[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Proposed Rules]
[Pages 6581-6584]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-2612]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0037; Directorate Identifier 2010-NM-273-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes
(Collectively Called A300-600 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:
[T]he FAA has published SFAR 88 (Special Federal Aviation
Regulation 88).
In their letters referenced 04/00/02/07/01-L296, dated March
4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the
JAA [Joint Aviation Authorities] recommended the application of a
similar regulation to the National Aviation Authorities (NAA).
Under this regulation, all holders of type certificates for
passenger transport aircraft * * * are required to conduct a design
review against explosion risks.
During improvement of the protection of fuel pump wiring against
short-circuit by accomplishment of Airbus Service Bulletin (SB)
A300-24-6094, a study led by the manufacturer concluded that the
harness, installed through the wing panel needed to be protected to
prevent possible damage in case of chafing which could potentially
lead to short-circuit [and intermittent function or loss of the
inner tank fuel pump. Loss of both inner tank fuel pumps could
result in inability to use the remaining fuel supply in the inner
tank. A short-circuit could also result in an ignition source in a
flammable leakage zone].
* * * * *
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 March 24, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: [email protected]; Internet http://www.airbus.com. You
[[Page 6582]]
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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-2011-0037;
Directorate Identifier 2010-NM-273-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://www.regulations.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 2010-0225, dated November 5, 2010 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
[T]he FAA has published SFAR 88 (Special Federal Aviation
Regulation 88).
In their letters referenced 04/00/02/07/01-L296, dated March
4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the
JAA [Joint Aviation Authorities] recommended the application of a
similar regulation to the National Aviation Authorities (NAA).
Under this regulation, all holders of type certificates for
passenger transport aircraft with either a passenger capacity of 30
or more, or a payload capacity of 3,402 kg (7,500 lb) or more, which
have received their certification since January 1st, 1958, are
required to conduct a design review against explosion risks.
During improvement of the protection of fuel pump wiring against
short-circuit by accomplishment of Airbus Service Bulletin (SB)
A300-24-6094, a study led by the manufacturer concluded that the
harness, installed through the wing panel needed to be protected to
prevent possible damage in case of chafing which could potentially
lead to short-circuit [and intermittent function or loss of the
inner tank fuel pump. Loss of both inner tank fuel pumps could
result in inability to use the remaining fuel supply in the inner
tank. A short-circuit could also result in an ignition source in a
flammable leakage zone].
For the reasons stated above, this [EASA] AD requires the
replacement of bushes in the hydraulic reservoir panel.
You may obtain further information by examining the MCAI in the AD
docket.
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
The Joint Aviation Authorities (JAA) has issued a regulation that
is similar to SFAR 88. (The JAA is an associated body of the European
Civil Aviation Conference (ECAC) representing the civil aviation
regulatory authorities of a number of European States who have agreed
to co-operate in developing and implementing common safety regulatory
standards and procedures.) Under this regulation, the JAA stated that
all members of the ECAC that hold type certificates for transport
category airplanes are required to conduct a design review against
explosion risks.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A300-24-6102, Revision
01, dated September 24, 2010. 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, 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.
[[Page 6583]]
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 120 products of U.S. registry. We also estimate that
it would take about 13 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Required parts would cost about $266 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $164,520, or $1,371 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, Incorporation by
reference, 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-2011-0037; Directorate Identifier 2010-NM-
273-AD.
Comments Due Date
(a) We must receive comments by March 24, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A300 B4-601, B4-603, B4-
620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant
F airplanes, certificated in any category, all certified models, all
serial numbers, except airplanes on which Airbus Service Bulletin
A300-24-6102 (Airbus Modification 13381) has been embodied.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical Power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
[T]he FAA has published SFAR 88 (Special Federal Aviation
Regulation 88).
In their letters referenced 04/00/02/07/01-L296, dated March
4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the
JAA [Joint Aviation Authorities] recommended the application of a
similar regulation to the National Aviation Authorities (NAA).
Under this regulation, all holders of type certificates for
passenger transport aircraft * * * are required to conduct a design
review against explosion risks.
During improvement of the protection of fuel pump wiring against
short-circuit by accomplishment of Airbus Service Bulletin (SB)
A300-24-6094, a study led by the manufacturer concluded that the
harness, installed through the wing panel needed to be protected to
prevent possible damage in case of chafing which could potentially
lead to short-circuit [and intermittent function or loss of the
inner tank fuel pump. Loss of both inner tank fuel pumps could
result in inability to use the remaining fuel supply in the inner
tank. A short-circuit could also result in an ignition source in a
flammable leakage zone].
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) Within 30 months after the effective date of this AD,
install Teflon bushes in the hydraulic reservoir panel at the lower
left-hand side in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-24-6102, Revision 01, dated
September 24, 2010.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(h) Actions done before the effective date of this AD in
accordance with Airbus Mandatory Service Bulletin A300-24-6102,
dated August 13, 2009, are acceptable for compliance with the
corresponding requirements of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(i) 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: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
[[Page 6584]]
Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
Information may be e-mailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD.
(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.
Related Information
(j) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2010-0225, dated November 5, 2010; and Airbus Mandatory
Service Bulletin A300-24-6102, Revision 01, dated September 24,
2010; for related information.
Issued in Renton, Washington, on January 31, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-2612 Filed 2-4-11; 8:45 am]
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