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FLSK EK22-1 > Dash-One: Section 1 > Flashcards

Dash-One: Section 1 Flashcards

(47 cards)

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1
Q

T-17 General Information

A

Single engine, propeller driven, all metal shoulder winged monoplane of semi-monocoque design.

Tricycle, fixed landing gear and can accommodate a crew of 3, with dual controls available in a side-by-side arrangement in the cockpit, and a third, rearward facing seat in the rear compartment.

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2
Q

Aircraft Gross Weight:

  • Normal:
  • Utility I:
  • Utility II:
  • Aerobatic:
A
  • Normal: 1200 kg
  • Utility I: 1125 kg
  • Utility II: 1000 kg
  • Aerobatic: 900 kg
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3
Q

Lighting equipment

A

The aircraft is equipped with:

  • Landing light
  • Taxi light
  • Navigational lights
  • Strobe lights
  • Anti-collision light
  • Dome light and map reading lights
  • Instrument lights
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4
Q

Propeller Fine Pitch

A

Fine pitch (high RPM) is maintained by means of oil pressure.

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5
Q

Propeller Coarse Pitch

A

Coarse pitch (low RPM) is maintained by a mechanical device comprising counterweights which are acted upon by centrifugal force.

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6
Q

Propeller Control

A

The propeller control has a detent in the high RPM portion of the operating range which allows for adjustment from 2500 RPM to 2700 RPM. To move the propeller control lever to the LOW RPM position the detent must be passed.

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7
Q

Propeller Governor

A

When the pilot has selected a desired engine RPM, the propeller governor will automatically adjust the pitch of the propeller blades to maintain selected RPM, by varying the oil pressure.

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8
Q

NOTE: Propeller Oil Pressure Loss

A

In case of total oil pressure loss the propeller blades move into coarse pitch (low RPM), thus preventing engine over speed.

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9
Q

NOTE: Throttle Control

A

Due to the constant speed propeller, opening of the throttle will increase the manifold pressure, not necessarily the RPM.

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10
Q

How is manifold pressure indicated?

A

In inches of Mercury.

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11
Q

Total Fuel Quantity

A

Each wing is equipped with an integral fuel tank holding 23,5 US gallons thus giving the aircraft a total capacity of 47 US gallons.

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12
Q

Unusable Fuel Quantity

A

The tanks can be completely emptied in level flight, but a normal amount of unusable fuel is 2,5 US gallons per tank. Thus, the total usable fuel is 42 US gallons.

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13
Q

NOTE: Fuel Quantity Accurate Indication

A

Straight and level flight is required for accurate indication of fuel quantity.

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14
Q

WARNING: Fuel Indication

A

Straight and level coordinated flight is required for the most accurate indication of the fuel quantity, but with partly filled tanks each fuel indicator may i.a.w. the technical specifications show as much as 3 1/2 US Gall more than the actual quantity, - and with completely empty tanks indicators may show as much as 2 Gall in each tank.

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15
Q

*NOTE: Fuel Tank Selector

A

From the OFF position the fuel tanks can be selected only by turning the fuel selector clockwise. Any tank can now be selected by turning the selector in either direction. The OFF position can be selected only by turning the fuel selector counterclockwise with the center lock depressed.

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16
Q

Fuel Pumps

A

The engine is equipped with an engine driven diaphragm fuel pump. An electrically driven auxiliary fuel pump is also incorporated in the fuel system.

(OBS: Only the auxiliary fuel pump can be operated by the pilot)

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17
Q

Generator (Volt, Output and Bus)

A

The electrical system is powered by an engine driven 28V generator with a maximum output of 70 amp.

The generator supplies power to both the primary and the secondary buses.

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18
Q

Battery (Volt and Bus)

A

24V.

In the ON position the aircraft battery is connected to the primary bus only.

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19
Q

CAUTION: Battery OFF with Generator ON

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A

If battery switch intentionally or unintentionally is turned odd while the generator is charging primary and secondary buses, do not turn battery back on, since it may cause damage to the voltage regulator and thence cause loss of generator power.

20
Q

NOTE: Battery with External Power

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A

BAT switch shall be in OFF position when external power is used, otherwise the external power is shut off.

21
Q

NOTE: EPU

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A

To operate the Standby Attitude Indicator, the VHF 2 COM radio and the map lights the EPU switch must be switched in ON position. Leaving the EPU in ON after aircraft shutdown could result in EPU battery discharge or damage.

22
Q

CAUTION: EPU with External Power

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A

The EPU switch shall be in OFF position whenever external power is connected to the aircraft.

23
Q

Canopy Warning Light

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A

The canopy warning system includes two micro-switches installed in the canopy frame.

When the canopy is unlocked and the BAT switch is ON, the red light CANOPY will illuminate. In addition to this warning, also an audio signal sounds, when any of the IGN switches is ON and the canopy is unlocked.

24
Q

Generator Caution Light

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A

An amber GEN caution light will illuminate if the voltage of the bus drops below 25 +/- 0,5V.

25
Engine Fire Warning Light
A red FIRE ENG caution light will illuminate if the temperature within the engine compartment rises to 275°C.
26
Oil Pressure Warning Light
A red OIL PRESS caution light will illuminate if the oil pressure drops below 6,5 +/- 2psi.
27
Fuel Pump Caution Light
An amber FUEL PUMP caution light will illuminate if the fuel pump is ON and delivering a minimum fuel pressure of 20 +/- 1psi.
28
Stall Warning
The stall warning transmitter is located on the RH wing and the horn will sound 5-10kts above the stalling speed.
29
WARNING: Rudder Pedals
Ensure that the locking pins are fully engaged when the rudder pedals have been moved.
30
CAUTION: Elevator Trim
Using both trim systems at the same time may cause damage to the system.
31
Wing Flap System (Pre-selected positions)
The flaps have 4 pre-selected positions: 0°, 10°, 20° and 38°.
32
Flight Instruments (Pressure Instruments)
- Altimeter - Airspeed Indicator - Vertical Speed Indicator
33
Flight Instruments (Electrical Instruments)
- Main Attitude Indicator - Stand-by Attitude Indicator - Radio Magnetic Indicator - Turn/Slip Indicator
34
NOTE: Obstructed Static Ports
When the aircraft has been exposed to moisture and/or icing conditions (especially on the ground), the possibility of obstructed static ports should be considered. Partial obstructions will result in the rate of climb indication being sluggish during a climb or descent. Verification of suspected obstructions is possible by switching to the ALT STATIC AIR system and noting a sudden sustained change in rate of climb. This may be accompanied by an increase in indicated airspeed of 5-10 kts and altitude changes beyond normal calibration differences.
35
NOTE: Inoperative Altimeter Internal Vibrator
If the altimeter's internal vibrator is inoperable, the pause-and-accelerate effect may be exaggerated. The pilot should be especially watchful for this behavior, when the minimum approach altitude lies within the "8" to "2", sector of the scale, e.g., 800-1200 feet, 1800-2200 feet, etc.
36
Attitude Encoder/Pneumatic Altimeter Diagonal Warning Signal
The diagonal warning symbol appears below 10.000 feet The CODE OFF warning symbol means that the altitude encoder is inoperative.
37
Attitude Encoder/Pneumatic Altimeter CODE OFF
Display of the CODE OFF flag only indicates an encoder power failure or a CODE OFF flag failure. In this event, check that DC power is available, and that the circuit breakers are in. If the flag is still visible, radio contact should be made with a ground radar site to determine, whether the AIMS altitude reporting function is operative, and the remainder of the flight should be conducted accordingly.
38
Main Attitude Indicator
The main attitude indicator is a direct reading instrument indicating pitch and bank attitude. Its operational range is +/- 360° both in pitch and bank.
39
Main Attitude Indicator Erection Rate
The system will erect the vertical gyro in pitch and roll to the vertical at a saturated erection rate of 2,5° per minute minimum.
40
Main Attitude Indicator Start Up
After the instrument has been energized, check that the power supply failure warning flag has disappeared. Within 30 seconds after power has been applied, gently pull the resetting knob. This operation must always be carried out after the instrument has been energized, and regardless of why the instrument was energized.
41
Main Attitude Indicator Resetting
In the event of abutment against the stops in pitch during a loop, a deflection can occur. This can be cancelled instantly by a resetting operation, as soon as the aircraft is in level flight once more. Failing this, the error will be absorbed in a few minutes by the action of the erection system.
42
Fire Detection System
A fire detection system with a detector is installed in the engine compartment through the right hand rear baffle plate
43
Alternate Air
In case of blocking of the induction air intake (ice formation, etc.) the air supply to the engine is automatically drawn from the engine compartment. This alternate air supply, which is unfiltered, has only minor negative effect on the engine performance.
44
NOTE: Exhaust Gas Temperature Indicator
During VHF-AM transmissions the EGT-indicator will show a false value caused by radiation from the VHF-AM transmitter.
45
Friction Lock
A friction lock located on the LH side of the centre pedestal is used to adjust the friction level of the throttle, mixture and propeller control levers.
46
Carbon Monoxide Indicator
Presence of CO will gradually turn the indicator black.
47
NOTE: Fire Extinguisher
If the fire extinguisher is used at a short distance and aimed at panels etc., the liquid HALON 1211 may get into the eyes and cause irritation. It is therefore suggested to lower the helmet visor before using the extinguisher.

FLSK EK22-1 (6 decks)

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