DA 42 typeQuest

Question 1

1) Name of engines:

Answer 1

2 Thielert Aircraft Engines TAE125

Question 2

2) Engine performance at MSL:

Answer 2

Max. power 99kW (135 HP) at 2300 RPM

Question 3

5) Oil quantity, MIN/MAX(L) per engine:

Answer 3

4.5/6 liters

Question 4

8) Describe how the engines are cooled:

Answer 4

Each engine is liquid cooled. The liquid cooling system consist of a radiator and a bypass to tis radiator.

Question 5

9) Maximum engine restart altitude: „

Answer 5

Max. restart altitude: 6000 ft, 80–120 KIAS

Question 6

11) How are the flaps operated:

Answer 6

a. The flaps are driven by an electric motor and have 3 settings. Cruise, approach and landing.

Question 7

12) How many oil systems are, and what are their purposes (per engine

Answer 7

Two oil systems.

1. Lubrication system for engine and turbo chrarger placed in a wet sump and cooled separted from:
2. Gearbox and propeller governor system, which is the second oil circuit lubricates he gear and serves the governor system and the regulation of the propeller.

Question 8

13) What happens in case of loss of propeller governor oil:

Answer 8

a. The propeller will feather and you must control RPM with throttle.

Question 9

14) Describe how is feathering of a failed engine, achieved:

Answer 9

Engine master off

Question 10

15) MAX operating altitude (Absolute ceiling):

Answer 10

18000

Question 11

16) Total fuel quantity MAIN TANKS:

17) Usable fuel quantity MAIN TANKS:

Answer 11

52 US gal.

2x25 US gal

Question 12

18) Total fuel quantity AUX TANKS:

Answer 12

a. 2x13.7 US gal

Question 13

19) Usuable fuel quantity AUX TANKS:

Answer 13

a. 2x13.2 US gal

Question 14

20) Describe the fuel system and its’ components:

Answer 14

a. fuel is stored in the tanks which are located in the wings.
On each engine fuel is injected with high pressure directly into the cylinders. The injection nozzles (one per cylinder) are supplied with fuel by the common rail. Pressure inside the rail is generated by a high pressure pump which receives fuel from a low pressure pump. Depending on the power setting the rail pressure is controlled by the ECU through an electric valve. Both pumps are powered mechanically by the engine. Fuel that is not injected is fed back into the appropriate wing tank. Both sides of the fuel system are interconnected by crossfeed lines. In each engine nacelle an auxiliary fuel tank may be installed

Question 15

21) Describe the purpose of the cross-feed function:

Answer 15

When CROSSFEED is selected, the engine will draw fuel from the tank on the opposite side in order to extend range and keep fuel weight balanced during single engine operation.

Question 16

23) Describe the DA42 electrical system:

Answer 16

The DA42 has 28 volt DC system, which can be sub-divided into:

1. Power generation: provided be two 60 ampere alternators.
2. Storage: Main battery power is stored in a 24 V, 10 ah lead-acid battery.
3. Distribution. Electrical power is distributed via the hot battery bus, the battery bus, the LH(RH) ecu bus, LH(RH) main bus, and the avionic bus.
4. Consumers: Everythin there needs power is connected to the appropriate bus via automatic circuit breakers.

Question 17

24) Describe the various batteries in the electrical system, and their

Answer 17

functions: Main battery is a 24 V which is connected to the “hot battery bus” and to the “battery bus”
When the engines are not running, a 10 ampere 24-volt battery provides current for starting.
In addition, a non-rechargeable dry battery is installed as a further source of power for the attitude gyro and the flood light.
To support the alternator electrical power supply to the ECUs in case of a malfunction of the main battery, additional sealed-lead-acid batteries are connected.

Question 18

25) Describe the purpose of the ECU:

Answer 18

a. The ECU monitors, controls and regulates all important paramaters for engine operation.

Question 19

26) How many static sources does the DA42 have:

Answer 19

a. Two. Installed at the lower and rear edges of the same probe

Question 20

27) Is there an alternatic static source:

Answer 20

a. yes, static pressure in the cabin can be used.

Question 21

29) MZFM/MTOM/MLM:

Answer 21

a. 1730/1785/1700 kg.

Question 22

32) State the maximum load factor at Va:

Answer 22

3.8 g

Question 23

41) Will a faulty hydraulic system affect the operation of landing gear?

Answer 23

o The landing gear might extend as the hydraulic system pressure decreases. Consider for higher aerodynamic drag, resulting in degraded flight performance, increased fuel consumption and decreased range.

Question 24

46) Describe the “variable elevator stop”:

Answer 24

a. The DA42 is equipped with an electrically acutuator that limits the elevator-up travel to 13° as soon as the power setting of both engines exceeds approx 20% power and flap selector to LDG. This is 2.5° less than the 15.5° full deflection.