DISTRIBUTION A. Approved for public release; distribution unlimited.
EZ-SB-19-01, Page 1 of 15
Number: EZ-SB-19-01
Date: 10 June 2019
Subject: Durability and Damage Tolerance Certification for Additive Manufacturing
of Aircraft Structural Metallic Parts
References:
1. MIL-STD-1530D Change 1, “Aircraft Structural Integrity Program”, 13 October
2016
2. MIL-HDBK-516C, “Airworthiness Certification Criteria”, 12 December 2014
3. FAA Order 8110.101A, “Type Certification Procedures for Military Commercial
Derivative Aircraft”,
4. EN-SB-11-001, “Guidance on Correlating Finite Element Models to Measurements
from Structural Ground Tests”, 24 June 2011
5. EZ-SB-13-002, “Correlating Durability Analysis to Unanticipated Fatigue Cracks in
Metallic Structure”, 26 June 2013
6. EZ-SB-14-003, “Durability Test Programs to Validate Aircraft Structure Service Life
Capability for Repairs, Modifications, and Materials & Processes Changes”, 9 April
2014
7. EZ-SB-13-001, “Substitution Guidelines Covering New Material, Product Form,
and Processes for Aircraft Metallic Components Parts”, 11 January 2013
8. EN-SB-08-001 Rev A, “Revised Damage Tolerance Requirements and
Determination of Fail-Safety Life Limits for Fail-Safe Metallic Structures”, 18 March
2011
Purpose:
The purpose of this Structures Bulletin (SB) is to establish the requirements for Durability
and Damage Tolerance (DADT) certification of aircraft structural metallic parts fabricated
from an Additive Manufacturing (AM) process. Alternate approaches may be used for
Military Commercial Derivative Aircraft (MCDA) that are approved by the Federal Aviation
Administration (FAA).
AFLCMC/EZ
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