[Federal Register: August 16, 2007 (Volume 72, Number 158)]
[Proposed Rules]
[Page 45978-45980]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16au07-29]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28944; Directorate Identifier 2006-NM-239-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes and
Airbus Model A300-600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (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) issued 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:
[T]he detection of cracks on multiple aircraft in lower skin
panel No. 2 forward of access panel 575FB/675FB held on the rear
dummy spar, inboard of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to several repairs and
modifications in previous years.
The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and
A300-57-6029 at Revision 4 define the various configurations for the
mandatory inspections to be conducted in order to control or correct
the development of cracks which could affect the structural
integrity of the aircraft.
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 September 17,
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: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
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-
28944; Directorate Identifier 2006-NM-239-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 because of those comments.
[[Page 45979]]
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 2006-0282, dated September 12, 2006 (referred
to after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
This Airworthiness Directive (AD) is published subsequent to the
detection of cracks on multiple aircraft in lower skin panel No. 2
forward of access panel 575FB/675FB held on the rear dummy spar,
inboard of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to several repairs and
modifications in previous years.
The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and
A300-57-6029 at Revision 4 define the various configurations for the
mandatory inspections to be conducted in order to control or correct
the development of cracks which could affect the structural
integrity of the aircraft.
The MCAI requires various repetitive inspections (detailed visual,
high frequency eddy current, x-ray) of the wing lower skin panel and
associated internal support structure for cracking and, if necessary,
corrective measures (modifying the lower panel inboard of rib 9 aft of
the rear spar and repairing cracks). You may obtain further information
by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins A300-57-0177, Revision 05,
dated March 23, 2007; and A300-57-6029, Revision 06, dated March 23,
2007. The compliance times for the initial inspections range
approximately from 200 flight cycles or 320 flight hours, whichever
occurs first, to 46,700 flight cycles or 63,900 flight hours, whichever
occurs first, depending on the model and configuration. The compliance
times for the repetitive inspections range from 50 flight cycles or 50
flight hours, whichever occurs first, to 3,600 flight cycles or 8,170
flight hours, whichever occurs first, depending on the model and
configuration. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
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, they
have notified us 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 162 products of U.S. registry. We also estimate that
it would take about 2 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 $25,920, or $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-2007-28944; Directorate Identifier 2006-NM-
239-AD.
Comments Due Date
(a) We must receive comments by September 17, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 series airplanes and
Model A300-600 series airplanes; certificated in any category; all
certified models, all serial numbers.
Subject
(d) Wings.
[[Page 45980]]
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
This Airworthiness Directive (AD) is published subsequent to the
detection of cracks on multiple aircraft in lower skin panel No. 2
forward of access panel 575FB/675FB held on the rear dummy spar,
inboard of rib 9, fuselage side, aft of the rear spar.
This area of structure has been subjected to several repairs and
modifications in previous years.
The AIRBUS Service Bulletins (SB) A300-57-0177 at Revision 3 and
A300-57-6029 at Revision 4 define the various configurations for the
mandatory inspections to be conducted in order to control or correct
the development of cracks which could affect the structural
integrity of the aircraft.
The MCAI requires doing repetitive inspections (detailed visual,
high frequency eddy current, x-ray) of the wing lower skin panel and
associated internal support structure for cracking and, if
necessary, doing corrective measures (modifying the lower panel
inboard of rib 9 aft of the rear spar and repairing cracks).
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii),
(f)(1)(iii), and (f)(1)(iv) of this AD: At the threshold specified
in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-0177,
Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06,
dated March 23, 2007; as applicable; perform the inspection of the
wing lower skin panel and associated internal support structure aft
of the rear spar and inboard of rib 9 and apply applicable
corrective measures in accordance with Airbus Service Bulletin A300-
57-0177, Revision 05, dated March 23, 2007; or A300-57-6029,
Revision 06, dated March 23, 2007; as applicable. All applicable
corrective measures must be done at the applicable times specified
in paragraph 1.E.(2) and the Accomplishment Instructions of the
applicable service bulletin.
(i) Where the tables in paragraph 1.(E).(2), ``Accomplishment
Timescale,'' of the service bulletins specify a grace period for
doing the actions, this AD requires that the action be done within
the specified grace period relative to the effective date of this
AD.
(ii) Where the tables in paragraph 1.E.(2)(e), ``config 04,'' of
Airbus Service Bulletin A300-57-0177, Revision 05, specify an
inspection interval but not an initial threshold, this AD requires
that the actions be done within the specified interval after
inspecting in accordance with Table 1A or 1B, as applicable, for
configuration 01 of the service bulletin and thereafter at the
inspection interval specified in the tables in paragraph 1.E.(2)(e),
``config 04,'' of Airbus Service Bulletin A300-57-0177, Revision 05.
(iii) Where the tables in paragraph 1.E.(2)(f), ``config 05,''
of A300-57-6029, Revision 06, specify an inspection interval but not
an initial threshold, this AD requires that the actions be done
within the specified interval after inspecting in accordance with
Table 1A or 1B, as applicable, for configuration 01 of the service
bulletin and thereafter at the inspection interval specified in the
tables in paragraph 1.E.(2)(f), ``config 05,'' of A300-57-6029,
Revision 06.
(iv) All crack lengths specified in Airbus Service Bulletin
A300-57-0177, Revision 05, and A300-57-6029, Revision 06, are
considered ``not to exceed'' lengths.
(2) Repeat the inspection at the intervals in, and according to
the instructions defined in, Airbus Service Bulletin A300-57-0177,
Revision 05, dated March 23, 2007; or A300-57-6029, Revision 06,
dated March 23, 2007; as applicable.
(3) Report to Airbus the first inspection results, whatever they
may be, at the applicable time specified in paragraph (e)(3)(i) or
(e)(3)(ii) of this AD.
(i) If the inspection was done after the effective date of this
AD, submit the report within 30 days after the inspection.
(ii) If the inspection was accomplished prior to the effective
date of this AD, submit the report within 30 days after the
effective date of this AD.
(4) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-57-0177, Revision 03,
dated May 29, 2006; Airbus Service Bulletin A300-57-0177, Revision
04, dated January 5, 2007; Airbus Service Bulletin A300-57-6029,
Revision 04, dated May 29, 2006; or A300-57-6029, Revision 05, dated
October 23, 2006; are considered acceptable for compliance with the
corresponding action specified in this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
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, Transport Airplane Directorate, 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: Tom
Stafford, Aerospace Engineer, International Branch, ANM-116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; 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 European Aviation Safety Agency Airworthiness
Directive 2006-0282, dated September 12, 2006; and the service
information in Table 1 of this AD; for related information.
Table 1.--Service Information
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Revision
Airbus Service Bulletin level Date
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A300-57-0177...................... 05 March 23, 2007.
A300-57-0222...................... 01 March 13, 2006.
A300-57-6029...................... 06 March 23, 2007.
A300-57-6064...................... 04 March 9, 2006.
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Issued in Renton, Washington, on July 31, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-16097 Filed 8-15-07; 8:45 am]
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