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

REQUIREMENT RATIONALE (A.3.7)

The EPS normally interfaces with many aircraft subsystems including propulsion, for prime motive power; airframe, for mechanical support; and environmental control, for cooling and pressurization.  The EPS, in turn, furnishes electric power to these and most other subsystems. General requirements for interfaces with load equipment, ground power, and auxiliary power are called out in the appropriate sections of the basic specification.  Definition of the detailed interface requirements necessary to integrate the EPS and its components into the aircraft is usually the responsibility of the airframe prime contractor.  However, a particular program may require that additional interface requirements be levied by the Air Force.

REQUIREMENT GUIDANCE (A.3.7)

Specify any additional interface requirements necessary for the particular application.

REQUIREMENT LESSONS LEARNED (A.3.7)

Inadequate cooling of the integrated drive generator has been a major interface problem in many aircraft.  Close attention must be given to this area.

A.4.7    Interface requirements.

Compliance with the EPS interface requirements of 3.7 shall be verified as follows:

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VERIFICATION RATIONALE (A.4.7)

All interface requirements will require appropriate means of verification.  Inspection, analyses, and tests can be used for this purpose.

VERIFICATION GUIDANCE (A.4.7)

Specify appropriate means of verification for each interface requirement.

VERIFICATION LESSONS LEARNED (A.4.7)

Verification of all interfaces assures that the system will work as advertised when installed.

A.3.8    Supportability.

A.3.8.1    Integrated diagnostics and testability.

The EPS shall be designed and constructed to permit system status and unambiguous location of faults to be reported within ------------ and ------------, respectively. Diagnostics/testability design and fault isolation times shall be constrained by operational and safety requirements, including maintenance system operational requirements, and life cycle cost.

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