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)

CONTENTS

PARAGRAPH                                                                                                                                     PAGE

1.                 SCOPE ................................................................................................................................1

1.1               Scope ...................................................................................................................................1

1.1.1            Application ..........................................................................................................................1

1.1.2            Tailoring ..............................................................................................................................1

2.                 APPLICABLE DOCUMENTS...........................................................................................1

2.1               General ................................................................................................................................1

2.2               Government documents.......................................................................................................1

2.2.1            Specifications, standards, and handbooks ...........................................................................1

2.2.2            Other Government documents, drawings, and publications................................................2

2.3               Non-Government publications ............................................................................................3

2.4               Order of precedence ............................................................................................................4

3.                 DEFINITIONS ....................................................................................................................4

3.1               Aircraft structure .................................................................................................................4

3.2               Baseline operational loads/environment spectrum (baseline spectrum)..............................4

3.3               Baseline service life.............................................................................................................4

3.4               Certification.........................................................................................................................4

3.5               Corrosion.............................................................................................................................4

3.6               Critical location ...................................................................................................................4

3.7               Damage................................................................................................................................4

3.8               Damage tolerance ................................................................................................................5

3.9               Design loads/environment spectrum ...................................................................................5

3.10             Design service life...............................................................................................................5

3.11             Durability ............................................................................................................................5

3.12             Economic life ......................................................................................................................5

3.13             Equivalent flight hours ........................................................................................................5

3.14             Equivalent initial flaw size (EIFS) distribution...................................................................5

3.15             Fail-safe structure................................................................................................................5

3.16             Fracture-critical part ............................................................................................................5

3.17             Fracture-critical traceable part.............................................................................................5

3.18             Initial quality .......................................................................................................................6

3.19             Inspectability .......................................................................................................................6

3.20             Maintenance-critical part.....................................................................................................6

3.21             Mission-critical part ............................................................................................................6

3.22             Multiple load path ...............................................................................................................6

3.23             Nondestructive inspection (NDI) ........................................................................................6

3.24             Onset of widespread fatigue damage (WFD) ......................................................................6

3.25             Probability of detection (POD)............................................................................................6

3.26             Producibility ........................................................................................................................6

3.27             Risk analysis........................................................................................................................6

3.28             Rotorcraft dynamic component ...........................................................................................7

3.29             Safe-life ...............................................................................................................................7

3.30             Safety-of-flight structure .....................................................................................................7

3.31             Single load path...................................................................................................................7

3.32             Slow damage growth structure ............................................................................................7

3.33             Stability ...............................................................................................................................7

3.34             Structural integrity...............................................................................................................7

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