The Effect of Peening on the Fatigue Life of 7050 Aluminium Alloy
The Effect of Peening on the Fatigue Life of 7050 Aluminium Alloy
The Effect of Peening on the Fatigue Life of 7050 Aluminium Alloy
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DSTO-RR-0208<br />
Figure 30: Locati<strong>on</strong> <str<strong>on</strong>g>of</str<strong>on</strong>g> <strong>the</strong> X-19 area <str<strong>on</strong>g>of</str<strong>on</strong>g> <strong>the</strong> Y470 bulkhead wheel well flange.<br />
Failure<br />
<strong>Fatigue</strong> initiati<strong>on</strong> sites in<br />
web fillet tangency and<br />
under flange.<br />
X19 from<br />
centreline<br />
Figure 31: Failure locati<strong>on</strong> at <strong>the</strong> X19 stiffener <strong>on</strong> ST16 after approximately 12000 SFH cycling.<br />
Failure was LH side. Looking forward.<br />
Based <strong>on</strong> <strong>the</strong> ST16 fatigue test and FE analysis MDA proposed ECP365 to improve <strong>the</strong><br />
fatigue life <str<strong>on</strong>g>of</str<strong>on</strong>g> <strong>the</strong> X19 and <strong>the</strong> crotch area <str<strong>on</strong>g>of</str<strong>on</strong>g> <strong>the</strong> Y470.5 bulkhead. <str<strong>on</strong>g>The</str<strong>on</strong>g> US Navy released <strong>the</strong><br />
X19 repair as AFC No. 174. Based <strong>on</strong> this AMRL proposed a modified repair for <strong>the</strong> X19<br />
pocket and a subsequent RAAF fleet lifing policy. <str<strong>on</strong>g>The</str<strong>on</strong>g> CF have completed ECP365<br />
modificati<strong>on</strong> process.<br />
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