Aircraft Electrical Systems Quiz

The system that provides electrical power to all aircraft equipment, including DC and AC systems.

It converts AC power to DC power, which is used by many aircraft systems like lighting and controls.

It provides AC power for high-power equipment, like the air conditioning system.

They are used to convert AC power to DC power and are part of the DC generation system.

They are used for connecting to external power sources on the ground, either AC or DC.

It supplies power to the aircraft when the engines are not running.

It helps distribute power to different parts of the aircraft.

It allows the aircraft to switch to different power sources automatically in case of failures.

A fault in the system where excessive current flows through a secondary feeder bus.

A circuit breaker that protects the TRU (Transformer Rectifier Unit) from over currents. It opens when the current exceeds a certain limit.

A device that connects two secondary feeder buses in the system. It closes after a delay of 7 seconds if a fault is detected on one of the buses.

A fuse that prevents a fault on one secondary feeder bus from affecting the other TRU, by interrupting the current flow between the buses.

The Electronic Power Control Unit (EPCU) is responsible for detecting faults in the aircraft's electrical system, including TRU source faults.

The main 28 VDC generation system is designed to provide reliable power to the aircraft and automatically isolates faults to maintain operation.

The system uses a combination of generators and batteries to provide the necessary power. The generators are the primary source, while batteries act as backup.

The main feeder busses are the primary distribution points for the 28 VDC power. Essential busses are used for critical components that require power even during emergencies.

The DC GCU (Generator Control Unit) monitors the DC starter/generator's speed and voltage.

If the DC starter/generator's voltage exceeds 32.5 ± 0.5 VDC, the DC GCU will shut it down to prevent damage.

The system has protective functions to prevent damage to the DC starter/generators, TRUs (Transformer Rectifier Units), or other related equipment during malfunctions or overloads.

If a fault is detected, the system isolates the problem from the rest of the system to maintain continued operation.

The DC GCUs monitor the DC starter/generators' speed and voltage while the DC generator toggle switch is in the DC GEN position.

The DC generation system in the DHC-8-400 provides emergency electrical power to the aircraft.

The DHC-8-400 DC generation system relies on three main power sources: NiCad batteries, engine-driven starter/generators, and Transformer Rectifier Units (TRUs).

Transformer Rectifier Units (TRUs) convert AC power to DC power, providing 28Vdc for aircraft systems.

The TRUs in the DHC-8-400 are powered by two engine-driven AC generators, which produce 115 VAC.

The DHC-8-400 uses two engine-driven AC generators to provide 115 VAC three-phase electrical power for non-frequency-sensitive systems.

The standby power unit (SPU) hydraulic pump and deicing heaters are examples of systems utilizing the 115 VAC three-phase electrical power generated by the AC generators in the DHC-8-400.

The DHC-8-400 battery system provides 28Vdc emergency electrical power to the aircraft.

The DHC-8-400 battery system includes main batteries, auxiliary batteries, and a standby battery, all connected through contactors located in contactor boxes.

The main electrical power source of the aircraft that supplies essential busses during emergency situations.

Three batteries connected to the main feeder busses, providing charging current and engine starting power.

These busses are supplied by the battery system and are essential for maintaining critical systems during emergency flight conditions.

The battery system's main source of charging current, connected to the main, auxiliary, and standby batteries.

The standby battery is disconnected from the main feeder bus during engine starts to prevent excessive loading. It remains connected to the essential busses to maintain power.

The battery system is controlled and monitored by the dc control panel in the flight compartment.

The Engine and System Integrated Display (ESID) presents electrical indications for the main 28 Vdc generation system.

The BATTERY MASTER toggle switch on the dc control panel is used to enable or disable the battery system.

During an emergency condition, the batteries automatically reconnect to the main feeder busses for the duration of the engine start sequence.

Vent and Drains are components connected to the main and auxiliary batteries that help maintain proper ventilation and prevent fluid buildup

The TRU circuit breaker opens after an overcurrent condition on a secondary feeder bus, isolating the faulty bus after a 1-second delay.

Contactors K5 and K6 are opened by the EPCU after a secondary feeder bus fault to isolate the faulty bus from the main feeder bus.

Two TRUs provide redundant power sources for the main DC generation system, ensuring continuous power availability even if one TRU fails.

The main DC generation system monitors for malfunctions and reconfigures power sources to ensure continuous power supply to the aircraft.

The EPCU (Electrical Power Control Unit) is responsible for coordinating and managing various aspects of the main 28 VDC generation system, including fault detection, protection, and power distribution.

The main feeder bus is the primary distribution point for 28 VDC power in the aircraft, providing power to numerous essential systems.

The 28 VDC generation system provides all the DC power needed for aircraft systems, including lighting, controls, and other essential equipment.

Secondary feeder buses provide power to various components within the aircraft, branching off from the main feeder bus.