Airworthiness Directives; Airbus Model A320-214, -232, and -233 Airplanes, 19714-19716 [2011-8409]

Download as PDF 19714 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules Compliance Time for AWL No. 28–AWL–03 (m) The initial compliance time for AWL No. 28–AWL–03 of Boeing TR 09–010, dated July 2010, to Section 9 of Boeing 757 MPD Document, D622N001–9, is within 120 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 24 months after the effective date of this AD, whichever occurs later. Accomplishing the actions required by this paragraph terminates the requirements of paragraph (h)(2) of this AD. Initial Inspection Compliance Times for AWL No. 28–AWL–25 and 28–AWL–26 (n) The initial inspection compliance time for AWL No. 28–AWL–25 of Boeing TR 09– 010, dated July 2010, to Section 9 of Boeing 757 MPD Document, D622N001–9, is within 72 months after accomplishing Boeing Service Bulletin 757–28A0088. (o) The initial inspection compliance time for AWL No. 28–AWL–26 of Boeing TR 09– 010, dated July 2010, to Section 9 of Boeing 757 MPD Document, D622N001–9, is within 12 months after accomplishing Boeing Service Bulletin 757–28A0105. No Alternative Inspections, Inspection Intervals, or CDCCLs (p) After accomplishing the actions specified in paragraph (l) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used unless the inspections, intervals, or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (u) of this AD. Terminating Action for AD 2008–11–07, Amendment 39–15529 (q) Incorporating AWLs No. 28–AWL–20 and No. 28–AWL–26 into the maintenance program in accordance with paragraph (l)(3) of this AD terminates the actions required by paragraphs (j) and (m) of AD 2008–11–07. mstockstill on DSKH9S0YB1PROD with PROPOSALS Terminating Action for AD 2009–06–20, Amendment 39–15857 (r) Incorporating AWL No. 28–AWL–22 into the maintenance program in accordance with paragraph (l)(3) of this AD terminates the actions required by paragraph (h) of AD 2009–06–20. Credit for Actions Accomplished in Accordance With Previous Service Information (s) Actions done before the effective date of this AD in accordance with Section 9 of the Boeing 757 MPD Document, D622N001– 9, Revision December 2008, is acceptable for compliance with the corresponding requirements of this AD. (t) Actions done before the effective date of this AD in accordance with Subsection G of Boeing TR 09–008, dated March 2008, to Section 9 of the Boeing 757 MPD Document, D622N001–9, is acceptable for compliance with the requirements of paragraphs (n) and (o) of this AD. components that have been identified as airworthy or installed on the affected airplanes before the revision of the maintenance program, as required by paragraphs (g) and (l) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the maintenance program has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs. Alternative Methods of Compliance (AMOCs) (u)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) 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. (3) AMOCs approved previously for AD 2008–10–11 are approved as AMOCs for the corresponding provisions of this AD. Related Information (v) For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425–917– 6499; fax: 425–917–6590; e-mail: takahisa.kobayashi@faa.gov. (w) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1, fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.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. Issued in Renton, Washington, on March 25, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–8407 Filed 4–7–11; 8:45 am] BILLING CODE 4910–13–P Explanation of CDCCL Requirements Note 4: Notwithstanding any other maintenance or operational requirements, VerDate Mar<15>2010 16:32 Apr 07, 2011 Jkt 223001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0305; Directorate Identifier 2010–NM–186–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A320–214, –232, and –233 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: * * * * * Results from a design review done by AIRBUS for documentation update have revealed that, on post-mod 38310 A320 aeroplanes only, in case of emergency electrical configuration combined with a Green and Yellow hydraulic system loss, during landing phase (nose landing gear extended), the roll control would only be provided by the left aileron. This condition, if not corrected, could lead to an asymmetrical landing configuration, resulting in reduced control of the aeroplane. * * * * * 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 May 23, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac E:\FR\FM\08APP1.SGM 08APP1 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet https://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 https:// 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1405; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: mstockstill on DSKH9S0YB1PROD with PROPOSALS 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–2011–0305; Directorate Identifier 2010–NM–186–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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0149, dated July 21, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: VerDate Mar<15>2010 16:32 Apr 07, 2011 Jkt 223001 In 2007, Airbus modification 38310 was introduced in production to simplify the ELAC2 [elevator aileron computer] and Trimmable Horizontal Stabiliser (THS) Motor 1 stand by power supply logic. Results from a design review done by AIRBUS for documentation update have revealed that, on post-mod 38310 A320 aeroplanes only, in case of emergency electrical configuration combined with a Green and Yellow hydraulic system loss, during landing phase (nose landing gear extended), the roll control would only be provided by the left aileron. This condition, if not corrected, could lead to an asymmetrical landing configuration, resulting in reduced control of the aeroplane. For the reasons described above, this [EASA] AD requires a modification of the electrical installation of ELAC2 and THS Motor 1 power supply, restoring the aeroplane to the pre-mod 38310 configuration. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletin A320–27–1199, Revision 02, including Appendix 01, dated September 20, 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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 19715 Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 666 products of U.S. registry. We also estimate that it would take about 35 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $3,370 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $4,225,770, or $6,345 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities E:\FR\FM\08APP1.SGM 08APP1 19716 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. Airbus: Docket No. FAA–2011–0305; Directorate Identifier 2010–NM–186–AD. Comments Due Date (a) We must receive comments by May 23, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A320– 214, -232, and -233 airplanes, all manufacturer serial numbers on which Airbus modification 38310 has been accomplished in production; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 27: Flight Controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: mstockstill on DSKH9S0YB1PROD with PROPOSALS * * * * Results from a design review done by AIRBUS for documentation update have revealed that, on post-mod 38310 A320 aeroplanes only, in case of emergency electrical configuration combined with a Green and Yellow hydraulic system loss, during landing phase (nose landing gear extended), the roll control would only be provided by the left aileron. This condition, if not corrected, could lead to an asymmetrical landing configuration, resulting in reduced control of the aeroplane. * * * * * 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. VerDate Mar<15>2010 Credit for Actions Accomplished in Accordance With Previous Service Information (h) Modifications done before the effective date of this AD in accordance with Airbus Service Bulletin A320–27–1199, Revision 01, dated March 4, 2010, are acceptable for compliance with the requirements of paragraph (g) of this AD. Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions [Amended] 2. The FAA amends § 39.13 by adding the following new AD: * (g) Within 24 months after the effective date of this AD, modify the electrical installation of the elevator aileron computer and trimmable horizontal stabilizer motor 1 power supply, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–27–1199, Revision 02, dated September 20, 2010. FAA AD Differences 1. The authority citation for part 39 continues to read as follows: § 39.13 Actions 16:32 Apr 07, 2011 Jkt 223001 (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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, sent it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1405; 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (j) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0149, dated July 21, 2010; and Airbus Mandatory Service Bulletin A320–27–1199, Revision 02, dated September 20, 2010; for related information. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on March 25, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–8409 Filed 4–7–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0306; Directorate Identifier 2010–NM–176–AD] RIN 2120–AA64 Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model 4101 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: SUMMARY: * * * BAE Systems (Operations) Ltd has issued Revision 33 of the AMM [airplane maintenance manual] to amend Chapter 05– 10–10 by adding one new Structurally Significant Item (SSI) and increasing the repeat inspection period on another SSI. Failure to comply with this revision constitutes an unsafe condition. The unsafe condition is failure of certain structurally significant items, including the main landing gear and the nose landing gear, which could result in reduced structural integrity of the airplane; and fuel vapor ignition sources, which could result in a fuel tank explosion and consequent loss of the airplane. 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 May 23, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– E:\FR\FM\08APP1.SGM 08APP1

Agencies

[Federal Register Volume 76, Number 68 (Friday, April 8, 2011)]
[Proposed Rules]
[Pages 19714-19716]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-8409]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0305; Directorate Identifier 2010-NM-186-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-214, -232, and -233 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

* * * * *
    Results from a design review done by AIRBUS for documentation 
update have revealed that, on post-mod 38310 A320 aeroplanes only, 
in case of emergency electrical configuration combined with a Green 
and Yellow hydraulic system loss, during landing phase (nose landing 
gear extended), the roll control would only be provided by the left 
aileron.
    This condition, if not corrected, could lead to an asymmetrical 
landing configuration, resulting in reduced control of the 
aeroplane.
* * * * *

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 May 23, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac

[[Page 19715]]

Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-
mail: account.airworth-eas@airbus.com; Internet https://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 https://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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1405; 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-2011-0305; 
Directorate Identifier 2010-NM-186-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 https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2010-0149, dated July 21, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    In 2007, Airbus modification 38310 was introduced in production 
to simplify the ELAC2 [elevator aileron computer] and Trimmable 
Horizontal Stabiliser (THS) Motor 1 stand by power supply logic.
    Results from a design review done by AIRBUS for documentation 
update have revealed that, on post-mod 38310 A320 aeroplanes only, 
in case of emergency electrical configuration combined with a Green 
and Yellow hydraulic system loss, during landing phase (nose landing 
gear extended), the roll control would only be provided by the left 
aileron.
    This condition, if not corrected, could lead to an asymmetrical 
landing configuration, resulting in reduced control of the 
aeroplane.
    For the reasons described above, this [EASA] AD requires a 
modification of the electrical installation of ELAC2 and THS Motor 1 
power supply, restoring the aeroplane to the pre-mod 38310 
configuration.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A320-27-1199, Revision 
02, including Appendix 01, dated September 20, 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

    Based on the service information, we estimate that this proposed AD 
would affect about 666 products of U.S. registry. We also estimate that 
it would take about 35 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $3,370 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
costs. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $4,225,770, or $6,345 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities

[[Page 19716]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2011-0305; Directorate Identifier 2010-NM-
186-AD.

Comments Due Date

    (a) We must receive comments by May 23, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A320-214, -232, and -233 
airplanes, all manufacturer serial numbers on which Airbus 
modification 38310 has been accomplished in production; certificated 
in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
* * * * *
    Results from a design review done by AIRBUS for documentation 
update have revealed that, on post-mod 38310 A320 aeroplanes only, 
in case of emergency electrical configuration combined with a Green 
and Yellow hydraulic system loss, during landing phase (nose landing 
gear extended), the roll control would only be provided by the left 
aileron.
    This condition, if not corrected, could lead to an asymmetrical 
landing configuration, resulting in reduced control of the 
aeroplane.
* * * * *

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 24 months after the effective date of this AD, modify 
the electrical installation of the elevator aileron computer and 
trimmable horizontal stabilizer motor 1 power supply, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A320-27-1199, Revision 02, dated September 20, 2010.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (h) Modifications done before the effective date of this AD in 
accordance with Airbus Service Bulletin A320-27-1199, Revision 01, 
dated March 4, 2010, are acceptable for compliance with the 
requirements of paragraph (g) of this AD.

FAA AD Differences

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

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. 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, sent it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-1405; 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.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

Related Information

    (j) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2010-0149, dated July 21, 2010; and Airbus 
Mandatory Service Bulletin A320-27-1199, Revision 02, dated 
September 20, 2010; for related information.

    Issued in Renton, Washington, on March 25, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-8409 Filed 4-7-11; 8:45 am]
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