Airworthiness Directives; Airbus Airplanes, 34098-34101 [2015-14229]

Download as PDF asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 34098 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules no market agencies selling livestock through privately negotiated sales. The stockyards in which privately negotiated sales occurred now sell livestock in public auctions. While some employees may have retained a ‘‘salesman’’ job title, these employees no longer perform those functions that made them key employees. GIPSA is requesting comments from livestock industry representatives that address the following: (1) Which of the following should be included as a key employee, and why: (a) Auctioneer (b) Clerk of Sale (c) Ringmen (d) Salesmen (e) Weighmaster/Weigher (f) Manager or Owner (2) If weighers are otherwise considered key employees, should a weigher be allowed to bid on livestock when: (a) The market scale is equipped with a digital indicator (b) Livestock are not sold by weight (3) If livestock scale operators remain on the list of key employees would you object to GIPSA referring to the livestock scale operator as the ‘‘weigher’’ rather than the ‘‘weighmaster’’ in 201.56(c)? GIPSA is also interested to hear comments on whether key employees may purchase livestock during a sale under specific circumstances, or for specific purposes, such as: (4) If a key employee would step down from the auctioneer’s booth or scale during a sale: (a) Could the key employee then bid on livestock for their own account from the bleachers with the other buyers as long as the employee provided no key services while doing so: (i) Should this be limited to a specific species; (ii) Should their time spent bidding or serving in a key capacity be documented, and if so, how; (iii) Should a key employee be allowed to return to the auctioneer’s booth or scale, to perform key employee duties, after bidding on livestock from the bleachers? (5) Should GIPSA allow a key employee to buy livestock for market support or to fill orders held by their employer, the market agency? (6) What is perceived to be the greatest impediment or barrier to effective competition at a market agency selling livestock on a commission basis? GIPSA welcomes any comments addressing these issues and any other aspects of the general subject of permitting key employees to purchase VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 livestock from consignments to a market agency. Susan B. Keith, Acting Administrator, Grain Inspection, Packers and Stockyards Administration. [FR Doc. 2015–14538 Filed 6–12–15; 8:45 am] BILLING CODE 3410–KD–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1981; Directorate Identifier 2014–NM–204–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 certain Airbus Model A330–200 Freighter, A330–200, A330–300, A340–200, and A340–300 series airplanes. This proposed AD was prompted by reports that the inner bore of some main landing gear (MLG) unit bogie beams were insufficiently re-protected against corrosion after inspection or maintenance actions were accomplished. This proposed AD would require, for certain MLG units, determining which revision of the component maintenance manual (CMM) was used to accomplish the most recent MLG unit overhaul; a detailed inspection for missing or damaged paint, and if necessary, a detailed inspection of the cadmium plating for discrepancies, measurement of the depth of the cadmium plating, a general visual inspection of the base metal for corrosion or damage, a detailed inspection of repaired areas for cracking or corrosion; and corrective actions if necessary. We are proposing this AD to detect and correct corrosion in the bore of each MLG unit bogie beam, which could result in collapse of a MLG unit, and subsequent damage to the airplane and injury to occupants. DATES: We must receive comments on this proposed AD by July 30, 2015. 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. SUMMARY: PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 • 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 Airbus service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@ airbus.com; Internet http:// www.airbus.com. For Messier-Dowty service information contact MessierDowty Limited, Cheltenham Road, Cloucester, GL2 9QH, England; telephone +44(0) 1452 712424; fax+ 44(0) 1452 713821; Internet http:// www.messier-dowtycom). 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–2015– 1981; 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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–2015–1981; Directorate Identifier E:\FR\FM\15JNP1.SGM 15JNP1 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 2014–NM–204–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 Union, has issued EASA Airworthiness Directive 2014–0222, dated October 6, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200 Freighter, A330–200, A330–300, A340–200, and A340–300 series airplanes. The MCAI states: asabaliauskas on DSK5VPTVN1PROD with PROPOSALS From in-service experience, it was found that the inner bore of some bogie beams had been insufficiently re-protected against corrosion after inspection and/or possible maintenance actions accomplished in this area (absence of corrosion inhibitor and damage to paint have been found in some specific areas). This condition, if not detected and corrected, could lead to corrosion on the bore of the bogie beam, potentially resulting in Main Landing Gear (MLG) collapse, ultimately resulting in damage to the aeroplane and injury to the occupants. To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A32L004–14, providing inspection instructions for some aeroplane configurations. For the reasons described above, this [EASA] AD requires identification of the MLG units that are possibly affected, [a detailed] inspection [for missing or damaged paint] of the MLG Bogie Beam bore and, depending on findings, accomplishment of the applicable corrective actions. This [EASA] AD also prohibits the installation of MLG units that have been overhauled by using instructions from an earlier Components Maintenance Manual (CMM) revision. Required actions also include a detailed inspection of the cadmium plating for discrepancies (gray in color), measurement of the depth of the cadmium plating if necessary, and a general visual inspection of the base metal for corrosion or damage, and a detailed inspection of repaired areas for cracking or corrosion. Corrective actions include removing cadmium plating and repairing any cracked, corroded, or VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 damaged areas; re-applying cadmium plating and paint; and re-applying temporary corrosion protection to the bores of the MLG bogie beams. 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–2015– 1981. Related Service Information Under 1 CFR Part 51 Airbus has issued Alert Operators Transmission A32L004–14, dated July 28, 2014, including Appendices 1, 2, 3, and 4, which are not dated. This service information describes procedures for inspections of the bogie beam bore of the MLG. Messier-Dowty has issued the following service information, which describes procedures for inspections of the internal diameter of the bogie beam for corrosion. • Service Bulletin A33/34–32–272, including Appendices A, B, C, and D, dated November 16, 2007. • Service Bulletin A33/34–32–272, Revision 1, including Appendices A, B, C, and D, dated September 22, 2008. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. 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 these same type designs. Costs of Compliance We estimate that this proposed AD affects 89 airplanes of U.S. registry. We also estimate that it would take about 12 work-hours 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 $90,780, or $1,020 per product. We have received no definitive data that would enable us to provide cost estimates for any necessary follow-on actions. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 34099 Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this proposed AD is 2120– 0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. 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; E:\FR\FM\15JNP1.SGM 15JNP1 34100 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 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 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–2015–1981; Directorate Identifier 2014–NM–204–AD. (a) Comments Due Date We must receive comments by July 30, 2015. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (b) Affected ADs None. (c) Applicability This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model A330–201, A330–202, A330– 203, A330–223, A330–223F, A330–243, A330–243F, A330–301, A330–302, A330– 303, A330–321, A330–322, A330–323, A330– 341, A330–342, and A330–343 airplanes; all manufacturer serial numbers; except those on which Airbus Modification 58896 has been embodied in production or embodied through Airbus Service Bulletin A330–32– 3237. (2) Model A340–211, A340–212, A340– 213, A340–311, A340–312, and A340–313 airplanes; all manufacturer serial numbers; except those on which Airbus Modification 58896 has been embodied in production or embodied through Airbus Service Bulletin A340–32–4279. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports that the inner bore of some main landing gear (MLG) unit bogie beams were insufficiently re- VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 protected against corrosion after inspection or maintenance actions were accomplished. We are issuing this AD to detect and correct corrosion in the bore of each MLG unit bogie beam, which could result in collapse of a MLG unit, and subsequent damage to the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Identification of Affected MLG Units Within 12 months after the effective date of this AD: For MLG units having a 201252 series or 201490 series part number, determine the revision of the Airbus component maintenance manual (CMM) used to do the most recent MLG unit overhaul. If it is determined that the Airbus CMM revision specified in paragraph (g)(1) or (g)(2) of this AD was used to accomplish the most recent MLG unit overhaul: Within 12 months after the effective date of this AD, clean the area between the bogie pivot pin and the bogie beam bore of each MLG unit and do a detailed inspection for missing or damaged paint, in accordance with the instructions of Airbus Alert Operators Transmission A32L004–14 dated July 28, 2014. (1) For MLG units having a part number in the 201252 series: Airbus CMM 32–11–74, Revision 25 or earlier. (2) For MLG units having a part number in the 201490 series: Airbus CMM 32–12–05, Revision 20 or earlier. (h) Inspection of Cadmium Plating If, during the inspection required by paragraph (g) of this AD, any missing or damaged paint is found: Before further flight, do a detailed inspection of the cadmium plating for discrepancies, measure the depth of the plating as applicable, and do a general visual inspection of the base metal for corrosion or damage. If any discrepancy, damage, or corrosion is found, before further flight, do all applicable corrective actions, and do a detailed inspection of repaired areas for cracking or corrosion, in accordance with Airbus Alert Operators Transmission A32L004–14, dated July 28, 2014, except where Airbus Alert Operators Transmission A32L004–14, dated July 28, 2014, specifies to contact Messier-Dowty if cracking or corrosion is found in a repaired area, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (i) Reporting Requirement At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, report the findings of the inspection required by paragraph (g) of this AD to Airbus, Customer Services Engineering—SEEL1, Attn: Philippe Kerangueven, Product Leader A330/A340, ATA–32, Landing Gear Systems, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; phone +33 (0) 5 67 19 18 42; fax +33 0 5 67 19 12–05; email philippe.kerangueven@airbus.com. The report must include the information specified PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 in Appendix 2 of Airbus Alert Operators Transmission A32L004–14, dated July 28, 2014. (1) If the inspection was done on or after the effective date of this AD: Within 90 days after that inspection. (2) If the inspection was done before the effective date of this AD: Within 90 days after the effective date of this AD. (j) Optional Method of Compliance Accomplishment of the boroscope inspection of the internal diameter of the bogie beam for corrosion or damage to the protective treatments, measurement of the depth of the protective treatments as applicable, and accomplishment of all applicable corrective actions, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, dated November 16, 2007; or Revision 1, including Appendices A, B, C, and D, dated September 22, 2008; are acceptable for the corresponding actions required by paragraphs (g) and (h) of this AD for that MLG unit, provided the actions in the Messier-Dowty Service Bulletins identified in paragraphs (j)(1) through (j)(5) of this AD have not been accomplished on that MLG unit. Where Messier-Dowty Service Bulletin A33/34–32–272, dated November 16, 2007; or Revision 1, including Appendices A, B, C, and D, dated September 22, 2008; specify to contact Messier-Dowty for repair information, the repair must be accomplished using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (1) Messier-Dowty Service Bulletin A33/ 34–32–285, dated July 9, 2010. (2) Messier-Dowty Service Bulletin A33/ 34–32–285, Revision 1, dated October 4, 2011. (3) Messier-Dowty Service Bulletin A33/ 34–32–285, Revision 2, dated October 4, 2012. (4) Messier-Dowty Service Bulletin A33/ 34–32–285, Revision 3, dated September 11, 2013. (5) Messier-Dowty Service Bulletin A33/ 34–32–285, Revision 4, dated January 23, 2014. Note 1 to paragraph (j) of this AD: Inspections done using the instructions in Messier-Dowty Service Bulletin A33/34–32– 285, Revision 5, dated August 14, 2014, do not affect the optional method of compliance provided by this paragraph. (k) Parts Installation Limitation As of the effective date of this AD, any overhauled MLG unit having a 201252 series or 201490 series part number may be installed on an airplane, provided the most recent MLG overhaul was done using an Airbus CMM that is not specified in paragraph (g)(1) or (g)(2) of this AD, or, prior to installation, the MLG unit passes the inspection required by paragraph (g) of this AD. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International E:\FR\FM\15JNP1.SGM 15JNP1 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0222, dated October 6, 2014, 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– 2015–1981. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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. VerDate Sep<11>2014 16:22 Jun 12, 2015 Jkt 235001 Issued in Renton, Washington, on June 3, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–14229 Filed 6–12–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1429; Directorate Identifier 2014–NM–246–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 certain Airbus Model A319–113, A319–114, A320–211, and A320–212 airplanes. This proposed AD was prompted by a report that the aft mount pylon bolts of the CFM56–5 engines may have been installed using the wrong torque values. This proposed AD would require identification of engines that were installed using the wrong torque values and re-torque of the four aft mount pylon bolts of those engines. We are proposing this AD to detect and correct improper torque of the aft mount pylon bolts, which, if combined with any maintenance damage, could lead to aft engine mount failure, possibly resulting in engine detachment and consequent reduced control of the airplane. DATES: We must receive comments on this proposed AD by July 30, 2015. 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: 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. SUMMARY: PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 34101 For service information identified in this proposed AD, contact Airbus, Airworthiness Office—EIAS, 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 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–2015– 1429; 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 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–2015–1429; Directorate Identifier 2014–NM–246–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 Union, has issued EASA Airworthiness E:\FR\FM\15JNP1.SGM 15JNP1

Agencies

[Federal Register Volume 80, Number 114 (Monday, June 15, 2015)]
[Proposed Rules]
[Pages 34098-34101]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14229]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1981; Directorate Identifier 2014-NM-204-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, 
and A340-300 series airplanes. This proposed AD was prompted by reports 
that the inner bore of some main landing gear (MLG) unit bogie beams 
were insufficiently re-protected against corrosion after inspection or 
maintenance actions were accomplished. This proposed AD would require, 
for certain MLG units, determining which revision of the component 
maintenance manual (CMM) was used to accomplish the most recent MLG 
unit overhaul; a detailed inspection for missing or damaged paint, and 
if necessary, a detailed inspection of the cadmium plating for 
discrepancies, measurement of the depth of the cadmium plating, a 
general visual inspection of the base metal for corrosion or damage, a 
detailed inspection of repaired areas for cracking or corrosion; and 
corrective actions if necessary. We are proposing this AD to detect and 
correct corrosion in the bore of each MLG unit bogie beam, which could 
result in collapse of a MLG unit, and subsequent damage to the airplane 
and injury to occupants.

DATES: We must receive comments on this proposed AD by July 30, 2015.

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: 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 Airbus service information identified in this proposed AD, 
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet 
http://www.airbus.com. For Messier-Dowty service information contact 
Messier-Dowty Limited, Cheltenham Road, Cloucester, GL2 9QH, England; 
telephone +44(0) 1452 712424; fax+ 44(0) 1452 713821; Internet http://www.messier-dowtycom). 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-2015-
1981; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM 116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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-2015-1981; 
Directorate Identifier

[[Page 34099]]

2014-NM-204-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 Union, has issued EASA 
Airworthiness Directive 2014-0222, dated October 6, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series 
airplanes. The MCAI states:

    From in-service experience, it was found that the inner bore of 
some bogie beams had been insufficiently re-protected against 
corrosion after inspection and/or possible maintenance actions 
accomplished in this area (absence of corrosion inhibitor and damage 
to paint have been found in some specific areas).
    This condition, if not detected and corrected, could lead to 
corrosion on the bore of the bogie beam, potentially resulting in 
Main Landing Gear (MLG) collapse, ultimately resulting in damage to 
the aeroplane and injury to the occupants.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A32L004-14, providing inspection 
instructions for some aeroplane configurations.
    For the reasons described above, this [EASA] AD requires 
identification of the MLG units that are possibly affected, [a 
detailed] inspection [for missing or damaged paint] of the MLG Bogie 
Beam bore and, depending on findings, accomplishment of the 
applicable corrective actions.
    This [EASA] AD also prohibits the installation of MLG units that 
have been overhauled by using instructions from an earlier 
Components Maintenance Manual (CMM) revision.

Required actions also include a detailed inspection of the cadmium 
plating for discrepancies (gray in color), measurement of the depth of 
the cadmium plating if necessary, and a general visual inspection of 
the base metal for corrosion or damage, and a detailed inspection of 
repaired areas for cracking or corrosion. Corrective actions include 
removing cadmium plating and repairing any cracked, corroded, or 
damaged areas; re-applying cadmium plating and paint; and re-applying 
temporary corrosion protection to the bores of the MLG bogie beams.
    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-2015-
1981.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission A32L004-14, dated 
July 28, 2014, including Appendices 1, 2, 3, and 4, which are not 
dated. This service information describes procedures for inspections of 
the bogie beam bore of the MLG.
    Messier-Dowty has issued the following service information, which 
describes procedures for inspections of the internal diameter of the 
bogie beam for corrosion.
     Service Bulletin A33/34-32-272, including Appendices A, B, 
C, and D, dated November 16, 2007.
     Service Bulletin A33/34-32-272, Revision 1, including 
Appendices A, B, C, and D, dated September 22, 2008.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
NPRM.

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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 89 airplanes of U.S. 
registry.
    We also estimate that it would take about 12 work-hours 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 $90,780, or $1,020 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for any necessary follow-on actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

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;

[[Page 34100]]

    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-2015-1981; Directorate Identifier 2014-NM-
204-AD.

(a) Comments Due Date

    We must receive comments by July 30, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A330-201, A330-202, A330-203, A330-223, A330-223F, 
A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-
322, A330-323, A330-341, A330-342, and A330-343 airplanes; all 
manufacturer serial numbers; except those on which Airbus 
Modification 58896 has been embodied in production or embodied 
through Airbus Service Bulletin A330-32-3237.
    (2) Model A340-211, A340-212, A340-213, A340-311, A340-312, and 
A340-313 airplanes; all manufacturer serial numbers; except those on 
which Airbus Modification 58896 has been embodied in production or 
embodied through Airbus Service Bulletin A340-32-4279.

(d) Subject

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

(e) Reason

    This AD was prompted by reports that the inner bore of some main 
landing gear (MLG) unit bogie beams were insufficiently re-protected 
against corrosion after inspection or maintenance actions were 
accomplished. We are issuing this AD to detect and correct corrosion 
in the bore of each MLG unit bogie beam, which could result in 
collapse of a MLG unit, and subsequent damage to the airplane and 
injury to occupants.

(f) Compliance

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

(g) Identification of Affected MLG Units

    Within 12 months after the effective date of this AD: For MLG 
units having a 201252 series or 201490 series part number, determine 
the revision of the Airbus component maintenance manual (CMM) used 
to do the most recent MLG unit overhaul. If it is determined that 
the Airbus CMM revision specified in paragraph (g)(1) or (g)(2) of 
this AD was used to accomplish the most recent MLG unit overhaul: 
Within 12 months after the effective date of this AD, clean the area 
between the bogie pivot pin and the bogie beam bore of each MLG unit 
and do a detailed inspection for missing or damaged paint, in 
accordance with the instructions of Airbus Alert Operators 
Transmission A32L004-14 dated July 28, 2014.
    (1) For MLG units having a part number in the 201252 series: 
Airbus CMM 32-11-74, Revision 25 or earlier.
    (2) For MLG units having a part number in the 201490 series: 
Airbus CMM 32-12-05, Revision 20 or earlier.

(h) Inspection of Cadmium Plating

    If, during the inspection required by paragraph (g) of this AD, 
any missing or damaged paint is found: Before further flight, do a 
detailed inspection of the cadmium plating for discrepancies, 
measure the depth of the plating as applicable, and do a general 
visual inspection of the base metal for corrosion or damage. If any 
discrepancy, damage, or corrosion is found, before further flight, 
do all applicable corrective actions, and do a detailed inspection 
of repaired areas for cracking or corrosion, in accordance with 
Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014, 
except where Airbus Alert Operators Transmission A32L004-14, dated 
July 28, 2014, specifies to contact Messier-Dowty if cracking or 
corrosion is found in a repaired area, before further flight, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA).

(i) Reporting Requirement

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD, report the findings of the inspection required by 
paragraph (g) of this AD to Airbus, Customer Services Engineering--
SEEL1, Attn: Philippe Kerangueven, Product Leader A330/A340, ATA-32, 
Landing Gear Systems, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; phone +33 (0) 5 67 19 18 42; fax +33 0 5 67 19 12-05; 
email philippe.kerangueven@airbus.com. The report must include the 
information specified in Appendix 2 of Airbus Alert Operators 
Transmission A32L004-14, dated July 28, 2014.
    (1) If the inspection was done on or after the effective date of 
this AD: Within 90 days after that inspection.
    (2) If the inspection was done before the effective date of this 
AD: Within 90 days after the effective date of this AD.

(j) Optional Method of Compliance

    Accomplishment of the boroscope inspection of the internal 
diameter of the bogie beam for corrosion or damage to the protective 
treatments, measurement of the depth of the protective treatments as 
applicable, and accomplishment of all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-272, dated November 16, 2007; or Revision 
1, including Appendices A, B, C, and D, dated September 22, 2008; 
are acceptable for the corresponding actions required by paragraphs 
(g) and (h) of this AD for that MLG unit, provided the actions in 
the Messier-Dowty Service Bulletins identified in paragraphs (j)(1) 
through (j)(5) of this AD have not been accomplished on that MLG 
unit. Where Messier-Dowty Service Bulletin A33/34-32-272, dated 
November 16, 2007; or Revision 1, including Appendices A, B, C, and 
D, dated September 22, 2008; specify to contact Messier-Dowty for 
repair information, the repair must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
    (1) Messier-Dowty Service Bulletin A33/34-32-285, dated July 9, 
2010.
    (2) Messier-Dowty Service Bulletin A33/34-32-285, Revision 1, 
dated October 4, 2011.
    (3) Messier-Dowty Service Bulletin A33/34-32-285, Revision 2, 
dated October 4, 2012.
    (4) Messier-Dowty Service Bulletin A33/34-32-285, Revision 3, 
dated September 11, 2013.
    (5) Messier-Dowty Service Bulletin A33/34-32-285, Revision 4, 
dated January 23, 2014.
    Note 1 to paragraph (j) of this AD: Inspections done using the 
instructions in Messier-Dowty Service Bulletin A33/34-32-285, 
Revision 5, dated August 14, 2014, do not affect the optional method 
of compliance provided by this paragraph.

(k) Parts Installation Limitation

    As of the effective date of this AD, any overhauled MLG unit 
having a 201252 series or 201490 series part number may be installed 
on an airplane, provided the most recent MLG overhaul was done using 
an Airbus CMM that is not specified in paragraph (g)(1) or (g)(2) of 
this AD, or, prior to installation, the MLG unit passes the 
inspection required by paragraph (g) of this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International

[[Page 34101]]

Branch, ANM-116, Transport Airplane Directorate, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0222, dated October 6, 
2014, 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-2015-1981.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@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.

    Issued in Renton, Washington, on June 3, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-14229 Filed 6-12-15; 8:45 am]
 BILLING CODE 4910-13-P