Originally Posted by wikipedia
To address stall issues in certain parts of the flight regime, the engine inlet design was modified in 1965-66, ending with the "Triple Plow I" and "Triple Plow II" designs.[27] The F-111A achieved a speed of Mach 1.3 in February 1965 with an interim intake design.[20][27] Cracks in the F-111's wing attach points were first discovered in 1968 during ground fatigue testing - an F-111 crashed the following year due to this issue. The attach structure required redesign and testing to ensure adequate design and workmanship.[28] Flight testing of the F-111A ran through 1973.[29]
Are we talking about a different aircraft...?