[Federal Register: December 1, 2005 (Volume 70, Number 230)]
[Proposed Rules]
[Page 72088-72090]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01de05-17]
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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]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-131, -132, and -133;
A320-232 and -233; and A321-131 and -231 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 adopt a new airworthiness directive (AD)
for certain Airbus Model A319-131, -132, and -133; A320-232 and -233;
and A321-131 and -231 airplanes. This proposed AD would require
inspecting for cracks or failure of the primary load path components of
the engine forward mount, and corrective action if necessary. This
proposed AD also would require removing, re-installing, and re-torquing
the attachment bolts for the secondary load path. This proposed 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 proposing 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: We must receive comments on this proposed AD by January 3, 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.
[[Page 72089]]
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; 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 ``FAA-2005-
23142; Directorate Identifier 2005-NM-154-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
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A319-131, -132, and
-133 airplanes; Model A320-232 and -233 airplanes; and Model A321-131
and -231 airplanes. The DGAC advises that, during modification of
certain forward engine mount assemblies of the left and right engines
done at an engine shop visit, an incorrect torque was applied to the
attachment bolts. Lower torque values used on the bolts reduce the bolt
fatigue life. The bolts are part of a secondary thrust load path that
is only active upon failure of the primary thrust load path. These
conditions, if not corrected, could result in separation of the engine
from the airplane.
Other Relevant Rulemaking
On November 30, 1999, we issued AD 99-25-10, amendment 39-11453 (64
FR 68623, December 8, 1999), for certain Airbus Model A319, A320, and
A321 series airplanes. That AD requires a one-time inspection of the
forward engine mount assembly of the left and right engines to verify
that the part number on each assembly is correct; re-identification of
the forward engine mount assembly; and follow-on actions, if necessary.
That AD was prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. We issued that
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.
When accomplishing the actions required by that AD during an engine
shop visit, an incorrect torque was applied to the attachment bolts.
Relevant Service Information
Airbus has issued All Operators Telex (AOT) A320-71A1036, Revision
1, dated June 28, 2005. The AOT describes procedures for accomplishing
a detailed inspection for cracks or failure of the primary load path
components of the engine forward mount, and performing corrective
action if necessary. The corrective action involves replacing defective
components with new components. The AOT also describes procedures for
removing, re-installing, and re-torquing the attachment bolts for the
secondary load path. The AOT recommends reporting inspection results to
the manufacturer.
The DGAC mandated the service information and issued French
emergency airworthiness directive UF-2005-117, dated June 29, 2005, to
ensure the continued airworthiness of these airplanes in France.
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. 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 airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Difference Among
French Airworthiness Directive, Proposed AD, and AOT.''
Differences Among French Emergency Airworthiness Directive, Proposed
AD, and AOT
Although the DGAC issued an emergency airworthiness directive to
address the unsafe condition of incorrect torque applied to the
attachment bolts, we have determined that issuing an immediately
adopted rule is not necessary. We have received confirmation that the
affected U.S. fleet has accomplished the inspection of the primary load
path in accordance with the AOT specified in the proposed AD.
Therefore, we have determined that issuing a notice of proposed
rulemaking will ensure that the identified unsafe condition is properly
addressed.
Although the AOT referenced in this proposed AD recommends that
inspection results be reported to the manufacturer, this proposed AD
does not include that requirement.
Costs of Compliance
This proposed AD would affect about 131 airplanes of U.S. registry.
The proposed inspection would take 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 proposed
inspection for U.S. operators is $17,030, or $130 per airplane.
The proposed removal, re-installation, and re-torquing would take
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 proposed adjustments for U.S. operators is
$68,120, or $520 per airplane.
[[Page 72090]]
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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2005-23142; Directorate Identifier 2005-NM-
154-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
3, 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 and
-231 airplanes; certificated in any category; as identified in
Airbus All Operators Telex (AOT) A320-71A1036, Revision 1, dated
June 28, 2005.
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 AOT
A320-71A1036, Revision 1, dated June 28, 2005. Do any corrective
action before further flight in accordance with the procedures in
the AOT. Perform the actions at the time specified in paragraph
(f)(1) or (f)(2) of this AD, as applicable.
(1) For Model A321-131 and -231 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.
(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 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 AOT
A320-71A1036, dated June 27, 2005, are acceptable for compliance
with the corresponding actions required by this AD.
No Reporting Required
(i) Although 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.
Issued in Renton, Washington, on November 18, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23513 Filed 11-30-05; 8:45 am]
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