DA42 Austro Question Bank Index

DA42 Austro Question Bank Index

• Section 1 is on Page 2
• Section 2 is on Page 3
• Section 3 is on Page 11
• Section 4 is on Page 14
• Section 5 is on Page 15
• Section 6 is on Page 18
• Section 7 is on Page 19

Section 1

• DA42 wingspan: 13.42 m
• DA42 wing area: 13.96 m²
• DA42 wing dihedral angle: 6 degrees
• DA42 wing aspect ratio: 11.06
• DA42 horizontal tail angle of incidence: -1.1 degrees
• DA42 rudder area: 0.78 m2
• DA42 wheel base: 1.735m
• DA42 propeller engine has 3 blades

Section 2

• The datum plane is located 2.196 meters (86.46 in) forward of the most forward point of the root rib on the stub wing
• Minimum speed for engine restart: 100 KIAS
• Exceeding MTOW results in:
• Degrading flight characteristics
• Overstressing aircraft structure
• Degrading flight performance
• Maximum continuous RPM: 2300
• VNAV information use for Instrument Approach Procedures does not guarantee step-down fix altitude protection
• Operation is prohibited north of 72° N and south of 70° S latitudes
• L/R ALTN FAIL means Left/Right engine generator has failed
• Maximum oil pressure: 6.5 bar
• GIA FAN FAIL means the cooling fan for the GIAs is inoperative
• Max load in Cockpit Baggage Compartment: 30 kg
• Negative Maneuvering Load Factor at Vo is -1.52
• When the seal on the emergency switch is broken, VFR flights can be taken
• Va for the DA42 above 1800 kgs: 122 KIAS
• Maximum landing gear extension speed of DA42: 188 KIAS
• Maximum landing gear retraction speed of DA42: 152 KIAS
• Maximum Emergency Gear Extension speed: 152 KIAS
• Flaps UP, Minimum control speed airborne of DA42 NG (Vmca): 71 KIAS
• VNO Max structural cruising speed of DA42 NG: 151 KIAS
• VNE Never exceed speed in smooth air of DA42 NG: 188 KIAS
• Yellow band "Caution" range, "Only in smooth air" of DA42: 151-188 KIAS
• Red band Minimum control speed, single engine of DA42: 71 KIAS
• Blue band Best rate of climb speed, single engine of the DA42: 85 KIAS
• The Positive Maneuvering Load Factor at Vo is 3.8
• The Positive Maneuvering Load Factor at VNE is 3.8
• The Positive Maneuvering Load Factor with Flaps down is 3.8
• The Negative Maneuvering Load Factor at Vo is -1.52
• The permitted negative Load Factor at VNE is -1.52
• The Total usable fuel quantity of the main fuel tanks of DA42 in gallons is 25x2
• Maximum Landing Weight of DA42 NG: 3979 lbs
• Oil temperature should be between 50-135 Deg F for continuous operation
• The minimum coolant temperature at start up: -30 deg C
• Maximum Gear box temperature:: 120 deg C
• Max speed that the landing gear wheels can be subjected to: 188 KIAS
• One engine inoperative speed for best ROC (Vyse) for DA42 NG: 85 KIAS
• Maximum flap extended speed in approach (VFE LDG): 113 KIAS
• VNO, maximum structural cruising speed of DA42 NG: 151 KIAS
• Green band Normal operating range of DA42: 68 - 151 KIAS
• Max flap extended speed is VFE
• Max number of occupants of DA42 is 4
• Minimum number of crew required for DA 42 NG is 1
• Normal Operating range of Oil Pressure is 2.5-6.0 bar
• Minimum and maximum oil quantity of DA42 NG is 5 Ltr, 7 Ltr
• Maximum oil pressure 6.5 bar
• Maximum and minimum voltage of the battery is 32.0 V, 24.1 V
• Max usable fuel in the main tanks is 2x 25 US gal
• The maximum difference allowed in fuel quantity between LH/RH main tanks is 5 USG
• Aerobatics, Spinning, & flight maneuvers are not permitted with more than 60° of bank angle in normal category
• The fuel used in DA 42 NG aircraft is JET A, JET A1
• The Engine oil used is SAE Grade 5W-30
• The Never Exceed Speed in smooth air of DA42 is 188 KIAS
• Usable fuel in auxiliary tanks is 2X13 US Gallons
• The max oil temperature of DA42 engine is 140 degrees C
• Minimum and maximum fuel pressure of DA42 NG is 4 bar, 7 bar
• The red arc of voltage starts at 24.1 V
• If any one power lever is below 25% with the landing gear retracted, the warning horn sounds to alert the pilot
• The landing gear unsafe warning light illuminates if the landing gear is not in the final up, not in the final down, or not in the locked position

Section 3

• Reduce airspeed below 110 KIAS and apply moderate yawing and pitching to assist in bringing the landing gear into the locked position
• If the oil pressure has not moved in the green sector after starting, shut down engine immediately
• If the oil pressure indication drops below the green sector and the oil temperature is normal, it is probable that the oil pressure indication is defective
• Best Rate-of-Climb Speed on one engine of DA42: 81 KIAS
• Manual extension of landing gear can take 20 sec
• Yawing and pitching can be done to assist the landing gear to lock down in case of manual lowering of the undercarriage. The speed should be reduced to 110 kts
• Max demonstrated airspeed for emergency opening the front canopy in flight: 117 KIAS
• Landing gear unsafe light should not be on for more than 20 sec
• After six starts the starter should be allowed to cool for 30 minutes
• If the auto pilot trim is inoperative disconnect the autopilot and trim the plan manually
• Depressing and holding the COM transfer button on the G1000 for 2 secs will tune the emergency frequency
• The failure of the Attitude and Heading Reference is indicated by All of the above which include:
• The Removal of the sky/ground presentation
• Red X
• Yellow "AHRS failure"
• In case of a RIGHT engine failure, to maintain lateral balance CROSS FEED must be selected on the Left fuel selector
• If the fuel selector is set on CROSS FEED, the engine will be supplied with fuel from the main tank on the opposite side
• If the Landing gear CB is pulled Red light is illuminated
• If the loss of power was due to the unintentional setting of the throttle lever, adjust the friction lock

Section 4

• Minimum Airspeed for Rotation with flaps up during takeoff for DA42 (Vr) upto 1900 kgs is 76 KIAS
• Minimum Airspeed for take-off climb with Flaps up(best rate of climb speed: Vy) upto 1900 kgs is 90 KIAS
• Minimum Final Approach Speed with Landing Flaps upto 1900 Kgs is 84 KIAS
• Minimum Go Around Speed for DA42NG Flaps up is 80 KIAS
• White band Operating range with flaps fully extended of DA42: 62-113 ΚIAS
• Toe brakes are used to augment steering during take-off in strong crosswinds
• Do not operate the starter motor for more than 20 Seconds
• If the oil pressure has not moved into the green sector within 3 seconds after starting, switch off the engine Master
• The electrically driven hydraulic pump comes on for 5-10 seconds when the electrical master is put on
• To check cross feed the engines should be run for a minimum of 30 seconds
• If take-off with the canopy in the cooling gap position, land the aircraft and close
• The engine instruments are available on the MFD only when the G1000 power up is completed

Section 5

• Stalling speed with FLAPS LAND, GEAR DOWN: 57 KIAS
• Stalling speed with FLAP UP, GEAR UP: 64 KIAS
• Maximum Operating altitude of DA42 18000
• The staling speed with flaps up and landing gear up is 68 Kts at a weight of 1900 Kgs
• Maximum demonstrated crosswind for flaps UP is 12 Kts
• The Maximum demonstrated crosswind for flaps APP is 20 Kts
• An upslope of 1% increases take off distance by 10%
• For each 14 Knots of headwind decrease takeoff distance by 2%
• For each 3 Knots of tailwind increase takeoff distance by 10%

Section 6

• The Datum plane is located at a distance of 2.196m from the wing root

Section 7

• Fuel information displayed when pushing the FUEL button: Are supplemental information and requires verification by the flight crew
• The primary function of the PFD is to provide attitude, heading, air data, navigation, and alerting information to the pilot
• The DA42 has a semi-monocoque structure
• L/R Oil Pressure Low: Left either Right engine oil pressure is less than 0.9 bar
• The ECU backup battery provides electrical power for ECU 30 minutes
• In case of strong winds, wind shear and turbulence: the airspeed on approach should be higher
• The Fuel Quantity Indicator range of DA42 NG aircraft is 1-25 Gal
• The Design of the Prop Feathering System does not allow the feathering of a prop with speed below 1300 RPM
• When the Lower light (WHITE) is illuminated, the flaps are in Landing position
• Instrument No 27 is the Auto Pilot control
• The Instrument No 21 is the Emergency Compass
• Instrument No 09 is the rotary button for instrument lights
• Instrument No 2 is the Avionics Master
• The minimum propeller RPM for feathering is 1300 RPM
• The DA 42 has a 28 V DC system
• The Warning Message or text is shown in Yellow
• Take offs are not permitted with the fuel selector knob in Off
• Before moving the fuel selector knob from CROSSFEED –ON or ON-CROSSFEED ensure the fuel pump is switched OFF