[Federal Register Volume 70, Number 249 (Thursday, December 29, 2005)]
[Rules and Regulations]
[Pages 76973-76974]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-24525]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-298-AD; Amendment 39-14354; AD 2005-22-10 R1]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111 Airplanes, and 
Model A320-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to certain Airbus Model A320-
111 airplanes, and Model A320-200 series airplanes. That AD currently 
requires a detailed inspection of the tail cone triangle to determine 
its position, and corrective actions if necessary. This document 
corrects the applicability by specifying that the AD affects only 
airplanes identified in Airbus Service Bulletin A320-27-1132, Revision 
01, dated June 19, 2002. This correction is necessary to ensure that 
only affected airplanes are subject to the requirements of the AD.

DATES: Effective December 5, 2005.
    The incorporation by reference of a certain publication listed in 
the regulations was approved previously by the Director of the Federal 
Register as of December 5, 2005 (70 FR 62232, October 31, 2005).

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: On October 20, 2005, the Federal Aviation 
Administration (FAA) issued AD 2005-22-10, amendment 39-14354 (70 FR 
62232, October 31, 2005), which applies to certain Airbus Model A320-
111 airplanes, and Model A320-200 series airplanes. That AD requires a 
detailed inspection of the tail cone triangle to determine its 
position, and corrective actions if necessary. That AD was prompted by 
a report that the tail cone triangles were not installed properly on 
certain airplanes during production, resulting in possible mis-rigged 
elevator servo-controls. The actions required by that AD are intended 
to prevent excessive vibrations of the elevators, which could result in 
reduced structural integrity and reduced controllability of the 
airplane.

Need for the Correction

    Information obtained recently by the FAA indicates that we 
inadvertently changed the applicability from that specified in the 
Notice of Proposed Rulemaking by omitting from the statement of 
applicability of AD 2005-22-10 that airplanes affected by the AD are 
those identified in Airbus Service Bulletin A320-27-1132, Revision 01, 
dated June 19, 2002.
    The FAA has determined that a correction to AD 2005-22-10 is 
necessary. The correction will revise the applicability to include a 
reference to Airbus Service Bulletin A320-27-1132, Revision 01, dated 
June 19, 2002.

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains December 5, 2005.
    Since this action reduces the number of airplanes affected by 
revising the applicability, it has no adverse economic impact and 
imposes no additional burden on any person.

[[Page 76974]]

Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Corrected]

0
2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2005-22-10 R1 Airbus: Amendment 39-14354. Docket 2002-NM-298-AD.

    Applicability: Model A320-111, -211, -212, -214, -231, -232, and 
-233 airplanes, certificated in any category; as listed in Airbus 
Service Bulletin A320-27-1132, Revision 01, dated June 19, 2002.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent excessive vibrations of the elevators, which could 
result in reduced structural integrity and reduced controllability 
of the airplane, accomplish the following:

Detailed Inspection and Corrective Action

    (a) Within 800 flight hours after the effective date of this AD, 
perform a detailed inspection to determine the position of each tail 
cone triangle in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-27-1132, Revision 01, dated June 19, 
2002. If the position of the tail cone triangle is not within the 
limits specified in the service bulletin: Within 3,500 flight hours 
after the inspection, re-rig the elevator servo controls to adjust 
the elevator neutral setting, and change the position of the tail 
cone triangle, in accordance with the service bulletin.


    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Actions Accomplished Per Previous Release of the Service Bulletin

    (b) Actions accomplished prior to the effective date of this AD 
in accordance with Airbus Service Bulletin A320-27-1132, dated March 
14, 2001, are considered acceptable for compliance with the 
corresponding actions required by this AD.

No Reporting Requirement

    (c) Although the service bulletin specifies to submit certain 
information to the manufacturer, this AD does not include such a 
requirement.

Alternative Methods of Compliance

    (d)(1) In accordance with 14 CFR 39.19, the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
is authorized to approve alternative methods of compliance for this 
AD.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Incorporation by Reference

    (e) Unless otherwise specified in this AD, the actions must be 
done in accordance with Airbus Service Bulletin A320-27-1132, 
Revision 01, excluding Appendix 01, dated June 19, 2002. This 
incorporation by reference was approved previously by the Director 
of the Federal Register as of December 5, 2005 (70 FR 62232, October 
31, 2005). To get copies of this service information, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 
To inspect copies of this service information, go to the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.


    Note 2: The subject of this AD is addressed in French 
airworthiness directive 2002-514(B) R1, dated November 13, 2002.

Effective Date

    (f) The effective date of this amendment remains December 5, 
2005.

    Issued in Renton, Washington, on December 15, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-24525 Filed 12-28-05; 8:45 am]
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