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MIL-STD-1530D w/CHANGE 1 13 October 2016 SUPERSEDING MIL-STD-1530D 31 August 2016 DEPARTMENT OF DEFENSE STANDARD PRACTICE AIRCRAFT STRUCTURAL INTEGRITY PROGRAM (ASIP) AMSC N/A FSC 15GP Distribution Statement A. Approved for public release; distribution is unlimited. . NOT MEASUREMENT SENSITIVE Source: https://assist.dla.mil -- Downloaded: 2026-07-20T01:47Z Check the source to verify that this is the current version before use. MIL-STD-1530D w/CHANGE 1 i FOREWORD 1. This standard is approved for use by all Departments and Agencies of the Department of Defense (DoD). 2. This standard implements Air Force Policy Directive (AFPD) 63-1, Acquisition and Sustainment Life Cycle Management, Air Force Instruction (AFI) 63-101, Acquisition and Sustainment Life Cycle Management and AFI 63-140, Aircraf
to verify the currency of this address information using the ASSIST Online database at https://assist.dla.mil. Source: https://assist.dla.mil -- Downloaded: 2026-07-20T01:47Z Check the source to verify that this is the current version before use. MIL-STD-1530D w/CHANGE 1 ii SUMMARY OF CHANGE 1 MODIFICATIONS The following modifications to MIL-STD-1530D have been made: Paragraph Modification TOC Corrected Heading number to 5.1.4 (from 5.2.1) TOC Added 5.1.6 Nondestructive Inspection (NDI) TOC Corrected Heading number to 5.1.7 (from 5.1.6) Table 1 C1 R8 Corrected paragraph reference number to 5.1.6 (from 5.1.5.3) Table 1 C2 R8 Corrected paragraph reference number to 5.2.6 (from 5.2.5) 5.2.1 Corrected paragraph number to 5.1.4 (from 5.2.1) 5.1.5.3 Corrected paragraph number to 5.1.6 (from 5.1
aster Plan, as specified in MIL-STD-1530 or MIL- STD-3063 respectively, documents the analysis and test verification methods required to certify the design for safe-life; that structural certification tasks are updated for modifications or changes to the air vehicle following initial AW certification basis; and all artifacts are developed IAW applicable sections of MIL-STD-1530 or MIL-STD-3063. (2) Verify detailed structural design criteria for safe-life, as specified in MIL-STD-1530 or MIL- STD-3063, documents the requirements to achieve structural integrity. (3) Verify test plans are scoped to apply a representative service life spectrum, monitor critical control points, and demonstrate static strength capability. (4) Verify the CPCP documents corrosion prevention systems, corrosion prev
s MIL-STD-882 System Safety MIL-STD-1530 Aircraft Structural Integrity Program (ASIP) MIL-STD-1797 Flying Qualities of Piloted Aircraft DEPARTMENT OF DEFENSE HANDBOOKS MIL-HDBK-470 Designing and Developing Maintainable Products and Systems, Volume I MIL-HDBK-516 Airworthiness Certification Criteria MIL-HDBK-522 Guidelines For Inspection Of Aircraft Electrical Wiring Interconnect Systems MIL-HDBK-525 Electrical Wiring Interconnect System (EWIS) Integrity Program MIL-HDBK-528 Design For Testability (DFT) for Boundary Scan Diagnostics (BSD) MIL-HDBK-1823 Nondestructive Evaluation System Reliability Assessment JOINT SERVICE SPECIFICATION GUIDE JSSG-2006 Aircraft Structures JSSG-2009 Air Vehicle Subsystems (Copies of these documents are available online at https://quicksearch.dla.mil/.) 2.2.2 O
roviding program managers and MAJCOMs verifiable engineering inspection reliability data based on probability of detection and proficiency studies. These studies are conducted in accordance with Military Handbook 1823 (MIL- HDBK-1823), Nondestructive Evaluation System Reliability Assessment and Military Standard 1530 (MIL-STD-1530), DoD Standard Practice for Aircraft Structural Integrity Program, every five years or sooner when requested by MAJCOMs or program managers. 2.4.3.7. Establishing and maintaining the Air Force-wide process for the certification of all Air Force civil service nondestructive inspection personnel who require certification in accordance with DAFI 21-101, AFMCI 21-100 V1, or this instruction. 2.5. Air Force Aircraft Structural Integrity Program Technical Advisor: 2.5.
the use of this standard. It should be used in accordance with MIL-STD-1587 in selection of materials and processes that will meet the requirements of the systems being designed in accordance with MIL-STD-1530 and MIL-STD-3063. 6.2 Acquisition requirements. Acquisition documents should specify the following: a. Title, number, and date of this standard. b. Corrosion Prevention and Control Plan (CPCP) (see 4.1). c. Finish specification (see 4.2). d. If Nondestructive Inspection (NDI) is required (see 4.5.6). e. Timelines and milestones for the CPCP and finish specification (see Appendix A). f. The establishment of Corrosion Prevention Teams (CPTs) (see Appendix B). NOTE: Corrosion Prevention Teams are referred to by many different names depending on the Service such as Corrosion Action Team
. . . . . . . . . . . . 1-2 1.1.11 Engineering Requirement Review Process (ERRP) and the Engineering Requirement De- velopment Packet (DevPac) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2 DEFINITION OF TERMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2.1 Aircraft Structural Integrity Program (ASIP) (MIL-STD 1530) . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2.2 Analytical Condition Inspection (ACI) AFMCI 21-102 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2.3 Airframe Condition Evaluation (ACE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 1.2.4 Controlled Interval Extension (CIE) AFMCI 21-104 . . . . . . . . . . . . . . . .
ordance with agreements made during the pre-contract conference. (AFMCI 21-100). 2.8 SERVICE LIFE EXTENSION PROGRAM (SLEP). 2.8.1 SLEP Defined. A SLEP is a modification to extend the existing service life limit of a system. As a secondary impact, the SLEP will often reduce the inspection burden. 2.8.1.1 More information is available in DAFI 63-140, MIL-STD-1530, MIL-HDBK-516, and JSSG-2006. 2.8.1.2 The service life extension modification can include fleet-wide repairs, modifications (e.g., doublers, cold-worked holes), and/or part or component replacements. It could require full-scale durability testing to validate analysis and demonstrate capability. TO 00-20-1 2-9 Figure 2-1. AFTO FORM 26, AIRCRAFT INSPECTION WORK DOCUMENT TO 00-20-1 2-10 CHAPTER 3 AEROSPACE EQUIPMENT FORMS DOCUMENTATION
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