AFGS�87219B APPENDIX A
d. External power receptacles SAE-AS35061 and SAE AS90362 comply with NATO and ASIC standardization agreements to which the U.S. subscribes. Only very unusual circumstances would warrant non-compliance. Pins E and F should not have 115 VAC applied since these should mate to 28 VDC circuits in compliance with international agreements. Older systems may refer to the obsolete MS3506, MS24442, MS90362, NATO STANAGs 3302 and 3303, and ASCC AIR STDs 12/6 and 12/7. These documents have been canceled, and should be used for information purposes only.
e. The safe and convenient location of external power receptacles should be a prime consideration to facilitate servicing and to minimize hazards to the ground crew.
f. It is necessary to protect the external power receptacle from dirt, fluids, and other contaminants when it is not in use. The design of the access door should preclude its being left open inadvertently after the ground servicing operation. Prominent identification of the receptacle is needed to facilitate aircraft servicing by the ground crew. Older systems may reference the canceled MS33739 to identify the access door. This should be used for information purposes only.
g. Consideration should be given to the use of the external power receptacle for connecting load banks to the aircraft for ground check-out of the EPS.
h. When dictated by operational requirements, the external power receptacles shall be installed so that external power will be automatically disengaged upon forward motion of the aircraft.
REQUIREMENT LESSONS LEARNED (A.3.2.S)
Some aircraft use the external power receptacle to connect loads to the aircraft for ground check of the EPS. This has eliminated the need to operate on-board equipment as loads for this purpose. Use of incompatible interfaces has caused damage to aircraft equipment when using the ground power carts provided by some installations.
A.4.2.S External ground power.
a. The capability of the EPS to accept and distribute the maximum external power requirements while maintaining the required power quality shall be determined by analyses and tests as follows: ------------.
b. Protection of the aircraft against unsuitable external power shall be verified by analyses and tests as follows: ------------.
c. The required power transfer characteristics shall be verified by analyses and tests as follows: ------------.
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