An aerobatic airplane has a key structural part of the empennage designed to undergo a design limit load of 7550 N at the operational maximum g- capability of the aircraft of 4.2 g. This part is made of a material with a yield stress of 250 MPa and an ultimate stress of 350 MPa. The static tests on this part made at the factory showed an ultimate margin of safety of 18.2% on this part. During training exercises, a g-meter shows that the pilot pulled a maneuver of 4.6 g. Upon review of the information from this exercise, the maintenance chief of the company that owns the plane needs to determine whether the plane can continue to be safely flown. 

Give your answer/thoughts in this regard with appropriate calculations as evidence.