MIL-STD-1530C(USAF)
4. GENERAL REQUIREMENTS.
4.1 ASIP goal and objectives.
The effectiveness of any military force depends, in part, on the safety and operational readiness of its weapon systems. One major item of an aircraft system that affects its operational readiness is the condition of the aircraft structure. Its capabilities, condition, and operational limitations must be established to maintain operational readiness. Potential structural or material problems must be identified early in the life-cycle to minimize their impact on the operational force. In addition, a preventive maintenance program must be developed and implemented to provide for the orderly scheduling of inspections and replacement or repair of life-limited elements of the aircraft structure. The overall program to provide USAF aircraft with the required aircraft structural characteristics is referred to as the Aircraft Structural Integrity Program, or "ASIP."
The goal of the ASIP is to ensure the desired level of structural safety, performance, durability, and supportability with the least possible economic burden throughout the aircraft's design service life.
The objectives of the ASIP are to:
a. define the structural integrity requirements associated with meeting Operational Safety, Suitability and Effectiveness requirements;
b. establish, evaluate, substantiate, and certify the structural integrity of aircraft structures;
c. acquire, evaluate, and apply usage and maintenance data to ensure the continued structural integrity of operational aircraft;
d. provide quantitative information for decisions on force structure planning, inspection, modification priorities, risk management, expected life cycle costs and related operational and support issues; and
e. provide a basis to improve structural criteria and methods of design, evaluation, and substantiation for future aircraft systems and modifications.
4.2 Primary tasks.
The ASIP consists of the following five, interrelated functional tasks as delineated in table I and table II, and on figure 2 and figure 3:
a. Task I (Design Information). Task I is development of those criteria which must be applied during design to ensure the overall program goals will be met.
b. Task II (Design Analysis and Development Testing). Task II includes the characterization of the environment in which the aircraft must operate, the initial testing of materials, components, and assemblies, and the analysis of the aircraft design.
c. Task III (Full-Scale Testing). Task III consists of flight and laboratory tests of the aircraft structure to assist in determining the structural adequacy of the analysis and design.
d. Task IV (Certification & Force Management Development). Task IV consists of the analyses that lead to certification of the aircraft structure as well as the development of the processes and procedures that will be used to manage force operations (inspections, maintenance, modifications, damage assessments, risk analysis, etc.) when the aircraft enters the inventory.
e. Task V (Force Management Execution). Task V executes the processes and procedures developed under Task IV to ensure structural integrity throughout the life of each individual aircraft. This task may involve revisiting elements of earlier tasks, particularly if the service life requirement is extended or if the aircraft is modified.
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