Alternators and Electrical Systems Featured

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Many single-engine aircraft rely on alternators to power aircraft systems, avionics and cockpit gadgets. A&P Jacqueline Shipe guides you through how alternators work and what to do when yours isn’t functioning correctly. 

Nowadays, with everything from glass cockpits to auxiliary power outlets for iPads and phone chargers, there are more demands on the average aircraft’s electrical system than ever before. Most General Aviation airplanes rely on an alternator to provide a steady, reliable source of electrical energy to power electrical components and recharge the battery. 

Electrical system components

The main components in an average airplane’s electrical system are the battery, alternator, voltage regulator, bus bar and wiring. 

The battery provides stored power for starting the engine. It also provides a reserve of electrical power in case the alternator malfunctions in flight. 

The electrical bus bar provides a central point of power distribution to almost all electrical components (except the starter). The bus bar receives its power from the battery or alternator. Electrical components are connected to the bus bar through a circuit breaker or fuse.

Electrical system specifications

The electrical system on most airplanes is either a 14- or 28-volt system. 14-volt systems have 12-volt batteries. 28-volt systems utilize 24-volt batteries. 

The system voltage refers to an airplane’s operating voltage, which is always higher than battery voltage. The system voltage has to be higher than battery voltage in order to recharge the battery. 

Most airplane electrical systems are “single-wire,” meaning that the airframe itself is used as a ground, eliminating the need to run two wires for a positive and ground connection to each electrical component. They are also DC systems, meaning that the components operate on direct current rather than alternating current (AC).

How alternators work

Alternators generate electric current based on the principle of magnetic induction. Any time magnetic lines of force have relative motion with a conductor that is in close proximity, a voltage will be induced in the conductor. 

Alternators have an electromagnet (called a rotor) that spins inside multiple windings of a conductor (called a stator). As the rotor spins, the varying north-south lines of magnetic force induce an alternating current in the conductor. 

Copper-colored stator windings are barely visible under alternator case.

The alternating current is converted to direct current through a series of diodes (rectifiers) that allow current to flow in one direction, but not the other. 

Aircraft alternators are usually “three-phase,” meaning that the stator has three separate conductor windings.

Stator windings.

The rotor is an electromagnet whose magnetic strength is controlled by the amount of current it receives from the voltage regulator. This allows the voltage output of the alternator to be regulated. If the rotor were made with a permanent fixed-strength magnet, voltage output would be unregulated and would vary with engine rpm. 

Rotor inside a disassembled alternator case half.
Voltage regulator

Aircraft alternators are externally regulated by a voltage regulator (sometimes called an alternator controller), which is usually mounted either on the firewall in the engine compartment or under the instrument panel.

Voltage regulator installed on the firewall of a Cessna.
This regulator has only three wires—a common configuration. The red wire is the current supply for the voltage regulator from the bus. The black wire is the ground connection. The blue wire is the field wire that connects to the F1 terminal of the alternator.

The voltage regulator controls system voltage by controlling the electrical circuit (called the field circuit) that energizes the electromagnet of the alternator rotor. On most single-engine planes, this is accomplished by varying the flow of electric current to the rotor.  

Many voltage regulators have only three wires, but this aircraft’s regulator has five wires in total. The orange wire and the black wire are used to sense alternator voltage directly from the B+ terminal and ground connection at the alternator. The orange wire connects to B+. The red wire is the current supply from the bus that powers the voltage regulator. The yellow wire is the field wire that connects to the alternator’s F1 terminal. There is another ground wire (not shown) for the voltage regulator itself that attaches under one of the voltage regulator mounting bolts.

Older-style voltage regulators had contact points that would wear over time. Modern voltage regulators are fully electronic and, other than a voltage adjustment screw on some models, are maintenance-free. Whenever one of these units fails, it is simply replaced. 

This Plane-Power voltage regulator is similar to a three-wire regulator. The sense wire and the aux wires are connected to the enable wire. The enable wire runs current from the bus to power the regulator. The field wire is the output to the alternator rotor, and the ground wire goes to ground under one of the mounting fasteners for the voltage regulator. This regulator is set up for a 14-volt system and has a built-in 16-volt overvoltage sensor. 
Aircraft alternator design

The original manufacturers for most of the single-engine alternators used on Cessna aircraft were Ford, Chrysler, Prestolite or Delco Remy. Ford alternators were the most commonly used type on Cessnas. Many of the original alternator designs are still in use. 

This alternator’s tag shows Chrysler as the original manufacturer.
Ford-style alternator on a Cessna.

Most aircraft alternators have only three wires connected to them. A field wire connects to the F1 (field) terminal on the alternator, an output wire comes from from the B+ terminal of the alternator and a ground wire connects the alternator frame to a suitable ground connection. 

Ford-style alternator on a Cessna. This alternator has the most common setup with only three wires attached. The braided ground strap is for the ground connection. The heavy wire in the front that connects to the red B+ terminal is the alternator output wire. The field wire connected to F1 is barely visible behind the B+ terminal.
All of the wires attach to terminals on the rear of this alternator.
This alternator has a ground wire from the F2 terminal to the ground connection for the alternator.
Many voltage regulators have only three wires, but this aircraft’s regulator has five wires in total. The orange wire and the black wire are used to sense alternator voltage directly from the B+ terminal and ground connection at the alternator. The orange wire connects to B+. The red wire is the current supply from the bus that powers the voltage regulator. The yellow wire is the field wire that connects to the alternator’s F1 terminal. There is another ground wire (not shown) for the voltage regulator itself that attaches under one of the voltage regulator mounting bolts. 

On most of these types of alternators, the F2 terminal has no wire attached to it and is grounded to the alternator frame. Some alternators have a ground wire routed from the F2 terminal to the ground wire connection on the alternator frame.

F2 terminal. No wire attaches here. The terminal itself is grounded to the alternator case.

The alternator’s rotor gets its electrical connection through two carbon brushes that ride on separate slip rings. One of the brushes transmits positive current from the voltage regulator to the rotor windings and the other provides the ground connection, either from the F2 terminal or from an internal ground to the alternator frame. 

Rotor slip rings. The carbon brushes ride on the slip rings to transmit electric current and provide a ground connection to the rotor windings.

This article covers the most common three-wire system. A pilot/owner performing troubleshooting or wanting specific details on how his/her system operates should reference the current wiring diagram for their aircraft’s model and serial number. 

Electric current flow through a typical system 

When the aircraft master switch is turned on, the battery contactor closes and battery power energizes the aircraft’s electrical bus bar. Current from the bus flows through the alternator field circuit breaker and aircraft master switch to the voltage regulator. 

Some aircraft are also equipped with an overvoltage sensor that is wired in series between the master switch and the voltage regulator. The sensor must be in the closed, unfaulted position to allow current to flow.

The regulator senses that alternator output is zero and sends full current flow through the field wire, which is connected from the voltage regulator output to the F1 terminal of the alternator. The electromagnet of the rotor becomes energized since it has a complete electrical circuit with power at F1 and a ground at F2. 

As the engine starts and the alternator is rotated mechanically with either a belt or gear, the stator windings have an alternating current induced into them from the magnetic field of the rotor. 

Insulated stator winding with a soldered connection to the diode. If the alternator mounts or bushings become loose, the alternator can vibrate and the windings can crack or break. This failure creates an open circuit.

There are usually three stator windings and a total of six diodes in each alternator. The alternating current from each stator winding is converted to direct current after passing through two diodes.

Recently-replaced diode. The diodes have soldered connections to the stator windings.

The output of all three stator windings is rectified and passes as direct current out the B+ terminal, through a heavy-gauge wire to the alternator circuit breaker (usually 60 amp), then to the aircraft bus bar. 

Alternator output terminal (B+).

The voltage regulator senses the alternator output voltage, though the monitoring location varies. Some voltage regulators sense bus voltage, and some are wired to sense voltage directly at the B+ terminal of the alternator. 

The voltage regulator then adjusts current flow to the rotor field as needed to maintain the set system voltage. Always refer to the aircraft maintenance manual for the correct voltage range when setting or checking system voltages. 

If the alternator output or bus voltage is too low, the regulator increases current flow to the rotor field, which in turn increases the strength of the electromagnet and increases the alternator output voltage. 

If alternator output voltage is too high, the regulator decreases current flow to the rotor field, decreasing the strength of the electromagnet, which in turn decreases alternator output voltage.

Troubleshooting basics

A good electrical multimeter and a current wiring diagram that is pertinent to the installed equipment on an airplane are necessary to accurately troubleshoot the charging system for faults. 

Red electrical multimeter probe inserted in auxiliary power port to check bus voltage with the engine running and the alternator on and charging. The black lead is connected to the seat track for a ground connection. When checking voltage using a meter probe in the auxiliary power port or cigarette lighter, make sure the probe isn’t touching both the center and side of the port at the same time. The tip of the probe should only contact the furthermost interior center portion. If the probe touches the center and side at the same time, a direct short to ground occurs. This will either cause the circuit breaker that powers the port to trip, or if the port is installed with an inline fuse, it will blow the fuse.


Always check to see if the field (sometimes called the controller) or alternator circuit breaker is tripped before troubleshooting the system. 

Assuming a tripped breaker is not the issue, the first step in checking a charging system is to run the airplane and check bus voltage from either an auxiliary power port (e.g., the cigarette lighter receptacle, not a 5-volt USB power port) or from the bus itself. 

When checking bus voltage on a 28-volt system, the voltage will have to be checked on the bus itself since the power ports on these planes usually have stepped-down voltages. 

You may be able to check system voltage using a panel-mount voltmeter, an engine monitor or a GPS, if so equipped.

Checking the bus voltage is best accomplished with two people, one to run the plane and the other operating the voltmeter. 

With the red probe on the bus bar, and the black probe connected to a good ground (the seat track usually works well), the voltmeter will read the bus voltage. 

Bus voltage should be checked before starting the engine, and then checked again with the engine running to compare battery voltage (not running) to alternator output voltage (running). If the two voltages are identical, the alternator is not charging at all.

If the alternator is charging, the voltage should be noted and then all the electrical equipment on the airplane should be placed in the on position. With the lights, radios, pitot heat and other electrical components turned on, the alternator should carry the full electrical load and still maintain a positive charging rate.

Alternator is not charging

One of the first and easiest checks a pilot/owner can do when troubleshooting an alternator that isn’t charging is to turn on the aircraft master switch (both the alternator and battery side) and see if the alternator rotor becomes magnetized. 

Alternators that are pulley-driven are very easy to check. The pulley should be magnetized enough to hold the steel tool in place. If the alternator is gear-driven, the rotor will still be magnetized enough to detect a magnetic pull on the steel tool held near or on the alternator case. 

If there is a magnetic tug on the tool, it confirms that the field circuit is intact, the voltage regulator is sending power to energize the rotor and the rotor circuit is intact. 

Checking for magnetization of the alternator is done with the engine not running, magnetos off and mixture full lean. It’s also good safety practice to not be near the propeller whenever the battery master switch is being turned on. A stuck starter solenoid could allow the propeller to rotate even though the ignition switch is off.

The integrity of the connections on the alternator itself should be checked to be sure they are secure. A loose connection can allow current to flow intermittently. All alternator ground connections should be checked to make sure they are secure and have a low resistance (less than 0.2 ohms) between them. This includes the connection from F2 to the alternator ground terminal, the alternator-to-engine ground and the airframe-to-engine ground.

Electrical multimeter showing bus voltage with alternator charging.

If the rotor is magnetized and appears to be working properly, the next step is to see if there is bus (battery) voltage on the B+ terminal of the alternator. If there is bus voltage there, it means that the circuit between the alternator output and the bus bar is intact. 

Check next for a mechanical defect in the drive mechanism for the alternator. A loose belt that slips or a failed gear coupling on a gear-driven alternator can cause the alternator malfunction. 

If all the above checks pass, then the most likely problem causing the alternator not to charge is within the alternator itself. It should be removed for repair. 

Alternator is not charging; rotor is not magnetized 

If the rotor is not magnetized whenever the master switch is turned on (make sure the field circuit breaker isn’t tripped), the next step in troubleshooting is to see if the rotor is getting both the current and ground it needs to energize the windings. 

Checking the field circuit and rotor with the master switch turned on. The magnetized rotor and pulley will hold a wrench in place.

Check all ground connections for excessive resistance (anything above about 0.2 ohms). Turn the master switch on and check for voltage at the F1 terminal. It should be within a couple of volts of battery voltage.

In the situation where there is voltage at F1 and all the ground connections have good continuity, the alternator rotor itself is probably faulted or the alternator’s brushes have excessive wear. 

Rotor brush.
Disassembled alternator. The two brushes for transmitting positive current and an electrical ground to the rotor are at right angles to each other. The square white plastic brush holder is surrounding the brush itself. The brushes are spring-loaded to keep them pressed firmly against the slip rings. 

When there is no voltage present at the F1 terminal, there are several things that could be faulted upstream, interrupting current flow. The aircraft’s wiring diagram will show all the installed electrical components in the circuit as well as the wire numbers. 

One of the first things to check in this case is the integrity of the field wire, especially right at the F1 terminal. The crimped terminal connection often breaks over time with vibration. Some engine compartments have a very small space for the alternator terminal attachments and the wires are sometimes routed with sharp bends, causing stress on the crimped terminal ends. The field wire often breaks at or near the alternator terminal. 

Repaired field wire. The field wire is much smaller and more fragile than the alternator outwput wire or the ground wire. It often breaks at or near the alternator terminal where it is attached. This wire has had a prior repair.

If the terminal end is in good shape, the field wire between the F1 terminal and the voltage regulator should be checked for continuity and/or shorts to ground. 

Cessna voltage regulator.

The field wire should only be removed from the alternator with the master switch off. If the master switch is turned on with the wire removed, take precautions to prevent the field wire from touching anything that would allow it to short to ground. The voltage regulator can be ruined if that happens.

The voltage regulator powers the field wire and should be checked next. Disconnect the plug for the regulator and see if the regulator is receiving current from the bus. The red-colored wire is usually the wire that provides power to the regulator. Always consult the wiring diagram. 

If the regulator is receiving power from the bus, check next for a good ground connection for the regulator. Some regulators have a ground wire that is connected under one of the mounting fasteners, and some regulators require a good ground connection between the regulator body and the airframe ground. These connections can corrode over time, causing too much resistance in the ground connection. Cleaning the connections with Scotch-Brite or a small piece of sandpaper usually re-establishes a good ground connection. 

If the voltage regulator has a good ground connection and is receiving bus voltage but is not sending current to the field terminal of the alternator, it is most likely faulted. 

Field terminal (F1).

Some regulators use two wires to sense alternator voltage, one going to the B+ terminal of the alternator and one going to the alternator ground wire. Both of these wires should be checked for continuity and proper attachments at the alternator before assuming the voltage regulator is faulted.

Checking for bus/battery voltage at the B+ terminal.

If the voltage regulator is not receiving power from the bus, the next upstream component is usually an overvoltage sensor. Again, always consult the wiring diagram—some airplanes don’t have overvoltage sensors at all, and some overvoltage sensors are incorporated into the voltage regulator itself. 

The overvoltage sensor opens the power circuit to the regulator if it detects a voltage higher than its preset upper limit. Occasionally the sensor fails in the open position and will not conduct bus voltage to the voltage regulator at all.

If the overvoltage sensor has normal bus voltage on the input wire (usually coming from the master switch), but no voltage on the output wire (between the overvoltage sensor and voltage regulator), the sensor itself is faulted and should be replaced. 

If there is no power to the overvoltage sensor, check for power on both sides of the master switch (alternator side), and for power on the output side of the circuit breaker. Although it is rare, sometimes circuit breakers erode or internally fail in the open position and will no longer conduct current. The master switch contacts can also erode over time. 

Aircraft alternators and electrical systems aren’t complicated once you understand how current flows through the system’s various parts. With a solid understanding of how the system works and an aircraft-specific wiring diagram in hand, combined with these tips for troubleshooting and the assistance of a friendly mechanic, a pilot/owner can diagnose many common problems.

Know your FAR/AIM and check with your mechanic before starting any work. Always get instruction from an A&P prior to attempting preventive maintenance tasks.

Jacqueline Shipe grew up in an aviation home; her dad was a flight instructor. She soloed at age 16 and went on to get her CFII and ATP certificate. Shipe also attended Kentucky Tech and obtained an airframe and powerplant license. She has worked as a mechanic for the airlines and on a variety of General Aviation planes. She’s also logged over 5,000 hours of flight instruction time. Send question or comments to .


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