Airworthiness Directives; Airbus Model A318-100 and A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and A321-200 Series Airplanes, 1558-1560 [E8-152]

Download as PDF 1558 Federal Register / Vol. 73, No. 6 / Wednesday, January 9, 2008 / Proposed Rules Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2007–0161, dated June 11, 2007, Airbus Service Bulletin A320–53–1195, Revision 02, dated April 5, 2007, and Airbus Service Bulletin A–320–53–1196, Revision 01, dated November 29, 2006, for related information. Issued in Renton, Washington, on December 19, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–164 Filed 1–8–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2007–0391; Directorate Identifier 2007–NM–271–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318–100 and A319–100 Series Airplanes; A320–111 Airplanes; A320– 200 Series Airplanes; and A321–100 and A321–200 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rwilkins on PROD1PC63 with PROPOSALS-1 AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A318–100 and A319–100 series airplanes; A320–111 airplanes; A320–200 series airplanes; and A321– 100 and A321–200 series airplanes. The VerDate Aug<31>2005 17:20 Jan 08, 2008 Jkt 214001 existing AD currently requires a onetime inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the hinge pin can move out of the hinge, and related investigative and corrective actions if necessary. This proposed AD would require installing a hinge pin stopper on the internal door of the 103VU electrical panel. This proposed AD results from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We are proposing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems. DATES: We must receive comments on this proposed AD by February 8, 2008. 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 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 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: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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–2007–0391; Directorate Identifier 2007–NM–271–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 because of 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 On January 26, 2006, we issued AD 2006–03–10, amendment 39–14474 (71 FR 6665, February 9, 2006), for certain Airbus Model A318–100 and A319–100 series airplanes; A320–111 airplanes; A320–200 series airplanes; and A321– 100 and A321–200 series airplanes. That AD requires a one-time inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the hinge pin can move out of the hinge, and related investigative and corrective actions if necessary. That AD resulted from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We issued that AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems. Actions Since Existing AD Was Issued Since we issued AD 2006–03–10, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has informed us that the inspections and applicable corrective actions specified in Airbus All Operators Telex 25A1440, dated February 15, 2005 (referred to in AD 2006–03–10 as the appropriate source of service information for the required actions), are not adequate to address the identified unsafe condition (i.e., contact between the horizontal hinge pin and the adjacent electrical wire harness, E:\FR\FM\09JAP1.SGM 09JAP1 Federal Register / Vol. 73, No. 6 / Wednesday, January 9, 2008 / Proposed Rules which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems). Relevant Service Information Airbus has issued Service Bulletin A320–25–1535, dated April 27, 2007. The service bulletin describes procedures for installing a hinge pin stopper on the internal door of the 103VU electrical panel. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2007– 0214, dated August 7, 2007, to ensure the continued airworthiness of these airplanes in the European Union. rwilkins on PROD1PC63 with PROPOSALS-1 FAA’s Determination and Requirements of the Proposed AD These airplanes are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2006–03–10. This proposed AD would require accomplishing the actions specified in the service bulletin described previously. Costs of Compliance This proposed AD would affect about 658 Airbus Model A318–100 and A319– 100 series airplanes; A320–111 airplanes; A320–200 series airplanes; and A321–100 and A321–200 series airplanes of U.S. registry. The new proposed actions would take about 1 work hour per airplane, at an average labor rate of $80 per work hour. Required parts would cost about $20 per airplane. Based on these figures, the estimated cost of the new actions specified in this proposed AD for U.S. operators is $65,800, or $100 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Aug<31>2005 17:20 Jan 08, 2008 Jkt 214001 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 have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. § 39.13 1559 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14474 (71 FR 6665, February 9, 2006) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2007–0391; Directorate Identifier 2007–NM–271–AD. Comments Due Date (a) The FAA must receive comments on this AD action by February 8, 2008. Affected ADs (b) This AD supersedes AD 2006–03–10. Applicability (c) This AD applies to Airbus Model A318– 111 and –112; A319–111, –112, –113, –114, –115, –131, –132, and –133; A320–111, –211, –212, –214, –231, –232, and –233; and A321– 111, –112, –131, –211, –212, –213, –231, and –232 airplanes; certificated in any category; all manufactured serial numbers; except for those airplanes on which Airbus Modification 36115 has been done in production or Airbus Service Bulletin A320– 25–1535, dated April 27, 2007, has been done in service. Unsafe Condition (d) This AD results from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/ or failure of associated systems. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation List of Subjects in 14 CFR Part 39 (f) Within 18 months after the effective date of this AD, install a hinge pin stopper on the internal door of the 103VU electrical panel in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–25–1535, dated April 27, 2007. Air transportation, Aircraft, Aviation safety, Safety. Alternative Methods of Compliance (AMOCs) The Proposed Amendment (g)(1) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\09JAP1.SGM 09JAP1 1560 Federal Register / Vol. 73, No. 6 / Wednesday, January 9, 2008 / Proposed Rules Related Information (h) European Aviation Safety Agency airworthiness directive 2007–0214, dated August 7, 2007, also addresses the subject of this AD. Issued in Renton, Washington, on December 19, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–152 Filed 1–8–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Fiscal Service 31 CFR Part 210 RIN 1510–AB00 Federal Government Participation in the Automated Clearing House Financial Management Service, Fiscal Service, Treasury. ACTION: Notice of proposed rulemaking with request for comment. rwilkins on PROD1PC63 with PROPOSALS-1 AGENCY: SUMMARY: We are proposing to amend our regulation which governs the use of the Automated Clearing House (ACH) system by Federal agencies. That regulation adopts, with some exceptions, the ACH Rules developed by NACHA—The Electronic Payments Association (NACHA) as the rules governing the use of the ACH Network by Federal agencies. We are issuing this proposed rule to address changes that NACHA has made to the ACH Rules since the publication of NACHA’s 2005 ACH Rules book. We are proposing to adopt, with one exception, all of the changes that NACHA has approved since the issuance of the 2005 ACH Rules book, as reflected in the 2007 ACH Rules book. In addition, the proposed rule would provide two exceptions to the deposit account requirement in the regulation. The regulation requires that an ACH credit entry representing a Federal payment other than a vendor payment be deposited into a deposit account at a financial institution in the name of the recipient. On April 21, 2005, Treasury waived this requirement in order to allow some or all of the amount to be reimbursed to a Federal employee for official travel credit card charges to be disbursed directly to the credit card issuing bank. The proposed rule would codify this waiver. The proposed rule would also provide an exception from the requirements in cases where a Federal payment is to be disbursed through a debit card, stored value card, VerDate Aug<31>2005 17:20 Jan 08, 2008 Jkt 214001 prepaid card or similar payment card program established by the Financial Management Service (Service). DATES: Comments on the proposed rule must be received by March 10, 2008. ADDRESSES: You can download this proposed rule at the following Web site: https://www.fms.treas.gov/ach. You may also inspect and copy this proposed rule at: Treasury Department Library, Freedom of Information Act (FOIA) Collection, Room 1428, Main Treasury Building, 1500 Pennsylvania Avenue, NW., Washington, DC 20220. Before visiting, you must call (202) 622–0990 for an appointment. In accordance with the U.S. government’s eRulemaking Initiative, the Service publishes rulemaking information on www.regulations.gov. Regulations.gov offers the public the ability to comment on, search, and view publicly available rulemaking materials, including comments received on rules. Comments on this rule, identified by docket FISCAL–FMS–2007–2008, should only be submitted using the following methods: • Federal eRulemaking Portal: www.regulations.gov. Follow the instructions on the Web site for submitting comments. • Mail: Bill Brushwood, Financial Management Service, 401 14th Street, SW., Room 400A, Washington, DC 20227. • The fax and e-mail methods of submitting comments on rules to the Service have been retired. Instructions: All submissions received must include the agency name (‘‘Financial Management Service’’) and docket number FISCAL–FMS–2007– 0008 for this rulemaking. In general, comments will be published on Regulations.gov without change, including any business or personal information provided. Comments received, including attachments and other supporting materials, are part of the public record and subject to public disclosure. Do not enclose any information in your comment or supporting materials that you consider confidential or inappropriate for public disclosure. FOR FURTHER INFORMATION CONTACT: Bill Brushwood, Financial Program Specialist, at (202) 874–1251 or bill.brushwood@fms.treas.gov; or Natalie H. Diana, Senior Counsel, at (202) 874–6680 or natalie.diana@fms.treas.gov. SUPPLEMENTARY INFORMATION: I. Background Title 31 CFR part 210 (Part 210) governs the use of the ACH Network by PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Federal agencies. The ACH Network is a nationwide electronic fund transfer (EFT) system that provides for the interbank clearing of electronic credit and debit transactions and for the exchange of payment related information among participating financial institutions. Part 210 incorporates the ACH Rules adopted by NACHA, with certain exceptions. From time to time we amend part 210 in order to address changes that NACHA periodically makes to the ACH Rules or to revise the regulation as otherwise appropriate. We are proposing to amend part 210 to address changes that NACHA has made to the ACH Rules since the publication of the 2005 ACH Rules. We are publishing this proposed rule in order to indicate which amendments to the ACH Rules we are planning to accept and which amendments we are planning to reject. We are requesting comment on the proposed amendments. We are also proposing to amend part 210 to codify a waiver allowing for split disbursements of Federal employee travel payments. Currently, section 210.5 requires that an ACH credit entry representing a Federal payment to a payee (other than a vendor payment) be deposited into a deposit account at a financial institution in the name of the recipient. On August 5, 2005, the Office of Management and Budget (OMB) revised Circular No. A–123 (Management’s Responsibility for Internal Control). This revision became effective in fiscal year 2006 (October 1, 2005). OMB Circular No. A–123, Appendix B (Improving the Management of Government Charge Card Programs), sec. 4.4 requires, as a general matter, that Federal executive branch agencies implement split disbursement when reimbursing employees for official travel charges. This requirement applies when the individual cardholder is responsible for making payment to the charge card vendor, i.e., the travel card issuing bank. Split disbursement ‘‘is the process of dividing a travel voucher reimbursement between the charge card vendor and traveler.’’ OMB Circular No. A–123, Appendix B, sec. 4.4.1. Under split disbursement, the ‘‘balance owed to each is sent directly to the appropriate party.’’ Id. In April 2005, the Department of the Treasury, under the authority of 31 CFR 210.5(b)(3), waived the section 210.5 requirement that an ACH entry be deposited into a deposit account at a financial institution in the name of the recipient for purposes of permitting split disbursement. This was necessary in order to implement OMB’s split disbursement policy since an account E:\FR\FM\09JAP1.SGM 09JAP1

Agencies

[Federal Register Volume 73, Number 6 (Wednesday, January 9, 2008)]
[Proposed Rules]
[Pages 1558-1560]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-152]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0391; Directorate Identifier 2007-NM-271-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-100 and A319-100 
Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and 
A321-100 and A321-200 Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A318-100 and A319-
100 series airplanes; A320-111 airplanes; A320-200 series airplanes; 
and A321-100 and A321-200 series airplanes. The existing AD currently 
requires a one-time inspection of the horizontal hinge pin of the 103VU 
electrical panel in the avionics compartment to determine if the hinge 
pin can move out of the hinge, and related investigative and corrective 
actions if necessary. This proposed AD would require installing a hinge 
pin stopper on the internal door of the 103VU electrical panel. This 
proposed AD results from a report indicating that electrical wire 
damage was found in the 103VU electrical panel due to contact between 
the hinge pin and the adjacent electrical wire harness. We are 
proposing this AD to prevent contact between the horizontal hinge pin 
and the adjacent electrical wire harness, which could result in damage 
to electrical wires, and consequent arcing and/or failure of associated 
systems.

DATES: We must receive comments on this proposed AD by February 8, 
2008.

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 W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
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 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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; 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-2007-0391; 
Directorate Identifier 2007-NM-271-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 because of 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

    On January 26, 2006, we issued AD 2006-03-10, amendment 39-14474 
(71 FR 6665, February 9, 2006), for certain Airbus Model A318-100 and 
A319-100 series airplanes; A320-111 airplanes; A320-200 series 
airplanes; and A321-100 and A321-200 series airplanes. That AD requires 
a one-time inspection of the horizontal hinge pin of the 103VU 
electrical panel in the avionics compartment to determine if the hinge 
pin can move out of the hinge, and related investigative and corrective 
actions if necessary. That AD resulted from a report indicating that 
electrical wire damage was found in the 103VU electrical panel due to 
contact between the hinge pin and the adjacent electrical wire harness. 
We issued that AD to prevent contact between the horizontal hinge pin 
and the adjacent electrical wire harness, which could result in damage 
to electrical wires, and consequent arcing and/or failure of associated 
systems.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-03-10, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has informed us that the inspections and applicable 
corrective actions specified in Airbus All Operators Telex 25A1440, 
dated February 15, 2005 (referred to in AD 2006-03-10 as the 
appropriate source of service information for the required actions), 
are not adequate to address the identified unsafe condition (i.e., 
contact between the horizontal hinge pin and the adjacent electrical 
wire harness,

[[Page 1559]]

which could result in damage to electrical wires, and consequent arcing 
and/or failure of associated systems).

Relevant Service Information

    Airbus has issued Service Bulletin A320-25-1535, dated April 27, 
2007. The service bulletin describes procedures for installing a hinge 
pin stopper on the internal door of the 103VU electrical panel. 
Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2007-0214, 
dated August 7, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2006-03-10. This proposed AD 
would require accomplishing the actions specified in the service 
bulletin described previously.

Costs of Compliance

    This proposed AD would affect about 658 Airbus Model A318-100 and 
A319-100 series airplanes; A320-111 airplanes; A320-200 series 
airplanes; and A321-100 and A321-200 series airplanes of U.S. registry. 
The new proposed actions would take about 1 work hour per airplane, at 
an average labor rate of $80 per work hour. Required parts would cost 
about $20 per airplane. Based on these figures, the estimated cost of 
the new actions specified in this proposed AD for U.S. operators is 
$65,800, or $100 per airplane.

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 have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14474 (71 FR 6665, February 9, 2006) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-0391; Directorate Identifier 2007-NM-
271-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
8, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-03-10.

Applicability

    (c) This AD applies to Airbus Model A318-111 and -112; A319-111, 
-112, -113, -114, -115, -131, -132, and -133; A320-111, -211, -212, 
-214, -231, -232, and -233; and A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category; all 
manufactured serial numbers; except for those airplanes on which 
Airbus Modification 36115 has been done in production or Airbus 
Service Bulletin A320-25-1535, dated April 27, 2007, has been done 
in service.

Unsafe Condition

    (d) This AD results from a report indicating that electrical 
wire damage was found in the 103VU electrical panel due to contact 
between the hinge pin and the adjacent electrical wire harness. We 
are issuing this AD to prevent contact between the horizontal hinge 
pin and the adjacent electrical wire harness, which could result in 
damage to electrical wires, and consequent arcing and/or failure of 
associated systems.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Installation

    (f) Within 18 months after the effective date of this AD, 
install a hinge pin stopper on the internal door of the 103VU 
electrical panel in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-25-1535, dated April 27, 2007.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

[[Page 1560]]

Related Information

    (h) European Aviation Safety Agency airworthiness directive 
2007-0214, dated August 7, 2007, also addresses the subject of this 
AD.

    Issued in Renton, Washington, on December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-152 Filed 1-8-08; 8:45 am]
BILLING CODE 4910-13-P

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