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• Information on defect depth not provided
signal amplitude [dB]
measured value result: C-scan image
x
z
•Display mode: C-scan (top view)
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 25
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Implementation - Quality Assurance
Principle of manual ultrasonic through transmission technique – single
channel mode using inspection tongs (for in-production and in-service
application)
• Basic principle: ultrasonic through transmission method in general comparable to
through transmission method in squirter technique, manual movement of the
transducers
• both-side accessibility required
• Display mode: A-scan
• A-scan: Assessment of indications by means of sound attenuation relative to the
defect-free surrounding area
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 26
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Structural Qualification - Requirements
Basis for Certification
• JCRI (JAA Certification Review Item) is a selected identified item of the
civil CS regulation with rules and policies established in other civil
programs.
• MCRI (Military Certification Review Item) is a selected extension of the
civil CS regulation with rules and policies derived from military
regulations and standards.
• Note: Although A400M is a militairy transport aircraft, the basis for
certification is the civil CS25 – former JAR25.
Hence CS25.571 (b) is applicable, which implies requirement of
Damage Tolerant design.
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 27
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Structural Qualification - Analysis
• Main Frame with FML-Strap is a Structure with Damage
Containment Feature (DCF).
• Calculated Components
Justification of FML strap (run-out and highest stressed location)
Justification of Frame Inner Flange
• Failure Criteria
F&DT: Fatigue, Crack Growth, No Defect Growth, Residual Strength.
Static: Material Strength, Stability
Analyses supported by Test Evidence
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 28
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Structural Qualification - Analysis
• Fatigue crack growth:
Load divided between Strap and Inner flange by product of
stiffness and area
Crack growth corrected for “crack bridging” by additional
function α
Edge cracks from bore holes and edges calculated
Strap bridging versus crack length
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0 10 20 30 40 50 60 70 80 90 100
c ra c k le ng t h a (mm)
S t rap bridging funct ion Expon. (S t rap bridging funct ion)
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 29
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Structural Qualification - Analysis
• Residual strength analysis
• Conclusion: Introducing an significant initial centred unbonded zone does not
lead to delamination growth under tensile as well as compressive limit load
neither. Final maximum size of acceptable delamination could not be found
due to limits of the model.
Based on this outcome the rivet pitch has been defined.
Frame stress
distribution at
ultimate positive
moment
Frame stress
distribution at
ultimate negative
moment
Frame Inner Flange with bonded
reinforcement modelled.
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 30
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Structural Qualification - Test
• Full-scale Fatigue Test with MSN5001
• Frames on Left Hand (LH) and Right Hand (RH) with FML straps:
LH side: normal series standard
RH side: small artificial delaminations in frame-strap bondline and Glare
• Simulating 2.5 DSG (25.000 FC)
Planned for Feb. 2010- Feb. 2011
Matthijs Plokker / Derk Daverschot - ICAF 2009 20/05/2009 Page 31
© AIRBUS DEUTSCHLAND GMBH. All rights reserved. Confidential and proprietary document.
Structural Qualification - Test
Overview Static component tests (three)
Aim of the static frame bending test series is to evaluate the bonding of the FML-strap in
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