SAE AIR 5552 : 2015

Superseded

View Superseded by

DEVELOPMENT AND QUALIFICATION OF COMPOSITE LANDING GEARS

Available format(s)

Hardcopy , PDF

Superseded date

21-09-2020

Language(s)

English

Published date

09-11-2015

Publisher

SAE International

1. SCOPE
2. REFERENCES
3. APPROACH
4. REQUIREMENTS
5. DEVELOPMENT APPROACH
6. DAMAGE TOLERANCE
7. THREAT ASSESSMENT
8. MATERIAL AND PROCESS CHARACTERISATION
9. COMPONENT DESIGN
10. HYBRID ASSEMBLY
11. COMPONENT TESTING
12. CONTINUING AIRWORTHINESS

Gives general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements.

Committee	A-5B
DocumentType	Standard
Pages	16
PublisherName	SAE International
Status	Superseded
SupersededBy	SAE AIR 5552:2010(R2020)
Supersedes	SAE AIR 5552 : 2010

FAA AC 23-13 : 2005	FATIGUE, FAIL-SAFE, AND DAMAGE TOLERANCE EVALUATION OF METALLIC STRUCTURE FOR NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES
SAE ARP 5644 : 2013(R2019)	LANDING GEAR SHOCK ABSORPTION TESTING OF CIVIL AIRCRAFT
SAE AIR 1494 : 1997	VERIFICATION OF LANDING GEAR DESIGN STRENGTH
SAE ARP 1311 : 2015	LANDING GEAR STRUCTURES AND MECHANISMS
FAA AC 20-107 : 2009	COMPOSITE AIRCRAFT STRUCTURE
FAA AC 25.571-1 : 2011	DAMAGE TOLERANCE AND FATIGUE EVALUATION OF STRUCTURE
SAE AIR 5914 : 2014	LANDING GEAR FATIGUE SPECTRUM DEVELOPMENT FOR PART 25 AIRCRAFT