Fatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components by Russell Wanhill & Simon Barter & Loris Molent

Fatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components by Russell Wanhill & Simon Barter & Loris Molent

Author:Russell Wanhill & Simon Barter & Loris Molent
Language: eng
Format: epub
ISBN: 9789402416756
Publisher: Springer Netherlands


Fig. 4.3Crack depths versus service flights for fatigue cracks in the AA7075-T6 lower spar caps from Macchi MB-326H (S/N A7-076): IDS = initial defect size; arrows point in the crack growth directions. After [76,89,133]

Fig. 4.4Crack depths versus full-scale test life for fatigue cracks in the AA7075-T6 spars (D17 location) from MB-326H (S/N A7-076) and other locations in spars from three different aircraft. After [76,89,133]

4.3 Further Examination of Wing Spars

Detailed investigation of the A7-076 failed spar cap revealed manufacturing discontinuities in many holes, making it probable that others would be present in spars from other aircraft in the fleet. An NDI procedure was developed and employed for fleet-wide detection (within the NDI limits) of any such cracks. This resulted in crack indications in three other wings besides those from the A7-076 accident. In addition, detailed (teardown) examination of the cracked lower spar cap from the right wing of A7-076 showed that there were many cracks growing from normal quality structural details [89]. This meant that the Safe Life of the entire fleet needed to be reassessed, and the results led to a fleet recovery programme. A full description of these activities is provided by Clark et al. [89] and summarised in Sects. 4.3.1 and 4.3.2.



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