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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AFGS�87219B APPENDIX A

VERIFICATION RATIONALE (A.4.2.4)

Analyses are appropriate for preliminary verification that requirements will be met.  Final verification is provided by component qualification tests and tests of subsystems in the laboratory and installed in the aircraft.

VERIFICATION GUIDANCE (A.4.2.4)

a.   Electrical load analyses, circuit analyses, component tests, and integrated subsystem testing are appropriate means for verifying emergency power requirements.

b.   Electrical load analyses per MIL-E-7016 and component qualification testing are needed to establish that the capacity of the emergency power unit is sufficient for the essential loads.

c.    Circuit analyses and subsystem testing are needed to verify proper control logic and compatibility with the rest of the EPS.

d.   The performance requirements of the EPS with respect to emergency power can be verified by mockup tests and aircraft tests.

e.   Complete verification of emergency power will be required when the system is installed on the aircraft.

VERIFICATION LESSONS LEARNED (A.4.2.4)

Analysis, followed up by system-level testing on the aircraft, is adequate verification.  Mockup testing may be used for initial verification, but final verification is required on the aircraft.  On- aircraft testing has been shown to produce results that were not predicted or seen in the mockup testing.

A.3.2.5    External ground power.

The EPS shall accept power from an external source for ground operations as required.  The EPS

shall be compatible with MIL-STD-704 quality power supplied by the following external electrical power sources: ------------.

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: ------------.

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