[Federal Register: October 12, 2005 (Volume 70, Number 196)]
[Rules and Regulations]
[Page 59229-59231]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12oc05-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22626; Directorate Identifier 2002-NM-295-AD;
Amendment 39-14332; AD 2005-20-35]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A320-111 airplanes. The
existing AD currently requires repetitive inspections for cracking in
the front and rear faces and at the crown fittings of the upper
stringers of the center wing box and applicable repairs. This new AD
requires continuing the repetitive inspections at revised thresholds
and intervals, and applicable repairs. This AD results from a
manufacturer survey of airplanes affected by the existing inspection
program that led to the consequent revision of the thresholds and
intervals of the repetitive inspections. We are issuing this AD to
detect and correct fatigue cracking of the upper stringers of the
center wing box, which could lead to loss of structural integrity of
the wing.
DATES: Effective October 27, 2005.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 27,
2005.
We must receive comments on this AD by December 12, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On October 13, 1993, the FAA issued AD 93-16-10, amendment 39-8667
(58 FR 47825, September 13, 1993). That AD applies to certain Airbus
Model A320 airplanes. That AD requires repetitive inspections for
cracking in the front and rear faces and at the crown fittings of the
upper stringers of the center wing box and applicable repairs, if
necessary. We issued that AD to detect fatigue cracking in the upper
stringer, which could lead to loss of structural integrity.
Actions Since Existing AD Was Issued
Since we issued AD 93-16-10, Airbus conducted a survey of the upper
stringers of the center wing boxes of airplanes affected by the
existing inspection program. The results of the survey demonstrated
that it was necessary to decrease the thresholds and intervals of the
repetitive inspections, due to an adjustment of the A320 family
reference fatigue mission.
Relevant Service Information
Airbus has issued Service Bulletin A320-57-1030, Revision 03, dated
August 28, 2002. The service bulletin describes procedures for
performing repetitive inspections--at thresholds and intervals which
have been revised from those specified in Service Bulletin A320-57-
1030, dated August 12, 1991, which is the service information
referenced in AD 93-16-10--for cracking in the front and rear faces and
at the crown fittings of the upper stringers of the center wing box
between frame (FR) 36 and FR42. The Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC), which is the airworthiness authority for
France, mandated the service information and issued French
airworthiness directive 2002-341(B), dated June 26, 2002, to ensure the
continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in France and is 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 supersede AD 93-16-10. This
new AD continues to require repetitive inspections with revised
inspection thresholds and intervals, applicable repairs; as specified
in the service information described previously, except as discussed
under ``Differences Between the AD and Service Information.''
Differences Between the AD and Service Information
Where the service bulletin describes procedures to contact the
manufacturer for repair methods, this AD requires operators to use a
repair method that we or the DGAC (or its delegated agent) approve.
Clarification of Inspection Terminology
In this AD, the ``detailed visual inspection'' specified in the
service bulletin is referred to as a ``detailed inspection.'' We have
included the definition for a detailed inspection in Note 1 of this AD.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
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
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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 2 work hours
per airplane, at an average labor rate of $65 per work hour. Based on
these figures, the estimated cost of the AD would be $130 per airplane,
per inspection cycle.
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
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-
2005-22626; Directorate Identifier 2002-NM-295-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
removing amendment 39-8667 (58 FR 47825, September 13, 1993) and by
adding the following new airworthiness directive (AD):
2005-20-35 Airbus: Amendment 39-14332. Docket No. FAA-2005-22626;
Directorate Identifier 2002-NM-295-AD.
Effective Date
(a) This AD becomes effective October 27, 2005.
Affected ADs
(b) This AD supersedes AD 93-16-10.
Applicability
(c) This AD applies to Airbus Model A320-111 airplanes,
certificated in any category, having manufacturer serial number 002
through 021 inclusive.
Unsafe Condition
(d) This AD results from a manufacturer survey of airplanes
affected by the inspection program required by AD 93-16-10 and the
consequent revision of the thresholds and intervals of the
repetitive inspections. We are issuing this AD to detect and correct
fatigue cracking of the upper stringers of the center wing box,
which could lead to loss of structural integrity of the wing.
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.
Initial Inspection
(f) Prior to the accumulation of 6,500 total flight cycles or
within 50 flight cycles after the effective date of this AD,
whichever occurs later, except as provided by paragraph (g) of this
AD, perform a detailed inspection for cracking in the front and rear
faces and at the crown fittings of the upper stringers of the center
wing box between frame (FR) 36 and FR42, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1030,
Revision 03, dated August 28, 2002.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(1) If no crack is found, repeat the inspection thereafter at
intervals not to
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exceed 5,500 flight cycles, in accordance with the service bulletin.
(2) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) or its
delegated agent.
Previous Initial Inspection
(g) Airplanes that received an initial inspection prior to the
effective date of this AD using any service information specified in
paragraph (h) of this AD must receive the next inspection within
2,000 flight cycles after the effective date of this AD or 7,500
flight cycles since the last inspection, whichever occurs first; in
accordance with paragraph (f) of this AD.
Previous Revisions of Service Bulletins
(h) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A320-57-1030, dated August
12, 1991; Revision 1, dated September 16, 1996; or Revision 02,
dated February 20, 1998; are considered acceptable for compliance
with the corresponding actions specified in paragraph (f) of this
AD, except as provided by paragraph (g) of this AD.
No Reporting Requirement
(i) Although Airbus Service Bulletin A320-57-1030, Revision 03,
dated August 28, 2002, describes procedures for reporting inspection
findings to Airbus, this AD does not require such a report.
Alternative Methods of Compliance (AMOCs)
(j)(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.
(3) AMOCs approved previously according to AD 93-16-10 are not
approved as AMOCs for this AD.
Related Information
(k) French airworthiness directive 2002-341(B), dated June 26,
2002, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus Service Bulletin A320-57-1030, Revision
03, dated August 28, 2002, 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 September 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-20069 Filed 10-11-05; 8:45 am]
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