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NOT MEASUREMENT SENSITIVE MIL-HDBK-1823A 7 April 2009 ————————— SUPERSEDING MIL-HDBK-1823 14 April 2004 DEPARTMENT OF DEFENSE HANDBOOK NONDESTRUCTIVE EVALUATION SYSTEM RELIABILITY ASSESSMENT This handbook is for guidance only. Do not cite this document as a requirement. AMSC N/A AREA NDTI DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. Source: https://assist.dla.mil -- Downloaded: 2026-07-20T01:50Z Check the source to verify that this is the current version before use. MIL-HDBK-1823A 2 FOREWORD 1. This handbook is approved for use by all Departments and Agencies of the Department of Defense. 2. This handbook is for guidance only and cannot be cited as a requirement. If it is, the contractor does not have to comply. 3. Comments, suggestions, or questions on

lished using the accompanying mh1823 POD software, which is completely new for this update of MIL-HDBK-1823 and is based on the open-source statistical language R. The latest version of the mh1823 POD software can be obtained from the Air Force, Engineering.Standards@wpafb.af.mil. The instructions for use are self-contained in the drop- down menus and in Appendix G of this handbook. 4.7.1 Missing data All of the inspections called for by the test matrix are to be performed. If some of the inspections of a balanced design are not performed, the POD analysis is not straightforward and may need the assistance of a professional statistician. If the experiment is designed to evaluate only the variability associated with different targets and one other factor, the mh1823 POD analysis program can

eriments (DOX, or sometimes DOE) like Box, Hunter, and Hunter (2005) discuss only one response variable. With NDE systems the response is the entire POD(a) curve, as summarized by its model parameters, even though any individual test may have a single response, either â or hit/miss. Multivariate situations are discussed for example in Johnson and Wichern, and in Kutner, et al. (2005). Box and Draper (1989) discuss response surface designs, which are better suited for NDE experiments. It is beyond the scope of MIL-HDBK-1823 to discuss statistical experimental design in detail; however some general rules are presented to help with the NDE experimental design. It should be recognized that the techniques of elementary DOX, which assumes only a univariate rather than multivariate response, are

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

d to identify the inspection methods required to detect anticipated damage. Selection of the inspection methods shall consider material, geometry, accessibility, human factors, and the required detection capability. The inspection capability shall be determined using the guidance of MIL-HDBK-1823 and as approved by the NDI team described in 5.1.6. 5.4.3.2 SHM system operation. The SHM system (if used) shall consider material, geometry, accessibility, sensor POD and resulting system-level POD when determining the SHM detection capability and monitoring intervals using processes aligned with the statistical methods described in MIL-HDBK-1823. SHM system mean time between failure rates, calibration, and self-diagnostic methods shall also be considered to establish SHM maintenance requirements

ide to Aircraft/Stores Compatibility MIL-HDBK-310 Global Climatic Data for Developing Military Products MIL-HDBK-704-1 Guidance for Test Procedures for Demonstration of Utilization Equipment Compliance to Aircraft Electrical Power Characteristics (Part 1 of 8 Parts) MIL-HDBK-1763 Aircraft/Stores Compatibility: Systems Engineering Data Requirements and Test Procedures MIL-HDBK-1823 Nondestructive Evaluation System Reliability Assessment (Copies of these publications are available online at https://quicksearch.dla.mil). 2.2.2 Other government publications. The following other government publications form a part of this document to the extent specified herein. AERONAUTICAL DESIGN STANDARD ADS-33E-PRF Handling Qualities Requirements for Military Rotorcraft (Copies of this standard are availabl

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.

ssess their individual capabilities, or to compare the abilities of inspection systems or procedures. Risk Assessment Engineers can use the 95% Confidence Bounds (90/95 POD) to set initial and recurring inspections for a particular application. More information on performing POD assessments can be found in MIL-HDBK- 1823, Nondestructive Evaluation System Reliability Assessment, available at https://assist.daps.dla.mil/quicksearch. 1.1.4.2 Analytical Condition Inspection (ACI). ACI inspections are required occasionally on certain areas of the aircraft. ACI inspections are added to normal routine inspections to determine if there are sites of damage not addressed under the ASIP, ENSIP, or other maintenance programs. When engineers have reason to believe there may be damage occurring to areas