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AC 43.13-1B CHG 1 9/27/01 11-35. ACCEPTABLE MEANS OF CONTROLLING OR MONITORING THE ELECTRICAL LOAD. a. Output Rating. The generator or al- ternator output ratings and limits prescribed by the manufacturer must be checked against the electrical loads that can be imposed on the af- fected generator or alternator by installed equipment. When electrical load calculations show that the total continuous electrical load can exceed 80 percent output load limits of the generator or alternator, and where special plac- ards or monitoring devices are not installed, the electrical load must be reduced or the gen- erating capacity of the charging system must be increased. (This is strictly a “rule of thumb” method and should not be confused with an electrical load analysis, which is a complete and accurate analysis, which is a complete and accurate of the composite aircraft power sources and all electrical loads) When a stor- age battery is part of the electrical power sys- tem, the battery will be continuously charged in flight. b. The use of placards is recommended to inform the pilot and/or crew members of the combination(s) of loads that may be connected to each power source. Warning lights can be installed that will be triggered if the battery bus voltage drops below 13 volts on a 14-volt system or 26 volts on a 28-volt system. c. For installations where the ammeter is in the battery lead, and the regulator system limits the maximum current that the generator or alternator can deliver, a voltmeter can be in- stalled on the system bus. As long as the am- meter never reads “discharge” (except for short intermittent loads such as operating the gear and flaps) and the voltmeter remains at “sys- tem voltage,” the generator or alternator will not be overloaded. d. In installations where the ammeter is in the generator or alternator lead and the regulator system does not limit the maximum current that the generator or alternator can de- liver, the ammeter can be redlined at 100 percent of the generator or alternator rat- ing. If the ammeter reading is never allowed to exceed the red line, except for short inter- mittent loads, the generator or alternator will not be overloaded. e. Where the use of placards or moni- toring devices is not practical or desired, and where assurance is needed that the battery will be charged in flight, the total continuous con- nected electrical load should be held to ap- proximately 80 percent of the total generator output capacity. When more than one genera- tor is used in parallel, the total rated output is the combined output of the installed genera- tors. f. When two or more generators and al- ternators are operated in parallel and the total connected system load can exceed the rated output of a single generator, a method should be provided for quickly coping with a sudden overload that can be caused by generator or engine failure. A quick load reduction system or procedure should be identified whereby the total load can be reduced by the pilot to a quantity within the rated capacity of the re- maining operable generator or generators. 11-36. ELECTRICAL LOAD DETER- MINATION. The connected load of an air- craft’s electrical system may be determined by any one or a combination of several acceptable methods, techniques, or practices. However, those with a need to know the status of a par- ticular aircraft’s electrical system should have accurate and up-to-date data concerning the capacity of the installed electrical power source(s) and the load(s) imposed by installed electrical power-consuming devices. Such Page 11-12 Par 11-35PDF Image | AFS-640
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