AD 2006-04-11 R1

AD Final Rules - 2006-04-11 R1.pdf
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AD Number:
2006-04-11 R1
Document Type:
AD Final Rules
Docket Number:
FAA-2006-24953
Subject Heading:
Airworthiness Directives; Airbus Model A321-100 Series Airplanes
Subject:
Main landing gear (MLG)
Status:
Current
Citation:
Federal Register: June 7, 2006 (Volume 71, Number 109)
Citation Publish Date:
06/07/2006
Effective Date:
06/22/2006
Make:
Airbus
Model:
A321-111 | A321-112 | A321-131
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
2006-04-11
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[Federal Register: June 7, 2006 (Volume 71, Number 109)]


[Rules and Regulations]


[Page 32807-32811]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr07jn06-2]


–––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. FAA-2006-24953; Directorate Identifier 2006-NM-084-AD; Amendment 39-14628;


AD 2006-04-11 R1]


RIN 2120-AA64


Airworthiness Directives; Airbus Model A321-100 Series Airplanes


AGENCY:
 
Federal Aviation Administration (FAA), Department of Transportation (DOT).


ACTION:
 
Final rule; request for comments.


–––––––––––––––––––––––––––––––––––


SUMMARY:
 
The FAA is revising an existing airworthiness directive (AD) that applies to certain


Airbus Model A321-111, -112, and -131 airplanes. That AD currently requires repetitive inspections


to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle


fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner


rear spar; and repair, if necessary. That AD also provides for optional terminating action for the


repetitive inspections, adds inspections of three additional mounting holes, and revises the thresholds


for the currently required inspections. We issued that AD to detect and correct fatigue cracking on the


inner rear spar of the wings, which could result in reduced structural integrity of the airplane. This


new AD retains the requirements and revises the applicability of that AD. This AD results from the


discovery of a typographical error in the applicability of that AD, which could cause the unsafe


condition on an affected airplane to remain uncorrected. We are issuing this AD to detect and correct


fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity


of the airplane.


DATES:
 
Effective June 22, 2006.


The incorporation by reference of the publications specified in the following table, as listed in


the regulations, was approved previously by the Director of the Federal Register as of March 8, 2006


(71 FR 8792, February 21, 2006).
2


MATERIAL INCORPORATED BY REFERENCE


Airbus service bulletin
 
Revision level
 
Date


A320–57–1100, including Appendix 01
 
(
 
1
 
)
 
July 28, 1997.


A320–57–1100, including Appendices 01 and 02
 
03
 
January 16, 2003.


A320–57–1101
 
03
 
July 30, 2003.


A320–57–1101
 
04
 
November 22, 2004.


1
 
Original


The incorporation by reference of Airbus Service Bulletin A320-57-1101, Revision 02, dated


October 25, 2001, as listed in the regulations, was approved previously by the Director of the Federal


Register as of April 21, 2004 (69 FR 17906, April 6, 2004).


The incorporation by reference of Airbus Service Bulletin A320-57-1101, dated July 24, 1997, as


listed in the regulations, was approved previously by the Director of the Federal Register as of


December 18, 1998 (63 FR 66753, December 3, 1998).


We must receive comments on this AD by August 7, 2006.


ADDRESSES:
 
Use one of the following addresses to submit comments on this AD.


•
 
DOT Docket Web site: Go to
 
http://dms.dot.gov
 
and follow the instructions for sending your


comments electronically.


•
 
Government-wide rulemaking Web site: Go to
 
http://www.regulations.gov
 
and follow the


instructions for sending your comments electronically.


•
 
Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street,


SW., Nassif Building, room PL-401, Washington, DC 20590.


•
 
Fax: (202) 493-2251.


•
 
Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street,


SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.


Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service


information identified in this AD.


FOR FURTHER INFORMATION CONTACT:
 
Dan Rodina, Aerospace Engineer, International


Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,


Washington 98055-4056; telephone (425) 227-2125; fax (425) 227-1149.


SUPPLEMENTARY INFORMATION:


Discussion


On February 9, 2006, we issued AD 2006-04-11, amendment 39-14492 (71 FR 8792, February


21, 2006), for certain Airbus Model A321-111, -112, and -131 airplanes. That AD requires repetitive


inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward


pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the


inner rear spar; and repair, if necessary. That AD also provides for optional terminating action for the


repetitive inspections, adds inspections of three additional mounting holes, and revises the thresholds


for the currently required inspections. That AD resulted from manufacturer analysis of the fatigue and


damage tolerance of the area surrounding certain mounting holes of the MLG. We issued that AD to


detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced


structural integrity of the airplane.