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9/27/01 AC 43.13-1B CHG 1 SECTION 3. INSPECTION OF EQUIPMENT INSTALLATION 11-30. GENERAL. When installing equip- ment which consumes electrical power in an aircraft, it should be determined that the total electrical load can be safely controlled or man- aged within the rated limits of the affected components of the aircraft’s electrical power supply system. Addition of most electrical utilization equipment is a major alteration and requires appropriate FAA approval. The elec- trical load analysis must be prepared in general accordance with good engineering practices. Additionally, an addendum to the flight man- ual is generally required. 11-31. INSTALLATION CLEARANCE PROVISIONS. All electrical equipment should be installed so that inspection and maintenance may be performed and that the in- stallation does not interfere with other systems, such as engine or flight controls. 11-32. WIRES, WIRE BUNDLES, AND CIRCUIT PROTECTIVE DEVICES. Be- fore any aircraft electrical load is increased, the new total electrical load (previous maximum load plus added load) must be checked to de- termine if the design levels are being ex- ceeded. Where necessary, wires, wire bundles, and circuit protective devices having the cor- rect ratings should be added or replaced. 11-33. ALTERNATOR DIODES. Alter- nators employ diodes for the purpose of con- verting the alternating current to direct current. These diodes are solid-state electronic devices and are easily damaged by rough handling, abuse, over heating, or reversing the battery connections. A voltage surge in the line, if it exceeds the design value, may destroy the di- ode. The best protection against diode destruction by voltage surges is to make certain that the bat- tery is never disconnected from the aircraft's electrical system when the alternator is in op- eration. The battery acts as a large capacitor and tends to damp out voltage surges. The battery must never be connected with reversed polarity as this may subject the diodes to a forward bias condition, allowing very high cur- rent conduction that will generally destroy them instantly. 11-34. STATIC ELECTRICAL POWER CONVERTERS. Static power converters em- ploy solid-state devices to convert the aircraft’s primary electrical source voltage to a different voltage or frequency for the operation of radio and electronic equipment. They contain no moving parts (with the exception of a cooling fan on some models) and are relatively main- tenance free. Various types are available for ac to dc or dc to ac conversion. a. Location of static converters should be carefully chosen to ensure adequate venti- lation for cooling purposes. Heat-radiating fins should be kept clean of dirt and other foreign matter that may impair their cooling proper- ties. b. Static power converters often emit un- acceptable levels of EMI that may disrupt communication equipment and navigation in- struments. Properly shielded connectors, ter- minal blocks, and wires may be required, with all shields well grounded to the airframe. CAUTION: Do not load convert- ers beyond their rated capacity. Par 11-30 Page 11-11PDF Image | AFS-640
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