Airworthiness Directives; Airbus Airplanes, 21651-21655 [2014-08727]

Download as PDF Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on April 8, 2014. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–08726 Filed 4–16–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0236; Directorate Identifier 2013–NM–184–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This proposed AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. This proposed AD would require revising the maintenance or inspection program to include the new life limits. We are proposing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. DATES: We must receive comments on this proposed AD by June 2, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond wreier-aviles on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0236; 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0236; Directorate Identifier 2013–NM–184–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0210, dated September 11, 2013 (referred to after this as the Mandatory Continuing PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 21651 Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Some life limits previously defined in Revision 00 of A300 ALS [airworthiness limitations section] Part 1 have been removed [from] that document at Revision 01 and should normally be included in an ALS Part 4. At this time, there are no plans to issue an ALS Part 4 for A300 aeroplanes. Nevertheless, failure to comply with these life limits could result in an unsafe condition. For the reasons described above, it has been decided to require the application of these life limits through a separate [EASA] AD. Consequently, this [EASA] AD requires application of life limits applicable to Main Landing Gear (MLG) barrel assembly, retraction actuator assembly linkage assembly and flanged duct which were previously contained in Airbus ALS Part 1 Revision 00. EASA AD 2007–0293 [which corresponds with FAA AD 2009–18–15, Amendment 39– 16011 (74 FR 48143, September 22, 2009)], which required compliance with the actions specified in ALS Part 1, will be superseded by a new [EASA] AD, requiring compliance with ALS Part 1 at Revision 1. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0236. 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. This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to the procedures specified in paragraph (i)(1) of this AD. The request should include a description of changes to the required E:\FR\FM\17APP1.SGM 17APP1 21652 Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules List of Subjects in 14 CFR Part 39 Costs of Compliance We estimate that this proposed AD affects 7 airplanes of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $595, or $85 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. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS 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); 3. Will not affect intrastate aviation in Alaska; and 4. 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. VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 (h) No Alternative Actions and Intervals Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. inspections that will ensure the continued operational safety of the airplane. After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (i)(1) of this AD. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2014–0236; Directorate Identifier 2013–NM–184–AD. (a) Comments Due Date We must receive comments by June 2, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4– 103, and B4–203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear; 36, Pneumatic. (e) Reason This AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Revise the Maintenance or Inspection Program Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the life limits specified in Appendix 1 of this AD into the Airbus A300 ALS Part 1. The initial compliance time for the replacement is identified in Appendix 1 of this AD and is prior to the applicable life limits specified in Appendix 1 of this AD or within 90 days after the effective date of this AD, whichever occurs later. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (i) Other FAA AD Provisions 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, WA 98057–3356; telephone (425) 227–2125; fax (425) 227– 1149. Information may be emailed to: 9ANM-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, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the DAH with a State of Design Authority’s design organization approval, as applicable). You are required to ensure the product is airworthy before it is returned to service. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) issued European Aviation Safety Agency Airworthiness Directive 2013–0210, dated September 11, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0236. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. BILLING CODE 4910–13–P E:\FR\FM\17APP1.SGM 17APP1 wreier-aviles on DSK5TPTVN1PROD with PROPOSALS VerDate Mar<15>2010 Jkt 232001 Assembly, Retraction Actuator Assembly Linkage, and Flange Duct PO 00000 Frm 00006 Fmt 4702 Sfmt 4725 E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules 14:53 Apr 16, 2014 Appendix 1 to Docket No. FAA-2014-0236 - New Life Limits for the Main Landing Gear (MLG) Barrel 21653 EP17AP14.008</GPH> wreier-aviles on DSK5TPTVN1PROD with PROPOSALS 21654 VerDate Mar<15>2010 Jkt 232001 Assembly, Retraction Actuator Assembly Linkage, and Flange Duct (continued) PO 00000 Frm 00007 Fmt 4702 Sfmt 9990 E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules 14:53 Apr 16, 2014 EP17AP14.009</GPH> Appendix 1 to Docket No. FAA-2014-0236 - New Life Limits for the Main Landing Gear (MLG) Barrel Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules Docket FAA–2014–0236. Issued in Renton, Washington, on April 8, 2014. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–08727 Filed 4–16–14; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0232; Directorate Identifier 2013–NM–100–AD] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain the Boeing Company Model DC–9–10, DC–9–20, DC–9–30, DC–9–40, and DC– 9–50 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the bulkhead dome tees, which connect the bulkhead web to the fuselage, are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections of the improved ventral aft pressure bulkhead tees and replacement if necessary. We are proposing this AD to detect and correct fatigue cracking of the bulkhead dome tees, which could result in reduced structural integrity and rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by June 2, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing wreier-aviles on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206– 766–5683; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0232; 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 (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5348; fax: 562–627–5210; email: eric.schrieber@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2014–0232; Directorate Identifier 2013– NM–100–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 21655 of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the E:\FR\FM\17APP1.SGM 17APP1

Agencies

[Federal Register Volume 79, Number 74 (Thursday, April 17, 2014)]
[Proposed Rules]
[Pages 21651-21655]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-08727]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0236; Directorate Identifier 2013-NM-184-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes. This proposed AD was prompted by 
our determination of the need to incorporate new life limits for the 
main landing gear (MLG) barrel assembly, retraction actuator assembly 
linkage, and flange duct. This proposed AD would require revising the 
maintenance or inspection program to include the new life limits. We 
are proposing this AD to prevent reduced structural integrity of the 
airplane and possible loss of controllability of the airplane.

DATES: We must receive comments on this proposed AD by June 2, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0236; 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 
Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM 116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125; 
fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0236; 
Directorate Identifier 2013-NM-184-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0210, dated September 11, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Some life limits previously defined in Revision 00 of A300 ALS 
[airworthiness limitations section] Part 1 have been removed [from] 
that document at Revision 01 and should normally be included in an 
ALS Part 4.
    At this time, there are no plans to issue an ALS Part 4 for A300 
aeroplanes.
    Nevertheless, failure to comply with these life limits could 
result in an unsafe condition.
    For the reasons described above, it has been decided to require 
the application of these life limits through a separate [EASA] AD. 
Consequently, this [EASA] AD requires application of life limits 
applicable to Main Landing Gear (MLG) barrel assembly, retraction 
actuator assembly linkage assembly and flanged duct which were 
previously contained in Airbus ALS Part 1 Revision 00.
    EASA AD 2007-0293 [which corresponds with FAA AD 2009-18-15, 
Amendment 39-16011 (74 FR 48143, September 22, 2009)], which 
required compliance with the actions specified in ALS Part 1, will 
be superseded by a new [EASA] AD, requiring compliance with ALS Part 
1 at Revision 1.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0236.

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.
    This AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections). Compliance with 
these actions is required by 14 CFR 91.403(c). For airplanes that have 
been previously modified, altered, or repaired in the areas addressed 
by this proposed AD, the operator may not be able to accomplish the 
actions described in the revisions. In this situation, to comply with 
14 CFR 91.403(c), the operator must request approval for an alternative 
method of compliance according to the procedures specified in paragraph 
(i)(1) of this AD. The request should include a description of changes 
to the required

[[Page 21652]]

inspections that will ensure the continued operational safety of the 
airplane.

Costs of Compliance

    We estimate that this proposed AD affects 7 airplanes of U.S. 
registry.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $595, or $85 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

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

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 airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-0236; Directorate Identifier 2013-NM-
184-AD.

(a) Comments Due Date

    We must receive comments by June 2, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear; 36, Pneumatic.

(e) Reason

    This AD was prompted by our determination of the need to 
incorporate new life limits for the main landing gear (MLG) barrel 
assembly, retraction actuator assembly linkage, and flange duct. We 
are issuing this AD to prevent reduced structural integrity of the 
airplane and possible loss of controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Revise the Maintenance or Inspection Program

    Within 90 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
life limits specified in Appendix 1 of this AD into the Airbus A300 
ALS Part 1. The initial compliance time for the replacement is 
identified in Appendix 1 of this AD and is prior to the applicable 
life limits specified in Appendix 1 of this AD or within 90 days 
after the effective date of this AD, whichever occurs later.

(h) No Alternative Actions and Intervals

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (i)(1) of this AD.

(i) Other FAA AD Provisions

    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, WA 98057-3356; telephone (425) 227-
2125; fax (425) 227-1149. Information may be emailed 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, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the DAH with a State of Design Authority's 
design organization approval, as applicable). You are required to 
ensure the product is airworthy before it is returned to service.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) issued European Aviation Safety Agency Airworthiness 
Directive 2013-0210, dated September 11, 2013, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2014-0236.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.
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Docket FAA-2014-0236.


    Issued in Renton, Washington, on April 8, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-08727 Filed 4-16-14; 8:45 am]
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