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D-1
FIGURE D-7. MODERATE WEAR
OF PI/PTFE ALLOY FROM
CLAMP WHEN MIXED WITH
XLETFE IN GROUP I
FIGURE D-8. MODERATE WEAR OF
PI/PTFE FROM CLAMP IN GROUP I
BUNDLE MIXED WITH MF-PTFE
FIGURE D-9. SEVERE WEAR OF
XLETFE ALLOY WIRE FROM
PLATE IN GROUP I
NONMIXED BUNDLE
FIGURE D-10. MODERATE WIRE-TOWIRE
WEAR ON XPI WIRE
WHEN MIXED WITH XLETFE
GROUP IIF BUNDLE
FIGURE D-11. MODERATE WIRETO-
WIRE WEAR ON PTFE/GLASS
IN NONMIXED GROUP IIF BUNDLE
FIGURE D-12. XPI WIRE DAMAGED
FROM PI/PTFE WIRE IN THE
80-POUND CRUSH TEST
D-2
FIGURE D-13. PI/PTFE WIRE
DAMAGED FROM PI WIRE IN
THE 80-POUND CRUSH TEST
FIGURE D-14. TEST BUNDLES
MOUNTED ON VIBRATION
FIXTURES
FIGURE D-15. FIXTURES MOUNTED
ON VIBRATION TABLE
D-3/D-4
DOT/FAA/AR-07/65
Air Traffic Organization
Operations Planning
Office of Aviation Research
and Development
Washington, DC 20591
Aging Aircraft Evaluation of
the Airbus A320 Rudder
Control System
March 2008
Final Report
This document is available to the U.S. public
through the National Technical Information
Service (NTIS), Springfield, Virginia 22161.
U.S. Department of Transportation
Federal Aviation Administration
NOTICE
This document is disseminated under the sponsorship of the U.S.
Department of Transportation in the interest of information exchange. The
United States Government assumes no liability for the contents or use
thereof. The United States Government does not endorse products or
manufacturers. Trade or manufacturer's names appear herein solely
because they are considered essential to the objective of this report. This
document does not constitute FAA certification policy. Consult your local
FAA aircraft certification office as to its use.
This report is available at the Federal Aviation Administration William J.
Hughes Technical Center's Full-Text Technical Reports page:
actlibrary.tc.faa.gov in Adobe Acrobat portable document format (PDF).
Report Documentation Page
1. Report No.
DOT/FAA/AR-07/65
2. Government Accession No. 3. Recipient's Catalog No.
4. Title and Subtitle
AGING AIRCRAFT EVALUATION OF THE AIRBUS A320 RUDDER
CONTROL SYSTEM
5. Report Date
March 2008
6. Performing Organization Code
7. Author(s)
Iyiin A. Chang, Joseph DiMambro, Paul W. Werner, and Jeffrey G. Blanchette
8. Performing Organization Report No.
9. Performing Organization Name and Address
Telemetry and Data Systems
Sandia National Laboratories
Albuquerque, New Mexico 87185-0986
10. Work Unit No. (TRAIS)
11. Contract or Grant No.
DE-AC04-94AL85000
12. Sponsoring Agency Name and Address
U.S. Department of Transportation
Federal Aviation Administration
Air Traffic Organization Operations Planning
Office of Aviation Research and Development
Washington, DC 20591
13. Type of Report and Period Covered
Final Report
14. Sponsoring Agency Code
ANM-100
15. Supplementary Notes
The Federal Aviation Administration Airport and Aircraft Safety R&D Division COTR was Robert McGuire.
16. Abstract
The study summarized in this document focused on the rudder system of the Airbus A320 family (A318, A319, A320, and A321)
and included a review of the system description and a safety/reliability analysis. Of particular interest were recommendations for
aging, infrequently maintained, or uninspectable parts, and parts that may have latent problems. The study found that the failure
probabilities evaluated fell reasonably within the regulatory requirements. However, it also found varying degrees of dependence
in the designs of redundant paths. Few corrosion issues were identified. The refurbished parts evaluated in this study had similar
failure modes as original parts but had significantly shorter product lives than the original units.
17. Key Words
Control systems, Rudder, Actuators, Refurbished, Risk
analysis
18. Distribution Statement
This document is available to the U.S. public through the
National Technical Information Service (NTIS), Springfield,
Virginia 22161.
19. Security Classif. (of this report)
Unclassified
20. Security Classif. (of this page)
Unclassified
21. No. of Pages
34
22. Price
Form DOT F 1700.7 (8-72) Reproduction of completed page authorized
ACKNOWLEDGEMENTS
The authors would like to thank Mr. Dieter Meese at Airbus Industries for coordinating efforts
among Airbus, the original equipment manufacturers, and Sandia National Laboratories. Also,
without the firm commitment of Mr. Meese’s management team (Laurent Alegre, Patrick Glapa,
　
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