[Federal Register: November 15, 2006 (Volume 71, Number 220)]
[Proposed Rules]
[Page 66472-66474]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15no06-16]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 66472]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26324; Directorate Identifier 2006-NM-214-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Airbus Model 330-300 series
airplanes. The existing AD currently requires reinforcement of the
structure of the center fuselage by installing external stiffeners
(butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand
(LH) and right-hand (RH) stringer (STR) 13, and related investigative
and corrective actions. This proposed AD would require additional
reinforcement of the structure of the center fuselage by installing
external stiffeners (butt straps) at frame FR53.3 on the fuselage skin
between LH and RH STR13, and related investigative and other specified
actions. This proposed AD also adds airplanes to the applicability.
This proposed AD results from cracking found at the circumferential
joint of FR53.3. We are proposing this AD to prevent fatigue cracking
of the fuselage, which could result in reduced structural integrity of
the fuselage.
DATES: We must receive comments on this proposed AD by December 15,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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 proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-26324; Directorate Identifier 2006-NM-214-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
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 proposed 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.
Discussion
On September 20, 2005, we issued AD 2005-20-07, amendment 39-14300
(70 FR 57732, October 4, 2005), for certain Airbus Model A330-300
series airplanes. That AD requires reinforcing the structure of the
center fuselage by installing external stiffeners (butt straps) at
frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-
hand (RH) stringer (STR) 13, and doing related investigative and
corrective actions. That AD resulted from a report that, during fatigue
tests of the fuselage, cracks initiated and grew at the circumferential
joint of FR53.3. We issued that AD to prevent fatigue cracking of the
fuselage, which could result in reduced structural integrity of the
fuselage.
Actions Since Existing AD Was Issued
Since we issued AD 2005-20-07, the European Aviation Safety Agency
(EASA), which is the airworthiness authority for the European Union,
notified us that further modification of Airbus Model A330-300 series
airplanes is necessary to correct the unsafe condition identified in AD
2005-20-07. The EASA has also notified us that the same unsafe
condition may also exist on Model A330-200 series airplanes.
Relevant Service Information
Airbus has issued Service Bulletin A330-53-3143, Revision 01,
including Appendix 01, dated June 29, 2006. The service bulletin
describes procedures for reinforcing the structure of the center
fuselage by installing external doublers (butt straps) at FR53.3 on the
fuselage skin between LH and RH STR13, and doing related investigative
and other specified actions. The related investigative actions are
rototests of certain fastener holes after fastener
[[Page 66473]]
removal. If any crack is found during a rototest, the service bulletin
specifies contacting Airbus for repair instructions. If no crack is
found, the service bulletin specifies doing other specified actions,
which include counter-drilling the fastener holes in the butt straps,
cold-expanding the matching holes in the fuselage, reaming and
deburring the holes, shimming, and applying sealant around the butt
straps. Accomplishing the actions specified in the service information
is intended to adequately address the unsafe condition. The EASA
mandated the service information and issued airworthiness directive
2006-0266, dated August 30, 2006, to ensure the continued airworthiness
of these airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are 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. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2005-20-07 and would retain the
requirements of the existing AD. This proposed AD would also add
airplanes to the applicability. This proposed AD would also require
accomplishing the actions specified in the service bulletin described
previously, except as discussed under ``Difference Between the Proposed
AD and EASA Airworthiness Directive.''
Difference Between the Proposed AD and EASA Airworthiness Directive
The applicability of EASA airworthiness directive 2006-0266
excludes airplanes on which Airbus Service Bulletin A330-53-3127,
Revision 01, dated November 21, 2003; or Airbus Service Bulletin A330-
53-3143, dated December 24, 2004; has been accomplished in service.
However, we have not excluded those airplanes in the applicability of
this proposed AD; rather, this proposed AD includes requirements to
accomplish the actions specified in those service bulletins, as
applicable. These requirements would ensure that the actions specified
in the service bulletins and required by this proposed AD are
accomplished on all affected airplanes. Operators must continue to
operate the airplane in the configuration required by this proposed AD
unless an alternative method of compliance is approved.
Explanation of Change Made to Requirements of Existing AD
Paragraph (g) of the existing AD specifies making repairs using a
method approved by either the FAA or the Direction Generale de
l'Aviation Civile (DGAC) (or its delegated agent). The EASA has assumed
responsibility for the airplane models that would be subject to this
AD. Therefore, we have revised paragraph (g) of this proposed AD to
specify making repairs using a method approved by the FAA, the DGAC (or
its delegated agent), or the EASA (or its delegated agent).
Clarification of Airbus Modification Number
The applicability of AD 2005-20-07 exempts airplanes on which
Airbus Modification 41652 had been incorporated in production. Airbus
Modification 41652 is the abbreviated modification number of Airbus
Modification 41652S11819. This proposed AD refers to Airbus
Modification 41652S11819, as identified in EASA airworthiness directive
2006-0266.
Costs of Compliance
Currently, the action required by AD 2005-20-07 and retained in
this proposed AD affects 12 airplanes of U.S. registry. However, we
have been advised that all affected U.S. operators have already
accomplished that action. If an affected airplane is imported and
placed on the U.S. Register in the future, the action required by AD
2005-20-07 takes about 315 work hours per airplane, at an average labor
rate of $80 per work hour. Required parts cost about $8,920. Based on
these figures, the estimated cost of the currently required action is
$34,120 per airplane.
The new proposed action would affect about 27 airplanes of U.S.
registry. The new proposed action would take about 316 work hours per
airplane, at an average labor rate of $80 per work hour. Required parts
would cost about $9,160 per airplane. Based on these figures, the
estimated cost of the new action specified in this proposed AD for U.S.
operators is $929,880, or $34,440 per airplane.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
[[Page 66474]]
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14300 (70 FR 57732, October 4, 2005) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2006-26324; Directorate Identifier 2006-NM-
214-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
15, 2006.
Affected ADs
(b) This AD supersedes AD 2005-20-07.
Applicability
(c) This AD applies to Airbus Model A330-201, -202, -203, -223,
-243, -301, -321, -322, -323, -341, -342, and -343 airplanes,
certificated in any category; except those on which Airbus
Modification 49202 has been incorporated in production.
Unsafe Condition
(d) This AD results from cracking found at the circumferential
joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue
cracking of the fuselage, which could 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.
Requirements of AD 2005-20-07
Installation for Model A330-300 Series Airplanes
(f) For Airbus Model A330-301, -321, -322, -323, -341, -342, and
-343 airplanes, except those on which Airbus Modification
41652S11819 has been incorporated in production: At the later of the
times in paragraphs (f)(1) and (f)(2) of this AD, install the butt
straps at FR53.3 on the fuselage skin between left-hand (LH) and
right-hand (RH) stringer (STR) 13, and do all related investigative
and corrective actions before further flight. Except as provided by
paragraph (g) of this AD, do all actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3127,
Revision 01, dated November 21, 2003.
(1) Before the accumulation of 14,700 total flight cycles or
51,400 total flight hours, whichever occurs earlier.
(2) Within 6 months after October 19, 2005 (the effective date
of AD 2005-20-07).
Contact the FAA/Direction G[eacute]n[eacute]rale de l'Aviation
Civile (DGAC)/European Aviation Safety Agency (EASA) for Certain
Repair Instructions
(g) For Airbus Model A330-301, -321, -322, -323, -341, -342, and
-343 airplanes, except those on which Airbus Modification
41652S11819 has been incorporated in production: If any crack is
detected during the related investigative actions (rototest)
required by paragraph (f) of this AD, before further flight, repair
the crack according to a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
the DGAC (or its delegated agent); or the EASA (or its delegated
agent).
New Requirements of This AD
Installation for Model A330-200 and -300 Series Airplanes
(h) For all airplanes: At the later of the times in paragraphs
(h)(1) and (h)(2) of this AD, install the butt straps at FR53.3 on
the fuselage skin between LH and RH STR13; and do all related
investigative and other specified actions before further flight, as
applicable. Do all actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-53-3143, Revision 01,
including Appendix 01, dated June 29, 2006; except if any crack is
detected during a related investigative action (rototest), before
further flight, repair the crack using a method approved by the
Manager, International Branch, ANM-116; or the EASA (or its
delegated agent).
(1) Before the accumulation of 17,600 total flight cycles or
61,600 total flight hours, whichever occurs earlier.
(2) Within 6 months after the effective date of this AD.
Credit for Actions Done in Accordance With Previous Service
Bulletin
(i) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A330-53-3143, including
Appendix 01, dated December 24, 2004, are acceptable for compliance
with the corresponding requirements of paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 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 Sec.
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
(k) EASA airworthiness directive 2006-0266, dated August 30,
2006, also addresses the subject of this AD.
Issued in Renton, Washington, on November 7, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19228 Filed 11-14-06; 8:45 am]
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