Airworthiness Directives; Airbus Model A310 Series Airplanes, 69598-69600 [E7-23457]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Rules and Regulations]
[Pages 69598-69600]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23457]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29117; Directorate Identifier 2007-NM-114-AD; 
Amendment 39-15291; AD 2007-25-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series 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:

    As a result of a Wide Spread Fatigue Damage (WFD) calculation on 
A310 aircraft it was found that a modification of the upper fuselage 
circumferential joint at FR (frame) 55/58 is necessary to enable the 
aircraft to reach the Extended Service Goal (ESG).

The unsafe condition is failure of the circumferential joint of the 
upper fuselage, which 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 January 14, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 14, 
2008.

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

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 September 7, 2007 
(72 FR 51386). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    As a result of a Wide Spread Fatigue Damage (WFD) calculation on 
A310 aircraft it was found that a modification of the upper fuselage 
circumferential joint at FR (frame) 55/58 is necessary to enable the 
aircraft to reach the Extended Service Goal (ESG).
    As a consequence, this Airworthiness Directive (AD) requires the 
reinforcement of the affected fuselage frame butt joint.

The unsafe condition is failure of the circumferential joint of the 
upper fuselage, which 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

    We estimate that this AD will affect about 67 products of U.S. 
registry. We also estimate that it will take about 330 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 $3,016 
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 parts. 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 to the 
U.S. operators to be $1,970,872, or $29,416 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 https://www.regulations.gov; or in person at the

[[Page 69599]]

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:

2007-25-09 Airbus: Amendment 39-15291. Docket No. FAA-2007-29117; 
Directorate Identifier 2007-NM-114-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
14, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310 series airplanes, 
certificated in any category; all certified models; all serial 
numbers; except airplanes that have received in-service application 
of Airbus Service Bulletin A310-53-2125.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    As a result of a Wide Spread Fatigue Damage (WFD) calculation on 
A310 aircraft it was found that a modification of the upper fuselage 
circumferential joint at FR (frame) 55/58 is necessary to enable the 
aircraft to reach the Extended Service Goal (ESG).
    As a consequence, this Airworthiness Directive (AD) requires the 
reinforcement of the affected fuselage frame butt joint.
    The unsafe condition is failure of the circumferential joint of 
the upper fuselage, which could result in reduced structural 
integrity of the airplane.

Actions and Compliance

    (f) Unless already done, do the following actions: Reinforce the 
fuselage butt joint at FR 55/58 in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2125, 
including Appendix 01, dated January 9, 2007, at the applicable 
compliance times listed in Table 1 (threshold) or Table 2 (grace 
period) of this AD, whichever occurs later.

                     Table 1.--Compliance Thresholds
------------------------------------------------------------------------
                                           Whichever occurs first after
                                           the effective date of this AD
                                         -------------------------------
                                            Accumulated     Accumulated
              Airbus model                  time since      time since
                                           first flight    first flight
                                            (in flight      (in flight
                                              cycles)         hours)
------------------------------------------------------------------------
A310-200 airplanes......................          41,500          83,500
A310-300 airplanes with an average                33,000          93,500
 flight time (AFT) <= to 4 hours........
A310-300 airplanes with an AFT > 4 hours          20,500         102,000
------------------------------------------------------------------------


                         Table 2.--Grace Periods
------------------------------------------------------------------------
                                           Whichever occurs first after
                                           the effective date of this AD
              Airbus model               -------------------------------
                                           Flight cycles   Flight hours
------------------------------------------------------------------------
A310-200 airplanes......................           1,500           3,000
A310-300 airplanes with an AFT <= 4                1,200           3,400
 hours..................................
A310-300 airplanes with an AFT > 4 hours             740           3,600
------------------------------------------------------------------------

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, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your 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 2007-0111, dated April 25, 2007; and Airbus Service 
Bulletin A310-53-2125, including Appendix 01, dated January 9, 2007; 
for related information.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A310-53-2125, including 
Appendix 01, dated January 9, 2007, 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

[[Page 69600]]

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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-23457 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P