Of course, if this could be used for large portions of the structure, that really changes the equations a lot. You don't need nearly as much lift for a given weight of cargo.
The Hindenburg used 200,000m^3 of hydrogen (generating a lifting force of approx. 215,000kg. Net useful load was only 10,000kg.
When selecting materials for building aircraft weight is only one of many concerns. Durability, flexibility, strength, cost, etc are all major issues. Considering the design goals for this material seem to primarily just be weight I would be surprised if it's strength to weight ratio was impressive enough to overcome cost issues.
Also compared to a modern blimp the Hindenburg an ancient design that's been far surpassed. A modern Zeppelin is much closer to 20% lift to weight ratio than 5 for the Hindenburg despite using less efficient helium gas. Their maximum permitted takeoff weight is 10,690 kg, with a payload of 1,900 kg.(http://en.wikipedia.org/wiki/Zeppelin_NT)
