AFGS�87219B
3.8 Supportability.
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.
3.8.1.1 Fault detection/isolation.
The EPS design shall facilitate complete and efficient fault detection and isolation at all levels of maintenance. The system design requirement is 100 percent for fault detection and isolation to an appropriate replaceable, adjustable, or repairable assembly or part. This shall be accomplished using an optimized combination of any or all of the fault detection/isolation methods listed herein. The fault detection/isolation capability shall consist of ------------.
3.8.1.2 Packaging, handling, storage, and transportation (PHST).
The EPS, its subsystems and components shall be designed with PHST characteristics that allow it to be readily transported in the logistics environment at the lowest life cycle cost. The PHST characteristics that will be established as requirements include ------------.
3.8.2 Tools.
Tools required to perform on aircraft organizational level maintenance functions shall be
limited to those on the STAM2 list. Tools required to perform intermediate level functions shall consist of ------------.
4. VERIFICATION
4.1 General.
The verifications (inspections/analyses/tests) specified herein shall verify the ability of EPS to meet the requirements of section 3 herein. All verifications shall be the responsibility of the contractor; the Government reserves the right to witness or conduct any verification.
4.2 Performance requirements.
Overall performance of the EPS shall be verified by the following tests of the integrated subsystem.
a. Laboratory tests of a subsystem mockup which accurately simulates the aircraft installation. Testing shall include the most adverse electrical loading, environmental, fault, and endurance conditions required of the subsystem.
b. Aircraft ground and flight tests of the installed EPS under the most adverse conditions of electrical loading, cooling, and flight maneuvers. Failure modes which are not
hazardous to personnel or the aircraft shall be simulated.
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