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CPL Air Tech & Loading > Gyroscopic Instruments > Flashcards

Gyroscopic Instruments Flashcards

1
Q

26.30.2 Describe the systems which typically require DC power in an aircraft

A

Electric starter motor, radios, transponder, electrical and engine instruments, cabin and instrument

lighting, eternal navigation and collision avoidance lighting.

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2
Q

26.30.4 (a) Explain the functions of the battery in a typical electrical system

A
  • initial electrical power to turn engine over and start with electric starter motor
  • Supplementary source of power if a short term demand is greater than alternator/generator can

supply

  • emergency source of electrical power should normal generating system fail
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3
Q

26.30.4 (b) Explain the functions of the ground power source in a typical electrical system

A
  • For starting large engines the capacity of the aircraft battery may not be sufficient so a ground

power unit is used to supple the entire electrical requirement during start up.

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4
Q

26.30.4 (c) Explain the functions of the alternator or generator in a typical electrical system

A
  • to provide electrical power to the aircraft
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5
Q

26.30.4 (d) Explain the functions of the bus bars in a typical electrical system

A
  • A bus bar is a main conductor and distributor or electrical power. Electrical power is supplied to the

bus bar by the alternator, generator or battery and is then distributed to electrical components that

need power

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6
Q

26.30.4 (e) Explain the functions of the over voltage protection in a typical electrical system

A
  • An alternator or generator can have the capacity to produce a higher voltage than required by the
    aircraft. The voltage is controlled by a voltage regulator. An over voltage protector is in place to

guard against malfunction of the regulator.

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7
Q

26.30.6 Given appropriate date determine the duration of battery operation following a generator

failure.

A
  • duration of battery can depend on battery age and turning off sources for battery use in the

aircraft that are not needed for flight. Can also be calculated using the amp/hour rating of the

battery itself.

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8
Q

26.30.8 Describe the relative advantages and disadvantages of a generator/alternator

A
  • for the same amount of electrical power produced, generators are heavier and larger than an

alternator

  • generators produce less current per rpm and are therefore less suited for low rpm operations
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9
Q

26.30.10 (a) Explain the functions and interpretation of left-zero ammeters

A

The left-zero ammeter measure only the output of the alternator

With the battery switch on and the engine not running or the engine running and the alternator

switch off the ammeter will show zero.

In normal operation with the engine running and the alternator switch on, the ammeter will then

show the alternator output – the amount of current flowing from the alternator to the electrical

services and battery.

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10
Q

26.30.10 (b) Explain the functions and interpretation of centre-zero ammeters

A

The centre zero ammeter measures flow of current either into or out of battery

Current into the battery is charge, with ammeter pointing to the right of centre toward the + side

Current out of the battery is discharge, with the ammeter pointing to the left of the centre toward

the – side

No current flow either into or out of the battery is shown with the needle in the centre-zero position

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11
Q

26.30.12 (a) Explain the functions and correct operation of a single battery master switch

A
  • The master switch must be turned on for any of the electrical services to receive power, or for the

battery to be recharged when the engine is running. It should be turned off after stopping the

engine, to prevent the battery from discharging by powering the electrical equipment which is still

connected to it

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12
Q

26.30.12 (b) Explain the functions and correct operation of a split battery/alternator switch

A

A split switch is when one half operates the battery and the other half operates the alternator

Both switches must be on for normal operation. They can be switched on separately but only the

alternator can be switched off separately – switching the battery off will automatically switch off the

battery aswell.

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13
Q

26.30.14 Explain the operation of (a) fuses

A
  • To protect the equipment from an electrical current overload. If there is an electrical overload or

short circuit a fuse-wire will melt.

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14
Q
  1. 30.14 Explain the operation of

(b) Circuit breakers

A
  • To protect the equipment from an electrical overload. If there is an electrical over load or short

circuit a circuit breaker will pop. i.e pop out and break the circuit so no current can flow through it.

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15
Q
  1. 30.14 Explain the operation of

(c) overload switches

A
  • To protect the equipment from an electrical overload. Overload switches are combined on/off

switch and overload protectors. Overload switches will switch themselves off if they experience an

electrical overload. The pilot can switch them back on like a resettable circuit breaker.

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16
Q

26.30.16 Explain operational principles for the handling of the electrical DC system (a) avoiding overheating electrical services if operated during pre-flight

A
  • During pre-flight inspections operate only briefly electrical services which require airflow past for

cooling e.g pitot heat, landing lights

17
Q
  1. 30.16 Explain operational principles for the handling of the electrical DC system
    (b) not starting or stopping the engine with unnecessary electrical equipment switched on
A
  • Large voltage fluctuations produced when the starter is engaged can damage sensitive electronic
    circuits. Switch on this equipment after the engine has started, and after checking that the

alternator is charging the battery. For the same reasons turn off equipment before shutting down

the engine.

18
Q
  1. 30.16 Explain operational principles for the handling of the electrical DC system
    (c) avoiding prolonged use of the starter motor
A
  • Starter motors place a large drain on the aircraft battery. Avoid prolonged starter operation.

Intermittent use helps the battery to recover to an extent and will prevent the starter motor fro

overheating.

19
Q
  1. 30.16 Explain operational principles for the handling of the electrical DC system
    (d) checking satisfactory operation of the alternator/generator after start and periodically during

flight

A
  • After start up check that the alternator/generator is operating satisfactorily. This is indicated by a

high charge indicated on the ammeter because the battery will require some charging after start.

During flight monitor the ammeter. Some light fluctuation is normal but a large continuous

deflection in one direction or other indicates a malfunction.

20
Q
  1. 30.16 Explain operational principles for the handling of the electrical DC system
    (e) ensuring the battery master is switched off before vacating the aircraft after flight
A
  • ensuring that the battery is switched off prevents it from being discharged overnight.. resulting in a

flat battery.

21
Q
  1. 30.16 Explain operational principles for the handling of the electrical DC system
    (f) use of a ground power unit
A
  • To use ground supply the aircraft master must incorporate a ground-flight select position so that its

not possible to load aircraft electrical circuits with both external and on-board battery power at the

same time. During start up this switch is placed to ground and once the engine is running it is switch

to flight position.

Different systems can allow for connection of GPU without the ground-flight switch is the aircraft

battery is serviceable.

In any case ensure that the GPU voltage matches that of the aircraft. Use of a larger voltage GPU can

cause severe damage to radios and other equipment.

22
Q
  1. 30.18 Explain the identification of

(a) an excessive charge rate

A
  • and excessive charge rate will be shown on a left zero ammeter and centre zero ammeter by an

abnormally high positive charge rate.

23
Q
  1. 30.18 Explain the identification of

(b) alternator/generator failure

A
  • left zero ammeter will drop to zero or centre-zero ammeter showing a discharge and/or

illumination of red warning lights

24
Q
  1. 30.18 Explain the identification of

(c) total electrical failure

A
  • specific procedures are required in the event of an electrical failure. Refer to the pilots operating

handbook for the procedures to be followed for the type of aircraft.

25
Q
  1. 30.20 Explain the risks associated with

(a) resetting blown fuse/popped circuit breakers

A
  • a circuit breaker pops twice, it is fairly certain that there is an electrical problem. They should not

be set again.

26
Q
  1. 30.20 Explain the risks associated with

(b) using fuses as a switch

A

If there is an electrical overload or short circuit, a fuse will melt to disconnect the circuit. Therefore

there isn’t a way to reconnect the circuit without replacing the fuse. Therefore it couldn’t be used as

a switch

27
Q

26.30.22 Explain the issues related specifically to ‘technically enchanced aircraft’ (TEA) during the

handling of electrical malfunctions.

A
  • During an electrical malfunction a TEA will have a back up system to run main instruments. The

disadvantage of TEA systems is that instrument information is lost, and landing as soon as

practicable is recommended.

CPL Air Tech & Loading (19 decks)

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