MIL-STD-1530 Aircraft Structural Integrity Program AsipThis standard describes the USAF Aircraft Structural Integrity Program ASIP which defines the requirements necessary to achieve structural integrity in USAF aircraft while managing cost and schedule risks through a series of disciplined, time-phased tasks. It provides direction to government personnel and contractors engaged in the development, production, modification, acquisition, and/or sustainment of USAF aircraft.

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MIL-STD-1530C(USAF)

International Society of Allied Weight Engineers, Inc.

SAWE RP No. 7                                   Mass Properties Management and Control for Military

Aircraft

(Copies are available from Society of Allied Weight Engineers, P.O. Box 60024, Terminal Annex, Los Angeles CA 90060-0024; https://www.sawe.org.)

2.4    Order of precedence.

In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence.  Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3.    DEFINITIONS.

3.1    Aircraft structure.

The structure of an aircraft includes the fuselage, wing, empennage, landing gear, rotorcraft rotor and drive systems, propellers, control systems and surfaces, airframe-engine interface components (including engine mounts), nacelles, air induction components, weapon mounts, structural operating mechanisms, components that perform a structural function, and other components as described in the contract specification.

3.2    Baseline operational loads/environment spectrum (baseline spectrum).

The baseline operational loads/environment spectrum is an update of the design spectrum based on measured data from operational aircraft (e.g., data obtained from the loads/environment spectra survey).

3.3    Baseline service life.

The baseline service life is the period of time (e.g., years, flight cycles, hours, landings, etc.) established subsequent to design, during which the structure is expected to maintain its structural integrity when flown to the baseline loads/environment spectrum.

3.4    Certification.

Certification is a repeatable process implemented to verify an aircraft can be safely maintained and operated within its described operational envelope.

3.5    Corrosion.

Corrosion is the deterioration of a material or its properties due to the reaction of that material with its chemical environment.

3.6    Critical location.

A critical location in an aircraft structure is one that has been identified through analysis, test, or service history as a being especially sensitive to the presence of damage.

3.7    Damage.

Damage to aircraft structure is any crack, flaw, corrosion, disbond, delamination, and/or other feature that degrades, or has the potential to degrade, the performance of the affected component.

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