Diamond DA42-VI

Handout
DA42-VI
Systems
INTENTIONALLY BLANK
 Diamond DA42-VI

Vers. 5.1

1
Compiled by Peter Schmidleitner

Dimensions

13,42 m

Span: 13,55 m with ACL (strobe lights)

2
Compiled by Peter Schmidleitner

1
 Dimensions

2,20 m
2,49 m

8,56 m
1,74 m

3
Compiled by Peter Schmidleitner

Dimensions

1,90 m

2,95 m

4
Compiled by Peter Schmidleitner

2
Minimum width for 180° turn

Full nosewheel deflection,

no brake

2,95 m

9,5 m

46 cm safety margin

5
Compiled by Peter Schmidleitner

Minimum width for 180° turn

Full nosewheel deflection,

max. brake on inner wheel
(wheel blocked)

2,95 m

6,0 m

30cm safety margin

6
Compiled by Peter Schmidleitner

3
Nose bagge compartment

7
Compiled by Peter Schmidleitner

ELT and VHF COM 1 antenna

8
Compiled by Peter Schmidleitner

4
 VHF COM 2 antenna

9
Compiled by Peter Schmidleitner

VHF NAV + GP antennas

in the stabilizer

10
Compiled by Peter Schmidleitner

5
Stormscope antenna

11
Compiled by Peter Schmidleitner

GPS antennas

Cabin roof

12
Compiled by Peter Schmidleitner

6
 Marker antenna

Fuselage belly

13
Compiled by Peter Schmidleitner

DME, TXPDR antennas

Fuselage belly

14
Compiled by Peter Schmidleitner

7
Landing and Taxi light

Fuselage belly

15
Compiled by Peter Schmidleitner

ADF antenna

Fuselage belly

16
Compiled by Peter Schmidleitner

8
TAS antennas

Fuselage belly

17
Compiled by Peter Schmidleitner

OAT Sensor

Battery vent, de-ice

fluid vent and overflow

OAT sensor

18
Compiled by Peter Schmidleitner

9
 Mass (Weight)

Empty (typical) 1450 kg

Max TKOF 1999 kg
Max Ramp + 8 kg

Max Zero Fuel 1835 kg

Max LDG 1999 kg
Min for flight 1450 kg

Max TKOF 2001 kg is an additional option

19
Compiled by Peter Schmidleitner

Max. Baggage Load

Nose compartment 30 kg

For Airconditioning or rear De-icing tank

„Short“
Cabin baggage Standard Baggage
Extension
Standard
compartment
45 kg 30 kg
Baggage
Extension
18 kg 15 kg

Total 45 kg 45 kg

20
Compiled by Peter Schmidleitner

10
Standard Baggage Compartment

CABIN

BAGGAGE
TRAY

21
Compiled by Peter Schmidleitner

„Short“ Baggage Extension

BAGGAGE
TRAY

22
Compiled by Peter Schmidleitner

11
 Mass

Attention!
JET fuel and Diesel are heavier than AVGAS!

Typical fuel weight:

JET A1: Diesel:

0,8 kg/ltr 0,84 kg/ltr
3,03 kg/USG 3,2 kg/USG

23
Compiled by Peter Schmidleitner

Intentionally blank

Compiled by Peter Schmidleitner

12
 Speeds

25
Compiled by Peter Schmidleitner

Characteristic speeds

VNO 151 KIAS

VNE 188 KIAS
112 KIAS
1700 kg

VO (VA) 119 KIAS

1800 kg

122 KIAS

26
Compiled by Peter Schmidleitner

13
 Characteristic speeds

1900 / 1999 kg
VSO 62 / 64 KIAS
VS1 68 / 72 KIAS
For short field take-off

Flaps UP Flaps APP

VMC 71 KIAS 68 KIAS

Vops ice 118-156 KIAS

27
Compiled by Peter Schmidleitner

Characteristic speeds

up to 1900 / > 1900 kg

For short field take-off
Flaps UP Flaps APP

VR 76/76 KIAS 71/74 KIAS

VX --- 77/77 KIAS
VY 90/92 KIAS 85/85 KIAS
VYSE 85/85 KIAS
Vyse „ice“ 88/90 KIAS

VCRZ CLB 90/92 KIAS

28
Compiled by Peter Schmidleitner

14
Characteristic speeds

VFE (Flaps APP) 133 KIAS

VFE (Flaps LDG) 113 KIAS

VLO E (= VNE) 188 KIAS

Emergency extension 152 KIAS

VLO R (=~VNO) 152 KIAS

VLE (= VNE) 188 KIAS

29
Compiled by Peter Schmidleitner

Characteristic speeds
Approach Reference Speeds

up to 1900 / > 1900 kg

VREF FLAPS UP 86/92 KIAS

VREF FLAPS APP 84/88 KIAS

VREF FLAPS LDG 84/86 KIAS

VGA FLAPS UP 90/90 KIAS

30
Compiled by Peter Schmidleitner

15
Diamond DA42-VI

Instrument Panel

Compiled by Peter Schmidleitner

Instrument panel

32
Compiled by Peter Schmidleitner

16
 Instrument Panel

Garmin 1000

33
Compiled by Peter Schmidleitner

Instrument Panel

Airspeed Horizon Altimeter Compass

Backup Instruments

34
Compiled by Peter Schmidleitner

17
 Instrument Panel
Flood Lights

Emergency Switch Emergency Battery

(non rechargeable)
IFR flights not permitted when seal on Emergeny Switch is broken

35
Compiled by Peter Schmidleitner

Instrument Panel

Lights ELT

36
Compiled by Peter Schmidleitner

18
 Instrument Panel

Circuit breakers

37
Compiled by Peter Schmidleitner

Instrument Panel

Alternators + ECU Control

38
Compiled by Peter Schmidleitner

19
 Digital Engine Control

„ ECU (EECU)
„ Engine Control Unit
„ Electric Engine Control Unit

this is a
„ FADEC
„ Full Authority Digital Engine
Control

39
Compiled by Peter Schmidleitner

Digital Engine Control

Will be explained in the

„Power Plant“ chapter

40
Compiled by Peter Schmidleitner

20
 Instrument Panel

Fuel Pumps

Pitot heat Engine master switches, Electric Master,

Engine start Avionic Master

41
Compiled by Peter Schmidleitner

Instrument Panel

Landing gear Flaps

42
Compiled by Peter Schmidleitner

21
Pitot probe

43
Compiled by Peter Schmidleitner

Static ports

44
Compiled by Peter Schmidleitner

22
 Alternate static valve

45
Compiled by Peter Schmidleitner

Lift detector (Stall warning)

46
Compiled by Peter Schmidleitner

23
 Diamond DA42-VI

Garmin 1000
Engine Indication System

Compiled by Peter Schmidleitner

DA42 Garmin 1000

PFD MFD
Primary Flight Display Multi Function Display
Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved.

48
Compiled by Peter Schmidleitner

24
 Garmin 1000 MFD
EIS / Engine Indication System

Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved.

49
Compiled by Peter Schmidleitner

Engine Indication System

Display when Display when
pushing the pushing the
Default page SYSTEM softkey FUEL softkey

Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved.

50
Compiled by Peter Schmidleitner

25
Engine Indication System
Display when Display when
pushing the pushing the
Default page SYSTEM softkey FUEL softkey

Upper part always the same

Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved.

51
Compiled by Peter Schmidleitner

Engine Indication System

Default SYSTEM FUEL

Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved.

52
Compiled by Peter Schmidleitner

26
 Diamond DA42-VI

Hydraulic System

Compiled by Peter Schmidleitner

Hydraulic brakes

Pilot applies brake

54
Compiled by Peter Schmidleitner

27
 Hydraulic brakes
Parking brake

Locked

55
Compiled by Peter Schmidleitner

Hydraulic brakes
Parking brake
Apply brake pressure

One-way valve is closed

Pressure is trapped

56
Compiled by Peter Schmidleitner

28
 Landing gear

57
Compiled by Peter Schmidleitner

Landing gear

„ Hydraulically operated
„ Electrically powered hydraulic
pump
„ Electrically actuated hydraulic
valves operated by gear selector
switch
„ „Squat switch“ prevents retraction
on ground

58
Compiled by Peter Schmidleitner

29
 Landing gear

„ Gear downlock = spring loaded

„ Downlock released by hydraulic
pressure for retraction
„ Green lights = gear down and locked
„ Red light = gear neither down nor up
„ Gear held up hydraulically
„ Emergency operation = free fall
(by releasing hydraulic pressure)

59
Compiled by Peter Schmidleitner

Landing gear

60
Compiled by Peter Schmidleitner

30
Landing gear

Emergency Extension

61
Compiled by Peter Schmidleitner

Landing gear

62
Compiled by Peter Schmidleitner

31
 Landing gear

„ Landing Gear Warning:

„ Gear UP
„ and
„ one power lever below ~20%
„ or
„ Flaps LDG

63
Compiled by Peter Schmidleitner

Landing gear

„ Gear Warning System

Horn Muting

Compiled by Peter Schmidleitner

32
 Landing gear

LH squat switch: FWD

• On ground landing gear
protection
RH squat switch:
• Stall warning heating
• Engine pre-glow
• ECU test
• TAS voice warning
Squat
switch

65
Compiled by Peter Schmidleitner

Nosewheel steering

„ Nosewheel steered with rudder

pedals
„ Steering angle:
„ 30° without use of brakes
„ 52° with one wheel fully braked

66
Compiled by Peter Schmidleitner

33
 Diamond DA42-VI

Flight Controls

Compiled by Peter Schmidleitner

Flight control operation

Ailerons, Elevator:
push rods

Flaps:
electrically by push rods

Rudder:
cables

68
Compiled by Peter Schmidleitner

34
Flight control operation

Inboard and outboard flaps have

separate bellcranks, but are
mechanically connected

69
Compiled by Peter Schmidleitner

Flap interconnection

70
Compiled by Peter Schmidleitner

35
 Variable elevator stop

„ Normal elevator „up“ deflection: 15,5°

„ Limited to „13° up“ when both power levers
above 20% (approach power setting)
„ Reason: With full elevator deflection in case
of stalling the handling qualities and stall
characteristics are degraded
„ Preflight check of this device is mandatory!
„ „STICK LIMIT“ caution when variable stop not
in proper position

71
Compiled by Peter Schmidleitner

Variable elevator stop

Power Backstop Caution

If Backstop is
levers shall be light

Both LOW
unlimiting limiting STICK LIMIT
Split

Both HIGH limiting unlimiting STICK LIMIT

72
Compiled by Peter Schmidleitner

36
Variable elevator stop
Preflight check

73
Compiled by Peter Schmidleitner

Option: Removal of the

Variable elevator stop

Normal CG limits: Without variable elevator stop :

74
Compiled by Peter Schmidleitner

37
Trim tabs

Elevator trim:
bowden cable

75
Compiled by Peter Schmidleitner

Trim tabs

Rudder trim:
bowden cable

76
Compiled by Peter Schmidleitner

38
 Rudder gap seal

77
Compiled by Peter Schmidleitner

Optional electric rudder pedal adjustment

78
Compiled by Peter Schmidleitner

39
 Diamond DA42-VI

Power Plant

Compiled by Peter Schmidleitner

Power plant
„ 2 Austro Engines E4-C
„ Four cylinders, liquid-cooled
„ 1991 ccm
„ Common-rail direct injection
„ Reduction gear 1:1,69
„ Dual digital engine control
„ Turbocharger
„ Torsion vibration damper isolates engine from
propeller
„ Max. power limitation: 100%, 2300 RPM
(5 minutes time limit)
123,5 kW (165,6 DIN-HP)
„ Max cont. power limitation: 92%, 2300 RPM
113,6 kW (152,3 DIN-HP)

80
Compiled by Peter Schmidleitner

40
 Austro Engine E4

81
Compiled by Peter Schmidleitner

Austro Engine E4

Turbo Charger

Alternator

Fuel High Pressure Pump

Oil Sump
Front View Propeller Shaft Gearbox

82
Compiled by Peter Schmidleitner

41
 Austro Engine E4
Turbo Charger

Fuel High Pressure Pump

Starter

Propeller Shaft
Water Pump
Gearbox
Engine Oil Filter Housing

Heat Exchanger

Rip Belt

Glow Plug Control Unit

Top View Oil Filler Cap

Alternator

83
Compiled by Peter Schmidleitner

Austro Engine E4
Turbo Charger

High Pressure Pump

Propeller Shaft

Starter

Water Pump

Engine Oil Filter Housing

Heat Exchanger
Side glass of Gearbox Oil Level
Rip Belt

Engine Oil Level and Refill Cap

Alternator
Left Hand View

84
Compiled by Peter Schmidleitner

42
Austro Engine E4

Gearbox

Oiltank

85
Compiled by Peter Schmidleitner

Austro Engine E4

Alternator

86
Compiled by Peter Schmidleitner

43
Austro Engine E4

Turbocharger

87
Compiled by Peter Schmidleitner

Austro Engine E4

Prop governor

88
Compiled by Peter Schmidleitner

44
ECU – Engine Control Unit

89
Compiled by Peter Schmidleitner

E.O.T. – Engine Order Telegraph

90
Compiled by Peter Schmidleitner

45
 Engine Control Unit

„ ECU „VOTER switches“

„ 3-position switches
„ Normally in AUTO position
„ Working ECU is automatically
selected according operating hours
or in case of malfunction

91
Compiled by Peter Schmidleitner

ECU test buttons

Test on ground (PWR lever idle)

92
Compiled by Peter Schmidleitner

46
 ECU test

„ ECU Test will not start when:

„ Power levers not in IDLE
„ VOTER switch not in AUTO
„ Gearbox temperature not in green range
„ „Air/Ground“ sensor transmits „aircraft in the air“

93
Compiled by Peter Schmidleitner

ECU FAIL Caution

„ An ECU FAIL caution is caused by various types of
malfunctions. These include internal ECU problems,
sensor failure or insufficient performance of air-, fuel- or
electrical supply system (e.g. air filter icing).
„ Depending on the type of failure, the ECU failure cautions
are either
„ ‘non latched’, i.e. the caution message disappears after the
cause of the caution is no longer present or
„ ‘latched’, i.e. the caution massage remains until cleared
through maintenance action.
„ Clearing of ‘non-latched’ caution:
„ on the active ECU: clears by itself
„ on the passive ECU: by switching to that ECU with the voter
switch.

94
Compiled by Peter Schmidleitner

47
 ECU Abnormal checklist

113
Compiled by Peter Schmidleitner

Simultaneous ECU fail indication

114
Compiled by Peter Schmidleitner

48
 Power plant
• Power lever selects „LOAD“ in %
• RPM automatically determined by selected power
2400

2350
100%
2300

2250

2200

2150 0%
Propeller Speed [rpm]

2100
92%
2050

2000

1950

1900

1850

1800

1750
20% Recommended Cruise
1700 Power Setting: 75%
1650

1600
0% 10% 20% 30% 40% 50% 60% 70% 80% 90% 100%
Power Lever [%]

97
Compiled by Peter Schmidleitner

Power vs altitude

98
Compiled by Peter Schmidleitner

49
 Propeller

„ 3-blade wooden propeller

„ Constant speed, feathering
„ Prop pitch set by ECU via an electro-
mechanical actuator on the governor
„ Governor operated by gearbox oil
„ Oil pressure up = pitch down = RPM up
„ Oil pressure down = pitch up = RPM down

99
Compiled by Peter Schmidleitner

Feathering system
„ Feathering by „Engine Master OFF“ if
RPM above 1300
„ Feathers when gear oil pressure is lost
„ If RPM below 1300: prop pitch remains
above high pitch lock
„ Unfeathering:
„ With unfeathering accumulator:
„ by oil pressure from accumulator when Engine
Master is ON
„ Without unfeathering accumulator:
„ by building up system oil pressure when cranking
the starter

100
Compiled by Peter Schmidleitner

50
 RPM malfunctions

101
Compiled by Peter Schmidleitner

Fuel pumps

„ 1 engine driven pump

„ this high pressure pump feeds the
common rail
„ (additional electrical fuel pumps are
part of the fuel system)

102
Compiled by Peter Schmidleitner

51
 Power plant limitations
„ Max overspeed: 2500 RPM, max 20 sec.
„ Oil pressure:
„ < 1500 RPM: min 0,9 bar
„ >= 1500 RPM: min 2,5 bar
„ Max: 6,5 bar
„ Normal: 2,5 – 6 bar
„ Intentional negative-g manoeuvers are not permitted
„ Oil quantity (per engine): 5.0 – 7.0 liters
„ Max. oil consumption: 0.1 liters/hr
„ Oil temperature: -30°C – 140 °C
„ Normal: 50°C – 135°C

103
Compiled by Peter Schmidleitner

Power plant limitations

„ Gearbox temperature:
„ Min: -30°C
„ Min at full load: 35°C
„ Max: 120°C
„ Normal: 35°C – 115°C

The yellow cautionary range is for

information only. There is no time limit
associated with the cautionary
temperature range.
However, prolonged operation is not
recommended.

104
Compiled by Peter Schmidleitner

52
 Power plant limitations

„ Coolant temperature:
„ min -30°C for start up
„ min 60°C full load
„ max 105°C
„ Normal 60°C – 95°C
„ Fuel temperature:
„ min -30°C, max 60°C
„ Normal: -20°C – 55°C
„ Fuel pressure:
„ min 4 bar, max 7 bar
„ no indication on G1000, but warning if below limit

105
Compiled by Peter Schmidleitner

Power plant limitations

AFM 3.7.4:
UNFEATHERING & RESTARTING THE ENGINE IN
FLIGHT
If the reason for the shutdown has been ascertained and
there is no indication of malfunction or engine fire a restart
may be attempted.
„ Max. restart altitude:
„ 18.000 ft for immediate restart
„ 10.000 ft for restart within 2 minutes
„ No restart attempt if shut down for more than 2
minutes!
„ Restart airspeeds:
„ starter assisted restart:
„ Max 100 KIAS or stationary prop, whichever is lower
„ Windmilling restart (only possible when unfeathering
accumulator is installed) :
„ 125 – 145 KIAS

106
Compiled by Peter Schmidleitner

53
 Power plant limitations

„ No intentional shutdown
„ below 3000ft AGL or above 10000ft PA
„ without unfeathering accumulator

107
Compiled by Peter Schmidleitner

Starter limitations

„ Normal operation on ground:

„ max 10 seconds
„ 60 seconds cool down time
„ Restarting in the air:
„ max 5 seconds
„ 30 seconds cool down time
„ max 3 attempts

108
Compiled by Peter Schmidleitner

54
Power plant fluid specifications

„ Fuel: JET A, JET A-1 (ASTM D 1655)

TS-1 (Russia, GOST 10227-86)
TS-1 (Ukraine, GSTU 320.00149943.011-99)
RT (Russia, GOST 10227-86)
RT (Ukraine GSTU 320.00149943.007-97)
No. 3 Jet Fuel (China, GB 6537-2006)
JP-8 (F34) (USA, MIL-DTL-83133G-2010)
For use of fuel additives
and blends thereof
see AFM !
Minimum cetane number of 37
(EN ISA 5165/ASTM D613)
recommended

Diesel (EN 590)

Special procedures to be observed!
See AFM Supplement

109
Compiled by Peter Schmidleitner

Power plant fluid specifications

„ Engine Oil:
„ SAE Grade 5W-30: „ SAE Grade 5W-40:
„ SHELL HELIX ULTRA „ SHELL HELIX ULTRA
„ ADDINOL SUPER POWER MV 0537 „ LIQUI MOLY 5W-40 LEICHTLAUF
„ BP VISCO 5000 5W-30 HIGH TECH
„ REPSOL ELITE COMMON RAIL „ MEGOL MOTORENOEL
5W30 HIGH CONDITION
„ GULF FORMULA GMX „ PETRONAS Syntium 3000
„ AEROSHELL Oil Diesel Ultra „ LUKOIL LUXE SYNTHETIC
„ CASTROL Edge 5W-30 A3 „ CASTROL Edge Professional A3
„ CASTROL Edge Professional A3 „ CASTROL Magnatac Professional A3
VALVOLINE SynPower HST
„ SAE Grade 0W-40: „

„ VALVOLINE SynPower
„ CASTROL SLX PROFESSIONAL
LONGTEC „ GULF Formula GX
„ CASTROL Edge 0W-40 A3/B4
„ CASTROL Edge Professional A3
„ SHELL HELIX ULTRA

110
Compiled by Peter Schmidleitner

55
Power plant fluid specifications

„ Gearbox oil: Shell Spirax GSX 75W-80

Shell Spirax S6 GSXME 75W-80
„ Coolant: Destilled water + cooler protection 1:1
(BASF Glysantin Alu Protect Plus/G48)
(freezing point –38 °C)

111
Compiled by Peter Schmidleitner

Engine operation

after line-up

112
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56
 Engine operation

113
Compiled by Peter Schmidleitner

Air inlets

Air inlet for engine air filter and intercooler

Air inlet for cabin heat, coolant heat exchanger, gearbox, fuel cooler

114
Compiled by Peter Schmidleitner

57
 Gearbox cooling

Gearbox cooling

115
Compiled by Peter Schmidleitner

Air outlet

116
Compiled by Peter Schmidleitner

58
 Alternate air

Alternate air lever Alternate air valve

117
Compiled by Peter Schmidleitner

Alternate air

Alternate air lever pulled Alternate air valve open

118
Compiled by Peter Schmidleitner

59
 Use of Alternate Air

AFM:

119
Compiled by Peter Schmidleitner

Use of Alternate Air

120
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60
Checking oil levels

Compiled by Peter Schmidleitner

Checking oil levels

Compiled by Peter Schmidleitner

61
Checking oil levels

Gearbox Oil

Engine Oil

Compiled by Peter Schmidleitner

Checking oil levels

Gearbox Oil
(hard to see through the
oil filler door)

Compiled by Peter Schmidleitner

62
Power plant warnings

125
Compiled by Peter Schmidleitner

Power plant cautions

126
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63
 Fire detection system

„ Overheat detector in hot area of

each engine
„ Warning above 250°C
„ Test button:

127
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Intentionally blank

Compiled by Peter Schmidleitner

64
Diamond DA42-VI

Cooling System

Compiled by Peter Schmidleitner

Cooling system

130
Compiled by Peter Schmidleitner

65
Cooling system

Coolant Temp.
< 88°

131
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Cooling system

Coolant Temp.
> 88°

132
Compiled by Peter Schmidleitner

66
Cooling system

133
Compiled by Peter Schmidleitner

Cooling system

134
Compiled by Peter Schmidleitner

67
 Cooling system

Cabin Heat

135
Compiled by Peter Schmidleitner

Cabin heating and defrosting system

Defrost from LH Engine Cabin Heat from RH Engine

136
Compiled by Peter Schmidleitner

68
 Ventilation

Cockpit

Cabin

155
Compiled by Peter Schmidleitner

Ventilation inlet

RH wing underside Winter Kit

156
Compiled by Peter Schmidleitner

69
Diamond DA42-VI

Turbocharger System

Compiled by Peter Schmidleitner

Turbo charger

Bypass for excess exhaust gas

Exhaust gas drives turbine

140
Compiled by Peter Schmidleitner

70
Turbo charger

Compressor compresses intake air

Exhaust gas drives turbine

141
Compiled by Peter Schmidleitner

Intentionally blank

Compiled by Peter Schmidleitner

71
Diamond DA42-VI

Fuel System

Compiled by Peter Schmidleitner

DA42 Fuel system

„ 2 Tanks (left and right),

each with 3 chambers:
„ 2 x 26 USG capacity
„ 2 x 25 USG usable
„ = 50 USG (189 ltr)
„ = 152 kg (at 0,80 kg/ltr)

144
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72
 DA42 Fuel system

„ Max unbalance: 5 USG

„ Fuel temperature limits:
„ -30° C to +60° C

145
Compiled by Peter Schmidleitner

DA42 Fuel system

3 chambers Fuel filler

Temperature sensor

Fuel pumps

Low level sensor

Drain Fuel level sensor 2 vents

146
Compiled by Peter Schmidleitner

73
 DA42 Fuel system
Drain valve in nacelle (gascolator)

147
Compiled by Peter Schmidleitner

DA42 NG-VI Fuel system

Fuel cooler

148
Compiled by Peter Schmidleitner

74
DA42 NG-VI Fuel system

Fuel Cooler

149
Compiled by Peter Schmidleitner

DA42 Fuel system

„Alternate means for
fuel quantity indication“

Position:
in front of drain,
approx. 10cm outboard
of nacelle

150
Compiled by Peter Schmidleitner

75
 DA42 Fuel system

ON

X-feed

OFF

151
Compiled by Peter Schmidleitner

DA42 NG-VI Fuel system

Fuel Valve „ON“

Supply

Return flow
up to 71 USG/hr
Average
45 USG/hr

152
Compiled by Peter Schmidleitner

76
DA42 NG-VI Fuel system

Fuel Valve „X-feed“

Supply

Return flow

153
Compiled by Peter Schmidleitner

DA42 NG-VI Fuel system

Fuel Valve „OFF“
opposite „X-feed“
Supply

Return flow

154
Compiled by Peter Schmidleitner

77
DA42 NG-VI Fuel system

X-feed operation

Supply

Return flow

155
Compiled by Peter Schmidleitner

Fuel valves schematic

Supply

Return flow
X-F ON X-F ON
ON X-F ON X-F

OFF OFF
OFF OFF

ON ON

X-FEED X-FEED

OFF OFF

156
Compiled by Peter Schmidleitner

78
 Both valves closed
Supply

Return flow
X-F ON X-F ON
ON X-F ON X-F

OFF OFF
OFF OFF

ON ON

X-FEED X-FEED

OFF OFF

157
Compiled by Peter Schmidleitner

Both engines running

Supply

Return flow
X-F ON X-F ON
ON X-F ON X-F

OFF OFF
OFF OFF

ON ON

X-FEED X-FEED

OFF OFF

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79
LH Eng. u/s, RH Eng. X-feed
Supply

Return flow
X-F ON X-F ON
ON X-F ON X-F

OFF OFF
OFF OFF

ON ON

X-FEED X-FEED

OFF OFF

159
Compiled by Peter Schmidleitner

Both engines from LH tank

Supply

Return flow
X-F ON X-F ON
ON X-F ON X-F

OFF OFF
OFF OFF

ON ON

X-FEED X-FEED

OFF OFF

160
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80
 Fuel system
„ For each engine:
„ 2 parallel electrical low pressure fuel pumps

„ each ECU has an associated fuel pump

(ECU A: pump A, ECU B: pump B)
„ normal Ops: only one pump working

„ when ECU switches over: fuel pumps switch

over as well
„ When pump fails (low fuel pressure):
„ automatic switch over to other pump by
switching to the other ECU
„ For TKOF, LDG and with fuel pressure failure:
„ both pumps switched ON manually with
FUEL PUMP switch

161
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Fuel pumps

162
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81
 Fuel pumps

163
Compiled by Peter Schmidleitner

Fuel pressure warning

„ Warning annunciation:
L/R FUEL PRES

164
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82
Fuel pressure warning

165
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Intentionally blank

Compiled by Peter Schmidleitner

83
Diamond DA42-VI

Auxiliary Fuel Tanks

Compiled by Peter Schmidleitner

Auxiliary Fuel Tanks

168
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84
 Auxiliary Fuel Tanks

„ One tank in each nacelle

„ Capacity: 13,7 USG per side
„ Useable: 13,2 USG per side

169
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Auxiliary Fuel Tanks

„ Electrical transfer pump (auxiliary

pump, „AUX PUMP“) feeds fuel from
the AUX tank to the main tank
„ Transfer must be initiated manually
„ Transfer in 2 steps:
„ First half when main tank 17 USG or
less (up to full main tank)
„ Second half when main tank again 17
USG or less

170
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85
 Auxiliary Fuel Tanks

„ AUX PUMP switched OFF

automatically when:
„ Main tank is full
„ AUX tank is empty

171
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Auxiliary Fuel Tanks

Main tanks AUX tanks Total

2 x 25 USG 2 x 13,2 USG 2 x 38 USG

50 USG 26,4 USG 76,4 USG

Maximum unbalance between main tanks:

5 USG
1 USG if there is an unbalance between AUX tanks

172
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86
Auxiliary Fuel Tanks

173
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Auxiliary Fuel Tanks

174
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87
 Auxiliary Fuel Tanks

CAUTION light

„ L/R AUX FUEL E

„ L/R AUX tank empty and fuel transfer
pump ON

175
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Auxiliary Fuel Tanks

176
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88
 Auxiliary Fuel Tanks

In case of a L or R AUX pump failure:

(AUX PUMP does not operate)
„ Use x-feed function to keep fuel balance

„ Amend flight plan for reduced amount

of available fuel

177
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Auxiliary Fuel Tanks

178
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89
 Auxiliary Fuel Tanks

Mass and Balance

Item Lever Arm (m)

Wing tanks 2.63
AUX tanks 3.20

179
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Auxiliary Fuel Tanks

Fuel quantity check

„ Verify AUX empty
„ Electrical Master ON
„ Fuel transfer ON
„ L/R AUX FUEL E CHECKED
„ Verify AUX full
„ Visual check

180
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90
 Auxiliary Fuel Tanks

„ Fuel quantity between „FULL“ and „EMPTY“

cannot be determined

181
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Auxiliary Fuel Tanks

Preflight fuel management

„ If possible transfer all AUX fuel to
main tanks
„ Use external power or one engine running
„ Electrical Master ON
„ Fuel transfer ON
until
„ L/R AUX FUEL E ON
(will take 10 minutes or even longer)

182
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91
Auxiliary Fuel Tanks

Drain

Vents

Compiled by Peter Schmidleitner

Intentionally blank

Compiled by Peter Schmidleitner

92
 Diamond DA42-VI

Diesel Operation

Compiled by Peter Schmidleitner

DA42NG Diesel Operation

186
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93
DA42NG Diesel Operation

„ Fuel Temperature
„ Diesel Operation
„ Minimum: -30°C
„ Maximum: 60°C
„ Modified G1000 Software:

187
Compiled by Peter Schmidleitner

DA42NG Diesel Operation

„ Operational Limitations:

188
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94
 DA42NG Diesel Operation
Diesel Fuel Classes (EN 590)
(„Temperate“ climatic zones)

„Winter Diesel“: Class F

„Arctic“ climatic zones: other classes

189
Compiled by Peter Schmidleitner

DA42NG Diesel Operation

„ Diesel Fuel or a blend of Diesel Fuel with JET

Fuel is not permitted in the auxiliary tanks.
„ If the airplane is operated in a cold
environment, it must be changed from Diesel
Fuel operation to JET Fuel operation.
„ The fuel filter is not heated!
„ In case of JET Fuel operation (when JET Fuel
temperature limitations are applied), make sure
that no Diesel Fuel is remaining in the tanks.
„ Otherwise the temperature limitations for Diesel
Fuel operation must be observed.

190
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95
 DA42NG Diesel Operation

„ To ensure that no blend of JET Fuel with Diesel

Fuel is in one of the tanks, each tank must be
refilled at least twice with more than 17.2 US
gal (65 l) of JET Fuel. Otherwise both tanks
must be drained before refueling with JET Fuel.

NOTE
„ In order to provide information about the fuel
grade it is recommended to enter the fuel grade
in the airplane log each time fuel is refilled.

191
Compiled by Peter Schmidleitner

DA42NG Diesel Operation

Performance below 10°C OAT

TKOF Ground Roll (normal and short field)

TKOF Distance add 7%

(Flaps UP and Flaps APP)
Climb reduce by 60 ft/min
1-engine climb Reduce by 30 ft/min
Make calculation from the basic AFM value before calculating additional corrections from other Supplements.

192
Compiled by Peter Schmidleitner

96
 Diamond DA42-VI

Electrical System

Compiled by Peter Schmidleitner

Electrical system
Power sources

Main Battery
LH 24V 13,6Ah
Alternator
28V 70A

RH
Alternator
28V 70A

ECU backup battery

ECU backup battery 7,2Ah
7,2Ah

Emergency Battery Not part of the electrical system

194
Compiled by Peter Schmidleitner

97
 Electrical system
Power distribution
Hot Battery Bus

Battery Bus

RH Main Bus
LH Main Bus

RH ECU Bus

LH ECU Bus

Avionic Bus

195
Compiled by Peter Schmidleitner

Electrical system
Battery Bus
Starter Starter

LH EPU RH
Alternator Alternator

3 Main Battery
24V 13,6Ah
3 Avionic Bus
ECU ECU
A A
B 2 2 B

LH ECU Hot Battery Bus RH ECU

Bus Bus
LH Main Bus RH Main Bus

ECU backup battery 24V 7,2 Ah ECU backup battery 24V 7,2 Ah

196
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98
Hot battery bus

„ Pilot map / reading light

197
Compiled by Peter Schmidleitner

Battery bus

„ LH / RH Main Bus
„ LH / RH starter heavy duty
power
„ LH / RH ECU BUS (via diode)

198
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99
 LH Main bus

„ PFD „ Pitot heating

„ Air Data Computer „ Oxygen system
„ AHRS „ Gear control
„ COM 1 „ Gear warning
„ GPS/NAV 1 „ Map light
„ Transponder „ Flood light
„ Engine „ Taxi light
Instruments „ Anticollision
lights

199
Compiled by Peter Schmidleitner

RH Main bus

„ Avionic Bus „ Stall warning

„ MFD „ Autopilot
„ Horizon warning
„ Starter control „ Landing light
„ Flap system „ Navigation lights
„ Avionic/ „ Instrument
CDU cooling fan lights

200
Compiled by Peter Schmidleitner

100
 Avionic bus
„ COM 2
„ GPS/NAV 2
„ Audio panel
„ Autopilot
„ (Data Link)
„ (WX 500)
„ (ADF)
„ DME
„ (Weather Radar)

201
Compiled by Peter Schmidleitner

Electrical system
Electric Master
„ Connects Battery Bus to Battery
(Battery Bus powers L/R Main Bus)
„ Enables Alternator Switches

202
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101
 Electrical system
L/R Alternator switch
„ Connects L/R Alternator to L/R Main
Bus

„ (In normal operation Alternator switches are

always ON)

203
Compiled by Peter Schmidleitner

Electrical system
L/R Engine Master
„ Enables starter activation
„ Connects L/R ECU (A+B) to L/R ECU Bus
„ Provides power for „GLOW“ and unfeathering
accumulator
„ Connects L/R alternator field to the
ECU Backup Battery

204
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102
 Electrical system
Avionic Master Switch
„ Connects Avionic Bus to RH Main Bus

205
Compiled by Peter Schmidleitner

External power connection

206
Compiled by Peter Schmidleitner

103
Engine start with external power

207
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Engine start with external power

Checklist:

208
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104
Engine start with external power

„ Why?
„ With the start of the RH engine using the
aircraft electrical system you check the
battery status.
„ If the battery is too weak it will not „buffer“
the load of the RH starter motor, the LH
alternator voltage will drop considerably, and
the RH starter will not operate

No Night VFR or IFR with empty battery!

Therefore:
No Night VFR or IFR if engine start with
external power was necessary.

209
Compiled by Peter Schmidleitner

Electrical malfunctions

If both low voltage indications are ON,

expect failure of both alternators

210
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105
Electrical malfunctions

May be temporarily triggered

during ground operation with low
engine power settings. This
indicates no system malfunction.

211
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Electrical malfunctions

212
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106
 Electrical system
2 types of amperemeter can be installed in aircraft:

213
Compiled by Peter Schmidleitner

Electrical system
Observe!
The Amperemeter on the G1000 is a

214
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107
 Diamond DA42-VI

Oxygen System

Compiled by Peter Schmidleitner

Oxygen system

„ Continous Flow System

„ Operation up to 18.000 ft
„ Oxygen cylinder (system) pressure:
MAX 1850 psi at 21° C
(i.e. 50 cubic feet, 1.41 cubic meters)
„ 4 cannulas plus 1 mask
„ Acc. AFM to be used above 10.000 ft

216
Compiled by Peter Schmidleitner

108
 Oxygen system

217
Compiled by Peter Schmidleitner

Oxygen system

„ Exact calculation of duration :

„ see AFM supplement
„ it depends on the
„ oxygen cylinder pressure
„ number of users and types of dispensing
equipment
„ flight altitude

218
Compiled by Peter Schmidleitner

109
 Oxygen system

Oxygen cylinder

Oxygen outlets

219
Compiled by Peter Schmidleitner

Oxygen system

220
Compiled by Peter Schmidleitner

110
Oxygen system

221
Compiled by Peter Schmidleitner

Oxygen system

Filling table
to chieve a cylinder (system) pressure of 1850 psi

222
Compiled by Peter Schmidleitner

111
Oxygen system

223
Compiled by Peter Schmidleitner

Oxygen system

224
Compiled by Peter Schmidleitner

112
 Oxygen system

225
Compiled by Peter Schmidleitner

Oxygen system

Quick connect

Adjustable flow valve

226
Compiled by Peter Schmidleitner

113
 Oxygen system
Flowmeter

Scale for „oxysaver“ cannula

Scale for mask

and
„standard“ cannula

227
Compiled by Peter Schmidleitner

Oxygen system

228
Compiled by Peter Schmidleitner

114
Oxygen system

Mass and Balance

Lever Arm
Item
(m)
Oxygen cylinder 0.82

In fact relevant for removal only.

Full Oxygen: CG moves FWD ~ 2mm

229
Compiled by Peter Schmidleitner

Oxygen system

230
Compiled by Peter Schmidleitner

115
 Diamond DA42-VI

Ice Protection System

Compiled by Peter Schmidleitner

Ice protection system

Fluid ice protection system

Product of

CAV Aerospace Ltd

(Celtic Aerospace Ventures Ltd)

commonly knows as
„TKS“

232
Compiled by Peter Schmidleitner

116
 „TKS“ Ice Protection
General

233
Compiled by Peter Schmidleitner

Ice protection system

„ How does it work?

„ Protection fluid acts a „freezing point
depressant“ (FPD)
„ Water droplets in the air combine with
FPD fluid to form a mixture with a
freezing temperature below the
temperature of the ambient air

234
Compiled by Peter Schmidleitner

117
 Ice protection system

„ Two means of FPD fluid application:

„ Spray nozzles (windshield, propeller)
„ Propeller:
„ Feeding into a „slinger ring“
„ Feeder tube to (rubber) leading edge
„ Porous skin panels

235
Compiled by Peter Schmidleitner

Ice protection system

„ Freezing point of glycol:

„ -12° C
„ Freezing point of glycol/water mixture:
„ is lower !!!

The „Eutectic-phenomenon“

236
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118
 „TKS“ Ice Protection
DA42

237
Compiled by Peter Schmidleitner

Ice protection system

2 versions:
Front tank Rear tank

Tank for de-icing fluid is

located behind the short
baggage compartment
(Modificationn 42-203).
Filler is located on LH side of
the fuselage.

30 liters
useable

238
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119
Ice protection system

Circuit breakers

239
Compiled by Peter Schmidleitner

Ice protection system

Minimum for dispatch:

22 liters

3/4

240
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120
 Ice protection system
2 „independent“ systems
Airframe and Windshield
Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2
2 x 2 pumps
ALTERNATE

LH Main BUS Normally powered from the LH Main Bus

Fluid tank
RH Main BUS

241
Compiled by Peter Schmidleitner

Ice protection system

Windshield ice protection

„ 2 pumps for redundancy

„ Only one pump operative at a time
„ Operated for 5 seconds by a push
button

242
Compiled by Peter Schmidleitner

121
 Ice protection system
Operational modes
Mode Designed to Selected when
cover the more frequent but icing conditions are
less severe known icing encountered and prior
NORM
conditions as defined by to ice formation
CS25/FAR Part 25, Appendix C
cover all known icing icing conditions are
conditions as defined by more demanding or
HIGH CS25/FAR Part 25, Appendix C ice has already
accumulated
provide maximum possible protection for conditions
MAX outside the icing envelope as defined by
CS25/FAR Part 25, Appendix C

243
Compiled by Peter Schmidleitner

Ice protection system

Operational modes
Operating
Mode Operating mode
time
2 pumps simultaneously,
NORM
Climb but cycled 30 secs ON and ~ 2,5 hrs
*)
+ 90 secs OFF
HIGH Cruise
Approach 1 pump continuously ON ~ 1,0 hr
**)
2 pumps simultaneously
MAX ON for 2 minutes ~ 0,5 hr

*) If no shedding of the ice in NORM mode Æ HIGH

If no shedding of the ice in HIGH mode Æ proceed with checklist
**)
INADVERTENT ICING ENCOUNTER & EXCESSIVE ICE ACCUMULATION

244
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122
Ice protection system

NORM

30s ON, 90s OFF

245
Compiled by Peter Schmidleitner

Ice protection system

Airframe and Windshield

Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE

LH Main BUS
Fluid tank
RH Main BUS

246
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123
Ice protection system

Continuously ON

HIGH

247
Compiled by Peter Schmidleitner

Ice protection system

Airframe and Windshield

Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE

LH Main BUS
Fluid tank
RH Main BUS

248
Compiled by Peter Schmidleitner

124
Ice protection system

2 minutes ON

MAX
+

HIGH

249
Compiled by Peter Schmidleitner

Ice protection system

Airframe and Windshield

Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE

LH Main BUS
Fluid tank
RH Main BUS

250
Compiled by Peter Schmidleitner

125
Ice protection system

5 seconds

Windshield deice

251
Compiled by Peter Schmidleitner

Ice protection system

Airframe and Windshield

Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE

LH Main BUS
Fluid tank
RH Main BUS

252
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126
Ice protection system

Main and Windshield

pump selector

253
Compiled by Peter Schmidleitner

Ice protection system

Airframe and Windshield

Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE

LH Main BUS
Fluid tank
RH Main BUS

254
Compiled by Peter Schmidleitner

127
Ice protection system

ALTERNATE switch
connects pump #2
directly to
RH main bus

System operates in
HIGH mode

255
Compiled by Peter Schmidleitner

Ice protection system

Airframe and Windshield

Prop
MAX

HIGH

NORM

PUMP 1 PUMP 2

ALTERNATE

LH Main BUS
Fluid tank
RH Main BUS

256
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128
 Ice protection system

Ice lights

257
Compiled by Peter Schmidleitner

Ice protection system

CAUTION lights
„ DEIC PRES LO
„ De-icing pressure is low
„ DEIC PRES HI
„ De-icing pressure is high
„ DEICE LVL LO
„ De-icing fluid level is low (below 10 ltrs)
„ max 45 mins in NORM mode,
max 22 mins in HIGH mode

258
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129
Ice protection system

DEICE LVL LO light ON

DEIC PRES LO light ON
after 120 seconds

Annunciator test
(simulates system ON)

259
Compiled by Peter Schmidleitner

Ice protection system

2 minutes

260
Compiled by Peter Schmidleitner

130
Ice protection system

261
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Ice protection system

262
Compiled by Peter Schmidleitner

131
 Ice protection system

263
Compiled by Peter Schmidleitner

Ice protection system

Approved fluids
„ For use in the system:
„ AL-5 (DTD 406B)
„ Aeroshell Compound 07
„ For de-icing on ground:
„ AL-5 (DTD 406B)
„ Aeroshell Compound 07
„ Kilfrost TKS 80

264
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132
 Ice protection system

Mass and Balance

Lever Arm
Item
(m)
De-icing fluid tank 1.00

1 ltr: 1,1 kg
30 ltr: 33,0 kg

265
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Ice protection system

„ YES on panels „ NO on panels

„ Water, soap „ Wax
„ Isopropyl alcohol „ Methyl ethyl
„ Ethyl alcohol ketone (MEK)
„ Methylated spirit „ Lacquer thinner
„ De-icing fluids „ Other thinners and
„ AVGAS solvents
„ Jet fuel

266
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133
 Ice protection system
Operational considerations

„ 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
ice protection system: -30°C

267
Compiled by Peter Schmidleitner

Ice protection system

Operational considerations

„ what defines „icing conditions“?

„ visually detected ice
„ visible moisture and OAT +3°C or
below

268
Compiled by Peter Schmidleitner

134
 Ice protection system
Operational considerations

„ what indicates conditions the

system my be unable to cope with?
„ heavy ice accumulation on windshield
„ ice on side areas of canopy
„ rapid formation and shedding of bars
thicker than 6mm from porous panels
„ what to do?
„ select HIGH/MAX
„ leave icing conditions

269
Compiled by Peter Schmidleitner

Ice protection system

Operational considerations

„ flight in „freezing rain“ or „freezing

drizzle“ is prohibited !
„ Exit icing conditions immediately
„ how to detect freezing rain or freezing
drizzle ?
„ unusually extensive ice where normally not
observed
„ ice on upper surface of wing aft of protected
area
„ ice on spinner further back than normally
observed

270
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135
 Ice protection system
Operational considerations

„ how to detect possible freezing rain or

freezing drizzle conditions?
„ visible rain in OAT below +5°C
„ droplets that splash on impact in OAT below
+5°C
„ performance loss larger than normally
experienced in icing conditions

271
Compiled by Peter Schmidleitner

Ice protection system

Operational considerations

„ Autopilot
„ may be used in icing conditions, but:
„ disconnect every 10 – 15 minutes to
detect out of trim conditions
„ PROHIBITED with
„ ice aft of protected area
„ unusual lateral trim
„ autopilot trim warning

272
Compiled by Peter Schmidleitner

136
 Ice protection system
Operational considerations

„ „Ice on unprotected areas“

(„normal“ in icing conditions)
„ not the same as:
„ „Residual ice“:
„ Ice that remains on a protected
surface immediately following the
actuation of a deicing system

273
Compiled by Peter Schmidleitner

Ice protection system

Operational considerations
„ With
„ residual ice,
„ ice on unprotected areas or
„ in icing conditions:
„ Maximum Landing Mass:
1900 kg
„ Landing distance (flaps APP):
„ Use FLAPS LDG information and
increase by 20%

274
Compiled by Peter Schmidleitner

137
 Ice protection system
Operational considerations
Airspeeds with ice on unprotected areas
Continuous operation in icing
conditions (except TKOF, LDG and 118 – 156 KIAS
maneuvers)
Minimum continuous climb speed in 118 KIAS
icing conditions (flaps UP)
Stalling speeds + 4-6 KIAS
App/Ldg Vref in icing conditions, 2-eng or 1-eng
Flaps UP 94/97 KIAS
up to 1900 / > 1900 kg
Flaps APP 90/93 KIAS
Flaps LDG prohibited

275
Compiled by Peter Schmidleitner

Ice protection system

Operational considerations

„ Flaps LDG prohibited:

„ in icing conditions (ice on unprotected
surfaces)
„ with residual ice
„ Intentional 1-eng operation under
known or forecast icing conditions is
prohibited

276
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138
 Ice protection system
Operational considerations

Performance in icing conditions (residual ice,

ice on unprotected areas)
Check AFM supplement
e.g.
„ Cruise performance: TAS -20 %
„ Max demonstrated crosswind component in
icing conditions: 20 kts

277
Compiled by Peter Schmidleitner

Ice protection system

Operational considerations
Performance with residual ice or in icing conditions
(ice on unprotected areas)

up to 1900 / > 1900 kg

Vyse: 88/90 KIAS
One engine inoperative climb performance
Check AFM supplement
A positive ROC cannot be expected

278
Compiled by Peter Schmidleitner

139
 Ice protection system
Operational considerations
„ Approach, landing in icing conditions (ice on
unprotected surfaces):
„ Gear down

„ 118-156 KIAS until on final

„ land with flaps APP: Vapp min 90 KIAS

„ LDG distance acc. AFM for flaps LDG + 20%

„ When ice protection system fails:

„ 118-156 KIAS until on final

„ land with flaps APP

„ Vapp with residual ice min 90/93 KIAS

„ Go around in icing conditions (residual ice, ice on

unprotected surfaces):
„ with Flaps APP, gear down, 1900 kg,
90 KIAS:
„ 8,2% (4,7°), 746 fpm climb

279
Compiled by Peter Schmidleitner

Ice protection system

Technical considerations

„ To avoid the need for repriming:

„ Maintain at least 2 ltrs in the tank
„ Operate system at least once a month
„ Priming of the system:
„ main pumps:
„ primed by windshield pumps
„ porous panels:
„ During climb or descent MAX mode in intervals of
5 minutes until fluid dissipates from all panels, but
not in icing conditions and only up to 4°C (above
4°C special maintenance action may be required)

280
Compiled by Peter Schmidleitner

140
 Diamond DA42-VI

Performance

Compiled by Peter Schmidleitner

TKOF, LDG Performance general

(Areas are indicated with a diagonal line).

Effect of wind
Headwind: minus 10% for each 14 kt
Tailwind: plus 10% for each 3 kt

TKOF uphill slope,

LDG downhill slope

282
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141
 X-wind

Max demonstrated crosswind component:

Flaps UP: 25 kts
Flaps APP: 20 kts
For short field take-off

Max demonstrated crosswind component in icing conditions:

20 kts

283
Compiled by Peter Schmidleitner

Performance Tables
„ Fuel Flow
„ Stalling Speeds
„ TKOF Ground Roll / TKOF Distance
„ Normal TKOF
„ Short Field TKOF
„ Climb Performance
„ All Engines Flaps UP
„ All Engines Flaps APP
„ One Engine Inoperative Climb
„ Time, Fuel, Distance to Climb
„ Cruise Performance
„ LDG Ground Roll / LDG Distance
„ Flaps LDG
„ Abnormal Flap Position
„ Go-Around Climb Performance

284
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142
 Fuel Flow

13 USG/hr

Fuel flow per hour for one

engine!
Peter Schmidleitner

Compiled by Peter Schmidleitner

Stalling Speeds

Compiled by Peter Schmidleitner

143
 Take off distance
Available tables:
Normal Procedure
1999 kg
1900 kg
1700 kg
Short field Procedure
1999 kg
1900 kg
1700 kg

Headwind: TKOF distance minus 10% for each 14 kt

Up to Tailwind: TKOF distance plus 10% for each 3 kt
10000 ft
Uphill slope: Ground roll plus 9% for each 1% of slope

Peter Schmidleitner

Compiled by Peter Schmidleitner

TKOF on Grass RWY

Length of
grass TKOF roll Wet grass

5 cm + 10%
additional
5 - 10 cm + 15%
+ 10%
>10 cm + 25%

> 25 cm TKOF should not be attempted

+ 45% on soft ground !

288
Compiled by Peter Schmidleitner

144
 Climb performance
Available tables:
Flaps UP
1999 kg
1900 kg
1700 kg
Flaps APP
1999 kg
1900 kg
1700 kg

Peter Schmidleitner

Compiled by Peter Schmidleitner

1-engine climb
Available tables:
Flaps UP
1999 kg
1900 kg
1700 kg

Peter Schmidleitner

Compiled by Peter Schmidleitner

145
 Climb performance

„ Climb Performance
„ Tables show rate of climb
„ Conversion to gradient:

„ with TAS: „still air gradient“ !

291
Compiled by Peter Schmidleitner

Time, Fuel, Dist to climb

Available tables:
Flaps UP
1999 kg
1900 kg
1700 kg

Peter Schmidleitner

Compiled by Peter Schmidleitner

146
 Time, Fuel, Dist to climb

„ Time, Fuel, Distance to Climb:

„ Based on ISA, zero wind
„ Add 10% to time, fuel and distance for
each 10° increase of OAT
„ Method of calculation:
„ 1. get values for airfield altitude
„ 2. get values for for cruise altitude
„ Result: subtract 1 from 2

293
Compiled by Peter Schmidleitner

True Air Speed

Up to
18000 ft

Peter Schmidleitner

Compiled by Peter Schmidleitner

147
 Landing distance
Available tables:
Flaps LDG
1999 kg
1900 kg
1805 kg
1700 kg
Flaps APP or UP
1999 kg
1900 kg
1805 kg
1700 kg

Headwind: LDG distance minus 10% for each 14 kt

Up to Tailwind: LDG distance plus 10% for each 3 kt
10000 ft
Downhill slope: Ground roll plus 9% for each 1% of slope

Peter Schmidleitner

Compiled by Peter Schmidleitner

LDG on wet or Grass RWY

LDG roll
Paved RWY
WET + 15%
Length of Wet grass or
grass soft ground

- 5 cm + 10%
additional
5 - 10 cm + 15%
+ 10%
>10 cm min + 25%

296
Compiled by Peter Schmidleitner

148
 Go around
Available tables:
Flaps LDG
1999 kg
1900 kg
1805 kg
1700 kg

Compiled by Peter Schmidleitner

Obstacles ?
„d“= (RWL + Obst.Dist.) - TOD
Gradient = („h“ / „d“) * 100

Gradient x TAS
ROC =
0.98

„h“

„d“
Obst. Dist.
TOD
RWL

298
Compiled by Peter Schmidleitner

149
 Diamond DA42-VI

Mass and Balance

Compiled by Peter Schmidleitner

Empty mass

„ Empty Mass includes:

„ Equipment as per Equipment Inventory
„ Brake fluid
„ Hydraulic fluid
„ Engine oil (2 x 7.0 liters)
„ Coolant (2 x 7.5 liters)
„ Gearbox oil (2 x 2.1 liters)
„ Unusable fuel in main tanks (2 USG)
„ Unusable fuel in AUX tanks (1 USG)

300
Compiled by Peter Schmidleitner

150
Center of gravity envelope

When operating in
known icing conditions

301
Compiled by Peter Schmidleitner

Center of gravity envelope

Without „Variable Elevator Stop“

302
Compiled by Peter Schmidleitner

151
 Moment arms
Item Lever Arm (m)
Front seats 2.30
Rear seats 3.25
Wing tanks 2.63
AUX tanks 3.20
De-icing fluid Front tank 1.00
Rear tank 4.52
Nose baggage 0.60
Cabin baggage 3.89
Baggage Extension 4.54
„Short baggage extension“:
Cabin baggage 3.65
Baggage Extension 3.97

303
Compiled by Peter Schmidleitner

M&B calculation
Lever arm Mass (kg) Moment (kgm)
Empty mass 1450 3488.0
Front seats 2.30 170 391.0
Rear seats 3.25 0 0.0
Nose baggage 0.60 0 0.0
Cabin baggage 3.89 30 116.7
Baggage extension 4.54 0 0.0
De-icing fluid 1.00 33 33.0
Zero Fuel Mass 2.39 1683 4028.7
Fuel (main tanks) 2.63 150 394.5
Fuel (AUX tanks) 3.20
Total TKOF Mass 2.41 1833 4423.2

304
Compiled by Peter Schmidleitner

152
Center of gravity envelope

TOM
1833kg, 2.41 m

ZFM
1683 kg, 2.39 m

305
Compiled by Peter Schmidleitner

„ Location of ECU backup battery to

improve CG:

Compiled by Peter Schmidleitner

153
 Diamond DA42-VI

Emergency Equipment

Compiled by Peter Schmidleitner

Emergency equipment

308
Compiled by Peter Schmidleitner

154
Emergency Exit
FW
D

309
Compiled by Peter Schmidleitner

Emergency Exit

2
FWD

310
Compiled by Peter Schmidleitner

155
(Optional) Emergency Axe

311
Compiled by Peter Schmidleitner

Intentionally blank

Compiled by Peter Schmidleitner

156
 Diamond DA42-VI

Kinds of Operation
Equipment List (KOEL)

Compiled by Peter Schmidleitner

Kinds of Operation Equipment List KOEL

314
Compiled by Peter Schmidleitner

157
Kinds of Operation Equipment List KOEL

Additional minimum equipment for the

intended operation
may be required by
national operating rules
and also depends on the
route to be flown.

315
Compiled by Peter Schmidleitner

Kinds of Operation Equipment List KOEL

316
Compiled by Peter Schmidleitner

158
Kinds of Operation Equipment List KOEL

317
Compiled by Peter Schmidleitner

Kinds of Operation Equipment List KOEL

318
Compiled by Peter Schmidleitner

159
 Diamond DA42-VI

Servicing

Compiled by Peter Schmidleitner

Unscheduled maintenance

„ Required after
„ Exceeding the operating limitations
(e.g. speeds, load factors, weights,..)
„ Hard landings
„ Propeller strike
„ Engine fire
„ Lightning strike
„ Other malfunctions and damage

320
Compiled by Peter Schmidleitner

160
Scheduled maintenance

„ Every
„ 100 hours
„ 200 hours

„ 1000 hours

„ 2000 hours

„ Annually

321
Compiled by Peter Schmidleitner

Refuelling

322
Compiled by Peter Schmidleitner

161
 Refuelling

323
Compiled by Peter Schmidleitner

Tire pressure

Mainwheel

324
Compiled by Peter Schmidleitner

162
 Tire pressure

Nosewheel

325
Compiled by Peter Schmidleitner

De-icing

„ Approved de-icing fluids:

„ Kilfrost TKS 80
„ Aeroshell Compound 07
„ AL-5 (DTD 406B)
„ Procedure:
„ Remove snow with brush
„ Spray de-icing fluid
„ Wipe dry

326
Compiled by Peter Schmidleitner

163
 Ground Handling

„ Moving by hand „ Moving by tow

„ Pushing or pulling vehicle
„ Inner section of prop „ Do not turn nosewheel
blades more than 40° either
side
„ Pushing
„ Qualified person must
Wing nose, center
„
be in cockpit
wing (do not damage
vortex generators!) „ Soft ground or snow:
Use towing lines on
Use steering bar or tow
„
„
main gear (check
bar AFM!)
„ NO: spinner, prop tips,
control surfaces, prop
de-icing nozzles

327
Compiled by Peter Schmidleitner

Steering/Tow bar

328
Compiled by Peter Schmidleitner

164
 Steering/Tow bar

329
Compiled by Peter Schmidleitner

Control surfaces gust lock

330
Compiled by Peter Schmidleitner

165
Mooring

331
Compiled by Peter Schmidleitner

Mooring

332
Compiled by Peter Schmidleitner

166
Mooring

333
Compiled by Peter Schmidleitner

Intentionally blank

Compiled by Peter Schmidleitner

167
 Diamond DA42-VI

Airconditioning

Compiled by Peter Schmidleitner

RACC:

Recirculating Air – Cabin Cooling

336
Compiled by Peter Schmidleitner

168
 Installation
Behind the baggage compartment,
therefore only „Short“ baggage compartment

337
Compiled by Peter Schmidleitner

RACC Elements

„ AUX Power switch

„ Control panel
„ on LH sidewall
„ Central unit
„ aft of baggage compartment
„ Additional alternator
„ LH engine compartment, belt driven from
propeller shaft
Not connected to the electrical system!

338
Compiled by Peter Schmidleitner

169
Addititional Alternator

339
Compiled by Peter Schmidleitner

Addititional Alternator

340
Compiled by Peter Schmidleitner

170
RACC Controls

341
Compiled by Peter Schmidleitner

RACC Controls

342
Compiled by Peter Schmidleitner

171
 RACC Concept

„ Cabin air is circulated through the

RACC and thereby cooled
„ Cabin air and outside air is also
needed for the operation of the
RACC

343
Compiled by Peter Schmidleitner

RACC Central Unit

Compiled by Peter Schmidleitner

172
RACC Central Unit

Front and left side

345
Compiled by Peter Schmidleitner

RACC Central Unit

Back and right side

346
Compiled by Peter Schmidleitner

173
Air inlet and compartment ventilation

from refrigeration
unit

347
Compiled by Peter Schmidleitner

Air outlet

348
Compiled by Peter Schmidleitner

174
RACC Schematic

349
Compiled by Peter Schmidleitner

RACC Schematic

350
Compiled by Peter Schmidleitner

175
 RACC Installation

Cooled air outlets

Compiled by Peter Schmidleitner

Cooled air outlets

352
Compiled by Peter Schmidleitner

176
 RACC Limitations

„ AUX POWER switch and RACC must be OFF

„ in all Emergencies
„ during Take-off, Landing, Go-Around
„ during Abnormal Operating Procedures
„ at OAT below 10° C (50° F)
„ above 10.000 ft MSL
„ when ADF system is used for navigation
„ RACC effects accuracy of the ADF system
and the WX 500 Stormscope

353
Compiled by Peter Schmidleitner

RACC Operation

„ On ground with External Power:

„ ELECTRIC MASTER: check OFF
„ AUX POWER: check OFF
„ Connect external power
„ RACC: ON
„ ELECTRIC MASTER: ON
„ On ground with engine running:
„ AUX POWER: ON
„ RACC: ON
„ Power Off:
„ RACC: OFF
„ AUX POWER: OFF

354
Compiled by Peter Schmidleitner

177
 RACC Operation

In flight:
„ switching RACC System ON:
„ AUX POWER: ON
„ RACC: ON
„ switching RACC System OFF:
„ RACC: OFF
„ AUX POWER: OFF

355
Compiled by Peter Schmidleitner

Climb Performance 2-eng

RACC ON: reduced by 70 ft/min

356
Compiled by Peter Schmidleitner

178
Cruising Speed

RACC OFF: reduced by 2%

RACC ON: reduced by 5%

357
Compiled by Peter Schmidleitner

Moment Arms
Lever Arm
Item
(m)

Front seats 2.30

Rear seats 3.25

Wing tanks 2.63

Standard bagge 3.65

Short baggage extension 3.97

358
Compiled by Peter Schmidleitner

179
 Diamond DA42-VI

Flight Procedures

Compiled by Peter Schmidleitner

Checklists

The checklists are not part of the AFM, and they are not
„officially Diamond factory-endorsed“.
They are published and used by „Diamond Flight Training“
and are a also a recommendation for an „Operator Checklist“

360
Compiled by Peter Schmidleitner

180
Handling of Emergencies

361
Compiled by Peter Schmidleitner

Basic Principle

„ First fly !
„ ... then handle

362
Compiled by Peter Schmidleitner

181
 „PPAA“

„ Power „ Max power

or „as required“
depending on situation

„ Performance „ Gear? Flaps?

Minimum speed?

„ Analysis „ Identify engine

Verify engine

„ Action „ Feather, shut

down

363
Compiled by Peter Schmidleitner

Take off Briefing

364
Compiled by Peter Schmidleitner

182
Take off malfunctions

365
Compiled by Peter Schmidleitner

Take off malfunctions

366
Compiled by Peter Schmidleitner

183
Take off malfunctions

367
Compiled by Peter Schmidleitner

Take-off

368
Compiled by Peter Schmidleitner

184
Short Field Take-off

369
Compiled by Peter Schmidleitner

Landing

370
Compiled by Peter Schmidleitner

185
Instrument Approach

371
Compiled by Peter Schmidleitner

1-engine approach

372
Compiled by Peter Schmidleitner

186