AFGS�87219B APPENDIX A
c. Capacity derating factors such as temperature and altitude d. Growth requirements
e. Redundancy for flight-critical systems
REQUIREMENT GUIDANCE (A.3.2.2)
a. The procedures of MIL-E-7016 are recommended for the analyses of load requirements and power source capacity.
b. EPS capacity should be at least twice the maximum continuous load of the initial production aircraft to provide for growth, unless other overriding considerations prevent this growth capacity.
c. Short duration load demands must be within the capacity of the EPS.
REQUIREMENT LESSONS LEARNED (A.3.2.2)
a. As a general rule, aircraft electrical loads continue to grow after the initial design. Some aircraft have been forced to eventually change to larger generators or add additional generating capability as the loads increased. Extra capacity is also needed for failure conditions which result in a generator loss, to assure that all systems can still function. Growth capacity also prevents brown-outs from occurring.
b. Some limited application aircraft and most missiles do not require growth capacity. If you feel this is your case, consult with the procuring activity.
c. Some aircraft that are converted over to special mission purposes require an entire new electrical system. Even a 100 percent growth capacity may not be enough. It is not uncommon to see original equipment 40-KVA generators replaced with 120-KVA generators.
A.4.2.2 Capacity.
The ability of the EPS to meet the capacity requirements of 3.2.2 shall be verified by analyses and tests as follows: .
VERIFICATION RATIONALE
Analyses of aircraft requirements are needed to establish the capacity required of the EPS for initial loads, growth and redundancy. Subsequent testing is necessary to confirm actual aircraft requirements and subsystem capacity.
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