[Federal Register Volume 71, Number 13 (Friday, January 20, 2006)]
[Rules and Regulations]
[Pages 3214-3215]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-465]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-143-AD; 
Amendment 39-14458; AD 2006-02-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-203, -204, and -222 
Airplanes, and Model A310-300 Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A310-203, -204, and -222 airplanes, and Model 
A310-300 series airplanes. This AD requires a one-time rototest 
inspection for cracking of the frame foot and adjacent frames and skin 
in the area surrounding the frame foot run-outs from fuselage frames 
(FR) 43 through FR 46, and repair if necessary. This AD also requires 
modification of certain fastener holes. This AD results from a 
structural evaluation of Model A310 airplanes for widespread fatigue 
damage of the frame foot run-outs from FR 43 through FR 46. The 
evaluation revealed that, on in-service airplanes, undetected cracking 
in this area can lead to the rupture of the frame foot and subsequent 
cracking of the adjacent frames and fuselage skin. We are issuing this 
AD to prevent fatigue cracking of the frame foot run-outs, which could 
lead to rupture of the frame foot and cracking in adjacent frames and 
skin, and result in reduced structural integrity of the fuselage.

DATES: This AD becomes effective February 24, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 24, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    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:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Airbus Model 
A310-203, -204, and -222 airplanes, and Model A310-300 series 
airplanes. That NPRM was published in the Federal Register on October 
27, 2005 (70 FR 61924). That NPRM proposed to require a one-time 
rototest inspection for cracking of the frame foot and adjacent frames 
and skin in the area surrounding the frame foot run-outs from fuselage 
frames (FR) 43 through FR 46, and repair if necessary. The NPRM also 
proposed to require modification of certain fastener holes.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the single comment received.

Request for Clarification of Service Bulletin Reference

    The commenter states that a reference to Airbus Service Bulletin 
A310-53-2124, dated April 4, 2005, was omitted in paragraph (f) of the 
NPRM. We agree with the commenter. We inadvertently omitted the service 
bulletin number in paragraph (f); that error has been corrected in this 
final rule.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the change described previously. 
This change will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Costs of Compliance

    This AD will affect about 59 airplanes of U.S. registry. The 
actions will take about 31 work hours per airplane, at an average labor 
rate of $65 per work hour. Required parts will cost about $1,730 per 
kit (two kits per airplane). Based on these figures, the estimated cost 
of the AD for U.S. operators is $323,025, or $5,475 per airplane.

[[Page 3215]]

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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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):

2006-02-06 Airbus: Amendment 39-14458. Docket No. FAA-2005-22810; 
Directorate Identifier 2005-NM-143-AD.

Effective Date

    (a) This AD becomes effective February 24, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, and -222 
airplanes, and Model A310-304, -322, -324, and -325 airplanes; 
certificated in any category; except those airplanes on which Airbus 
Modification 13023 has been accomplished in production.

Unsafe Condition

    (d) This AD results from a structural evaluation of Model A310 
airplanes for widespread fatigue damage of the frame foot run-outs 
from frame (FR) 43 through FR 46. We are issuing this AD to prevent 
fatigue cracking of the frame foot run-outs, which could lead to 
rupture of the frame foot and cracking in adjacent frames and skin, 
and result in reduced structural integrity of the fuselage.

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.

Inspection/Repair/Modification

    (f) At the later of the times specified in paragraphs (f)(1) and 
(f)(2) of this AD, perform a one-time rototest inspection for 
cracking of the frame foot and adjacent frames and skin in the area 
surrounding the frame foot run-outs from fuselage frame FR 43 
through FR 46 by doing all the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, 
dated April 4, 2005. Except as required by paragraph (g) of this AD, 
repair any cracking before further flight in accordance with the 
Accomplishment Instructions of the service bulletin. Before further 
flight after performing the inspection, modify the fastener holes 
located between FR 43 and FR 46 on the center box and on the upper 
fuselage bent sections in accordance with the Accomplishment 
Instructions of the service bulletin.
    (1) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in the Accomplishment 
Timescale table in paragraph 1.E.(2), ``Compliance'' of the service 
bulletin.
    (2) At the earlier of the times specified in paragraphs 
(f)(2)(i) and (f)(2)(ii) of this AD.
    (i) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in Notes 01, 02, and 
03 in paragraph 1.E.(2), ``Compliance'' of the service bulletin, 
after the effective date of this AD.
    (ii) Within 3,000 flight cycles after the effective date of this 
AD.

Repair Per FAA or Direction G[eacute]n[eacute]rale de l'Aviation Civile 
(DGAC)

    (g) For any cracking found during any inspection required by 
this AD for which the service bulletin specifies to contact the 
manufacturer for an appropriate repair: Before further flight, 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the DGAC (or its delegated agent).

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (i) French airworthiness directive F-2005-078, dated May 11, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Airbus Service Bulletin A310-53-2124, dated 
April 4, 2005, 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on January 10, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-465 Filed 1-19-06; 8:45 am]
BILLING CODE 4910-13-P