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POH PA34 > POH 4.9 Electrical System > Flashcards

POH 4.9 Electrical System Flashcards

1
Q

POH.4.9.1 General information

A
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2
Q

What’s the electrical system of the Seneca II capable of?

A

The electrical system of the Seneca II is capable of supplying sufficient current for complete night IFR equipment.

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3
Q

POH.4.9.2 Alternators

A
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4
Q

How many alternators does the Seneca II have?

A

Electrical power is supplied by two 65 ampere alternators, one mounted on each engine.POH.4.9.3 Battery

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5
Q

POH.4.9.3 Battery

A
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6
Q

How many ampere-hour, volt and what type of current does the battery provide?

A

A 35 ampere-hour. 12-volt battery provides current for starting, for use of electrical equipment when the engines are not running, and for a source of stored electrical power to back up the alternator output.

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7
Q

Where is the battery located and how can we access it? How is it kept charged?

A

The battery, which is located in the nose section and is accessible through the forward baggage compartment, is normally kept charged by the alternators.

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8
Q

POH.4.9.4 Alternator Control Units

A
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9
Q

How is effective load sharing maintained while regulating electrical system bus voltage?

A

Two solid state voltage regulators maintain effective load sharing while regulating electrical system bus voltage to 14-volts.

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10
Q

What’s the purpose of the overvoltage relay? How does it work?

A

An overvoltage relay in each alternator circuit prevents damage to electrical and avionics equipment by taking an alternator off the line if its output exceeds 14-volts.

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11
Q

What happens when there is an overvoltage?

A

If this should occur, the alternator light on the annunciator panel will illuminate. Voltage regulators and overvoltage relays are located forward of the bottom of the bulkhead separating the cabin section from the nose section.

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12
Q

POH.4.9.5 Switches

A
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13
Q

Where are most of electrical swtiches located?

A

Most of the electrical switches, including the battery switch and switches for alternators, magnetos, starters, fuel pumps, pitot heat and lights are conveniently located on the switch panel to the left of the pilot’s control wheel.

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14
Q

POH.4.9.6 Circuit Breakers

A
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15
Q

Where are the breakers that protect the eletrical system and equipment?

A

The electrical system and equipment are protected by circuit breakers located on a circuit breaker panel on the lower right side of the instrument panel.

he circuit breaker panel is provided with enough blank spaces to accommodate additional circuit breakers if extra electrical equipment is installed.

In the event of equipment malfunctions or a sudden surge of current, a circuit breaker can trip automatically.

The pilot can reset the breaker by pressing it in (preferably after a few minutes cooling period). The circuit breakers can be pulled out manually.

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16
Q

POH.4.9.7 System Monitors

A
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17
Q

How many RPM are required to obtain full alternator output?

A

Approximately 2000 RPM or more is required to obtain full alternator output of 65 amperes.

It is normal to have zero output at idle RPM. This is due to the reduced drive ratio from the engine.

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18
Q

How do we monitor the electrical system operation?

A

Dual ammeters and the ALT annunciator light provide an easy means of monitoring the electrical system operation.

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19
Q

How is the output of the alternators indicated?

A

The two ammeters (load meters) indicate the output of the alternators.

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20
Q

What if an ammeter indicates a load much higher than the known consumption of the electrical equipment in use?

A

Should an ammeter indicate a load much higher than the known consumption of the electrical equipment in use. it should be suspected of a malfunction and turned off.

In this event, the remaining alternator’s ammeter should show a normal indication after approximately one minute.

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21
Q

What if both ammeters show a load much higher than the known consumption for more than 5 minutes?

A

If both ammeters indicate a load much higher than the known consumption for more than approximately five minutes, an electrical defect other than the alternator system should be suspected because a discharged battery will reduce the alternator load as it approaches the charged conditions.

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22
Q

What happens if there is a zero-ammeter reading ?

A

A zero-ammeter reading indicates an alternator is not producing current and should be accompanied by illumination of the ALT annunciator light.

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23
Q

How’s continued flight with only one alternator functioning? what care must be exercised?

A

A single alternator is capable of supporting a continued flight in case of alternator or engine failure in most conditions; however, with deicing equipment and other high loads, care must be exercised to prevent the loads from exceeding the 65-ampere rating and subsequent depletion of the battery.

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24
Q

Annunciator panel.

What does it include?

A

The annunciator panel on the upper left of the instrument panel is installed as an electrical accessory

It includes:
- manifold pressure overboost
- gyro pressure
- oil pressure, and
- alternator indicator lights.

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25
Q

What does illumination of any light in the annunciator panel indicate?

A

Illumination of any light indicates that the pilot should monitor system gauges to determine if a failure has occurred and if corrective action is required.

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26
Q

How can light function be tested?

A

Light function may be tested with a “push to test” switch.

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27
Q

What about with models with a primer system installation?

A

In addition, on models with a primer system’ installation, an amber light illuminates when the corresponding HI auxiliary fuel pump is energized. The auxiliary fuel pump annunciator lights will not illuminate when the “push to test” switch is actuated. Auxiliary fuel system light function is tested when the primer switches are actuated.

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28
Q

What do ammeter indicate when all electrical equipment is turned off?

A

When all electrical equipment is turned off (except the master switch), the ammeters will indicate current being used to charge the battery and operate the instruments.

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29
Q

What’s happening if the sum of the two readings is significant?

What should the pilot do in this case?

A

If the sum of the two readings is significant, this is an indication that the battery has a low charge.

The pilot should try to determine why it is low, and if no cause is apparent, the condition of the battery and the electrical system should be checked by a mechanic.

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30
Q

What do you do when both alternators fail during flight?

A

If both alternators should fail during flight, the battery becomes the only source of electrical power; therefore, all unnecessary electrical equipment should be turned off.

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31
Q

How is the length of battery life measured?

A

The length of time the battery will be able to supply power to the necessary equipment depends on the current drained by the equipment, the time it took for the pilot to notice the dual failure and to execute protective procedures, and the condition of the battery.

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32
Q

POH.4.9.8 Vacuum System

A
33
Q

How are directional gyros and attitude indicators driven?

A

The directional gyros and attitude indicators are driven by positive air pressure.

34
Q

What does the pressure system consist on?

A

The pressure system consists of a pressure pump on each engine, plus plumbing and regulating equipment.

35
Q

How is air for the system taken?

A

Air for the system is taken from the engine nacelle area through inlet filters and passed through pressure pumps installed on the engines.

36
Q

Where are the pressure regulators mounted? What’s their purpose?

A

Pressure regulators mounted on the fire walls maintain the air at constant pressure to prevent damage to the instruments.

37
Q

Where are check valves, pressure air manifol and inline filters mounted?

A

Check valves, a pressure air manifold, and inline filters are mounted In the cabin at the forward bulkhead.

38
Q

What’s the purpose of check valves?

A

The check valves close to allow pressure instruments to function during single-engine operation or in the event of malfunction of one of the pressure pumps.

39
Q

Where do the instruments receive air from?

A

The instruments receive air from the manifold

40
Q

What’s the pressure gauge?

A

A pressure gauge on the instrument panel, to the left of the pilot’s control wheel shaft, is connected to the manifold and indicates the pressure the gyros are receiving.

After air has passed through the gyro instruments, it is exhausted overboard through the forward bulkhead.

41
Q

What are the operating limits for the gyro pressure system?

A

The operating limits for the gyro pressure system are 4.5 to 5.2 inches of mercury for all operations.

42
Q

How’s the operation of the gyro pressure system monitored?

A

Operation of the gyro pressure system can be monitored through a gyro pressure gauge mounted to the left of the copilot’s control wheel.

The two warning indicators mounted on the gauge serve to alert the pilot should one of the engines be producing less than sufficient pressure to operate the gyro instruments.

Additional warning of a possible malfunction in the gyro pressure system is provided by a light in the annunciator panel.

43
Q

POH.4.9.9 Pitot Static System

A
44
Q

How is pitot pressure for the airspeed indicator sensed?

A

Pitot pressure for the airspeed indicator is sensed by an aluminum pitot head installed on the bottom of the left wing and carried through lines within the wing and fuselage to the gauge on the instrument panel.

45
Q

How is static pressure sensed?

A

Static pressure for the altimeter, vertical speed and airspeed indicators is sensed by two static source pads, one on each side of the rear fuselage forward of the stabilator.

46
Q

How are these static source pads connected?

A

They connect to a single line leading to the instruments. The dual pickups balance out differences in static pressure caused by side slips or skids.

47
Q

Where is the alternate static source located?

What happens when the valve is set to the alternate position?

A

An alternate static source control valve is located below the instrument panel to the right of the control quadrant.

When the valve is set to the alternate position, the altimeter, vertical speed indicator and airspeed indicator will be using cabin air for static pressure.

During alternate static source operation, these instruments may give slightly different reading, depending on conditions within the cabin.

Airspeed, setting of heating and ventilating controls, or the position of the storm window can influence cabin air pressure.

The pilot can determine the effects of the alternate static source on instrument readings by switching from standard to alternate sources at different airspeeds and heating and ventilating configurations (including open storm window below 130 KIAS.

48
Q

What can we do if one or more of the pitot static instruments malfunction?

A

If one or more of the pitot static instruments malfunction, the system should be checked for dirt, leaks, or moisture.

The pitot and the static lines may be drained through separate drains.

A drain on the lower left front of the side panel may be used to drain moisture from the pressure line running from the pitot head to the instrument panel.

On earlier models the alternate static source control is at the low point in the system, selecting the alternate static source will drain the static pressure lines. On later models the low point and drain in the static system is beside the pitot drain.

The holes in the sensors for pitot and static pressure must be fully open and free from dirt, bugs, or polish. Blocked sensor holes will give erratic or zero readings on the instruments.

49
Q

What should you note about the pre-flight inspection and pitot cover?

A

NOTE
During preflight, check to make sure the Pitot cover is removed.

50
Q

What may you use to alleviate problems in the pitot system with icing and heavy rain?

A

A heated pitot head, which alleviates problems with icing and heavy rain, is available as optional equipment. Static source pads have been demonstrated to be non-icing; however, in the event icing does occur, selecting the alternate static source will alleviate the problem.

51
Q

POH.4.9.10 Instrument Panel

A
52
Q

How is the panel instrument designed?

A

The instrument panel is designed to be functional and professional. There is sufficient space for the pilot’s flight instruments and complete engine instruments, plus optional copilot’s flight instruments and a wide range of avionics and additional optional instruments. Equipment is available to allow the Seneca II to be uniquely suited to individual needs.

53
Q

Were can we find flight instruments?

A

Flight instruments are grouped in the upper instrument panel

54
Q

What about in the lower instrument panel?

A

engine and electrical system monitoring instruments, the autopilot, and the circuit breaker panel

55
Q

How are left and right engine instrument separated?

A

Left and right engine instruments are conveniently separated by the left control wheel shaft.

56
Q

Where are the radios mounted?

A

Radios are mounted in the center of the upper instrument panel.

57
Q

Where can we find the control quadrant?

A

The control quadrant - throttles and propeller and mixture controls - is in the center of the lower instrument panel.

58
Q

Where is the landing gear selector?

A

To the left of the control quadrant is the landing gear selector.

This arrangement makes these installations conveniently accessible to both pilot and copilot.

59
Q

Where are the various warning lights?

A

Various warning lights are located with the pilot’s flight instruments on the left upper instrument panel

60
Q

Where is the gear unsafe warning light?

A

The gear unsafe warning light is to the left of the annunciator panel;

61
Q

Where is the stall warning light?

A

the stall warning light is to the far left of the pilot’s flight instruments.

62
Q

Where is the annunciator panel with manifold pressure overboost, oil pressure, gyro pressure and alternator light? what does it incorporate?

A

The annunciator panel, with manifold pressure overboost, oil pressure, gyro pressure and alternator lights, and incorporating a press-to-test feature, is located to the upper left of the radios.

63
Q

What does the illumination of these lights in flight indicate?

A

The illumination of these lights in flight is an indication of a possible System malfunction

64
Q

What should the pilot do if a light illuminates?

A

The pilot should closely monitor instrument panel gauges to check the condition of a system whose corresponding light on the annunciator panel illuminates.

65
Q

What does the illumination of the manifold pressure overboost light mean?

A

Illumination of the manifold pressure overboost lights indicates manifold pressure at or above the maximum allowable 40 inches Hg.

66
Q

What should the pilot do during pre-flight checks?

A

During preflight, the operational status of the annunciator panel, except auxiliary fuel pump lights, should be tested by use of the press-to-test button. When the button is depressed, all annunciator panel lights, except auxiliary fuel pump lights, should illuminate.

67
Q

What happens when an engine is feathered?

A

NOTE
When an engine is feathered, the alternator, gyro vacuum and engine oil pressure annunciator lights will remain illuminated.

68
Q

How’s instrument panel lighting dimmed or brightened?

A

Instrument panel lighting can be dimmed or brightened by rheostat switches to the right of the control quadrant.

Back-lights are standard equipment, and map lights, and reading lights are available as options.

69
Q

What happens when instrument panel lights are turned on?

A

When instrument panel lights are turned on, annunciator lights are dimmed. However, they will not show dim when the press-to-test switch is depressed.

70
Q

Where are most of the electrical switches located?

A

Most of the electrical switches are located on the switch panel on the left side of the cockpit.

71
Q

Where is the radio power switch located in later models?

What does this switch control and through what switch?

What positions does it have?

A

In later models a radio power switch is located near the top of the instrument panel between the radio stacks.

It controls the power to all radios through the aircraft MASTER switch.

The radio power switch has an OFF, NORMAL and AUXILIARY position.

The AUXILIARY position provides a secondary power circuit for all radios.

72
Q

Where are the manifold pressure line drain valves located? What does it allow? How is the drain accomplished?

What must you exert caution about when you drain the manifold pressure line?

A

The manifold pressure lines have drain valves located behind and below the dual manifold pressure gauge.

This allows any moisture which may have collected from condensation to be pulled into the engines.

This is accomplished by depressing the two valves for 5 seconds while operating the engines at 1000 RPM.

NOTE
Do not depress the valves when manifold pressure exceeds 25 inches Hg.

73
Q

POH.4.9.11 Stall Warning

A
74
Q

How is the approaching stall indicated?

A

An approaching stall is indicated by a stall warning indicator which is activated between five and ten knots above stall speed.

75
Q

What other symptoms can refer to an approaching stall?

A

Mild airframe buffeting and gentle pitching may also precede the stall.

76
Q

Where can we check the stall speeds?

A

Stall speeds are shown on the Stall Speed vs Angle of Bank graph in the Section 5.

77
Q

What does the stall warning indicator consist of?

A

The stall warning indicator consists of a continuous sounding horn located behind the instrument panel. The stall warning horn has a different sound from that of the gear warning horn which has a 90 cycles per minute beeping sound.

78
Q

How is the stall warning indicator activated?

A

The stall warning indicator is activated by two lift detectors on the leading edge of the left wing, outboard of the engine nacelle.

The inboard detector activates the indicator when the flaps are in the 25- and 40-degree positions, the outboard when the flaps are in other positions.

POH PA34 (10 decks)

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