[Federal Register Volume 72, Number 153 (Thursday, August 9, 2007)]
[Rules and Regulations]
[Pages 44748-44750]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-15414]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28017; Directorate Identifier 2007-NM-005-AD; 
Amendment 39-15146; AD 2007-16-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-203, A310-204, A310-
222, A310-304, A310-322, and A310-324 Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    * * * some structural areas have been identified for which 
existing recommended SB (service bulletin) needs to be rendered 
mandatory.
    As a consequence, and because it has been shown that the torque 
applied to the tension bolts connecting the beam (stringer 49) to 
the forward and aft beam extension at FR11 and FR17 may be 
insufficient, this AD renders mandatory the replacement of those 
tension bolts, in order to limit the risks of damage or corrosion of 
the specified areas.

    Damage or corrosion of the specified areas could result in reduced 
structural integrity of the airplane. We are issuing this AD to require 
actions to correct the unsafe condition on these products.

DATES: This AD becomes effective September 13, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
13, 2007.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200

[[Page 44749]]

New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This AD references the MCAI and related service information that we 
considered in forming the engineering basis to correct the unsafe 
condition. The AD contains text copied from the MCAI and for this 
reason might not follow our plain language principles.

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on April 26, 2007 (72 
FR 20785). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During the A310 life extension exercise performed by Airbus, the 
Airlines Representatives and the Airworthiness Authorities, some 
structural areas have been identified for which existing recommended 
SB (service bulletin) needs to be rendered mandatory.
    As a consequence, and because it has been shown that the torque 
applied to the tension bolts connecting the beam (stringer 49) to 
the forward and aft beam extension at FR11 and FR17 may be 
insufficient, this AD renders mandatory the replacement of those 
tension bolts, in order to limit the risks of damage or corrosion of 
the specified areas.

    Damage or corrosion of the specified areas could result in reduced 
structural integrity of the airplane. You may obtain further 
information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 29 products of U.S. registry. We also estimate that it will take 
about 9 work-hours per product to comply with the basic requirements of 
this AD. The average labor rate is $80 per work-hour. Required parts 
will cost about $886 per product. Where the service information lists 
required parts costs that are covered under warranty, we have assumed 
that there will be no charge for these costs. As we do not control 
warranty coverage for affected parties, some parties may incur costs 
higher than estimated here. Based on these figures, we estimate the 
cost of this AD on U.S. operators to be $46,574, or $1,606 per product.

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 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 this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains the NPRM, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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 FAA amends Sec.  39.13 by adding the following new AD:


[[Page 44750]]


2007-16-07 Airbus: Amendment 39-15146. Docket No. FAA-2007-28017; 
Directorate Identifier 2007-NM-005-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 13, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-203, A310-204, A310-
222, A310-304, A310-322, and A310-324 airplanes, certificated in any 
category, manufacturing serial numbers 283 through 434 inclusive. 
Airplanes which have received application of Airbus Service Bulletin 
A310-53-2045 at original issue up to Revision 05 are not affected by 
this AD.

Subject

    (d) Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During the A310 life extension exercise performed by Airbus, the 
Airlines Representatives and the Airworthiness Authorities, some 
structural areas have been identified for which existing recommended 
SB (service bulletin) needs to be rendered mandatory.
    As a consequence, and because it has been shown that the torque 
applied to the tension bolts connecting the beam (stringer 49) to 
the forward and aft beam extension at FR11 and FR17 may be 
insufficient, this AD renders mandatory the replacement of those 
tension bolts, in order to limit the risks of damage or corrosion of 
the specified areas.
    Damage or corrosion of the specified areas could result in 
reduced structural integrity of the airplane.

Actions and Compliance

    (f) Unless already done, do the following actions at the 
applicable time specified in paragraph (f)(1) or (f)(2) of this AD: 
Rework the structure between frame 11 and frame 17 of the nose 
landing gear well of the fuselage in accordance with the 
instructions of Airbus Service Bulletin A310-53-2045, Revision 05, 
dated July 20, 2006.
    (1) For Model A310-300 airplanes: Prior to accumulation of 
35,000 total flight cycles from first flight of the airplane, or 
within 30 days after the effective date of this AD, whichever occurs 
later.
    (2) For Model A310-200 airplanes: Prior to the accumulation of 
40,000 total flight cycles from the first flight of the airplane, or 
within 30 days after the effective date of this AD, whichever occurs 
later.
    (3) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-53-2045, dated March 
11, 1988; Revision 1, dated June 16, 1988; Revision 2, dated 
September 7, 1988; Revision 3, dated October 4, 1989; or Revision 4, 
dated April 20, 1990; is acceptable for compliance with the 
requirements of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom 
Stafford, Aerospace Engineer, International Branch, ANM-116, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any AMOC approved in accordance with Sec.  39.19 on any 
airplane to which the AMOC applies, notify the appropriate principal 
inspector (PI) in the FAA Flight Standards District Office (FSDO), 
or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2006-0367, dated December 5, 2006; and Airbus Service 
Bulletin A310-53-2045, Revision 05, dated July 20, 2006; for related 
information.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A310-53-2045, Revision 
05, dated July 20, 2006, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 30, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-15414 Filed 8-8-07; 8:45 am]
BILLING CODE 4910-13-P