1.Purpose This AMC establishes methods of compliance with CS 25.307, which specifies the requirements for Proof of Structure.
2.Related Certification Specifications CS 25.303 “Factor of safety” CS 25.305 “Strength and deformation” CS 25.651 “Proof of strength”
3.Definitions
3.1. Detail. A structural element of a more complex structural member (e.g. joints, splices, stringers, stringer run-outs, or access holes).
3.2. Sub Component. A major three-dimensional structure which can provide complete structural representation of a section of the full structure (e.g., stub-box, section of a spar, wing panel, wing rib, body panel, or frames).
3.3. Component. A major section of the airframe structure (e.g., wing, body, fin, horizontal stabiliser) which can be tested as a complete unit to qualify the structure.
3.4. Full Scale. Dimensions of test article are the same as design; fully representative test specimen (not necessarily complete airframe).
3.5. New Structure. Structure for which behaviour is not adequately predicted by analysis supported by previous test evidence. Structure that utilises significantly different structural design concepts such as details, geometry, structural arrangements, and load paths or materials from previously tested designs.
3.6. Similar New Structure. Structure that utilises similar or comparable structural design concepts such as details, geometry, structural arrangements, and load paths concepts and materials to an existing tested design.
3.7. Derivative/Similar Structure. Structure that uses structural design concepts such as details, geometry, structural arrangements, and load paths, stress levels and materials that are nearly identical to those on which the analytical methods have been validated.
3.8. Previous Test Evidence. Testing of the original structure that is sufficient to verify structural behaviour in accordance with CS 25.305.
4.Introduction As required by subparagraph (a) of CS 25.307, the structure must be shown to comply with the strength and deformation requirements of Subpart C of CS-25. This means that the structure must:
(a)be able to support limit loads without detrimental permanent deformation, and:
(b)be able to support ultimate loads without failure. This implies the need of a comprehensive assessment of the external loads (addressed by CS 25.301), the resulting internal strains and stresses, and the structural allowables. CS 25.307 requires compliance for each critical loading condition. Compliance can be shown by analysis supported by previous test evidence, analysis supported by new test evidence or by test only. As compliance by test only is impractical in most cases, a large portion of the substantiating data will be based on analysis. There are a number of standard engineering methods and formulas which are known to produce acceptable, often conservative results especially for structures where load paths are well defined. Those standard methods and formulas, applied with a good understanding of their limitations, are considered reliable analyses when showing compliance with CS 25.307. Conservative assumptions may be considered in assessing whether or not an analysis may be accepted without test substantiation. The application of methods such as Finite Element Method or engineering formulas to complex structures in modern aircraft is considered reliable only when validated by full scale tests (ground and/or flight tests). Experience relevant to the product in the utilisation of such methods should be considered.
5.Classification of structure
(a)The structure of the product should be classified into one of the following three categories: New Structure Similar New Structure Derivative/Similar Structure
(b)Justifications should be provided for classifications other than New Structure. Elements that should be considered are:
(i)The accuracy/conservatism of the analytical methods, and
(ii)Comparison of the structure under investigation with previously tested structure. Considerations should include, but are not limited to the following: external loads (bending moment, shear, torque , etc.); internal loads (strains, stresses, etc.); structural design concepts such as details, geometry, structural arrangements, load paths; materials; test experience (load levels achieved, lessons learned); deflections; deformations; extent of extrapolation from test stress levels.
6.Need and Extent of Testing The following factors should be considered in deciding the need for and the extent of testing including the load levels to be achieved:
(a)The classification of the structure (as above);
(b)The consequence of failure of the structure in terms of the overall integrity of the aeroplane;
(c)The consequence of the failure of interior items of mass and the supporting structure to the safety of the occupants. Relevant service experience may be included in this evaluation.
7.Certification Approaches The following certification approaches may be selected:
(a)Analysis, supported by new strength testing of the structure to limit and ultimate load. This is typically the case for New Structure. Substantiation of the strength and deformation requirements up to limit and ultimate loads normally requires testing of sub-components, full scale components or full scale tests of assembled components (such as a nearly complete airframe). The entire test program should be considered in detail to assure the requirements for strength and deformation can be met up to limit load levels as well as ultimate load levels. Sufficient limit load test conditions should be performed to verify that the structure meets the deformation requirements of CS 25.305(a) and to provide validation of internal load distribution and analysis predictions for all critical loading conditions. Because ultimate load tests often result in significant permanent deformation, choices will have to be made with respect to the load conditions applied. This is usually based on the number of test specimens available, the analytical static strength margins of safety of the structure and the range of supporting detail or sub-component tests. An envelope approach may be taken, where a combination of different load cases is applied, each one critical for a different section of the structure. These limit and ultimate load tests may be supported by detail and sub-component tests that verify the design allowables (tension, shear, compression) of the structure and often provide some degree of validation for ultimate strength.
(b)Analysis validated by previous test evidence and supported with additional limited testing. This is typically the case for Similar New Structure. The extent of additional limited testing (number of specimens, load levels, etc.) will depend upon the degree of change, relative to the elements of paragraphs 5(b)(i) and (ii). For example, if the changes to an existing design and analysis necessitate extensive changes to an existing test-validated finite element model (e.g. different rib spacing) additional testing may be needed. Previous test evidence can be relied upon whenever practical. These additional limited tests may be further supported by detail and sub-component tests that verify the design allowables (tension, shear, compression) of the structure and often provide some degree of validation for ultimate strength.
(c)Analysis, supported by previous test evidence. This is typically the case for Derivative/ Similar Structure. Justification should be provided for this approach by demonstrating how the previous static test evidence validates the analysis and supports showing compliance for the structure under investigation. Elements that need to be considered are those defined in paragraphs 5(b)(i) and (ii). For example, if the changes to the existing design and test-validated analysis are evaluated to assure they are relatively minor and the effects of the changes are well understood, the original tests may provide sufficient validation of the analysis and further testing may not be necessary. For example, if a weight increase results in higher loads along with a corresponding increase in some of the element thickness and fastener sizes, and materials and geometry (overall configuration, spacing of structural members, etc.) remain generally the same, the revised analysis could be considered reliable based on the previous validation.
(d)Test only. Sometimes no reliable analytical method exists, and testing must be used to show compliance with the strength and deformation requirements. In other cases it may be elected to show compliance solely by tests even if there are acceptable analytical methods. In either case, testing by itself can be used to show compliance with the strength and deformation requirements of CS-25 Subpart C. In such cases, the test load conditions should be selected to assure all critical design loads are encompassed. If tests only are used to show compliance with the strength and deformation requirements for single load path structure which carries flight loads (including pressurisation loads), the test loads must be increased to account for variability in material properties, as required by CS 25.307(d). In lieu of a rational analysis, for metallic materials, a factor of 1.15 applied to the limit and ultimate flight loads may be used. If the structure has multiple load paths, no material correction factor is required.
8.Interpretation of Data The interpretation of the substantiation analysis and test data requires an extensive review of: the representativeness of the loading ; the instrumentation data ; comparisons with analytical methods ; representativeness of the test article(s) ; test set-up (fixture, load introductions) ; load levels and conditions tested ; test results. Testing is used to validate analytical methods except when showing compliance by test only. If the test results do not correlate with the analysis, the reasons should be identified and appropriate action taken. This should be accomplished whether or not a test article fails below ultimate load. Should a failure occur below ultimate load, an investigation should be conducted for the product to reveal the cause of this failure. This investigation should include a review of the test specimen and loads, analytical loads, and the structural analysis. This may lead to adjustment in analysis/modelling techniques and/or part redesign and may result in the need for additional testing. The need for additional testing to ensure ultimate load capability, depends on the degree to which the failure is understood and the analysis can be validated by the test.
[Amdt 25/1]