[Federal Register: March 30, 2006 (Volume 71, Number 61)]
[Rules and Regulations]
[Page 16025-16027]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30mr06-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23142; Directorate Identifier 2005-NM-154-AD;
Amendment 39-14532; AD 2006-07-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-131, -132, and -133;
A320-232 and -233; and A321-131, -231, and -232 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 A319-131, -132, and -133; A320-232 and -233; and
A321-131, -231, and -232 airplanes. This AD requires inspecting for
cracks or failure of the primary load path components of the engine
forward mount, and corrective action if necessary. This AD also
requires removing, re-installing, and re-torquing the attachment bolts
for the secondary load path. This AD results from a report that, during
modification of certain engine forward mount assemblies of the left and
right engines done at an engine shop visit, an incorrect torque was
applied to the attachment bolts. We are issuing this AD to prevent
structural failure of the secondary load path of the forward engine
mount, which, if combined with failure of the primary load path, could
result in separation of the engine from the airplane.
DATES: This AD becomes effective May 4, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 4, 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: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; 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
[[Page 16026]]
part 39 to include an AD that would apply to certain Airbus Model A319-
131, -132, and -133; A320-232 and -233; and A321-131 and -231
airplanes. That NPRM was published in the Federal Register on December
1, 2005 (70 FR 72088). That NPRM proposed to require inspecting for
cracks or failure of the primary load path components of the engine
forward mount, and corrective action if necessary. That NPRM also
proposed to require removing, re-installing, and re-torquing the
attachment bolts for the secondary load path.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received from
one commenter.
Clarification of Applicability
The commenter states that Airbus Model A321-232 airplanes are not
identified in the applicability of the AD. The commenter notes that
there have been nine of these airplanes delivered that are not U.S.-
registered.
We infer that the commenter wants us to include Airbus Model A321-
232 airplanes in the applicability of the AD. We agree with the
commenter. The proposed AD is applicable to Airbus Model A319-131, -
132, and -133; A320-232 and -233; and A321-131 and -231 airplanes.
Model A321-232 airplanes have been approved, but are not yet identified
in the type certificate data sheet (TCDS). Considering this approval,
we have changed the applicability throughout the AD accordingly.
Additionally, no Model A321-232 airplane is currently on the U.S.
Register so no additional work is required for U.S. operators.
Clarification of Applicability in Paragraph (f) of the NPRM
We note that paragraph (f) of the NPRM contains an error in
referencing the airplane models on which the detailed inspection must
be done. Our intent was to specify all of the airplane models
identified in Airbus All Operators Telex A320-71A1036, Revision 1,
dated June 28, 2005, as referenced in the applicability section;
however, we inadvertently excluded Model A320-232 and -233 airplanes in
paragraph (f). We have verified that the inspection has been
accomplished on all affected models. Therefore, no additional work is
required for U.S. operators. Adding these models to paragraph (f) will
ensure that any affected airplane that is imported into the U.S. after
the effective date of this AD is inspected, as required by this AD. We
have added a new paragraph (f)(3) to the AD to include these models.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD with the changes described
previously. These changes will neither increase the economic burden on
any operator nor increase the scope of the AD.
Costs of Compliance
This AD affects about 131 airplanes of U.S. registry.
The inspection takes about 2 work hours per airplane (1 work hour
per engine), at an average labor rate of $65 per work hour. Based on
these figures, the estimated cost of the inspection for U.S. operators
is $17,030, or $130 per airplane.
The removal, re-installation, and re-torquing takes about 8 work
hours per airplane (4 work hours per engine), at an average labor rate
of $65 per work hour. Based on these figures, the estimated cost of the
adjustments for U.S. operators is $68,120, or $520 per airplane.
If any Model A321-232 airplane is imported and placed on the U.S.
Register in the future, it will take about 2 work hours per airplane
for the inspection and 8 work hours per airplane for the removal, re-
installation, and re-torquing, at an average labor rate of $65 per work
hour. Based on these figures, the estimated cost of the AD will be $750
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 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):
2006-07-05 Airbus: Amendment 39-14532. Docket No. FAA-2005-23142;
Directorate Identifier 2005-NM-154-AD.
Effective Date
(a) This AD becomes effective May 4, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319-131, -132, and -133
airplanes; Model A320-232 and -233 airplanes; and Model A321-131, -
231, and -232 airplanes; certificated in any category; as identified
in Airbus All Operators Telex (AOT) A320-71A1036, Revision 1, dated
June 28, 2005.
[[Page 16027]]
Unsafe Condition
(d) This AD results from a report that, during modification of
certain engine forward mount assemblies of the left and right
engines done at an engine shop visit, an incorrect torque was
applied to the attachment bolts. We are issuing this AD to prevent
structural failure of the secondary load path of the forward engine
mount, which, if combined with failure of the primary load path,
could result in separation of the engine from the airplane.
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.
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.''
Inspection and Corrective Action
(f) Perform a detailed inspection for cracks or failure of the
primary load path components of the engine forward mount by doing
all the applicable actions in accordance with the procedures in
Airbus AOT A320-71A1036, Revision 1, dated June 28, 2005. Perform
the actions at the time specified in paragraph (f)(1), (f)(2), or
(f)(3) of this AD, as applicable. Do any corrective action before
further flight in accordance with the procedures in the AOT.
(1) For Model A321-131, -231, and -232 airplanes: Do the
inspection within 5 days after the effective date of this AD.
(2) For Model A319-131, -132, and -133 airplanes: Do the
inspection within 10 days after the effective date of this AD.
(3) For Model A320-232 and -233 airplanes: Do the inspection
within 10 days after the effective date of this AD.
(g) For all airplanes: At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, remove, re-install, and re-
torque each of the attachment bolts of the engine forward mount
assembly in accordance with the procedures in Airbus AOT A320-
71A1036, Revision 1, dated June 28, 2005.
(1) If the inspection specified in paragraph (f) of this AD was
accomplished after the effective date of this AD: Do the actions
within 2,250 flight cycles after accomplishing the inspection.
(2) If the inspection specified in paragraph (f) of this AD was
accomplished before the effective date of this AD: Do the actions
within 2,250 flight cycles after the effective date of this AD.
Actions Accomplished Previously
(h) Inspections, adjustments or repairs done before the
effective date of this AD in accordance with the procedures in
Airbus AOT A320-71A1036, dated June 27, 2005, are acceptable for
compliance with the corresponding actions required by this AD.
No Reporting Required
(i) Although Airbus AOT A320-71A1036, Revision 1, dated June 28,
2005, recommends that inspection results be reported to the
manufacturer, this AD does not include that requirement.
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) French emergency airworthiness directive UF-2005-117, dated
June 29, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus All Operators Telex A320-71A1036,
Revision 1, dated June 28, 2005, to perform the actions that are
required by this AD, unless the AD specifies otherwise. (Only page 1
of the all operators telex contains the document number, revision
number, and date of the document; no other page of the document
contains this information.) 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 March 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2961 Filed 3-29-06; 8:45 am]
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