Airworthiness Directives; Airbus Airplanes, 65936-65938 [2011-27005]

Download as PDF 65936 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations restrictions on the interstate movement of breeding swine from Texas. Comments on the interim rule were required to be received on or before July 18, 2011. We received one comment by that date. The comment, from a State animal health agency, supported the interim rule. Therefore, for the reasons given in the interim rule, we are adopting the interim rule as a final rule without change. This action also affirms the information contained in the interim rule concerning Executive Order 12866 and the Regulatory Flexibility Act, Executive Orders 12372 and 12988, and the Paperwork Reduction Act. Further, for this action, the Office of Management and Budget has waived its review under Executive Order 12866. List of Subjects in 9 CFR Part 78 Animal diseases, Bison, Cattle, Hogs, Quarantine, Reporting and recordkeeping requirements, Transportation. PART 78—BRUCELLOSIS Accordingly, we are adopting as a final rule, without change, the interim rule that amended 9 CFR part 78 and that was published at 76 FR 28885– 28886 on May 19, 2011. ■ Done in Washington, DC, this 19th day of October 2011. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2011–27572 Filed 10–24–11; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0255; Directorate Identifier 2010–NM–253–AD; Amendment 39–16844; AD 2011–22–02] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. erowe on DSK2VPTVN1PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes; Model A300 B4–600, B4–600R, and F4– 600R series airplanes; and Model C4– 605R variant F airplanes (collectively called A300–600 series airplanes). This SUMMARY: VerDate Mar<15>2010 15:13 Oct 24, 2011 Jkt 226001 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: An operator reported several cases of wire damages at the pylon/wing interface. Analysis revealed that wires damages are due to installation quality issue resulting from lack of information in installation drawings and job cards. Moreover detailed analysis has highlighted that the Low Pressure Valve (LPV) wires were not segregated by design. * * * * * If left uncorrected, the wire chafing could impact fire protection and detection system. It may also induce dormant failure on LPV preventing its closure leading to a permanent and uncontrolled fire (in case of fire ignited upstream the High Pressure Valve (HPV)). * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 29, 2011. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 22, 2011 (76 FR 15870). That NPRM proposed to correct an unsafe condition for the specified products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued revised parallel mandatory continuing airworthiness information (MCAI) AD 2010–0178R1, dated May 20, 2011. The revised MCAI states: An operator reported several cases of wire damages at the pylon/wing interface. Analysis revealed that wires damages are due to installation quality issue resulting from lack of information in installation drawings and job cards. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Moreover detailed analysis has highlighted that the Low Pressure Valve (LPV) wires were not segregated by design. Due to design similarities, A310, A300–600 and A300–600ST aeroplanes can be affected, depending on the wires installation in the concerned area. If left uncorrected, the wire chafing could impact fire protection and detection system. It may also induce dormant failure on LPV preventing its closure leading to a permanent and uncontrolled fire (in case of fire ignited upstream the High Pressure Valve (HPV)). For the reasons explained above, this AD requires the modification of the electrical installation in the pylon/wing interface to avoid wire damages. Shortly after this [EASA] AD was issued, it was discovered that Airbus Service Bulletin (SB) A310–24–2106, associated to Airbus modification 13541, contained wrong Low Pressure Valve installation drawings. This makes it impossible for the operators to accomplish the SB instructions. Consequently, Airbus have revised the SB to correct the error. Revision 1 of this [EASA] AD is issued to require modification 13541 to be incorporated in accordance with the instructions of Airbus SB A310–24–2106 at Revision 1. The modification includes a general visual inspection of wires for damage, and repair if necessary. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Change Compliance Time UPS stated that it agreed with the actions proposed in the NPRM (76 FR 15870, March 22, 2011); however, it requested that the 30-month compliance time be extended to 36 months. UPS stated that extending the compliance time to 36 months would reduce the potential for special maintenance visits for unmodified airplanes. UPS stated that the additional 6 months would reduce potential operator hardship and allow for a timely correction of the unsafe condition. UPS also stated that, in accordance with EASA Airworthiness Directive 2010–0178, dated August 23, 2010; Airbus Mandatory Service Bulletin A300–24–6106, dated March 31, 2010; and Airbus Mandatory Service Bulletin A310–24–2106, dated May 27, 2010; the original wire damage was a result of installation defects during production, and the issues related to wiring segregation, conduit installation, and improved clamping and lacing were all identified by Airbus during the twoyear investigation process. UPS stated that these design improvements are not related to the correction of the installation defects, and they are not E:\FR\FM\25OCR1.SGM 25OCR1 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations critical airworthiness concerns, thus justifying a longer compliance period. We disagree with extending the compliance time. In developing an appropriate compliance time, we considered the safety implications and normal maintenance schedules for timely accomplishment of the modification. The FAA considered the potential repercussion of wire chafing and the fact that some failures are hidden. In particular, there may be some dormant failures on the LPV preventing its closure in case of fire upstream the HPVs. Accomplishment of the service bulletins will correct the electrical installation if there are any defects, avoiding further damages at the pylon/ wing interface. Affected operators, however, may request an extension of the compliance time under the provisions of paragraph (h)(1) of this AD by submitting data substantiating that the change would provide an acceptable level of safety. Revised Service Information Since the NPRM (76 FR 15870, March 22, 2011) has been issued, EASA has issued Airworthiness Directive 2010– 0178R1, dated May 20, 2011. We have received a report that Airbus Mandatory Service Bulletin A310–24–2106, dated May 27, 2010, associated with Airbus Modification 13541, contained the wrong installation drawings of the LPV. This made it impossible for operators to accomplish the instructions in that service bulletin. Airbus has issued Mandatory Service Bulletin A310–24– 2106, Revision 01, including Appendix 01, dated April 4, 2011, to address the error. We have revised paragraph (g) of this AD accordingly to reflect the new service information. erowe on DSK2VPTVN1PROD with RULES Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not increase the economic burden on any operator or increase the scope of the AD. 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. VerDate Mar<15>2010 15:13 Oct 24, 2011 Jkt 226001 We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Revised Costs of Compliance Since the NPRM (76 FR 15870, March 22, 2011) was issued, Airbus has issued Mandatory Service Bulletin A310–24– 2106, Revision 01, including Appendix 01, dated April 4, 2011, which updated the cost for required parts to $1,340 per product. We have revised the Costs of Compliance section of this AD accordingly to reflect the new parts cost. Costs of Compliance We estimate that this AD will affect 185 products of U.S. registry. We also estimate that it will take about 16 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost up to $1,340 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 parts. 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 this AD to the U.S. operators to be up to $499,500, or $2,700 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 65937 or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 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 AD and placed it in the AD docket. 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 the NPRM (76 FR 15870, March 22, 2011), 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2011–22–02 Airbus: Amendment 39–16844. Docket No. FAA–2011–0255; Directorate Identifier 2010–NM–253–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 29, 2011. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 E:\FR\FM\25OCR1.SGM 25OCR1 65938 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations airplanes; Model A300 B4–605R and B4– 622R airplanes; Model A300 F4–605R and F4–622R airplanes; Model A300 C4–605R Variant F airplanes; and Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 24: Electrical Power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: An operator reported several cases of wire damages at the pylon/wing interface. Analysis revealed that wires damages are due to installation quality issue resulting from lack of information in installation drawings and job cards. Moreover detailed analysis has highlighted that the Low Pressure Valve (LPV) wires were not segregated by design. * * * * * If left uncorrected, the wire chafing could impact fire protection and detection system. It may also induce dormant failure on LPV preventing its closure leading to a permanent and uncontrolled fire (in case of fire ignited upstream the High Pressure Valve (HPV)). * * * * * 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 or 4,000 flight hours after the effective date of this AD, whichever occurs first: Modify the electrical installation in the pylon/wing interface on the left-hand and right-hand side by doing a general visual inspection of wires for damage and doing all applicable repairs, replace the cable tie with lacing tape, improve the electrical installation at the level of the electrical ramp, and improve the segregation of both routes of the LPV channels 1 and 2 between LPV connector and ramp; in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–24–6106, excluding Appendix 01, dated March 31, 2010 (for Airbus Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes); or Airbus Mandatory Service Bulletin A310–24– 2106, Revision 01, including Appendix 01, dated April 4, 2011 (for Airbus Model A310 series airplanes). Do all applicable repairs before further flight. FAA AD Differences erowe on DSK2VPTVN1PROD with RULES Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. VerDate Mar<15>2010 15:13 Oct 24, 2011 Jkt 226001 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: 9ANM-11-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. (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 (i) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010– 0178R1, excluding Appendix 01, dated May 20, 2011; Airbus Mandatory Service Bulletin A300–24–6106, dated March 31, 2010; and Airbus Mandatory Service Bulletin A310–24– 2106, Revision 01, including Appendix 01, dated April 4, 2011; for related information. Material Incorporated by Reference (j) You must use Airbus Mandatory Service Bulletin A300–24–6106, excluding Appendix 01, dated March 31, 2010; or Airbus Mandatory Service Bulletin A310–24–2106, Revision 01, including Appendix 01, dated April 4, 2011; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this 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.airwortheas@airbus.com; Internet http:// www.airbus.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on October 11, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–27005 Filed 10–24–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0650; Directorate Identifier 2010–NM–257–AD; Amendment 39–16846; AD 2011–22–04] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: SUMMARY: [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 [Joint Aviation Authorities] JAA 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. * * * * * The unsafe condition is insufficient electrical bonding of the over-wing refueling cap adapter, which could result in a possible fuel ignition source in the fuel tanks. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 29, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 29, 2011. ADDRESSES: You may examine the AD docket on the Internet at http:// E:\FR\FM\25OCR1.SGM 25OCR1

Agencies

[Federal Register Volume 76, Number 206 (Tuesday, October 25, 2011)]
[Rules and Regulations]
[Pages 65936-65938]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27005]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0255; Directorate Identifier 2010-NM-253-AD; 
Amendment 39-16844; AD 2011-22-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A310 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes; and Model C4-605R variant F airplanes 
(collectively called A300-600 series airplanes). This 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:

    An operator reported several cases of wire damages at the pylon/
wing interface. Analysis revealed that wires damages are due to 
installation quality issue resulting from lack of information in 
installation drawings and job cards.
    Moreover detailed analysis has highlighted that the Low Pressure 
Valve (LPV) wires were not segregated by design.
* * * * *
    If left uncorrected, the wire chafing could impact fire 
protection and detection system. It may also induce dormant failure 
on LPV preventing its closure leading to a permanent and 
uncontrolled fire (in case of fire ignited upstream the High 
Pressure Valve (HPV)).
* * * * *

    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective November 29, 2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on March 22, 2011 (76 
FR 15870). That NPRM proposed to correct an unsafe condition for the 
specified products. The European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued revised parallel mandatory continuing airworthiness 
information (MCAI) AD 2010-0178R1, dated May 20, 2011. The revised MCAI 
states:

    An operator reported several cases of wire damages at the pylon/
wing interface. Analysis revealed that wires damages are due to 
installation quality issue resulting from lack of information in 
installation drawings and job cards.
    Moreover detailed analysis has highlighted that the Low Pressure 
Valve (LPV) wires were not segregated by design.
    Due to design similarities, A310, A300-600 and A300-600ST 
aeroplanes can be affected, depending on the wires installation in 
the concerned area.
    If left uncorrected, the wire chafing could impact fire 
protection and detection system. It may also induce dormant failure 
on LPV preventing its closure leading to a permanent and 
uncontrolled fire (in case of fire ignited upstream the High 
Pressure Valve (HPV)).
    For the reasons explained above, this AD requires the 
modification of the electrical installation in the pylon/wing 
interface to avoid wire damages.
    Shortly after this [EASA] AD was issued, it was discovered that 
Airbus Service Bulletin (SB) A310-24-2106, associated to Airbus 
modification 13541, contained wrong Low Pressure Valve installation 
drawings. This makes it impossible for the operators to accomplish 
the SB instructions. Consequently, Airbus have revised the SB to 
correct the error.
    Revision 1 of this [EASA] AD is issued to require modification 
13541 to be incorporated in accordance with the instructions of 
Airbus SB A310-24-2106 at Revision 1.

    The modification includes a general visual inspection of wires for 
damage, and repair if necessary. You may obtain further information by 
examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Change Compliance Time

    UPS stated that it agreed with the actions proposed in the NPRM (76 
FR 15870, March 22, 2011); however, it requested that the 30-month 
compliance time be extended to 36 months. UPS stated that extending the 
compliance time to 36 months would reduce the potential for special 
maintenance visits for unmodified airplanes. UPS stated that the 
additional 6 months would reduce potential operator hardship and allow 
for a timely correction of the unsafe condition. UPS also stated that, 
in accordance with EASA Airworthiness Directive 2010-0178, dated August 
23, 2010; Airbus Mandatory Service Bulletin A300-24-6106, dated March 
31, 2010; and Airbus Mandatory Service Bulletin A310-24-2106, dated May 
27, 2010; the original wire damage was a result of installation defects 
during production, and the issues related to wiring segregation, 
conduit installation, and improved clamping and lacing were all 
identified by Airbus during the two-year investigation process. UPS 
stated that these design improvements are not related to the correction 
of the installation defects, and they are not

[[Page 65937]]

critical airworthiness concerns, thus justifying a longer compliance 
period.
    We disagree with extending the compliance time. In developing an 
appropriate compliance time, we considered the safety implications and 
normal maintenance schedules for timely accomplishment of the 
modification. The FAA considered the potential repercussion of wire 
chafing and the fact that some failures are hidden. In particular, 
there may be some dormant failures on the LPV preventing its closure in 
case of fire upstream the HPVs. Accomplishment of the service bulletins 
will correct the electrical installation if there are any defects, 
avoiding further damages at the pylon/wing interface. Affected 
operators, however, may request an extension of the compliance time 
under the provisions of paragraph (h)(1) of this AD by submitting data 
substantiating that the change would provide an acceptable level of 
safety.

Revised Service Information

    Since the NPRM (76 FR 15870, March 22, 2011) has been issued, EASA 
has issued Airworthiness Directive 2010-0178R1, dated May 20, 2011. We 
have received a report that Airbus Mandatory Service Bulletin A310-24-
2106, dated May 27, 2010, associated with Airbus Modification 13541, 
contained the wrong installation drawings of the LPV. This made it 
impossible for operators to accomplish the instructions in that service 
bulletin. Airbus has issued Mandatory Service Bulletin A310-24-2106, 
Revision 01, including Appendix 01, dated April 4, 2011, to address the 
error. We have revised paragraph (g) of this AD accordingly to reflect 
the new service information.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the change described previously. We determined that this change 
will not increase the economic burden on any operator or increase the 
scope of the AD.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Revised Costs of Compliance

    Since the NPRM (76 FR 15870, March 22, 2011) was issued, Airbus has 
issued Mandatory Service Bulletin A310-24-2106, Revision 01, including 
Appendix 01, dated April 4, 2011, which updated the cost for required 
parts to $1,340 per product. We have revised the Costs of Compliance 
section of this AD accordingly to reflect the new parts cost.

Costs of Compliance

    We estimate that this AD will affect 185 products of U.S. registry. 
We also estimate that it will take about 16 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost up to $1,340 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 parts. 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 this AD to the 
U.S. operators to be up to $499,500, or $2,700 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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 AD and placed it in the AD docket.

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 the NPRM (76 FR 15870, March 22, 
2011), 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-22-02 Airbus: Amendment 39-16844. Docket No. FAA-2011-0255; 
Directorate Identifier 2010-NM-253-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
29, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 B4-601, B4-603, B4-
620, and B4-622

[[Page 65938]]

airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R and F4-622R airplanes; Model A300 C4-605R Variant F airplanes; 
and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes; certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 24: 
Electrical Power.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    An operator reported several cases of wire damages at the pylon/
wing interface. Analysis revealed that wires damages are due to 
installation quality issue resulting from lack of information in 
installation drawings and job cards.
    Moreover detailed analysis has highlighted that the Low Pressure 
Valve (LPV) wires were not segregated by design.
* * * * *
    If left uncorrected, the wire chafing could impact fire 
protection and detection system. It may also induce dormant failure 
on LPV preventing its closure leading to a permanent and 
uncontrolled fire (in case of fire ignited upstream the High 
Pressure Valve (HPV)).
* * * * *

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 or 4,000 flight hours after the effective 
date of this AD, whichever occurs first: Modify the electrical 
installation in the pylon/wing interface on the left-hand and right-
hand side by doing a general visual inspection of wires for damage 
and doing all applicable repairs, replace the cable tie with lacing 
tape, improve the electrical installation at the level of the 
electrical ramp, and improve the segregation of both routes of the 
LPV channels 1 and 2 between LPV connector and ramp; in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A300-24-6106, excluding Appendix 01, dated March 31, 2010 
(for Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes); or Airbus 
Mandatory Service Bulletin A310-24-2106, Revision 01, including 
Appendix 01, dated April 4, 2011 (for Airbus Model A310 series 
airplanes). Do all applicable repairs before further flight.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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-11-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.
    (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

    (i) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0178R1, excluding Appendix 01, dated May 20, 2011; 
Airbus Mandatory Service Bulletin A300-24-6106, dated March 31, 
2010; and Airbus Mandatory Service Bulletin A310-24-2106, Revision 
01, including Appendix 01, dated April 4, 2011; for related 
information.

Material Incorporated by Reference

    (j) You must use Airbus Mandatory Service Bulletin A300-24-6106, 
excluding Appendix 01, dated March 31, 2010; or Airbus Mandatory 
Service Bulletin A310-24-2106, Revision 01, including Appendix 01, 
dated April 4, 2011; as applicable; to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this 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.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 11, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-27005 Filed 10-24-11; 8:45 am]
BILLING CODE 4910-13-P