DA42NG Flash Card Data - Layer 1 CSVUTF8
1
Q
VSO
A
Stall Speed Landing Configuration - 62 KIAS
2
Q
VS1
A
Stall Speed - Flaps Up - 69 KIAS
3
Q
VMC
Flaps Approach
A
Minimum Control Speed, Flaps Approach - 73 KIAS
4
Q
VR
(Flaps Approach)
A
Rotation Speed - Flaps Approach - 76 KIAS
5
Q
VR
Clean
A
Rotation Speed - Flaps Up - 80 KIAS
6
Q
VX
Flaps Approach
A
Best Angle of Climb - Flaps Approach - 82KIAS
7
Q
VYSE
A
Best Single Engine Rate of Climb - 85 KIAS
8
Q
VY
Flaps Approach
A
Best Rate of Climb - Flaps Approach - 85 KIAS
9
Q
VY
Clean
A
Best Rate of Climb - No Flaps - 90 KIAS
10
Q
VFE
Full
A
Max Full Flap Extended Speed - 113 KIAS
11
Q
VO < 3748 lbs
A
Operating maneuvering speed under 3748 lbs - 112
12
Q
3748 < VO < 3968
A
Operating maneuvering speed between 3748 and 3968 - 119
13
Q
VO > 3968
A
Operating maneuvering speed above 3968 = 122 KIAS
14
Q
VFE
Approach
A
Max speed for flaps approach 133 KIAS
15
Q
VFE
Full
A
Max speed for full flaps - 113 KIAS
16
Q
VNO
A
Maximum structural cruising speed - 151KIAS
17
Q
VLOR
A
Maximum Landing Gear Operating - Retraction - 152 KIAS
18
Q
VLOE
A
Maximum Landing Gear Operating - Extension - 188 KIAS
19
Q
VNE
A
Never Exceed Speed - 188
20
Q
Max Demo X-Wind Flaps Approach
A
20 Knots
21
Q
Max Demo X-Wind Flaps Up
A
25 knots
22
Q
What material is used to construct the airframe and flight controls?
A
GFRP - Glass fiber reinforced plastic (polymer)
23
Q
What material is used to construct the main bulkheads?
A
CFRP - Carbon fiber reinforced plastic (polymer)
24
Q
What is the DA42’s wingspan
A
44’ 6”
25
How are the ailerons, elevator and rudder actuated?
Control Rods
26
Does the DA42 have elevator and rudder trim?
Yes. Elevator trim is controlled by a trim control wheel between the seats and a split switch (arm and control) on the stick. Rudder trim is cable actuated by use of a knob beneath the center of the console.
27
Why is lightning protection required on the DA42?
Because the composite materials are poor conductors of electricity. As such there is no efficient way for the fuselage to dissipate the energy from a lightning strike, increasing the risk of serious structural damage. The lightning protection system provides a highly conductive path to transfer the energy away from the structure.
28
What is the elevator friction damper and why is it needed?
It prevent aerodynamic flutter in the event elevator trim cable loses function or breaks (FOM p 23)
29
What does the variable elevator backstop do and how is it actuated?
It's design to reduce the likelihood of a stall during a go around by limiting the up elevator deflection to 13° (normal is 15-1/2°). Actuated through an electronically driven linear actuator activated by extending flaps or power on both engines exceeding 20%.
30
How many hinges are on each flap?
The are ten aluminum bracket hinges on each flap.
31
How many doors are there on this aircraft?
Four, including the front canopy and baggage doors. There is the front canopy accessing the cockpit, one rear door on the left accessing the rear seats, and two baggage compartment doors accessing the baggage area, de-icing fluid reservoir, and main battery.
32
What are the possible flap settings?
There are three. Zero: Cruise setting. 20° - Flaps Approach, and 42° - Landing.
33
What flap settings are allowed for take-off?
Two. Normal take-off is flaps up, short field is flaps approach (DA42NG and VI Only). (20°)
34
What flap settings are allowed for landing?
One (as far as I could find). FLaps full.
35
What makes the flaps extend and retract?
Flaps are extended and retracted by control rods that connect to a single electric motor. Flap operation is commanded by a three way switch located on the console.
36
Describe the stall warning system.
A mechanical stall switch is located on the left wing. When a sufficiently high angle of attack is reached, it activates an audible alert inside the cabin. It's heated; the heat being activate by the pitot heat switch, with an override which is triggered by the squat switch on the right main landing gear.
37
Describe the landing gear.
The landing gear is in a tricycle configuration, hydraulically actuated and retractable. It incorporates nose gear based ground steering activated with the rudder pedals and supplemented with differential braking of the main gear.
38
What makes the landing gear extend and retract?
Landing gear is controlled through a switch that activates hydraulic landing gear actuators in a pressurized hydraulic system. Electronically controlled solenoids direct hydraulic fluid to both sides of the Landing Gear Actuators. When commanded to extend, the switch activates the extend and the retract solenoids and equal hydraulic pressure is provided to each side of the actuators. Greater surface on the retraction side of the actuator causes differential pressure that favors the retraction side of the actuators, causing the actuators to lengthen, which retracts the gear. In extending the gear, both solenoids are de-energized which causes the fluid to flow into the extend side of the actuator but out of the retraction side.
39
What is the purpose of the landing gear hydraulic accumulator?
The hydraulic accumulator helps maintain constant hydraulic pressure, reducing pump operating time and dampening the impact of pressure changes on the system.
40
How can you test the landing gear indicator lights?
By pressing the Gear/Fire Test button
41
What keeps the gear from being retracted on the ground if the gear selector is set to UP?
A squat switch, located on the left main gear, prevents the gear from retracting if the gear selector is set to UP when the aircraft is on the ground
42
What three conditions cause the gear warning horn to sound?
Engine power below 25% on either engine_Full flaps_Selector set to GEAR UP while aircraft is on the ground.
43
Describe the manual gear extension procedure.
Press the Gear/Fire Test to check lights_Verify Electric Master is On and Voltage is 24.1 to 28.5_Verify Gear Selector is on Down_Reduce speed below VLO (DA42NG: 152)_Pull the Manual Gear Extension handle_Induce moderate yawing and pitch changes to assist gear in gravity drop.
44
Describe the brake system.
The DA42NG used hydraulically actuated disc brakes, located on each of the main gear and activated by a brake cylinder at each pedal. (2 for the pilot and 2 for the copilot.
45
How would you activate the parking brake?
Push the parking brake lever to lack and then pumping the brakes two or three times.
46
What is the total usable fuel quantity?
Total usable fuel is 78.2 gallons.
47
How many chambers make up each main wing tank?
Each main fuel tank consists of three chamber connected rubber hoses.
48
How many chambers make up each auxiliary tank?
Each auxiliary tank, located behind the engines, consists of… [Couldn't find an answer - assume 1 each.]
49
Which tanks have fuel gauges?
Main fuel tanks only. Located in the outer and inner chambers of each.
50
What grade of fuel is used?
Jet A and Jet A-1 are approved fuels.
51
Can you feed fuel from the right main tank to the left engine?
Yes, by using the X-Feed setting on the fuel selector.
52
How many fuel pumps are there?
There are four low-pressure electric fuel pumps, excluding the auxiliary transfer pumps in the DA42NG. There is one for each ECU.
53
Why is a fuel cooler required?
The fuel is compressed to 15,000 psi prior to being delivered to the engine. A byproduct of the compression is heat. Because more fuel is compressed than the engine needs, and the remainder is returned to the tanks, that fuel has to be cooled back down to prevent fuel over-heating.
54
Are the main tanks heated?
The main tanks are heated by the reintroduction of fuel that had been pressurized, then depressurized and then cooled.
55
Are the auxiliary tanks heated?
The auxiliary tanks do not received return fuel and are not pressurized.
56
Can the engine draw fuel directly from the auxiliary tanks?
No. Fuel must be transferred to the main tanks, and each auxiliary tank can only transfer fuel to the main tank on the same side.
57
What is PRIST, and is its use allowed?
PRIST is a brand of FSII (fuel system icing inhibitor), or an anti icing, antimicrobial fuel additive and it is permitted in the DA42NG.
58
Where are the aircraft bonding (grounding) locations to be used when fueling?
Either left or the right engine exhaust stack can be used.
59
Describe the DA42s engines.
The DA42NG is powered by 4-cylinder, compression combustion diesel engines which are turbocharged and water cooled. Engines have 168 HP at 100% power (with a time limit of 5 minutes) and 153 horsepower at 92% power, which is the maximum approved continuous power.
60
Does the G1000 display engine RPM or propeller RPM?
The G1000 display propeller RPM.
61
What is an ECU (or FADEC), how many are installed, and how are they powered? (Learn more about this…)
There are a total of four ECUs (or FADECs, standing for Full Authority Digital Engine Control)-two per engine-and they are electrically powered. The ECUs monitor and regulate key engine parameters including: Manifold pressure and air temp; Propeller RPM; Turbocharger Wastegate Position; Power Lever Position; Crankshaft and Camshaft Position (????), Fuel Injection Timing, Fuel Pressure, and Glow Plugs
62
What are the starter limitations?
Starter limitations are a 10 second max starter motor engagement, with 20 second "rests" between engagements and a maximum of 6 tries, after which the starter needs to cool for 30 minutes.
63
Can the engines continue to run without electrical power?
No. Because the ECUs require power. Without it, the engine will stop and the propellers will feather. (ECUs have back-up batteries.)
64
What five things occur when the engine master is turned on?
Turning on the master switch will: Connect the engine starter relays to the battery bus; Connect the ECUs to the battery back-up; Cause the ECUs to activate the glow plugs for engine start; Connect the alternator to the excitation battery; Rel ease engine oil from the propeller unfeathering accumulator in the gear box and into the propeller hub.
65
What are the engine oil capacity and operating limits?
Oil capacity (DA42NG) is 7.0 liters (7.4 quarts) with a minimum of 5.0 liters (5.28 quarts). An oil quantity between 4.5 and 6 is considered acceptable, and minimum allowable consumption for planning is 0.1 liter per hour.
66
What kind of engine oil does the DA42 use?
Aerostal Oil Diesel 10W-40 is listed as a recommended oil.
67
How are the engines cooled?
The engines are water cooled and use a one to one water/antifreeze mixture circulated by an engine driven pump. Heat exchanges provide heat for cabin heating and canopy defrost.
68
Where is the coolant level sensor located?
The coolant level sensor is located in the expansion tank, and cannot be checked during preflight. A warning displays is coolant level falls below normal operating temperature.
69
What do you do if low coolant level and high coolant temperature warnings are both displayed?
If both high engine temperature and low coolant level warnings are displayed, assume a coolant leak, prepare for engine failure and land as soon as possible.
70
What is the purpose of the intercooler?
The turbocharger compresses the air to compensate for lower density at altitude. The compression causes the air to heat. The intercooler, cools it down prior to its delivery to the engine for better engine performance.
71
Describe the engine fire protection system.
The engine fire detection system uses a thermocouple located near the turbocharger to detect high engine compartment temperature. If the compartment temperature exceeds 20°C, the system will activate a aural alarm. It can be tested by pressing and holding the Gear/Fire Test button.
72
What is the function of the gear box?
The gear box reduces engine RPM by a ration of 1:1.69 for a lower propeller RPM, and includes a clutch or dual mass flywheel that isolates the propeller from torque pulses that occur in the diesel engine.
73
Describe the propellers.
The DA42NG uses an MT Propeller (German manufacturer), which is a three blade, wood composite propeller with a FRP (fiber reinforced plastic) coating. The inner edge is protected by a rubber strip and the outer edge by stainless steel cladding. The propeller is a hydraulically regulated constant speed propeller and is fully feathering. The propeller uses counterweights and spring tension to move to a coarse pitch, and moves to fine pitch angles through the use of the Constant Speed Unit (CSU), a propeller governor, controlled by the ECU, that adjusts the propeller angle by varying the volume of gearbox oil inside the propeller hub.
