[Federal Register Volume 69, Number 216 (Tuesday, November 9, 2004)]
[Proposed Rules]
[Pages 64871-64873]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-24938]


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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, [email protected].

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]
BILLING CODE 4910-13-U