AFGS-87219 Electrical Power Systems, AircraftThis specification establishes the performance requirements and verifications for electric power subsystems EPS for aerospace vehicles, including aircraft, helicopters, and missiles.

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AFGS�87219B

g. Distribution buses shall be enclosed within junction boxes to reduce vulnerability. The junction boxes shall be located to take maximum advantage of the protection offered by aircraft structure.

h. Other requirements for control and protection are as follows: ------------.

3.2.9 Major components.

Criteria shall be established for major components of the EPS as necessary to enable the requirements of the integrated subsystem to be met.

3.2.9.1 Aircraft wiring.

The design and installation of wiring associated with the electric power subsystem shall be as follows: ------------.

3.2.9.2 Batteries.

Batteries which are components of the vehicle electric system shall be capable of providing the specified battery power under the environmental and operational conditions to which they will be subjected.

a. Battery design and performance shall be in accordance with: ------------.

b. A battery relay shall be installed in each battery circuit to enable the flight crew to isolate the battery from the rest of the electric subsystem. The battery relay shall be controlled by a crew station battery switch. Any circuits which must remain connected to the battery with the battery switch OFF shall be connected directly to the battery through suitable fuses or circuit breakers.

c. On-board charging of batteries shall be controlled to enable the battery to become fully charged without excessive gassing or heating throughout the entire range of specified battery temperatures. The charging rate shall be sufficient to maintain the battery in a state of charge which will meet the battery power demands of normal ground and airborne operation of the aircraft. Battery charging shall be provided as follows:

------------.

d. Each battery shall be located and installed so that it can be readily inspected and easily removed from the aircraft without removing other components except for a readily opened access panel or door.

e. The location and design of the battery installation shall be such that the release of heat, smoke, gases, electrolyte or other products of a severe battery failure will not damage adjacent components or structure, endanger personnel, or adversely affect crew performance.