Airworthiness Directives; Airbus Model A340-200 and A340-300 Series Airplanes

[Federal Register Volume 70, Number 172 (Wednesday, September 7, 2005)]
[Rules and Regulations]
[Pages 53051-53053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-17606]



[[Page 53051]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22291; Directorate Identifier 2005-NM-038-AD; 
Amendment 39-14251; AD 2005-18-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A340-200 and A340-300 
Series Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A340-200 and A340-300 series airplanes. This AD 
requires a one-time inspection for discrepancies of the spotfacing for 
the pylon-to-engine attachment bolts on the pyramid forward fitting of 
the engine pylon, and repair if necessary. This AD results from a 
report that, during a routine inspection, it was found that the 
diameter of the spotfacings was too small for two of the pylon-to-
engine attachment bolts on the pyramid forward fitting. We are issuing 
this AD to prevent reduced structural integrity of the pylon-to-engine 
attachment bolts on the pyramid forward fitting, which could result in 
separation of an engine from the airplane.

DATES: This AD becomes effective September 22, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 22, 
2005.
    We must receive comments on this AD by November 7, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A340-200 and A340-
300 series airplanes. The DGAC advises that, during a routine 
inspection, it was found that the diameter of the spotfacings was too 
small for two of the pylon-to-engine attachment bolts on the pyramid 
forward fitting. Investigation revealed that, because the diameter of 
the spotfacings on the two front fasteners was incorrect, the bolt head 
did not fit correctly on the flat part of the spotfacing, causing 
possible damage of the spotfacing area and cracking/wear of the pylon-
to-engine attachment bolt. This condition, if not corrected, could 
result in separation of an engine from the airplane.

Relevant Service Information

    Airbus has issued Service Bulletin A340-54-4009, including Appendix 
01, Revision 01, dated February 15, 2005. The service bulletin 
describes procedures for a one-time inspection for discrepancies of the 
spotfacing for the pylon-to-engine attachment bolts on the pyramid 
forward fitting of the engine pylon, and repair if necessary. The 
discrepancies include incorrect dimensions of the spotfacing and 
misalignment of the bolt. The repair involves measuring and machining 
the spotfacing to the correct dimension and installing new bolts and 
washers. Accomplishing the actions specified in the service information 
is intended to adequately address the unsafe condition. The DGAC 
mandated the service information and issued French airworthiness 
directive F-2005-011, dated January 19, 2005, to ensure the continued 
airworthiness of these airplanes in France.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are issuing this AD to prevent reduced structural 
integrity of the pylon-to-engine attachment bolts on the pyramid 
forward fitting, which could result in separation of an engine from the 
airplane. This AD requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Difference Between the AD and Service Bulletin.''

Difference Between the AD and Service Bulletin

    Airbus Service Bulletin A340-54-4009 recommends concurrently 
accomplishing Airbus Service Bulletin A340-71-4001, or the equivalent 
production modification. The equivalent production modification has 
been done on the airplanes specified in the applicability of this AD. 
Additionally, the French airworthiness directive does not mandate 
accomplishment of the concurrent service bulletin. In light of these 
factors, this AD would not require accomplishing the concurrent service 
bulletin.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, the required inspection would take about 1 work hour per 
airplane, at an average labor rate of $65 per work hour. Based on these 
figures, the estimated cost of the inspection would be $65 per 
airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is

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unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to the 
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2005-22291; Directorate Identifier 2005-NM-038-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the AD that 
might suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of that Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you may visit 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-18-11 Airbus: Amendment 39-14251. Docket No. FAA-2005-22291; 
Directorate Identifier 2005-NM-038-AD.

Effective Date

    (a) This AD becomes effective September 22, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A340-211, -212, and -213, 
and A340-311, -312, and -313 airplanes; certificated in any 
category; as identified in Airbus Service Bulletin A340-54-4009, 
Revision 01, dated February 15, 2005.

Unsafe Condition

    (d) This AD results from a report that, during a routine 
inspection, it was found that the diameter of the spotfacings was 
too small for two of the pylon-to-engine attachment bolts on the 
pyramid forward fitting. The FAA is issuing this AD to prevent 
reduced structural integrity of the pylon-to-engine attachment bolts 
on the pyramid forward fitting, which could result in separation of 
an engine from the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

One-Time Inspection/Repair

    (f) Within 18 months after the effective date of this AD: 
Perform a one-time detailed inspection for discrepancies of the 
spotfacing for the pylon-to-engine attachment bolts on the pyramid 
forward fitting of each engine pylon, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-54-4009, 
Revision 01, dated February 15, 2005. Repair any discrepancy before 
further flight in accordance with the service bulletin. Inspections 
and repairs accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A340-54-4009, dated August 
25, 2004, are acceptable for compliance with this paragraph.

    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.''

No Reporting Requirement

    (g) Although the referenced service bulletin describes 
procedures for submitting a report of inspection results to the 
manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.

[[Page 53053]]

Related Information

    (i) French airworthiness directive F-2005-011, dated January 19, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Airbus Service Bulletin A340-54-4009, Revision 
01, dated February 15, 2005, excluding Appendix 01, to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference of this document in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this 
service information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW., 
Room PL-401, Nassif Building, Washington, DC; on the Internet at 
http://dms.dot.gov; or at 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 29, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-17606 Filed 9-6-05; 8:45 am]
BILLING CODE 4910-13-P

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