Resulting ACs, Regulatory Guidance and Policy

There were no specific ACs resulting from this accident. However, as a result of the events of November 3, 1973, the following changes were made:

Engine/Airplane Design Changes:

1. Number of inlet cowl brackets increased from 12 to 21.
2. Blade axial retention increased from 18,000 to 60,000 pounds-force ultimate.
3. Fan blade/case tip clearance increased.

GEAE Design Practice:

GEAE engine design practice was updated to incorporate lessons learned regarding fan rotor and case harmful interacting vibratory modes.

Advisory Material:

This accident provided data and information relative to engine fragment spread angles that were used for development of FAA Order 8110.11, titled "Design Considerations for Minimizing Damage Caused by Uncontained Aircraft Turbine Engine Rotor Failures," dated November 19, 1975.

The information in this Order was subsequently revised and issued in AC 20-128. Note this link will take you to the FAA Regulatory and Guidance Library. You will have to use the Back arrow in your browser to return to the lesson.