AITM 1-0006 is an Airbus Industry Test Method used to determine Mode II (in-plane shear) interlaminar fracture toughness energy (often reported as GIIc) for fiber-reinforced polymer composites such as CFRP laminates.
If you need help mapping your laminate form, thickness, and target data-reduction approach to the right fixture and instrumentation, talk with our team about your test setup before ordering equipment.
AITM 1-0006 — Airbus Industry Test Method
AITM 1-0006 is commonly cited in aerospace qualification and materials characterization work where delamination resistance under Mode II loading is needed. The measured toughness value is used to compare material systems, assess processing and contamination effects, and support allowables and damage-tolerance decisions.
Quick definition
Standard focus: Mode II interlaminar fracture toughness energy (GIIc) for composite laminates.
Typical output: A critical strain-energy release rate value for shear-driven crack growth (initiation and/or propagation, depending on the cited procedure and reporting practice).
Typical loading style: A flexural-style configuration used to drive stable shear delamination growth.
What This Standard Covers
AITM 1-0006 addresses how to generate Mode II delamination growth in a controlled way and how to calculate an interlaminar fracture toughness energy value from force–displacement behavior and specimen geometry. In practice, this is used to characterize a laminate’s resistance to shear-driven delamination along a ply interface or insert plane.
This method is typically applied to flat laminate coupons prepared with an intentional starter crack/insert to define the delamination plane, with testing performed under defined conditioning and rate requirements specified by the controlling program documentation.
Why This Standard Matters in Testing
Mode II toughness is frequently used when delamination under shear is a design driver (for example, in regions where bending and shear can promote interply crack growth). Programs may use GIIc as an input to damage-growth models, for material down-selection, or to compare production variables such as cure, surface preparation, or environmental exposure.
Because toughness values can be sensitive to specimen preparation, data-reduction approach, and how crack growth is identified, the exact edition and reporting expectations referenced in a purchase order or qualification plan matter for reproducible results.
Common Materials, Product Types, or Applications Covered
Common materials: Carbon-fiber/epoxy and other fiber-reinforced polymer matrix composites (including aerospace-grade laminate forms).
Common product forms: Flat cured panels used to machine coupons for interlaminar delamination testing.
Common application contexts: Aerospace material qualification, process-change substantiation, comparative studies of laminate toughening concepts, and bonded/laminated structures where delamination resistance is a key performance metric.
Common Test or Verification Workflow
A typical AITM 1-0006 workflow includes coupon preparation to create a defined delamination plane, conditioning to the required lab or environmental state, and controlled loading to drive Mode II crack growth. The test record generally includes the force–displacement response and the key dimensions needed to compute an energy release rate value.
Common workflow elements: Coupon machining and insert/starter crack preparation, fixture setup and alignment, monotonic loading with continuous data capture, and calculation/reporting of GIIc values as required by the controlling document.
Equipment Commonly Used for This Standard
Equipment selection is driven by the expected force range, specimen dimensions, and how displacement and crack growth are monitored. Most labs run this on a servo-hydraulic or electromechanical universal testing system with a dedicated bending-style fixture and stable, low-noise data acquisition.
Common equipment: Universal testing machine (UTM), calibrated load cell, flexural test fixture (Mode II delamination configuration), displacement measurement (crosshead and/or external), and appropriate software for test control and calculation.
If you are comparing frame capacity, fixture span range, and instrumentation options for Mode II delamination work, you can request a detailed quote for a configuration matched to your force range and reporting needs.
How to Read This Designation or Revision
Designation meaning: “AITM” identifies an Airbus Industry Test Method, and “1-0006” is the specific method number commonly associated with Mode II interlaminar fracture toughness energy.
Revision sensitivity: Many Airbus test methods are controlled by issue level/date in contractual or program documentation. When a drawing, material specification, or qualification plan cites AITM 1-0006, match the exact referenced issue (and any program-specific deviations) before finalizing procedures, calculations, or report templates.
Related Standards, Methods, or Frameworks
Depending on the program, Mode II interlaminar fracture toughness may also be specified using regional or industry methods covering similar measurements and specimen concepts. When multiple documents are allowed, the permitted calculation approach and reporting format can differ enough to change results and comparability.
Commonly encountered related references: EN 6034 (aerospace composites—Mode II interlaminar fracture toughness energy) and other Mode II delamination methods used for unidirectional polymer matrix composites.
Get help selecting a setup for AITM 1-0006
To scope an AITM 1-0006 test system, the most important inputs are your expected force range, specimen size/span needs, and how you plan to capture displacement and crack-growth indicators for your required report format. Share your cited issue level and target materials, and we’ll help you narrow the right frame, fixture, and instrumentation package—contact our team to discuss your application.