RR NDB
"Sequential Failure". A time worn concept, whether "crumple zone", or ablative skin.
The problem is at least "twofold". One is the almost unavoidable problem of mating plastic to metal, mechanically (1), or bonded (2).
On the Airbus VS it is mechanical. This presents the "focal energy" obstacle. A concentration of stress in Epoxy/Reinforced structures is counter intuitive to the material's strong point. Thus a dowel, pin, or clevis, bracket system focuses failure sums of energy on an assembly whose design is related to stress/spread for maximum load areas. Note the A350 has gone to 5 (five) saddle/pin systems.
The second, bonded, is universally avoided unless some spread can be attained.
The most important consideration is the fact that this most critical assembly is "surface mounted". This concentrates virtually all Stresses on an inescapably small area. The VS/Rudder is vertically cantilevered, a swell looking and very efficient way to alleviate drag from external wetted areas.
However.......
edit... I cannot locate the "lateral rods" on the bare aft fuse of the 587 A300. These were added to later a/c....... There are pictures of these rods on the VS (447). After the fact design, hmmm.......
edit... Disregard, I did find a remnant of the "Lateral Rod" on aft bracket.
sorry...