[Federal Register: October 27, 2005 (Volume 70, Number 207)]
[Proposed Rules]
[Page 61924-61927]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27oc05-13]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-143-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203, -204, and -222
Airplanes, and Model A310-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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[[Page 61925]]
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A310-203, -204, and -222 airplanes, and Model
A310-300 series airplanes. This proposed AD would require a one-time
rototest inspection for cracking of the frame foot and adjacent frames
and skin in the area surrounding the frame foot run-outs from fuselage
frames (FR) 43 through FR 46, and repair if necessary. The proposed AD
also requires modification of certain fastener holes. This proposed AD
results from a structural evaluation of Model A310 airplanes for
widespread fatigue damage of the frame foot run-outs from FR 43 through
FR 46. The evaluation revealed that, on in-service airplanes,
undetected cracking in this area can lead to the rupture of the frame
foot and subsequent cracking of the adjacent frames and fuselage skin.
We are proposing this AD to prevent fatigue cracking of the frame foot
run-outs, which could lead to rupture of the frame foot and cracking in
adjacent frames and skin, and result in reduced structural integrity of
the fuselage.
DATES: We must receive comments on this proposed AD by November 28,
2005.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; 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-
22810; Directorate Identifier 2005-NM-143-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 A310-203, -204, and
-222 airplanes, and Model A310-300 series airplanes. The DGAC advises
that a structural evaluation for widespread fatigue damage of the frame
foot run-outs from fuselage frame (FR) 43 through FR 46 was done on the
subject airplanes. The evaluation revealed that, on in-service
airplanes, undetected cracking in this area can lead to the rupture of
the frame foot and subsequent cracking of the adjacent frames and
fuselage skin. Such cracking would require an extensive repair and
could have an impact on pressure loading strength capacity of the
structure. These conditions, if not corrected, could result in reduced
structural integrity of the fuselage.
Relevant Service Information
Airbus has issued Service Bulletin A310-53-2124, dated April 4,
2005. The service bulletin describes procedures for performing a one-
time rototest inspection to find cracking of the frame foot and
adjacent frames and skin in the area surrounding the frame foot run-
outs from FR 43 through FR 46, and repair of cracking within certain
limits. If the cracking is outside the limits specified in the service
bulletin, the service bulletin procedures recommend contacting the
manufacturer for repair instructions. The service bulletin also
describes procedures for modification of certain fastener holes. The
modification includes cold expanding the fastener holes most
susceptible to fatigue, which are located between FR 43 and FR 46 on
the center box and on the upper fuselage bent sections, and installing
new fasteners. Accomplishing the actions specified in the service
information is intended to adequately address the unsafe condition. The
DGAC mandated the service information and issued French airworthiness
directive F-2005-078, dated May 11, 2005, to ensure the continued
airworthiness of these airplanes in France.
Section 1.E., Compliance, of the service bulletin specifies
compliance times for the actions in the service bulletin. The
thresholds for the one-time inspection and modification range from
between 22,200 flight cycles or 51,700 flight hours, whichever is
first, to 26,800 flight cycles or 77,700 flight hours, whichever is
first, depending on the configuration of the airplane. The service
bulletin also includes a grace period of 3,000 flight cycles for
airplanes that have exceeded certain flight-hour or flight-cycle
thresholds, depending on the configuration of the airplane.
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
[[Page 61926]]
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 ``Differences Among
Proposed AD, French Airworthiness Directive, and Service Bulletin.''
Differences Among Proposed AD, French Airworthiness Directive, and
Service Bulletin
The applicability of the French Airworthiness Directive excludes
airplanes on which Airbus Service Bulletin A310-53-2124 has been
accomplished in service. However, we have not excluded those airplanes
in the applicability of this proposed AD; rather, this proposed AD
would include a requirement to accomplish the actions specified in that
service bulletin. This proposed AD would ensure that the actions
specified in the service bulletin 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.
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method that we or the
DGAC (or its delegated agent) approve. In light of the type of repair
that would be required to address the unsafe condition, and consistent
with existing bilateral airworthiness agreements, we have determined
that, for this proposed AD, a repair we or the DGAC approve would be
acceptable for compliance with this proposed AD.
Costs of Compliance
This proposed AD would affect about 59 airplanes of U.S. registry.
The proposed actions would take about 31 work hours per airplane, at an
average labor rate of $65 per work hour. Required parts would cost
about $1,730 per kit (two kits per airplane). Based on these figures,
the estimated cost of the proposed AD for U.S. operators is $323,025,
or $5,475 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:
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-2005-22810; Directorate Identifier 2005-NM-
143-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310-203, -204, and -222
airplanes, and Model A310-304, -322, -324, and -325 airplanes;
certificated in any category; except those airplanes on which Airbus
Modification 13023 has been accomplished in production.
Unsafe Condition
(d) This AD results from a structural evaluation of Model A310
airplanes for widespread fatigue damage of the frame foot run-outs
from frame (FR) 43 through FR 46. We are issuing this AD to prevent
fatigue cracking of the frame foot run-outs, which could lead to
rupture of the frame foot and cracking in adjacent frames and skin,
and 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.
Inspection/Repair/Modification
(f) At the later of the times specified in paragraphs (f)(1) and
(f)(2) of this AD, perform a one-time rototest inspection for
cracking of the frame foot and adjacent frames and skin in the area
surrounding the frame foot run-outs from fuselage frame FR 43
through FR46 by doing all the applicable actions specified in the
Accomplishment Instructions of the service bulletin. Except as
required by paragraph (g) of this AD, repair any cracking before
further flight in accordance with the Accomplishment Instructions of
the service bulletin. Before further flight after performing the
inspection, modify the fastener holes located between FR 43 and FR
46 on the center box and on the upper fuselage bent sections in
accordance with the Accomplishment Instructions of the service
bulletin.
(1) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in the Accomplishment
Timescale table in paragraph 1.E.(2), ``Compliance'' of the service
bulletin.
(2) At the earlier of the times specified in paragraphs
(f)(2)(i) and (f)(2)(ii) of this AD.
(i) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in Notes 01, 02, and
03 in paragraph 1.E.(2), ``Compliance'' of the service bulletin,
after the effective date of this AD.
(ii) Within 3,000 flight cycles after the effective date of this
AD.
Repair Per FAA or Direction G[eacute]n[eacute]rale de l'Aviation Civile
(DGAC)
(g) For any cracking found during any inspection required by
this AD for which the
[[Page 61927]]
service bulletin specifies to contact the manufacturer for an
appropriate repair: Before further flight, repair in accordance with
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the DGAC (or its delegated
agent).
Alternative Methods of Compliance (AMOCs)
(h)(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.
Related Information
(i) French airworthiness directive F-2005-078, dated May 11,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on October 20, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-21428 Filed 10-26-05; 8:45 am]
BILLING CODE 4910-13-P