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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A.3.2.9.2 Batteries.

AFGS�87219B APPENDIX A

Batteries, components of the vehicle electric system, shall be capable of providing specified battery power under environmental and operational conditions.

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 it can be readily inspected and easily removed from the aircraft through an access panel or door and without removing other components.

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.

f. The battery and/or battery compartment shall be ventilated to prevent the accumulation of explosive mixtures of gases. All vent tubes leading to the exterior of the aircraft shall be designed to preclude the collection of rainwater and other liquids for all ground and flight environments.

g. The installation shall provide for maintaining battery temperature within the limits specified for battery operation. Any heater or thermal insulation required for low temperature operation shall be provided as part of the aircraft's battery compartment and not as an integral part of the battery.

h. Other battery requirements are as follows: ------------.