New criteria were developed in coordination with the Federal Aviation Administration for the certification of adhesively bonded composite structure. The published FAA Special Condition requires residual strength and stiffness capability of bonded composite structure in the event of failure of critical bondlines. Methods available for meeting the requirements are discussed including: non-destructive investigation of joint strength, multiple load path design, mechanical fastening, and production unit proof testing. No single method has proven applicable for all designs. Examples of the different methods are given.