C-130H Centre Wing Lower Surface Tang Blend Repair Management

Ross Stewart; Alvin Ng; Stuart Trezise; Phillip East; Kevin Jackson

doi:10.4028/www.scientific.net/AMR.891-892.1071

Paper Titles

Bayesian Updating of Aircraft Risk Assessments Using Results of Inspection
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Structural Integrity – Yesterday – Today – Tomorrow
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Pseudo Fatigue Testing for Rapid Certification to Service
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Practical Application of Structural Repair Fatigue Life Determination on the AP-3C Orion Platform
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C-130H Centre Wing Lower Surface Tang Blend Repair Management
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QinetiQ Aircraft Structural Integrity Experience and Lessons Learnt
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Cost Effective Safety from Full System Teardowns
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Development of a Probabilistic Model for the Prediction of Fatigue Life in the Very High Cycle Fatigue (VHCF) Range Based on Inclusion Population
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Fatigue Crack Growth in Ultrafine-Grained Copper Obtained by ECAP
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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 891-892C-130H Centre Wing Lower Surface Tang Blend Repair...

C-130H Centre Wing Lower Surface Tang Blend Repair Management

Abstract:

The RAAF found significant corrosion on the C-130H fleet Centre Wing Lower Surface (CWLS) panels at the tangs adjacent to the rainbow fittings. Repair of this corrosion involves blends and spot facing, and often requires the addition of a doubler to reinforce the region. All RAAF C-130H aircraft had various combinations of spot faces, blends and in some cases doublers at this location. Due to the number and combination of repairs, providing fleet wide management advice is problematic. The fleet condition was assessed from damage maps, repairs and previous analyses. From this a number of worst case configurations were determined. A Finite Element Model was developed and used to determine the bearing and by-pass loads in each fastener row of the panel tangs. Stress intensity correction factors were developed for cracks growing from or to a spot face using Stress Check. These correction factors were applied on top of geometry factors for the baseline configuration. A Damage Tolerance Assessment (DTA) was performed to assess the impact of spot face and blend repairs on the centre wing lower surface panel tangs, in order to develop a fleet wide management strategy. Based on the results for the repair cases, it was shown that the repairs identified in the damage maps could be managed within the existing safety by inspection program.