Bolts are torqued to improve their resistance to fatigue when loads either fluctuate greatly or vibrate. The torque forces the clamped materials to deform slightly, and the bolt stretches, too. Trying to separate the parts now requires a considerable amount of load just to begin to open a gap. In service these parts will not shake free, and the joint is now much more reliable.
When such a joint is very highly loaded, such as in critical places like landing gear, wing struts, engine mounts, the bolt represents a single point where failure can cause catastrophe. The joint therefore demands a fastener that can withstand large loads, making it necessary to use a very high-strength bolt. But given the fact that all of the loads have been upped, and the stresses are so high, the torque on the bolt must also go up for it to be effective.
Around the engine, the temperatures make the situation worse by introducing thermal expansion and contraction into the equation. Again, the parts can either separate in service, or expand against the bolt enough to cause it to break.
Now the question is "how does that bolt get torqued when it is installed". Put an old 12-point socket on a 1/2"-20 bolt hex head and don't expect to get 100 ft-Lb without damaging the hex on the bolt head (or maybe the socket). This doesn't fit the tidy way aerospace people like to do things. It was probably tried, and didn't work. A new head form was devised with a spline to reduce the slippage. Now the bolt can be installed, torqued, checked 100 hours later, removed during a late night overhaul, put back, re-torqued, and removed one last time, without any worry of smashing the points so smooth that you can't get it out again.
BTW, the head is forged at the factory, just like a hex. Getting the shape right is a matter of tooling, but I don't think it would be a radical new process from the factory's point of view. I doubt that it would be a pain to manufacture. I could be corrected on that point.
Steven Fahey, CET