DA42 NG

Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Instrument Panel Circuit breakers © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Instrument Panel Alternators + ECU Control 21 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Digital Engine Control „ ECU (EECU) „ Engine Control Unit „ Electric Engine Control Unit this is a „ FADEC „ Full Authority Digital Engine Control © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Digital Engine Control Will be explained in the „Power Plant“ chapter 22 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Instrument Panel Engine master switches, Engine start Pitot heat Electric Master, Avionic Master Fuel Pumps © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Instrument Panel Flaps Landing gear 23 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Instrument panel („Upgrade NG“ with KAP140) New ECU panel Fuel pumps Fuel pump CBs © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Instrument panel („Upgrade NG“ with KAP140) 24 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Pitot probe © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Static ports 25 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Alternate static valve © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Lift detector (Stall warning) 26 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Garmin 1000 Engine Indication System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Garmin 1000 MFD PFD Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved. Primary Flight Display Multi Function Display 27 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Garmin 1000 MFD EIS / Engine Indication System Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved. © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Default page Display when pushing the SYSTEM softkey Engine Indication SystemDisplay when pushing the FUEL softkey Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved. 28 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Display when pushing the FUEL softkey Engine Indication System Default page Display when pushing the SYSTEM softkey Upper part always the same Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved. © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Engine Indication System SYSTEM FUEL Default Image reproduced with the permission of Garmin. © Copyright 2006 Garmin Ltd. or its subsidiaries. All Rights Reserved. 29 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Hydraulic System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Hydraulic brakes Pilot applies brake 30 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Hydraulic brakes Parking brake Locked © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Hydraulic brakes One-way valve is closed Parking brake „Pumping“ Pressure builds up 31 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ Hydraulically operated „ Electrically powered hydraulic pump „ Electrically actuated hydraulic valves operated by gear selector switch „ „Squat switch“ prevents retraction on ground Landing gear 32 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear FWD Squat switch LH squat switch: • On ground landing gear protection RH squat switch: • Stall warning heating • Engine pre-glow • ECU test • TAS voice warning © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear Downlock FWD 33 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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) Landing gear © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear 34 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear Emergency Extension © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear 35 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Landing gear „ Landing Gear Warning: „ Gear UP „ and „ one power lever below ~20% „ or „ Flaps LDG © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Nosewheel steering „ Nosewheel steered with rudder pedals „ Steering angle: „ 30° without use of brakes „ 52° with one wheel fully braked 36 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Flight Controls © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Flight control operation Rudder: cables Flaps: electrically by push rods Ailerons, Elevator: push rods 37 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Flight control operation Inboard and outboard flaps have separate bellcranks, but are mechanically connected © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Flap interconnection 38 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Variable elevator stop Power levers Stop shall be Stop is Caution light Both LOW Split Both HIGH unlimiting limiting unlimiting limiting STICK LIMIT STICK LIMIT 39 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Variable elevator stop Preflight check © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Option: Removal of the Variable elevator stop Normal CG limits: Without variable elevator stop : DA42 NG: DA42 NG -VI: 40 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Trim tabs Elevator trim: bowden cable © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Trim tabs Rudder trim: bowden cable 41 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional electric rudder pedal adjustment © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 42 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Power Plant © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Power plant „ 2 Austro Engines E4-B („Dash-6“: 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%, 2100 RPM („Dash-6“: 2300 RPM) 113,6 kW (152,3 DIN-HP) 43 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B Fuel High Pressure Pump Turbo Charger Oil Sump Alternator Gearbox Propeller Shaft Front View 44 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B Gearbox Glow Plug Control Unit Turbo Charger Fuel High Pressure Pump Water Pump Rip Belt Engine Oil Filter Housing Alternator Starter Oil Filler Cap Heat Exchanger Top View Propeller Shaft © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B High Pressure Pump Starter Side glass of Gearbox Oil Level Alternator Water Pump Heat Exchanger Rip Belt Turbo Charger Engine Oil Level and Refill Cap Left Hand View Engine Oil Filter Housing Propeller Shaft 45 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B Gearbox Oiltank © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B Alternator 46 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B Turbocharger © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Austro Engine E4-B Prop governor 47 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner ECU – Engine Control Unit © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner E.O.T. – Engine Order Telegraph 48 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner ECU test buttons Test on ground (PWR lever idle) 49 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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“ © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner ECU FAIL indication 50 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner ECU Abnormal checklist © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Simultaneous ECU fail indication 51 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 0% 100% 92% 20% 1600 1650 1700 1750 1800 1850 1900 1950 2000 2050 2100 2150 2200 2250 2300 2350 2400 0% 10% 20% 30% 40% 50% 60% 70% 80% 90% 100% Power Lever [%] Propeller Speed [rpm] • Power lever selects „LOAD“ in % • RPM automatically determined by selected power Power plant Recommended Cruise Power Setting: 75% © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 52 © Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner RPM malfunctions 53 © Peter Schmidleitner Compiled by Peter Schmidleitner 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) © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 „ 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 54 © Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 55 © Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Power plant limitations „ Intentional negative-g manoeuvers are not permitted „ No intentional shutdown „ below 3000ft AGL or above 10000ft PA „ without unfeathering accumulator 56 © Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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) and blends thereof Minimum cetane number of 37 (EN ISA 5165/ASTM D613) recommended Power plant fluid specifications 57 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Power plant fluid specifications „ Oil: „ SAE Grade 5W-30: „ SHELL HELIX ULTRA „ ADDINOL SUPER POWER MV 0537 „ BP VISCO 5000 5W-30 „ REPSOL ELITE COMMON RAIL 5W30 „ GULF FORMULA GMX „ SAE Grade 5W-40: „ SHELL HELIX ULTRA „ LIQUI MOLY 5W-40 LEICHTLAUF HIGH TECH „ MEGOL MOTORENOEL HIGH CONDITION „ SYNTIUM 3000 „ LUKOIL LUXE SYNTHETIC „ SAE Grade 0W-40: „ CASTROL SLX PROFESSIONAL LONGTEC © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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) 58 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Engine operation after line-up © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Engine operation 59 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Air inlets Air inlet for Cabin Heat Air inlet for coolant heat exchanger and gearbox Air inlet for engine air filter and intercooler Air inlet for Cabin Heat © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Air inlets Modified air inlet for Cabin Heat 60 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Air inlets Coolant heat exchanger Some air directed to the gearbox © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „Dash-6“ Air inlets Air inlet for Cabin heat, coolant heat exchanger, gearbox Air inlet for engine air filter and intercooler 61 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Air outlet © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Alternate air Alternate air lever Alternate air valve 62 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Use of Alternate Air AFM: © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Use of Alternate Air 63 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Checking oil levels Engine Oil Gearbox Oil © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Checking oil levels 64 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Power plant warnings © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Power plant cautions 65 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fire detection system „ Overheat detector in hot area of each engine „ Warning above 250°C „ Test button: © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 66 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Cooling System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cooling system 67 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cooling system Coolant Temp. < 88° © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cooling system Coolant Temp. > 88° 68 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cooling system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cooling system 69 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cooling system Cabin Heat © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cabin heating and defrosting system Cabin Heat from RH Engine Defrost from LH Engine 70 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cockpit Cabin Ventilation © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ventilation inlet RH wing underside 71 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Turbocharger System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Exhaust gas drives turbine Bypass for excess exhaust gas Turbo charger 72 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Compressor compresses intake air Turbo charger Exhaust gas drives turbine © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 73 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Fuel System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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) DA42 Fuel system 74 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ Max unbalance: 5 USG „ Fuel temperature limits: „ -30° C to +60° C DA42 Fuel system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Fuel level sensor 3 chambers Fuel filler 2 vents Drain Temperature sensor Low level sensor Fuel pumps 75 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Drain valve in nacelle (gascolator) © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Fuel cooler 76 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Fuel Cooler Air Outlet Fuel Cooler Air Inlet © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „dash-6“ Fuel system Fuel cooler 77 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „dash-6“ Fuel Cooler, Gearbox cooling Fuel Cooler Gearbox cooling © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system „Alternate means for fuel quantity indication“ Position: in front of drain, approx. 10cm outboard of nacelle 78 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system ON X-feed OFF © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Fuel Valve „ON“ Supply Return flow up to 71 USG/hr Average 45 USG/hr 79 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Fuel Valve „X-feed“ Supply Return flow © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42 Fuel system Fuel Valve „OFF“ opposite „X-feed“ Return flow Supply 80 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Supply Return flow DA42 Fuel system X-feed operation © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel valves schematic Supply Return flow ON X-FEED OFF ON X-FEED OFF ON OFF X-F OFF ON X-F ON OFF X-F OFF ON X-F 81 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Both valves closed Supply Return flow ON X-FEED OFF ON X-FEED OFF ON OFF X-F OFF ON X-F ON OFF X-F OFF ON X-F © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Both engines running Supply Return flow ON X-FEED OFF ON X-FEED OFF ON OFF X-F OFF ON X-F ON OFF X-F OFF ON X-F 82 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LH Eng. u/s, RH Eng. X-feed Supply Return flow ON X-FEED OFF ON X-FEED OFF ON OFF X-F OFF ON X-F ON OFF X-F OFF ON X-F © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Both engines from LH tank Supply Return flow ON X-FEED OFF ON X-FEED OFF ON OFF X-F OFF ON X-F ON OFF X-F OFF ON X-F 83 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel system „ For each engine: 2 parallel electrical low pressure fuel pumps „ Normal Ops: only one pump working „ When pump fails (low fuel pressure): automatic switch over to other pump „ When ECU switches over: fuel pumps switch over as well „ For TKOF, LDG and with fuel press failure: both pumps switched on manually with FUEL PUMP switch „ DA42NG (NOT for „Dash-6“): FUEL PUMP ON with CROSSFEED normally prohibited (only for emergency; special maintenance of high pressure pump required) © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel pumps 84 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel pumps © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel pressure warning „ Warning annunciation: L/R FUEL PRES 85 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel pressure warning © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 86 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks 87 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ One tank in each nacelle „ Capacity: 13,7 USG per side „ Useable: 13,2 USG per side Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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 Optional Auxiliary Fuel Tanks 88 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ AUX PUMP switched OFF automatically when: „ Main tank is full „ AUX tank is empty Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Maximum unbalance between main tanks: 1 USG if there is an unbalance between AUX tanks 5 USG 76,4 USG 26,4 USG 50 USG 2 x 38 USG 2 x 13,2 USG 2 x 25 USG Total AUX tanks Main tanks Optional Auxiliary Fuel Tanks 89 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks Drain 90 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner CAUTION light „ L/R AUX FUEL E „ L/R AUX tank empty and fuel transfer pump ON Optional Auxiliary Fuel Tanks 91 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 Optional Auxiliary Fuel Tanks 92 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Mass and Balance 3.20 AUX tanks 2.63 Wing tanks Lever Arm (m) Item Optional Auxiliary Fuel Tanks 93 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fuel quantity check „ Verify AUX empty „ Electrical Master ON „ Fuel transfer ON „ L/R AUX FUEL E CHECKED „ Verify AUX full „ Visual check Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Optional Auxiliary Fuel Tanks „ Fuel quantity between „FULL“ and „EMPTY“ cannot be determined 94 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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) Optional Auxiliary Fuel Tanks © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 95 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Diesel Operation © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42NG Diesel Operation 96 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42NG Diesel Operation „ Fuel Temperature „ Diesel Operation „ Minimum: -30°C „ Maximum: 60°C „ Modified G1000 Software: © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42NG Diesel Operation „ Operational Limitations: 97 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42NG Diesel Operation Diesel Fuel Classes (EN 590) („Temperate“ climatic zones) „Arctic“ climatic zones: other classes „Winter Diesel“: Class F © Peter Schmidleitner Compiled by Peter Schmidleitner 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 JET Fuel is used, make sure that no Diesel Fuel is remaining in the tanks. „ Otherwise the temperature limitations for Diesel Fuel operation must be observed. „ The fuel filter is not heated! 98 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42NG Diesel Operation „ If the airplane is operated in a cold environment, it must be changed from Diesel Fuel operation to JET Fuel 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. © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner DA42NG Diesel Operation Reduce by 30 ft/min 1-engine climb (Flaps UP and Flaps APP) Reduce by 60 ft/minClimb TKOF Distance (normal and short field) Add 7% TKOF Ground Roll Performance below 10° C OAT Make calculation from the basic AFM value before calculating additional corrections from other Supplements. 99 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Electrical System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system Power sources LH Alternator 28V 70A RH Alternator 28V 70A Main Battery 24V 13,6Ah ECU backup battery 7,2Ah ECU backup battery 7,2Ah Emergency Battery Not part of the electrical system 100 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system Power distribution Hot Battery Bus Battery Bus LH Main Bus LH ECU Bus Avionic Bus RH ECU Bus RH Main Bus © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system There are 2 versions of the electrical system „ „Modified electrical system“: „Standard“ in the „Dash-6“ 101 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „Modified“ Electrical system Hot Battery Bus Battery Bus LH Main Bus RH Main Bus Main Battery 24V 13,6Ah LH Alternator RH Alternator Starter Starter EPU ECU A B ECU A B LH ECU Bus RH ECU Bus ECU backup battery 24V 7,2 Ah ECU backup battery 24V 7,2 Ah Avionic Bus © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Hot battery bus „ Pilot map / reading light Battery bus „ LH / RH Main Bus „ LH / RH starter heavy duty power „ LH / RH ECU BUS (via diode) 102 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LH Main bus „ PFD „ Air Data Computer „ AHRS „ COM 1 „ GPS/NAV 1 „ Transponder „ Engine Instruments „ Pitot heating „ Oxygen system „ Gear control „ Gear warning „ Map light „ Flood light „ Taxi light „ Anticollision lights © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner RH Main bus „ Avionic Bus „ MFD „ Horizon „ Starter control „ Flap system „ Avionic/ CDU cooling fan „ Stall warning „ Autopilot warning „ Landing light „ Navigation lights „ Instrument lights 103 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Avionic bus „ COM 2 „ GPS/NAV 2 „ Audio panel „ Autopilot „ (Data Link) „ (WX 500) „ (ADF) „ DME „ (Weather Radar) © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system „ Connects Battery Bus to Battery (Battery Bus powers L/R Main Bus) „ Enables Alternator Switches Electric Master 104 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system „ Connects L/R Alternator to L/R Main Bus „ (In normal operation Alternator switches are always ON) L/R Alternator switch © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system „ 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 L/R Engine Master 105 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system „ Connects Avionic Bus to RH Main Bus Avionic Master Switch © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner External power connection 106 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Engine start with external power © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Engine start with external power Checklist: 107 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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. © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical malfunctions 108 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical malfunctions © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical malfunctions 109 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system 2 types of amperemeter: © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Electrical system Amperemeter on the G1000: 110 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Oxygen System © Peter Schmidleitner Compiled by Peter Schmidleitner 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 111 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ Exact calculation of duration : „ see AFM supplement „ it depends on the „ oxygen cylinder pressure „ number of users and types of dispensing equipment „ flight altitude Oxygen system 112 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system Oxygen cylinder Oxygen outlets © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system 113 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Filling table to chieve a cylinder (system) pressure of 1850 psi Oxygen system 114 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system 115 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system Quick connect Adjustable flow valve 116 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system Flowmeter Scale for mask and „standard“ cannula Scale for „oxysaver“ cannula © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system 117 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Mass and Balance 0.82 Oxygen cylinder Lever Arm (m) Item Oxygen system In fact relevant for removal only. Full Oxygen: CG moves FWD ~ 2mm © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Oxygen system 118 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Ice Protection System © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid ice protection system Product of CAV Aerospace Ltd (Celtic Aerospace Ventures Ltd) commonly knows as „TKS“ Ice protection system 119 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „TKS“ Ice Protection General © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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 Ice protection system 120 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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 Ice protection system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ Freezing point of glycol: „ -12° C „ Freezing point of glycol/water mixture: „ is lower !!! Ice protection system The „Eutectic-phenomenon“ 121 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „TKS“ Ice Protection DA42 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system 30 liters useable 122 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Minimum for dispatch: 22 liters 3/4 123 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE 2 „independent“ systems 2 x 2 pumps Normally powered from the LH Main Bus Ice protection system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Windshield ice protection „ 2 pumps for redundancy „ Only one pump operative at a time „ Operated for 5 seconds by a push button Ice protection system 124 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system icing conditions are more demanding or ice has already accumulated cover all known icing conditions as defined by CS25/FAR Part 25, Appendix CHIGH provide maximum possible protection for conditions outside the icing envelope as defined by CS25/FAR Part 25, Appendix C MAX icing conditions are encountered and prior to ice formation cover the more frequent but less severe known icing conditions as defined by CS25/FAR Part 25, Appendix C NORM Selected when Designed to Mode Operational modes © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Approach Climb + Cruise ~ 0,5 hr 2 pumps simultaneously ON for 2 minutesMAX ~ 1,0 hr 1 pump continuously ON HIGH **) ~ 2,5 hrs 2 pumps simultaneously, but cycled 30 secs ON and 90 secs OFF NORM *) Operating time Operating mode Mode Operational modes If no shedding of the ice in HIGH mode Æ proceed with checklist INADVERTENT ICING ENCOUNTER & EXCESSIVE ICE ACCUMULATION **) If no shedding of the ice in NORM mode Æ HIGH *) 125 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system NORM 30s ON, 90s OFF © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE Ice protection system 126 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system HIGH Continuously ON © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE Ice protection system 127 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system MAX HIGH + 2 minutes ON © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE Ice protection system 128 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Windshield deice 5 seconds © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE Ice protection system 129 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Main and Windshield pump selector © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE Ice protection system 130 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system ALTERNATE switch connects pump #2 directly to RH main bus System operates in HIGH mode © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Fluid tank Airframe and Prop Windshield LH Main BUS RH Main BUS MAX HIGH NORM PUMP 1 PUMP 2 ALTERNATE Ice protection system 131 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Ice lights © Peter Schmidleitner Compiled by Peter Schmidleitner 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 132 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Annunciator test DEICE LVL LO light ON DEIC PRES LO light ON after 120 seconds (simulates system ON) © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system 2 minutes 133 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system 134 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 Ice protection system 135 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Mass and Balance 1.00 De-icing fluid tank Lever Arm (m) Item Ice protection system 1 ltr: 1,1 kg 30 ltr: 33,0 kg © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ YES on panels „ Water, soap „ Isopropyl alcohol „ Ethyl alcohol „ Methylated spirit „ De-icing fluids „ AVGAS „ Jet fuel „ NO on panels „ Wax „ Methyl ethyl ketone (MEK) „ Lacquer thinner „ Other thinners and solvents Ice protection system 136 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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 Ice protection system Operational considerations © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Operational considerations „ what defines „icing conditions“? „ visually detected ice „ visible moisture and OAT +3°C or below 137 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner 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 138 © Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 139 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Operational considerations Airspeeds with ice on unprotected areas 118 KIASMinimum continuous climb speed in icing conditions (flaps UP) + 4-6 KIAS Stalling speeds 118 – 156 KIAS Continuous operation in icing conditions (except TKOF, LDG and maneuvers) prohibited Flaps LDG 90 KIAS Flaps APP 94 KIAS Flaps UP App/Ldg V ref in icing conditions, 2-eng or 1-eng © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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 Ice protection system Operational considerations 140 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Operational considerations Performance with residual ice or in icing conditions (ice on unprotected areas) Vyse: 88 KIAS One engine inoperative climb performance 250 fpm 12000 – 18000 ft positive ROC may not be achieved reduced by Rate of climb 200 fpm 6000 – 12000 ft 150 fpm Up to 6000 ft © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Operational considerations Performance in icing conditions (ice on unprotected areas) Cruise performance TAS -20 % Max demonstrated crosswind component in icing conditions: 20 kts 141 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Ice protection system Operational considerations „ Approach, landing in icing conditions (ice on unprotected surfaces): „ Gear down „ Flaps UP: Vapp min 94 KIAS „ Flaps APP:Vapp min 90 KIAS „ LDG distance acc. AFM ! „ When ice protection system fails: „ 118 KIAS until on final „ approach with flaps APP, minimum slip „ Vapp with residual ice min 90 KIAS „ Go around in icing conditions (ice on unprotected surfaces): „ with Flaps APP, gear down, 1900 kg, 88 KIAS: „ 8,2% (4,7°), 746 fpm climb © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner „ 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: „ MAX mode in intervals of 5 minutes until fluid dissipates from all panels Ice protection system Technical considerations 142 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Performance © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Performance „ DA42 NG according CS 23: „ Normal, Utility & Aerobatic category „ Reciprocating engine „ Weight < 2722 kg „ VSO < 61 kt 143 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Performance For commercial operation: „ DA42 NG according „Regulation Air Operations – OPS“: „ Propeller driven „ MAPSC max 9 „ Weight < 5700 kg „ Performance Class B © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner The „DA42“ and „Density altitude“ „ Attention! „ Performance data which are engine- power dependant cannot be determined by just using „Density Altitude“! „ Reason: the engine power output does not correspond to density altitude but pressure and temperature have their own, independent influence „ This is a feature of the ECU controlled, turbocharged Diesel-engine 144 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Stalling speeds © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 145 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner TOD, TOR tabular format Short Field TKOF, Flaps APP, 82 KIAS © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner TKOF distance Short Field TKOF, Flaps APP, 82 KIAS 146 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Grass Runway + 45% on soft ground ! TKOF should not be attempted > 25 cm + 25% >10 cm + 15% 5 - 10 cm additional + 10% + 10% - 5 cm Wet grass TKOF roll Length of grass © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Climb performance 2-eng Short field take-off (Flaps APP 85 KIAS): Reduce climb performance by 30 ft/min 147 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LD, LR tabular format © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Go around Required gradient acc. CS 23.77 (a): 3,3% at Sea Level 84 KIAS 84 KIAS 148 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner ROC to gradient conversion Formula in AFM: © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Grass Runway min + 25% >10 cm + 15% 5 - 10 cm additional + 10% + 5% - 5 cm Wet grass LDG run Length of grass 149 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Obstacles ? RWL TOD Obst. Dist. „d“ „h“ „d“= (RWL + Obst.Dist.) - TOD Gradient = („h“ / „d“) * 100 ROC = Gradient x TAS 0.95 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 150 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Performance „Dash-6“ © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Performance „ DA42 NG according CS 23: „ Normal, Utility & Aerobatic category „ Reciprocating engine „ Weight < 2722 kg „ VSO < 61 kt 151 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Performance For commercial operation: „ DA42 NG according „Regulation Air Operations – OPS“: „ Propeller driven „ MAPSC max 9 „ Weight < 5700 kg „ Performance Class B © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner The „DA42“ and „Density altitude“ „ Attention! „ Performance data which are engine- power dependant cannot be determined by just using „Density Altitude“! „ Reason: the engine power output does not correspond to density altitude but pressure and temperature have their own, independent influence „ This is a feature of the ECU controlled, turbocharged Diesel-engine 152 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Stalling speeds Most forward CG Power OFF KIAS values may not be accurate at stall © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner TKOF, LDG Performance general Effect of wind TKOF uphill slope, LDG downhill slope Headwind: minus 10% for each 14 kt Tailwind: plus 10% for each 3 kt 153 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner 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 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner TKOF Roll, TKOF Distance 154 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner TKOF Roll, TKOF Distance © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner TKOF on Grass Runway + 45% on soft ground ! TKOF should not be attempted > 25 cm + 25% >10 cm + 15% 5 - 10 cm additional + 10% + 10% 5 cm Wet grass TKOF roll Length of grass 155 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Climb Performance 2-eng © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Climb Performance 1-eng 156 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner ROC to Gradient conversion Formula in AFM: © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Cruising speed 75% 157 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LDG Roll, LDG Distance Flaps LDG © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LDG Roll, LDG Distance 158 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LDG Roll, LDG Distance Flaps APP or UP © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LDG Roll, LDG Distance 159 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner LDG on wet or Grass Runway LDG roll + 15% Paved RWY WET min + 25% >10 cm + 15% 5 - 10 cm additional + 10% + 10% - 5 cm Wet grass or soft ground Length of grass © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Go-Around Required gradient acc. CS 23.77 (a): 3,3% at Sea Level 160 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Obstacles ? RWL TOD Obst. Dist. „d“ „h“ „d“= (RWL + Obst.Dist.) - TOD Gradient = („h“ / „d“) * 100 ROC = Gradient x TAS 0.98 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 161 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Mass and Balance © Peter Schmidleitner Compiled by Peter Schmidleitner 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) 162 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Center of gravity envelope NG Dash-6 Without „Variable Elevator Stop“ When operating in known icing conditions © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Moment arms 3.97 Baggage Extension 3.65 Cabin baggage „Short baggage extension“: 1.00 De-icing fluid 3.20 AUX tanks 4.54 Baggage Extension 3.89 Cabin baggage 0.60 Nose baggage 2.63 Wing tanks 3.25 Rear seats 2.30 Front seats Lever Arm (m) Item 163 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner M&B calculation 3.20 Fuel (AUX tanks) 1.00 De-icing fluid 2.63 4.54 3.89 0.60 3.25 2.30 Lever arm Total TKOF Mass Fuel (main tanks) Zero Fuel Mass Baggage extension Cabin baggage Nose baggage Rear seats Front seats 3488.0 1450 Empty mass Moment (kgm) Mass (kg) 0 170 0 30 0 1683 150 1833 391.0 0.0 0.0 116.7 0.0 4028.7 394.5 4423.2 33 33.0 2.39 2.41 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Center of gravity envelope ZFM TOM 1683 kg, 2.39 m 1833kg, 2.41 m Trim weights in tail: 1-3x 5 kg; 15kg: CG shift of ~ 2cm: 164 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Emergency Equipment © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Emergency equipment 165 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Emergency Exit FWD 1 2 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Emergency Exit FWD 1 2 166 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner (Optional) Emergency Axe © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Intentionally blank 167 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Kinds of Operation Equipment List (KOEL) © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Kinds of Operation Equipment List KOEL 168 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Additional minimum equipment for the intended operation may be required by national operating rules and also depends on the route to be flown. Kinds of Operation Equipment List KOEL © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Kinds of Operation Equipment List KOEL 169 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Kinds of Operation Equipment List KOEL © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Kinds of Operation Equipment List KOEL 170 Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Diamond DA42 NG Servicing © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Unscheduled maintenance „ Required after „ Hard landings „ Propeller strike „ Engine fire „ Lightning strike „ Other malfunctions and damage 171 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Scheduled maintenance „ Every „ 100 hours „ 200 hours „ 1000 hours „ 2000 hours „ Annually © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Refuelling 172 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Refuelling © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Tire pressure Mainwheel 173 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Tire pressure Nosewheel © Peter Schmidleitner Compiled by Peter Schmidleitner 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 174 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Tow bar © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Control surfaces gust lock 175 © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Mooring © Peter Schmidleitner Compiled by Peter Schmidleitner Compiled by Peter Schmidleitner Mooring