AFGS�87219B APPENDIX A
VERIFICATION GUIDANCE (A.4.2.2)
a. Use the procedures of MIL-E-7016 to determine the required capacity of the EPS and its components.
b. Verify actual aircraft loads and installed subsystem performance by aircraft testing.
c. Actual loads will not be available until all vendors have tested their equipments to verify the actual power utilized. The system contractor must work very closely with the vendors early in the program to obtain best estimates on loads so that the EPS can be sized correctly from the start.
VERIFICATION LESSONS LEARNED (A.4.2.2)
In the early stages of design, the electrical power needed is usually underestimated by the vendor; and by the time the first operational aircraft is delivered, the actual loads are above the original estimates. Careful review of vendor estimates of needed power should occur early in the program to assure that the electrical system is sized correctly. Adding 25 percent larger generators halfway through the design can severely impact the total system design.
A.3.2.3 Uninterruptible power.
Fly-by-wire flight controls, and other flight critical subsystems and components which cannot tolerate power interruption, shall be provided with power from full-time redundant power sources. During flight, each redundant power source shall be fully active and shall be either powering the critical loads or capable of assuming such loads without power interruption in the event of failure of other sources.
a. Uninterruptible power (is) (is not) required.
b. A minimum of ------------ failures of sources of uninterruptible power shall be accommodated without interruption or degradation of power to flight-critical loads. This requirement shall be met without crew action or automatic reconfiguration of the power system.
REQUIREMENT RATIONALE (A.3.2.3)
Special consideration must be given to power sources for fly-by-wire flight controls and other flight-critical loads which require continuous power to maintain control of the aircraft. Not only are redundant sources required, but these sources must be capable of instantly assuming the loads without manual or automatic switching which would degrade system integrity. In contrast to the emergency power units for less critical loads, which may operate only when needed, sources of uninterruptible power must be capable of continuous in-flight operation.
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