[Federal Register: November 9, 2004 (Volume 69, Number 216)]
[Proposed Rules]
[Page 64871-64873]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09no04-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19560; Directorate Identifier 2004-NM-121-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Model A310 series airplanes. This proposed AD would
require modifying the wire routing of electrical harness 636VB in the
right-hand wing. This proposed AD is prompted by the manufacturer's
analysis for compliance with Special Federal Aviation Regulation No.
88, which has shown that wiring 2M of the 115V anti-collision white
strobe lights and wiring 2S of the fuel quantity indication system
(FQIS) should be rerouted into separate conduits. We are proposing this
AD to prevent chafing damage to wiring 2M and 2S, which could result in
a short circuit and consequently introduce an electrical current into
the wiring of the FQIS and create an ignition source in the fuel tank.
DATES: We must receive comments on this proposed AD by December 9,
2004.
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.
By 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.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Technical information: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
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 under ADDRESSES. Include ``Docket No. FAA-2004-19560;
Directorate Identifier 2004-NM-121-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 submitted 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 our
docket 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 can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
[[Page 64872]]
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket
You can 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 DMS receives them.
Discussion
We have examined the underlying safety issues involved in recent
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' (67
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 another 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 proposed 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.
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 all Airbus Model A310 series airplanes.
The DGAC advises that the manufacturer's analysis for compliance with
SFAR 88 has shown that wiring 2M of the 115V anti-collision white
strobe lights and wiring 2S of the fuel quantity indication system
(FQIS) should be rerouted into separate conduits. The existing routing
of wiring 2M and 2S through the same conduit could cause chafing damage
to wiring 2M and 2S. This condition, if not corrected, could result in
a short circuit and consequently introduce an electrical current into
the wiring of the FQIS and create an ignition source in the fuel tank.
Relevant Service Information
Airbus has issued Service Bulletin A310-28-2140, Revision 04, dated
March 31, 2004. The service bulletin describes procedures for modifying
the wire routing of electrical harness 636VB in the right-hand wing.
Modification of the wire routing includes:
Removing certain components at the right-hand wing;
Checking cable harnesses for damage and, if necessary,
replacing any damaged wires;
Installing a bracket;
Rerouting of wiring 2M and 2S through separate conduits;
Installing the conduits of wiring 2M and 2S and the wires
to 2212VC and to the pylon;
Rerouting the wires to 2212VC and to the pylon; installing
the conduit with the wires to 2212VC and to the pylon; and
Testing.
The DGAC mandated the service information and issued French
airworthiness directive F-2004-005, dated January 7, 2004, to ensure
the continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in France and are type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. According 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 AD action is
necessary for products of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require modifying
the wire routing of electrical harness 636VB in the right-hand wing.
The proposed AD would require you to use the service information
described previously to perform these actions, except as discussed
under ``Differences Between the Proposed AD and French Airworthiness
Directive.''
Difference Between the Proposed AD and French Airworthiness Directive
The applicability of French airworthiness directive F-2004-005
excludes airplanes that accomplished Airbus Service Bulletin A310-38-
2140 in service. However, we have not excluded those airplanes in the
applicability of this proposed AD; rather, this proposed AD includes a
requirement to accomplish the actions specified in that service
bulletin. Such a requirement would ensure that the actions specified in
the service bulletin and required by this proposed AD are
[[Page 64873]]
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.
Costs of Compliance
This proposed AD would affect about 51 airplanes of U.S. registry.
The proposed actions would take about 34 work hours per airplane, at an
average labor rate of $65 per work hour. Required parts would cost
about $356 per airplane. Based on these figures, the estimated cost of
the proposed AD for U.S. operators is $130,866 or $2,566 per airplane.
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. 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 FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2004-19560; Directorate Identifier 2004-NM-
121-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by December 9, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A310-203, -204, -221, -
222, -304, -322, -324, and -325 series airplanes, certificated in
any category.
Unsafe Condition
(d) This AD was prompted by the manufacturer's analysis for
compliance with Special Federal Aviation Regulation No. 88, which
has shown that wiring 2M of the 115V anti-collision white strobe
lights and wiring 2S of the fuel quantity indication system (FQIS)
should be rerouted into separate conduits. We are issuing this AD to
prevent chafing damage to wiring 2M and 2S, which could result in a
short circuit and consequently introduce an electrical current into
the wiring of the FQIS and create an ignition source in the fuel
tank.
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.
Modification
(f) Within 72 months after the effective date of this AD, modify
the routing of electrical harness 636VB in the right-hand wing by
accomplishing all of the actions in the Accomplishment Instructions
of Airbus Service Bulletin A310-28-2140, Revision 04, dated March
31, 2004.
Credit for Previously Accomplished Service Bulletins
(g) Modification of the routing of electrical harness 636VB
accomplished before the effective date of this AD in accordance with
Airbus Service Bulletin A310-28-2140, Revision 02, dated May 24,
2002; or Revision 03, dated November 21, 2002; is acceptable for
compliance with the requirements of paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(h) 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.
Related Information
(i) French airworthiness directive F-2004-005, dated January 7,
2004, also addresses the subject of this AD.
Issued in Renton, Washington, on November 1, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-24938 Filed 11-8-04; 8:45 am]
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