AFGS�87219B
a. The EPS shall be capable of handling the maximum external power required for ground operations while maintaining power characteristics in accordance with 3.2.1.
b. The EPS shall provide protection to prevent unsuitable external power from being applied to the aircraft.
c. The EPS shall provide for the power transfer from the external power source to the
on-board power source(s) and in the reverse direction in a manner consistent with the transient and power interruption requirements of 3.2.1. Power transfer is required as follows: ------------.
d. Receptacles for 28-volt DC external power shall be in accordance with either SAE-AS35061or ASIC AIR STD 25/18, and shall be connected in accordance with NATO STANAG 7073. Receptacles for 115 volt, 400 Hz external power shall be in accordance with SAE-AS90362, and shall be connected in accordance with either
MS17793 or STANAG 7073. Receptacles shall be isolated from aircraft power circuits when the mating plug is disengaged to ensure that dangerous voltages are not present.
e. External power receptacles shall be accessible from ground level and shall be located to minimize hazards to ground personnel. They shall not be located in or near hazardous areas such as air inlet or exhaust, APU or JFS exhaust, propellers or propeller blasts, or fuel servicing or vent areas.
f. The receptacle should be designed such that should ground maintenance personnel forget to remove the plug, the power cable and plug will pull out of the receptacle when the aircraft moves forward.
g. External power receptacles shall be covered by hinged access doors that will automatically remain closed when the receptacle is not in use. The access door shall be identified in accordance with MIL-STD-2161 and NATO STANAG 3109.
h. Other external ground power requirements are as follows: ------------.
3.2.6 Auxiliary power.
The EPS shall be capable of generating, controlling, and distributing power from on-board auxiliary power units for ground or airborne operations as follows: ------------.
3.2.7 Power distribution.
Electric power shall be distributed from the various power sources to the aircraft loads in a safe and effective manner.
a. The buses and distribution circuits shall be configured so normal EPS operation loads receive power from the aircraft primary power source(s), ground power, or an auxiliary power source as applicable.
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