MIL-HDBK-1530B(USAF)
3.8 Multiple load path. Multiple load path is identified with redundant structures in which the applied loads would be safely distributed to other load-carrying members in the event of failure of individual elements.
3.9 Onset of widespread fatigue damage. Onset of widespread fatigue damage in a structure is characterized by the simultaneous presence of cracks at multiple structural details which are of sufficient size and density whereby the structure will no longer meet its damage tolerance requirement (e.g., maintaining required residual strength after partial structural failure).
3.10 Principal structural element (PSE). A PSE is an element of structure which contributes significantly to carrying flight, ground, and pressurization loads, and whose integrity is essential to maintenance of the overall structural integrity of the air vehicle.
3.11 Single load path. Single load path is where the applied loads are eventually distributed through a single member, the failure of which would result in the loss of the structural capability to carry the applied loads.
3.12 Structural operating mechanisms. Structural operating mechanisms are those operating, articulating, and control mechanisms which transmit structural forces during actuation and movement of structural surfaces and elements.
4. GENERAL GUIDELINES
4.1 ASIP goals. The effectiveness of any military force depends in part on the operational readiness of weapon systems. One major item of an air vehicle system that affects its operational readiness is the condition of the structure. The complete structure, herein referred to as "the airframe," includes the fuselage, wing, empennage, landing gear, control systems and surfaces, engine section, nacelle, air induction, weapon mount, engine mounts, structural operating mechanisms, and other components as described in the contract specification. The capabilities, condition, and operational limitations of the airframe of each air vehicle weapon and support system 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, and a preventive maintenance program must be
determined to provide for the orderly scheduling of inspections and replacement or repair of life-limited elements of the airframe. The overall program to provide USAF air vehicles with the required airframe structural characteristics is referred to as the Aircraft Structural Integrity Program, or "ASIP." The primary purposes of the ASIP are to:
a. establish, evaluate, and substantiate the structural integrity (airframe strength, rigidity, damage tolerance, and durability) of air vehicle structures;
b. acquire, evaluate, and apply operational usage data to provide a continual update of the structural integrity of operational air vehicles;
c. provide quantitative information for decisions on force structure planning, inspection, modification priorities, and relate operational and support decisions; and
d. provide a basis to improve structural criteria and methods of design, evaluation, and substantiation for future air vehicle systems and modifications.
4.2 Primary tasks. ASIP consists of the following five, interrelated functional tasks as delineated in table I
and on figures 1, 2, 3, and 4:
a. Task I (design information). Task I is development of those criteria which must be applied during design so the overall program goals will be met.
b. Task II (design analysis and development tests). Task II is development of the design environment in which the airframe must operate and the response of the airframe to the design environment.
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