[Federal Register: September 13, 2007 (Volume 72, Number 177)]
[Proposed Rules]
[Page 52309-52311]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13se07-11]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29170; Directorate Identifier 2007-NM-075-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319 and A320 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Some taperlocks used in the wing-to-fuselage junction at rib 1
were found to be non-compliant with the applicable specification,
resulting in a loss of pre-tension in the fasteners. In such
conditions, the structural integrity of the aircraft could be
affected.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by October 15,
2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: http://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
; or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
29170; Directorate Identifier 2007-NM-075-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on 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 we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2007-0067R1, dated June 7, 2007 (referred to
after this
[[Page 52310]]
as ``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Some taperlocks used in the wing-to-fuselage junction at rib 1
were found to be non-compliant with the applicable specification,
resulting in a loss of pre-tension in the fasteners. In such
conditions, the structural integrity of the aircraft could be
affected.
This Airworthiness Directive mandates a repetitive internal
inspection of the lower stiffeners, and a repetitive external
inspection of the lower panels in center and outer wing box at level
of rib 1 junction.
The corrective action includes contacting Airbus for repair
instructions and repair if any crack is found. You may obtain further
information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins A320-57-1129 and A320-57-1130,
both Revision 01, both dated July 28, 2006. The actions described in
this service information are intended to correct the unsafe condition
identified in the MCAI.
Depending on airplane configuration, the compliance times specified
in Service Bulletin A320-57-1129 range from between 37,500 and 42,000
flight cycles and 96,100 and 107,300 flight hours, whichever occurs
first, from AD effective date; the repetitive intervals range from
between 6,100 and 6,500 flight cycles and 15,700 and 16,800 flight
hours, whichever occurs first; the grace period is 6,100 flight cycles
or 15,600 flight hours, whichever occurs first.
Depending on airplane configuration, the compliance times specified
in Service Bulletin A320-57-1130 range from between 23,600 and 45,000
flight cycles and 60,400 and 101,000 flight hours, whichever occurs
first, from AD effective date; the repetitive intervals range from
between 6,100 and 10,000 flight cycles and 15,600 and 22,500 flight
hours, whichever occurs first; the grace period is 6,100 flight cycles
or 15,600 flight hours, whichever occurs first.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 583 products of U.S. registry. We also estimate that
it would take about between 16 and 77 work-hours per product to comply
with the basic requirements of this proposed AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
the proposed AD on U.S. operators to be between $746,240 and
$3,591,280, or between $1,280 and $6,160 per product.
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 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 this 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.
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 FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2007-29170; Directorate Identifier 2007-NM-
075-AD.
Comments Due Date
(a) We must receive comments by October 15, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319 and A320 series
airplanes, certificated in any category, all certified models, all
serial numbers (MSN); except airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD. Model A320 series airplanes MSN 2164
through MSN 2688 that have partially received Airbus Modification
33421 in production are affected by the requirements of this AD.
(1) Model A319 series airplanes that have received Airbus
Modifications 28238, 28162, and 28342 in production, or Airbus
Modification 33421 in production.
(2) Model A320 series airplanes that have received Airbus
Modification 33421 fully embodied in production.
[[Page 52311]]
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Some taperlocks used in the wing-to-fuselage junction at rib 1
were found to be non-compliant with the applicable specification,
resulting in a loss of pre-tension in the fasteners. In such
conditions, the structural integrity of the aircraft could be
affected.
This Airworthiness Directive mandates a repetitive internal
inspection of the lower stiffeners, and a repetitive external
inspection of the lower panels in center and outer wing box at level
of rib 1 junction.
The corrective action includes contacting Airbus for repair
instructions and repair if any crack is found.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) For A320-200 aircraft: Before the defined threshold or
within the defined grace period after the effective date of this AD,
whichever occurs later, as listed in paragraph 1.E., ``Compliance,''
of Airbus Service Bulletin A320-57-1129, Revision 01, dated July 28,
2006, and following the instructions given in the service bulletin,
perform an internal ultrasonic inspection of the lower stiffeners in
the center and outer wing box at the level of the rib 1 junction to
detect cracks, and if any crack is found, before further flight
contact Airbus for repair instructions and repair. Repeat this
inspection at the intervals defined in paragraph 1.E.,
``Compliance,'' of the service bulletin.
(2) For all aircraft: Before the defined threshold or within the
defined grace period after the effective date of this AD, whichever
occurs later, as listed in paragraph 1.E., ``Compliance,'' of Airbus
Service Bulletin A320-57-1130, Revision 01, dated July 28, 2006, and
following the instructions given in the service bulletin, perform an
external ultrasonic inspection of the lower stiffeners in the center
and outer wing box at the level of the rib 1 junction to detect
cracks, and if any crack is found, before further flight contact
Airbus for repair instructions and repair. Repeat this inspection at
the intervals defined in paragraph 1.E., ``Compliance,'' of the
service bulletin. Aircraft that have already accomplished Airbus
Service Bulletin A320-57-1130, dated September 10, 2004, are
compliant with this paragraph.
(3) Modification of the aircraft in accordance with the
instructions contained in Airbus Service Bulletins A320-57-1131,
A320-57-1137, or A320-57-1140, all dated November 21, 2006;
terminates the repetitive inspection requirements of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows:
Although the MCAI or service information does not specify a
compliance time for corrective action (repair of cracks), paragraphs
(f)(1) and (f)(2) of this AD require that the corrective action be
done before further flight.
Although the MCAI and/or service information specify a
compliance time for accomplishing the inspections after the
effective date on the MCAI, this AD requires compliance within the
specified compliance time after the effective date of this AD.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. Send information to ATTN: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-2141; fax (425) 227-1149. Before using any approved AMOC
on any airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2007-0067R1,
dated June 7, 2007; and Airbus Service Bulletins A320-57-1129 and
A320-57-1130, both Revision 01, both dated July 28, 2006; for
related information.
Issued in Renton, Washington, on September 4, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-18046 Filed 9-12-07; 8:45 am]
BILLING CODE 4910-13-P