[Federal Register Volume 70, Number 29 (Monday, February 14, 2005)]
[Rules and Regulations]
[Pages 7386-7389]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-2579]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-256-AD; Amendment 39-13968; AD 2005-03-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 Series Airplanes

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

ACTION: Final rule.

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[[Page 7387]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A330, A340-200, and A340-300 series 
airplanes. This AD requires initial and repetitive inspections of 
certain frame stiffeners to detect cracking. If any cracking is found, 
this AD requires replacement of the stiffener with a new, reinforced 
stiffener. Replacement of the stiffener constitutes terminating action 
for certain inspections. This AD also requires a one-time inspection of 
any new, reinforced stiffener; and repair or replacement of the new, 
reinforced stiffener if any cracking is found during the one-time 
inspection. This AD also provides for an optional terminating action 
for certain requirements of this AD. The actions specified by this AD 
are intended to prevent fatigue failure of certain frame stiffener 
fittings, which could result in reduced structural integrity of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective March 21, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 21, 2005.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; 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.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A330, A340-
200, and A340-300 series airplanes, was published as a supplemental 
notice of proposed rulemaking (NPRM) in the Federal Register on 
November 22, 2004 (69 FR 67869). That supplemental NPRM proposed to 
require initial and repetitive inspections of certain frame stiffeners 
to detect cracking. If any cracking is found, that supplemental NPRM 
proposed to require replacement of the stiffener with a new, reinforced 
stiffener. Replacement of the stiffener would constitute terminating 
action for certain inspections. That supplemental NPRM also proposed to 
require a one-time inspection of any new, reinforced stiffener; and 
repair or replacement of the new, reinforced stiffener if any cracking 
is found during the one-time inspection. That supplemental NPRM also 
provided for an optional terminating action for certain requirements of 
that supplemental NPRM. In addition, that supplemental NPRM also 
proposed to reduce the compliance time for the initial inspections of 
the affected frame stiffeners.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the 
supplemental NPRM or on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
in the supplemental NPRM.

Cost Impact

    We estimate that 20 Model A330 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
airplane to accomplish the required inspection, and that the average 
labor rate is $65 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $5,200, or $260 
per airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted. The cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    If an operator chooses to do the optional terminating action rather 
than continue the repetitive inspections, it will take about 74 work 
hours per airplane to accomplish the installations, at an average labor 
rate of $65 per work hour. Required parts will cost about $7,860 per 
airplane. Based on these figures, we estimate the cost of this optional 
terminating action to be $12,670 per airplane.
    Currently, there are no affected Model A340-200 or A340-300 series 
airplanes on the U.S. Register. However, if an affected airplane is 
imported and placed on the U.S. Register in the future, it will take 
approximately 4 work hours to accomplish the required inspection, at an 
average labor rate of $65 per work hour. Based on these figures, we 
estimate the cost of this AD to be $260 per airplane, per inspection 
cycle.

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 Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is

[[Page 7388]]

contained in the Rules Docket. A copy of it may be obtained from the 
Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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  [Amended]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2005-NM-03-12 Airbus: Amendment 39-13968. Docket 2003-NM-256-AD.

    Applicability: Model A330 series airplanes; and Model A340-200 
and A340-300 series airplanes; certificated in any category; except 
those on which Airbus Modification 49694 has been installed.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue failure of certain frame stiffener fittings, 
which could result in reduced structural integrity of the airplane, 
accomplish the following:

Initial and Repetitive Inspections

    (a) Prior to the accumulation of 13,000 total flight cycles or 
within 6 months after the effective date of this AD, whichever 
occurs later: Conduct a high-frequency eddy current (HFEC) 
inspection for cracking of the FR12A stiffener fitting in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-53-3135, Revision 01, dated July 7, 2003 (for Model A330 series 
airplanes); or Airbus Service Bulletin A340-53-4141, Revision 02, 
dated August 13, 2004 (for Model A340-200 and A340-300 series 
airplanes); as applicable. Repeat the inspection at intervals not to 
exceed 10,000 flight cycles until the replacement required by 
paragraph (b) of this AD is accomplished; or until the optional 
terminating action in paragraph (d) of this AD is accomplished. The 
actions in paragraphs (b) and (d) of this AD constitute terminating 
action for the repetitive inspections only for the side on which the 
actions are taken.

Replacement

    (b) If any cracking is detected during any inspection required 
by paragraph (a) of this AD: Before further flight, replace the 
affected FR12A stiffener with a new reinforced FR12A stiffener in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3135, Revision 01, dated July 7, 2003; or Airbus 
Service Bulletin A340-53-4141, Revision 02, dated August 13, 2004; 
as applicable. Replacement of the stiffener constitutes terminating 
action for the repetitive inspections required by paragraph (a) of 
this AD, only for the side on which the replacement is made.

Follow-On Inspection

    (c) For airplanes on which a new, reinforced stiffener is 
installed in accordance with paragraph (b) of this AD: Within 14,600 
flight cycles following the installation, perform an HFEC inspection 
of the FR12A stiffener fitting for cracking, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3135, 
Revision 01, dated July 7, 2003; or Airbus Service Bulletin A340-53-
4141, Revision 02, dated August 13, 2004; as applicable. If any 
cracking is detected, before further flight, repair or replace the 
new reinforced stiffener with a new stiffener in a manner approved 
by either the Manager, International Branch, ANM-116, FAA; or the 
Direction Generale de l'Aviation Civile (or its delegated agent).

Optional Terminating Action

    (d) Replacement of the FR12A stiffeners with new, reinforced 
stiffeners; installation of new reinforced junction fittings between 
FR12A/FR13 and FR13/FR13A at the stringer 26 level; and installation 
of a new shear web that joins the fitting to the cabin floor track; 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3130, Revision 01, dated October 10, 2003; or 
Airbus Service Bulletin A340-53-4137, Revision 01, dated October 10, 
2003; as applicable; constitutes terminating action for the 
inspection requirements of paragraphs (a) and (c) of this AD, only 
for the side on which the replacement and installations are made.

Actions Accomplished per Previous Issues of Service Bulletins

    (e) Actions accomplished before the effective date of this AD in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletins A330-53-3130, dated May 26, 2003; A330-53-3135, dated May 
26, 2003; A340-53-4137, dated May 26, 2003; A340-53-4141, dated May 
26, 2003; or A340-53-4141, Revision 01, dated July 7, 2003; are 
considered acceptable for compliance only with the following 
requirements of this AD: The HFEC inspections required by paragraph 
(a) of this AD, the replacement required by paragraph (b) of this 
AD, and the actions in paragraph (d) of this AD.

No Reporting Requirements

    (f) Although the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3135, Revision 01, dated July 7, 2003; and Airbus 
Service Bulletin A340-53-4141, Revision 02, dated August 13, 2004; 
describe procedures for submitting certain information to the 
manufacturer, this AD does not require those actions.

Alternative Methods of Compliance

    (g) 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.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions must be 
done in accordance with the service information listed in Table 1 of 
this AD, as applicable. This incorporation by reference was approved 
by the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from Airbus, 1 Rond 
Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be 
inspected 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 the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

              Table 1.--Material Incorporated by Reference
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                                   Revision
     Airbus Service Bulletin         level               Date
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A330-53-3130....................          01  October 10, 2003.
A330-53-3135....................          01  July 7, 2003.
A340-53-4137....................          01  October 10, 2003.
A340-53-4141....................          02  August 13, 2004.
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[[Page 7389]]

    Note 1: The subject of this AD is addressed in French 
airworthiness directives 2003-205(B), dated May 28, 2003; and 2003-
206(B), dated May 28, 2003.

Effective Date

    (i) This amendment becomes effective on March 21, 2005.

    Issued in Renton, Washington, on January 31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-2579 Filed 2-11-05; 8:45 am]
BILLING CODE 4910-13-P