This paper presents the approach to certification of commercial aircraft primary composite structure. The approach to certification is based on analysis supported by coupon and component test evidence in compliance with guidelines issued by the FAA and EASA. Principles of certification methodology on static strength, fatigue and damage tolerance for primary composite structure are given herein according to AC20-107B issued by FAA recently.The paper eventually provides executable flowchart of full-scale static strength, fatigue and damage tolerance component test. The approach developed here is complying with regulations and advisory circular published by airworthiness authority.