diamond da40-tdi g1000 diamond da 40-tdi g1000 dimensions

1

Diamond DA 40-TDIG1000

DA40-TDI-G1000 Version 1.1

Diamond DA40-TDI G1000

Compiled by Peter Schmidleitner

Dimensions

© Peter SchmidleitnerCompiled by Peter Schmidleitner

Dimensions

11,94 m


Dimensions

8,01 m

1,97 m

1,68 m

2,97 m



Exterior


ELT and VHF COM 1 Antenna

ELT antenna in fuselage structure

VHF COM 1

2


VHF COM 2 antenna


VHF NAV + GP Antennas

in the horizontal stabilizer


Marker Antenna

Fuselage belly


GPS Antennas

Cabin roof


DME, TXPDR Antenna

Fuselage belly


ADF antenna

Fuselage belly

3


Pitot/Static Probe

Left wing


Pitot/Static Probe

PitotStatic


Lift Detector (Stall Warning)

Left wing


Engine Oil


Engine Oil


Air Inlets

Intercooler Coolant heatexchanger

Oil Cooler

4


RH frontVentilation

Engine air intake

Cabin air heater

Air Inlets


LH front Ventilation

Air Inlets



Operating Limitation


Temperature Limitation

The airplane may only be operated whenits temperature prior to operation is notless than -20°C and not higher than54°C.With the airplane cold soaked and itstemperature below -20°C the use of an external pre-heater for the engine and pilot compartment prior to operation ismandatory.



Mass


Mass (Weight)

45 kg(max 18 kg in

aftcompartment)

Max Baggage with„BaggageExtension“

30 kgMax Baggage

1150 kg Max LDG

1150 kgMax TKOF

830 kgEmpty (typical)

5


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

108 KIASVA 980-1150 kg

94 KIASVA 780-980 kg

178 KIASVNE

129 KIASVNO



52 KIASVS1

49 KIASVSO

91 KIASVFE (Flaps LDG)

108 KIASVFE (Flaps T/O)



71 KIAS

73 KIAS

73 KIAS

66 KIAS

1150 kg

63 KIAS

68 KIAS

68 KIAS

60 KIAS

1000 kg850 kg

58 KIASVLDG Flaps LDG

60 KIASVLDG Flaps UP

60 KIASV climb

54 KIASVX = VY


Stalling Speeds

980 kg

1150 kg

VS1VSO

42 47

49 52

6


Stalling Speeds

VS1VSO

57 58

62 66

980 kg

1150 kg


Stalling Speeds

VS1VSO

71 73

76 79

980 kg

1150 kg



Flight Controls


Flight Control Operation

Rudder:cables

Ailerons, Elevator:push rods


Flight Control Operation

Flaps:electrically by push rods,

left and right mechanicallyinterconnected


Intentionally blank

7



Instrument Panel


Instrument Panel

Garmin 1000


Instrument Panel

Backup Instruments

Horizon AltimeterAirspeed Compass


Instrument Panel

Emergency Battery(non rechargeable)

Flood Lights

Emergency Switch


Instrument Panel

ELTLights


Instrument Panel

Circuit breakers

8


Instrument Panel

Essential BusElectric Master

Starter


Instrument Panel

Engine control


Instrument Panel

AvionicMaster

Fuel x-fer pump,Pitot heat


Instrument Panel

FlapsAutopilot


Alternate Static Valve


Engine Indication SystemDefault SYSTEM FUEL

1



Hydraulic System


Hydraulic brakes

Pilot applies brake


Hydraulic brakes

One-way valve is closed

Parking brake

„Pumping“

Pressure builds up


Parking brake



Power Plant


Thielert Aircraft Engine TAE125-02-99Previously: TAE125-01

Four cylinders, liquid-cooled1991 ccm (TAE125-01: 1689 ccm)

Common-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

Diamond DA40 TDI Engine

10



Thielert Aircraft Engine TAE125Four cylinders, liquid-cooled, 1689 ccmCommon-rail direct injectionReduction gear 1:1,69Digital engine controlTurbochargerMax. power 99kW (135 PS) at 2300 RPMMax cont. power 99kW (135 PS) at 2300 RPM


Digital Engine Control

ECUEngine Control Unit

this is a

FADECFull Authority Digital EngineControl


ECU – Engine Control Unit


E.O.T. – Engine Order Telgraph („Chadburn“)


• Power lever selects power (LOAD in %)

• RPM automatically determined by selected power




Engine air filter

Alternate air valve

Heat Exchanger for Cabin Heat System

1


Intercooler




Coolant Heat Exchanger

Reduction Gear

Coolant Reservoir

Generator


Power plant – Gear oil





Is this the little bubble ?


Power plant limitations

Italic figures are for the „old“ 125-01 engine

Max RPM: 2300Oil pressure: 1.0 – 6.5 barOil quantity (per engine): 4.5 – 6.0 litersMax. oil consumption: 0.1 liters/hrOil temperature: -30 (-32) °C – 140 °CGearbox temperature: max. 120 °CCoolant temperature: -30 (-32) °C – 105 °CMax. restart altitude: 8000 ft (6500 ft),73–120 KIAS

12


Fuel: JET A-1 or JET A (ASTM D 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: DAI-G30-MIXspecial water (TAE-125-OM-02-01) + cooler protection 1:1 (BASF Glysantin Alu Protect Plus/G30)(freezing point –36 °C)

!

Power plant fluid specifications


„Diesel“ limitations

Temperature limitsBelow -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 the tanks?each tank to be refilled at least twice withmore than

10,6 USG (40 ltrs) (normal tanks)17,2 USG (65 ltrs) (long range tanks)

of Jet fuelotherwise

tank must be drained



JET fuel

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

Diesel, Diesel/JET blend or unknown Engine start

Take-off

Analogue indication

FUEL page


Default page



Cooling System


DA 40 TDI Cooling System

13



Coolant Temp.< 80°



Coolant Temp.> 80°



Cabin Heat


DA 40 TDI Cabin Heat


Cockpit

DA 40 TDI Ventilation

CabinCabin


DA 40 TDI Ventilation

Left wing

Rear cabin ventilation air inlet

14



TurbochargerSystem


DA 40 TDI Turbo Charger

Exhaust gas drives turbineBypass for excess exhaust gas


DA 40 TDI Turbo Charger

Turbine drives compressorCompressor compresses intake air



Fuel System


2 x 14 USG usable= 28 USG= 85 kgAt 70% power: ~ 5 USG/hr

DA 40 TDI Fuel System


Long Range Tanks:2 x 19,5 USG usable= 39 USG= 120 kgMax indicated fuel per tank: 15 USGMax. unbalance: 9 USG


15







18-21 USG/hr

~60 USG/hrFuel cooler


Fuel cooler

Right wing

Air inletAir outlet



U/S



18-21 USG/hr

U/SFuel cooler

16


DA 40 Fuel system

„Alternate means forfuel quantity indication“

Position:at the bore in the stall strip


Fuel vents


Fuel tank drain

FWD


Fuel gascolator drain



Electrical System


DA40 TDI G1000 Electrical System

17



Power sources

Generator12-14V 90A

Main Battery12V 45Ah

ECU Backup Battery12V 12Ah

Excitation Battery12V 1,3 Ah



Power distribution

Hot Battery Bus

Battery Bus Main Bus

Essential Bus

ECU Bus

Avionic Bus


Electric Master, Essential Bus


Engine Master


DA40 TDI G1000 Electrical SystemOFF

ON

OFF

Before Engine Start



ON

OFF

Preparing Engine StartON

18



ON

OFF

ONEngine Start

START



ON

OFF

ON

ON

After Engine Start


External Power Receptable


Emergency Switch


The mysteriousEssential Bus

Switch

DA40-TDI G1000


Switch location

19


When is it used ?

When the generator failsto disconnect unnecessaryelectrical consumersto supply battery power to essential electrical consumers


Essential Electrial Power

Essential BusPFDHorizon *)AHRSADCFlapsLanding lightPitot HeatingLanding LightFlood Light *)

*) Emergency Battery

COM 1GPS / NAV Receiver 1TransponderEngine instruments

Hot Battery Bus(Essential Bus)Pilot‘s map/reading lightAuxiliary jack


Main unserviceable systemsFuel x-fer pumpMFDAcionic / CDU fanPosition light, Strobe lights, Taxi lightInstrument lights, Map lightStarter(Avionics Bus)

COM2, NAV/GPS2, ADF, DME, WX500, Audio, Autopilot

Essential Electrial Power


What happens ...

... if it is switched ON duringnormal operation?Will the battery be discharged?

NO !


Normal Situation

Hot

Bat

tery

Bus

Batt

ery

Bus

Esse

ntia

l Bus

GEN

BATT

Avio

niic

Bus

ECU

Bus

Mai

n Bu

s

Battery is charged

DA40-TDI G1000, Ess. Bus switch


GEN u/s, Ess. PWR OFF

Hot

Bat

tery

Bus

Batt

ery

Bus

Esse

ntia

l Bus

GEN

BATT

Avio

niic

Bus

ECU

Bus

Mai

n Bu

s

Battery will bedischarged


20


GEN u/s, Ess. PWR ONH

ot B

atte

ryBu

s

Batt

ery

Bus

Esse

ntia

l Bus

GEN

BATT

Avio

niic

Bus

ECU

Bus

Mai

n Bu

s

Battery will bedischargedat slow rate



GEN OK, Ess. PWR ON

Hot

Bat

tery

Bus

Batt

ery

Bus

Esse

ntia

l Bus

GEN

BATT

Avio

niic

Bus

ECU

Bus

Mai

n Bu

s

Battery is still charged



Hot

Bat

tery

Bus

Batt

ery

Bus

Esse

ntia

l Bus

GEN

BATT

Avio

niic

Bus

ECU

Bus

Mai

n Bu

s


Essential Bus ON by mistake

COM2, NAV/GPS2,Audio,ADF, DME, AutopilotWX 500

Fuel x-fer pumpMFDAvion./CDU fanFAN / OAT indicationPosition lightStrobe lightsTaxi light, Map light Instrument lightsStarter


A very special engine start problem:Start witch ONNothing happens!

Why?Essential Bus switch ON by mistake!




Generator + Battery FailON

ECU backup battery


Intentionally blank

21



AutopilotKAP140


KAP 140 has 2 functions:if not engaged: Altitude warningif engaged („ON“): Autopilot

Autopilot


Autopilot

HeadingYES

Stearing signalYES


Autopilot

AltitudeNO

Baro settingNO


Autopilot limitations


Autopilot

AP disconnectCWS

Manual Electric Trim

22


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


Autopilot

PitchMode:

VSALT ARM

ALTGS

Roll Mode:

ROLHDG

NAV ARMNAV

APR ARMAPR

REV ARMREV

GS ARM


ALT

AutopilotAltitude Preselect

Select Altitude

Check ALT ARM

Adjust V/S

Check ALT ALERT

Check ALT Hold


Autopilot – Altitudepreselect

Selecting altitude when autopilot is ON:Altitude ARMED automatically

Switching autopilot ON with a preselected altitude (e.g. when altitudewas preselected before TKOF):

Altitude must be ARMed manually!


AutopilotAltitude Hold Mode

Toggles between ALT HLD and V/S

Vertical Speed Mode

Toggles between ALT HLD and V/S

23



Performance


The „DA 40 TDI“ 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


Cruise Power Setting


Cruising Speed

e.g. 6000 ft, ISA, 70 %

121 kts


TOD

SL, ISA, 1150 kg: 640 m


TKOF Distance

24


TKOF Run


Grass Runway

min + 25%>10 cm

+ 15%5 - 10 cmmay be

significantlylonger

+ 10%- 5 cm

Wet grassTKOF rollLength of grass


Take off climb66 KIAS

Attention!Increasingdownward


Cruise Climb

73 KIAS


ROC to gradient conversion


LD, LR tabular format

Flaps LDGVREF 71 KIAS

Flaps UPVREF 73 KIAS

25


Landing Distance


Landing Run


Grass Runway

min + 25%>10 cm

+ 15%5 - 10 cmmay be

significantlylonger

+ 5%- 5 cm

Wet grassLDG runLength of grass


Go Around


Obstacles ?

RWLTOD

Obst. Dist.„d“

„h“

„d“= (RWL + Obst.Dist.) - TOD

Gradient = („h“ / „d“) * 100


Vöslau RWY 31

950650

830 m1130

98 ft

„d“= (950 + 830) – 650 = 1130

Gradient = (30 / 1130) * 100 = 2,65 %

Acc. Performance Graph:~ 9 %

26



Mass and Balance


Empty Mass

Empty Mass includes:Equipment as per Equipment InventoryBrake fluidCoolant fluidGear oilEngine oilUnusable fuel (2 x 1,0 USG)


Center of Gravity Envelope

2.46 2.59


Moment Envelope


Moment Arms

4.54Aft baggage

3.89Fwd. baggage

2.63Wing tanks

3.25Rear seats

2.30Front seats

LeverArm (m)

Item


Typical M+B data

2,4602032,3826,2„N-VFR“-version

2,4692057,7833,5„IFR“-version (ADF, WX500)

CG armMomentEmpty mass

27


M&B Calculation

2.63

3.89

3.25

2.30

2.47

Leverarm

Total TKOF Mass

Fuel

Zero Fuel Mass

Fwd. Baggage

Rear seats

Front seats

2050.1830 Empty mass

Moment (kgm)

Mass (kg)

80

170

10

1090

60

1150

391.0

260.0

38.9

2740.0

157.8

2897.8

170 x 2.30 = 391.0

80 x 3.25 = 260.0

~20 USG


M&B Calculation

2.63

3.89

3.25

2.30

2.47

Leverarm

Total TKOF Mass

Fuel

Zero Fuel Mass

Fwd. Baggage

Rear seats

Front seats


Moment (kgm)

Mass (kg)

80

170

10

1090

60

1150

391.0

260.0

38.9

2740.0

157.8

2897.8

2740.0 : 1090 = 2.514

2897.8 : 1150 = 2.52

2.514

2.52


ZFM1090 kg , 2.514 m

TOM1150 kg , 2.52 m

Center of Gravity Envelope


M&B Calculation

2.63

3.89

3.25

2.30

2.47

Leverarm

Total TKOF Mass

Fuel

Zero Fuel Mass

Fwd. Baggage

Rear seats

Front seats


Moment (kgm)

Mass (kg)

80

170

10

1090

60

1150

391.0

260.0

38.9

2740.0

157.8

2897.8


Moment Envelope

ZFM1090 kg , 2740.0

TOM1150 kg , 2897.8


Intentionally blank

28



EmergencyEquipment


Emergency equipment


Emergency Exit

FWD

1

2


Emergency Exit

FWD

1

2



Kinds of Operation Equipment List

(KOEL)


Kinds of Operation Equipment List KOEL

29






Kinds of Operation Equipment ListKOEL


Additional minimum equipment for theintended operationmay be required by

national operating rulesand also depends on the

route to be flown.

Kinds of Operation Equipment ListKOEL



Servicing


Scheduled maintenance

Every100 hours200 hours1000 hours2000 hours

Annually

30


Refuelling


De-icing

Approved de-icing fluids:Kilfrost TKS 80Aeroshell Compound 07

Procedure:Remove snow with brushSpray de-icing fluidWipe dry


Control surfaces gust lock


Mooring


Mooring


Tow bar

1



Flight Procedures


TKOF Profile

Rotate at 59 kt


LDG Profile


Checklists

The checklists are not part of the AFM, and they are not„officially Diamond-endorsed“.

They are a recommendation for „Operator Checklists“published by „Diamond Aircraft Flight Training Division“.


Thank you for your attention!

diamond da40-tdi g1000 diamond da 40-tdi g1000 dimensions

Documents