handouts 10 1