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[Federal Register Volume 76, Number 196 (Tuesday, October 11, 2011)]
[Proposed Rules]
[Pages 62653-62656]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26106]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1060; Directorate Identifier 2011-NM-015-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: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. 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:

    Within the scope of the Fuel System Safety Program (FSSP), 
analyses of the wire routing showed that the route 2S of the fuel 
electrical circuit in the Right Hand (RH) wing must be modified in 
order to ensure better segregation between fuel quantity indication 
wires and the 115 Volts Alternating Current (VAC) wires of route 2S.
    This condition, if not corrected, could result in short circuits 
leading to arcing, and possible fuel tank explosion.
* * * * *
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 November 25, 
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 W12-140, 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: account.airworth-eas@airbus.com; Internet http://www.airbus.com. You 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-2011-1060; 
Directorate Identifier 2011-NM-015-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

    On January 3, 2008, we issued AD 2008-01-05, Amendment 39-15330 (73 
FR 2795, January 16, 2008). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2008-01-05, Amendment 39-15330 (73 FR 2795, 
January 16, 2008), we have determined

[[Page 62654]]

that the route 2S of the fuel electrical circuit in the right hand wing 
must be modified to ensure better segregation between fuel quantity 
indication wires and the 115 volts alternating current wires of route 
2S. The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2011-0005, dated January 17, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Within the scope of the Fuel System Safety Program (FSSP), 
analyses of the wire routing showed that the route 2S of the fuel 
electrical circuit in the Right Hand (RH) wing must be modified in 
order to ensure better segregation between fuel quantity indication 
wires and the 115 Volts Alternating Current (VAC) wires of route 2S.
    This condition, if not corrected, could result in short circuits 
leading to arcing, and possible fuel tank explosion.
    To address this unsafe condition, [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD 
2002-578(B) [which corresponds to FAA AD 2004-15-16, Amendment 39-
13750 (69 FR 45578, July 30, 2004)] to require improvements of the 
design as specified in Airbus Service Bulletin (SB) A310-28-2148 
original issue or Revision 01. EASA AD 2007-0230 [which corresponds 
to FAA AD 2008-01-05 (73 FR 2795, January 16, 2008)], which 
superseded DGAC France AD 2002-578(B), required those same actions, 
plus additional work as defined in Airbus SB A310-28-2148 Revision 
02.
    Since EASA AD 2007-0230 was issued, an operator reported the 
possibility of chafing with the new routing of the wire bundle 2S in 
the RH wing pylon area to the generator wire bundle of engine 2. The 
modification of this zone was introduced by A310-28-2148 Revision 02 
as additional work. Investigation showed that, to avoid the risk of 
chafing, the affected wiring harnesses must be installed at a higher 
position to provide sufficient clearance with the newly routed wire 
bundle 2S conduit.
    Airbus published Revision 03 of SB A310-28-2148 to describe 
these changes, but a new interference has been found and requires 
updating SB A310-28-2148 to Revision 04 [or 05].
    For the reasons described above, this new [EASA] AD retains the 
requirements of EASA AD 2007-0230, which is superseded, and requires 
the additional work as specified in Revision 04 [or 05] of Airbus SB 
A310-28-2148.

Required actions include modifying the wire routings and installing a 
modified bracket. You may obtain further information by examining the 
MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A310-28-2148, Revision 
05, dated August 3, 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.

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

    We estimate that this proposed AD would affect 61 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD.

                                             Table--Estimated Costs
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                                                                                         Number  of
                                              Work     Average                Cost per     U.S.-
                   Action                     hours   labor rate    Parts     airplane   registered   Fleet cost
                                                       per hour                          airplanes
----------------------------------------------------------------------------------------------------------------
Modification (required by AD 2004-15-16,         35          $85     $4,459     $7,434           68     $505,512
 Amendment 39[dash]13750 (69 FR 45578, July
 30, 2004))................................
Modification (required by AD 2008-01-05,         22           85      1,870      3,740           68      254,320
 Amendment 39[dash]15330 (73 FR 2795,
 January 16, 2008))........................
Modification (new proposed action).........      62           85      2,210      7,480           61      456,280
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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.

[[Page 62655]]

    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 removing Amendment 39-15330 (73 FR 
2795, January 16, 2008) and adding the following new AD:

Airbus: Docket No. FAA-2011-1060; Directorate Identifier 2011-NM-
015-AD.

Comments Due Date

    (a) We must receive comments by November 25, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-01-05, Amendment 39-15330 (73 FR 
2795, January 16, 2008).

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, -221, -222, 
-304, -322, -324, and -325 airplanes; certificated in any category; 
all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Within the scope of the Fuel System Safety Program (FSSP), 
analyses of the wire routing showed that the route 2S of the fuel 
electrical circuit in the Right Hand (RH) wing must be modified in 
order to ensure better segregation between fuel quantity indication 
wires and the 115 Volts Alternating Current (VAC) wires of route 2S.
    This condition, if not corrected, could result in short circuits 
leading to arcing, and possible fuel tank explosion.
* * * * *

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.

Restatement of Requirements of AD 2004-15-16 Amendment 39-13750 (69 FR 
45578, July 30, 2004), With New Service Information

Modification

    (g) For all airplanes except airplanes on which Airbus Service 
Bulletin A310-28-2148, Revision 02, dated March 9, 2007, has been 
done (Airbus Modifications 12427 and 12435): Within 4,000 flight 
hours after September 3, 2004 (the effective date of AD 2004-15-16 
(69 FR 45578, July 30, 2004)), modify the routing of wires in the RH 
wing by installing cable sleeves, per the Accomplishment 
Instructions of Airbus Service Bulletin A310-28-2148, Revision 01, 
dated October 29, 2002; Revision 02, dated March 9, 2007; or 
Revision 05, dated August 3, 2010. As of February 20, 2008 (the 
effective date of AD 2008-01-05, Amendment 39-15330 (73 FR 2795, 
January 16, 2008)), Revision 02 must be used. As of the effective 
date of this AD, Revision 05 must be used.

Actions Accomplished Previously

    (h) Modification of the routing of wires accomplished before 
September 3, 2004, per Airbus Service Bulletin A310-28-2148, dated 
January 23, 2002, is acceptable for compliance with the 
corresponding requirements of paragraph (g) of this AD.

Restatement of Requirements of AD 2008-01-05, Amendment 39-15330 (73 FR 
2795, January 16, 2008), With New Service Information

Modification (Additional Work)

    (i) For airplanes on which the actions specified in Airbus 
Service Bulletin A310-28-2148, dated January 23, 2002; or Airbus 
Service Bulletin A310-28-2148, Revision 01, dated October 29, 2002; 
have been done before February 20, 2008, except for airplanes on 
which Airbus Service Bulletin A310-28-2148, Revision 02, dated March 
9, 2007, has been done (Airbus Modifications 12427 and 12435): 
Within 6,000 flight hours or 30 months after February 20, 2008, 
whichever occurs first, perform further modification by installing 
additional protection sleeves in the outer wing area near the 
cadensicon sensor and segregating wire route 2S in the RH pylon 
area, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007; or 
Revision 05, dated August 3, 2010. As of the effective date of this 
AD, Revision 05 must be used.

New Requirements of This AD

Additional Modification/Installation for Certain Airplanes

    (j) For airplanes on which the actions specified in Airbus 
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007, 
have been accomplished, and do not have production modification 
07633 and on which Airbus Service Bulletin A310-36-2015 has not been 
done: Within 6,000 flight hours or 30 months after the effective 
date of this AD, whichever occurs first, modify the wire routings, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-28-2148, Revision 05, dated August 3, 2010.
    (k) For airplanes on which the actions specified in Airbus 
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007, 
have been accomplished, and have production modification 07633 or on 
which Airbus Service Bulletin A310-36-2015 has been done: Within 
1,000 flight hours after the effective date of this AD, install a 
modified bracket, in accordance with paragraph 3.B.(7) ``Additional 
Work 2'' of the Accomplishment Instructions of Airbus Service 
Bulletin A310-28-2148, Revision 05, dated August 3, 2010.
    (l) For airplanes on which the actions specified in Airbus 
Service Bulletin A310-28-2148, Revision 03, dated June 2, 2009, have 
been accomplished; and have modification 07633 done in production or 
on which the actions specified in Airbus Service Bulletin A310-36-
2015 have been done; no further action is required by this AD.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (m) Modifications done in accordance with Airbus Service 
Bulletin A310-28-2148, Revision 04, dated April 14, 2010, before the 
effective date of this AD are acceptable for compliance with the 
corresponding modification required by paragraph (g), (i), (j), and 
(k) 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

    (n) 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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: 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. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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. AMOCs approved previously in accordance with AD 2008-01-05, 
Amendment 39-15330 (73 FR 2795, January 16, 2008), are approved as 
AMOCs for the corresponding provisions of 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

[[Page 62656]]

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

    (o) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2011-0005, dated January 17, 2011; and 
Airbus Service Bulletin A310-28-2148, Revision 05, dated August 3, 
2010; for related information.

    Issued in Renton, Washington, on September 28, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-26106 Filed 10-7-11; 8:45 am]
BILLING CODE 4910-13-P
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