AFGS�87219B APPENDIX A
meet the power quality requirements. The final verification lies in subsystem testing in the laboratory and on the aircraft.
VERIFICATION GUIDANCE (A.4.2.1)
a. Component requirements and test results should be analyzed to ensure that component performance is consistent with overall subsystem requirements.
b. The entire EPS must be tested as a subsystem to verify that the power quality at the inputs to the utilization equipment is within specified limits for all normal and abnormal conditions.
c. Laboratory testing of the EPS in an aircraft configuration is required to demonstrate this requirement. Testing shall include the most adverse electrical loading, fault, and endurance conditions required of the subsystem. The EPS laboratory testing should be in a configuration that includes all components of the subsystem up to the utilization equipment.
VERIFICATION LESSONS LEARNED (A.4.2.1)
Functional subsystem mockups should be retained for the life of the program for analyses of subsystem design and failures.
A.3.2.2 Capacity.
The EPS shall be capable of supplying all electric power requirements for all modes of vehicle operation plus additional capacity to provide for growth loads as follows: ------------.
The buses, conductors, and circuit breakers should be capable of handling the load growth provisions.
REQUIREMENT RATIONALE (A.3.2.2)
The capacity of the EPS is determined by the electric power requirements of the aircraft. All modes of aircraft operation must be considered as well as provisions for load growth and any necessary redundancy.
Historically, electric power requirements for most aircraft have increased significantly during their service life as the result of modifications and changing mission. Unless the potential for such growth is recognized and provided for when the EPS is developed, costly retrofit programs may be required in later years to increase EPS capacity. Factors which should be considered are:
a. Transient and steady state load requirements b. Component power ratings
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