Airworthiness Directives; Airbus Airplanes, 8134-8138 [2016-03215]

Download as PDF 8134 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations Currency in issuing interagency guidance stating that, depending on the facts and circumstances, a depository institution might violate the prohibition against unfair or deceptive practices in the FTC Act and the Dodd-Frank Act if it engages in the practices prohibited by the former credit practices rules.14 wgreen on DSK2VPTVN1PROD with RULES II. Discussion Fourteen commenters responded to the proposed repeal of Regulation AA. Three individual commenters stated that Regulation AA was a necessary and helpful regulation; two of these commenters stated that the Board’s reasons for repealing the regulation were unclear. A comment letter received from seven consumer advocate organizations acknowledged that the Board’s repeal of Regulation AA was required by the Dodd-Frank Act. In their letter, these commenters also provided recommendations to the Bureau regarding acts or practices that the Bureau now has to authority to regulate if it finds they are unfair or deceptive.15 Eight commenters addressed the interagency guidance that was issued simultaneously with the proposed repeal of Regulation AA. One individual commenter believed the guidance would discourage banks from engaging in unfair or deceptive acts or practices, but seven consumer advocate commenters recommended strengthening the guidance language. The consumer advocate commenters also recommended that the Board issue additional guidance regarding other acts or practices that the commenters believe should be declared unfair or deceptive acts or practices. The Board is finalizing the repeal of Regulation AA as proposed. As the Board discussed in the Proposed Rule, the Dodd-Frank Act eliminated the Board’s rule writing authority under the FTC Act, which nullified the regulation. The Board will continue to monitor developments with respect to unfair or deceptive acts or practices and assess whether to issue additional supervisory guidance. The repeal of Regulation AA also eliminates Subpart A of the regulation, which generally describes the internal procedures used by the Board in handling consumer complaints. The Board did not receive comment on the 14 ‘‘Interagency Guidance Regarding Unfair or Deceptive Credit Practices’’ (Aug. 22, 2014). http://www.federalreserve.gov/newsevents/press/ bcreg/bcreg20140822a2.pdf. 15 One state chartered bank commenter did not address the proposed repeal, but objected to examiners’ citations of banks for unfair or deceptive practices in the supervisory process. Two individual commenters did not address the proposed repeal of Regulation AA. VerDate Sep<11>2014 14:29 Feb 17, 2016 Jkt 238001 removal of these internal procedures from the Code of Federal Regulations. Information about how the Board processes consumer complaints is provided on the Board’s public Web site.16 III. Final Regulatory Flexibility Analysis The Regulatory Flexibility Act 17 (RFA) generally requires an agency to perform an assessment of the impact a rule is expected to have on small entities. Based on its analysis, and for the reasons stated below, the Board believes that this final rule will not have a significant economic impact on a substantial number of small entities. 1. Statement of the need for, and objectives of, the final rule. Regulation AA was issued pursuant to section 18(f)(1) of the FTC Act. As noted above, the Dodd-Frank Act repealed this provision of the FTC Act.18 Accordingly, the Board is repealing its Regulation AA. 2. Summary of issues raised by comments in response to the initial regulatory flexibility analysis. The Board did not receive any comments on the initial regulatory flexibility analysis. 3. Small entities affected by the final rule. The final rule repeals Regulation AA, which was issued pursuant to section 18(f)(1) of the FTC. As a result of the FTC Act amendments made by the Dodd-Frank Act, the Board no longer has rule writing authority under section 18(f)(1). The legislative repeal of the Board’s rulemaking authority nullified the provisions in Regulation AA that were issued pursuant to that authority. Consequently, the Board’s repeal of the regulation, which no longer has legal effect, will not affect any entity, including any small entity. The repeal of Regulation AA will also remove information about how the Board processes consumer complaints from the Code of Federal Regulations. This is not expected to have an effect on small entities because that information is provided on the Board’s public Web site. 4. Recordkeeping, reporting, and compliance requirements. The final rule repeals Regulation AA and therefore does not impose any recordkeeping, reporting, or compliance requirements on any entities. 5. Significant alternatives to the final revisions. Because the repeal of Regulation AA will have no impact, there are no alternatives that would 16 https://www.federalreserveconsumerhelp.gov/. 17 5 U.S.C. 601 et seq. section 1092(2) of the Dodd-Frank Act. 18 See PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 further minimize the economic impact of the final rule on small entities. IV. Paperwork Reduction Act In accordance with the Paperwork Reduction Act (PRA) of 1995 (44 U.S.C. 3506; 5 CFR 1320 Appendix A.1), the Board reviewed the rule under the authority delegated to the Federal Reserve by the Office of Management and Budget (OMB). The final rule contains no requirements subject to the PRA. List of Subjects in 12 CFR Part 227 Banks, Banking, Consumer protection, Credit, Federal Reserve System, Finance. Authority and Issuance For the reasons set forth in the preamble, and under the authority of section 1092(2) of Public Law 111–203, 124 Stat. 1376 (Jul. 21, 2010), the Board amends 12 CFR chapter II by removing part 227. PART 227—[REMOVED] By order of the Board of Governors of the Federal Reserve System, February 11, 2016. Robert deV. Frierson, Secretary of the Board. [FR Doc. 2016–03228 Filed 2–17–16; 8:45 am] BILLING CODE–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–0467; Directorate Identifier 2016–NM–008–AD; Amendment 39–18395; AD 2016–04–01] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2015–26– 02 for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Airbus Model A340–200, A340–300, A340–500, and A340–600 series airplanes. AD 2015– 26–02 required, for certain airplanes, identification of the part number, serial number, and standard of the ram air turbine (RAT) pump, RAT module, RAT actuator, and RAT lower gearbox assembly; replacement of the balance SUMMARY: E:\FR\FM\18FER1.SGM 18FER1 wgreen on DSK2VPTVN1PROD with RULES Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations weight screw, modification of the actuator coil spring, modification of the actuator, an inspection of the anti-stall valve for correct installation in the RAT pump housing; and corrective actions if necessary. For certain other airplanes, AD 2015–26–02 required reidentification or replacement of the RAT module. This new AD requires the same actions as AD 2015–26–02. This new AD was prompted by a report of a typographical error in the regulatory text of AD 2015–26–02. We are issuing this AD to prevent loss of the impeller function and RAT pump pressurization capability, which, if preceded by a total engine flame-out, could result in loss of control of the airplane. DATES: This AD becomes effective March 4, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 2, 2016 (80 FR 81174, December 29, 2015). We must receive comments on this AD by April 4, 2016. 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 final rule, 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.A330A340@ airbus.com; Internet http:// www.airbus.com. For Hamilton Sundstrand service information identified in this final rule, contact Hamilton Sundstrand, Technical Publications, Mail Stop 302–9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125–7002; telephone 860–654–3575; fax 860–998–4564; email tech.solutions@hs.utc.com; Internet http://www.hamiltonsundstrand.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue VerDate Sep<11>2014 14:29 Feb 17, 2016 Jkt 238001 SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 0467. 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–2016– 0467; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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: Discussion On December 9, 2015, we issued AD 2015–26–02, Amendment 39–18350 (80 FR 81174, December 29, 2015) (‘‘AD 2015–26–02’’). AD 2015–26–02 applied to all Airbus Model A330–200, A330– 200 Freighter, and A330–300 series airplanes; and Airbus Model A340–200, A340–300, A340–500, and A340–600 series airplanes. AD 2015–26–02 was prompted by a report indicating that, during a production flight test, the RAT did not pressurize the green hydraulic system. AD 2015–26–02 required for certain airplanes, identification of the part number, serial number, and standard of the RAT pump, RAT module, RAT actuator, and RAT lower gearbox assembly; replacement of the balance weight screw, modification of the actuator coil spring, modification of the actuator, an inspection of the antistall valve for correct installation in the RAT pump housing; and corrective actions if necessary. For certain other airplanes, AD 2015–26–02 required reidentification or replacement of the RAT module. We issued AD 2015–26–02 to prevent loss of the impeller function and RAT pump pressurization capability, which, if preceded by a total engine flame-out, could result in loss of control of the airplane. Since we issued AD 2015–26–02, we received a report of a typographical PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 8135 error in the regulatory text of AD 2015– 26–02. Paragraph (m) of AD 2015–26–02 inadvertently referred to paragraph (n) and should have referred to paragraph (o), ‘‘Parts Installation Prohibition.’’ The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013–0274, dated November 15, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Airbus Model A340–200, A340–300, A340–500, and A340–600 series airplanes. The MCAI states: During a production flight test of an A330– 300 aeroplane, the Ram Air Turbine (RAT) did not pressurize the green hydraulic system. Investigation revealed that the impeller drive (hex) shaft had a reduced length of engagement with the pump drive shaft. This caused the impeller drive shaft to disengage from the pump and disconnect the impeller. It was determined that the disconnection was the result of internal hex dimensions on the pump impeller shaft, which had been changed in a manufacturing drawing. From the investigation analysis, it was possible to identify a list of affected parts. This condition, if not detected and corrected, could lead to the loss of impeller function and RAT pump pressurization capability, possibly resulting, in case of total engine flame out, to the loss of control of the aeroplane. To address this unsafe condition, a new design RAT pump shaft has been developed with a decreased hexagonal shaft housing depth, which increases the hexagonal drive shaft engagement in the impeller shaft to carry the impeller torque. Airbus issued Service Bulletin (SB) A330–29–3122, SB A340–29–4093 and SB A340–29–5021 to provide instructions for in-service replacement of the affected RAT hydraulic pumps, or re-identification of the RAT pump and complete RAT module, as applicable. For the reasons described above, this [EASA] AD requires identification and replacement [modification] or reidentification of all affected RAT hydraulic pumps on A330 and A340–200/300 aeroplanes, and replacement [modification] of all affected RAT modules on A340–500/ –600 aeroplanes. For affected pumps, the required actions also include concurrent actions, as applicable, including replacement of the balance weight screw, modification of the actuator coil spring, modification of the actuator, an inspection of the antistall valve for correct installation in the RAT pump housing and re-installation if necessary. For affected pumps, corrective actions include replacement of the RAT hydraulic pump, and reidentification of the part number of the E:\FR\FM\18FER1.SGM 18FER1 8136 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations RAT module. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 0467. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Airbus Service Bulletin A330–29– 3122, dated October 25, 2012. • Airbus Service Bulletin A340–29– 4093, dated October 25, 2012. This service information describes procedures for identifying the part number, serial number, and standard of the RAT pump, RAT module, RAT actuator, and RAT lower gearbox assembly; replacing the balance weight screw, modifying the actuator coil spring, modifying the actuator, and doing an inspection of the anti-stall valve for correct installation; and reidentifying the part numbers of the RAT hydraulic pump and RAT module. Airbus also issued Service Bulletin A330–29–3126, dated June 12, 2014; and Service Bulletin A340–29–4097, dated June 12, 2014, which describe procedures for identifying the part number and serial number of the RAT actuator; modifying the RAT actuators; and re-identifying the part numbers of the RAT module. In addition, Airbus issued Service Bulletin A340–29–5021, dated October 2, 2012; and Service Bulletin A340–29– 5025, dated June 16, 2014, which describe procedures for replacing (modifying) the RAT module. Hamilton Sundstrand has issued Service Bulletin ERPS06M–29–19, dated August 6, 2012, which identifies the serial numbers of the suspect hydraulic pump. 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. wgreen on DSK2VPTVN1PROD with RULES FAA’s Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. VerDate Sep<11>2014 14:29 Feb 17, 2016 Jkt 238001 FAA’s Determination of the Effective Date We are superseding AD 2015–26–02 to correct a typographical error in the regulatory text. No other changes have been made to AD 2015–26–02. Therefore, we determined that notice and opportunity for prior public comment are unnecessary. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–0467; Directorate Identifier 2016–NM–008– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. Costs of Compliance We estimate that this AD affects 66 airplanes of U.S. registry. We also estimate that it will take about 14 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $78,540, or $1,190 per product. In addition, we estimate that any necessary follow-on actions will take about 18 work-hours and require parts costing up to $427,301, for a cost of $428,831 per product. We have no way of determining the number of aircraft that might need this action. 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2015–26–02, Amendment 39–18350 (80 FR 81174, December 29, 2015), and adding the following new AD: ■ 2016–04–01 Airbus: Amendment 39–18395; Docket No. FAA–2016–0467; Directorate Identifier 2016–NM–008–AD. (a) Effective Date This AD becomes effective March 4, 2016. E:\FR\FM\18FER1.SGM 18FER1 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations (b) Affected ADs (1) This AD replaces AD 2015–26–02, Amendment 39–18350 (80 FR 81174, December 29, 2015). (2) This AD affects AD 2012–21–19, Amendment 39–17235 (77 FR 65812, October 31, 2012); and AD 2012–21–20, Amendment 39–17236 (77 FR 65799, October 31, 2012). (c) Applicability This AD applies to all Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, all manufacturer serial numbers. (1) Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (2) Model A340–211, –212, –213, –311, –312, –313, –541, and –642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic Power. (e) Reason This AD was prompted by a report indicating that, during a production flight test, the ram air turbine (RAT) did not pressurize the green hydraulic system. We are issuing this AD to prevent loss of the impeller function and RAT pump pressurization capability, which, if preceded by a total engine flame-out, could result in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. wgreen on DSK2VPTVN1PROD with RULES (g) Identification of RAT Components For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes: Except as provided by paragraph (i) of this AD, within 36 months after the effective date of this AD, identify the part number, serial number, and standard (through the mod-dots) of the RAT pump, RAT module, RAT actuator, and RAT lower gearbox assembly, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. A review of airplane maintenance records is acceptable in lieu of this identification if the part number, serial number, and standard can be conclusively determined from that review. (1) For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes: Airbus Service Bulletin A330–29– 3122, dated October 25, 2012. (2) For Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes: Airbus Service Bulletin A340–29–4093, dated October 25, 2012. (h) Corrective and Concurrent Actions If the serial number of the RAT hydraulic pump is included in table 7, ‘‘Suspect Hydraulic Pump Serial Numbers,’’ of Hamilton Sundstrand Service Bulletin ERPS06M–29–19, dated August 6, 2012: Within 36 months after the effective date of VerDate Sep<11>2014 14:29 Feb 17, 2016 Jkt 238001 this AD, do all applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. Prior to or concurrently with doing the corrective actions required by this paragraph, do the actions specified in paragraphs (h)(1) through (h)(4) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 29–3122, dated October 25, 2012 (for Model A330–200, –200 Freighter, and –300 series airplanes); or Airbus Service Bulletin A340– 29–4093, dated October 25, 2012 (for Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes). (1) Replace the balance weight screw. (2) Modify the actuator coil spring. (3) Modify the actuator. (4) Do a general visual inspection of the anti-stall valve for correct installation in the RAT pump housing, and if any incorrect installation is found, before further flight, correctly install the anti-stall valve. (i) Exception to Service Information Specifications Airbus Service Bulletin A330–29–3122, dated October 25, 2012 (for Model A330–200, –200 Freighter, and –300 series airplanes), refers to Hamilton Sundstrand Service Bulletin ‘‘EPRPS06M–29–13’’ as an additional source of guidance for doing certain actions required by paragraph (h) of this AD. The first ‘‘P’’ in the citation should have been omitted; the correct reference is to Hamilton Sundstrand Service Bulletin ‘‘ERPS06M–29–13.’’ (j) Re-Identification of Part Numbers If the serial number of the RAT hydraulic pump is not included in table 7, ‘‘Suspect Hydraulic Pump Serial Numbers,’’ of Hamilton Sundstrand Service Bulletin ERPS06M–29–19, dated August 6, 2012: Within 36 months after the effective date of this AD, re-identify the part numbers of the RAT hydraulic pump and RAT module, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. (k) Service Information for Optional Actions Accomplishment of the actions required by paragraphs (g), (h), and (j) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 29–3126, dated June 12, 2014; or Airbus Service Bulletin A340–29–4097, dated June 12, 2014, as applicable, constitutes compliance with the requirements of paragraphs (g), (h), and (j) of this AD. (l) RAT Module Replacement (Modification) For Airbus Model A340–541 and –642 airplanes having RAT module part number (P/N) 772722D, 772722E, 772722F, or 772722G: Within 36 months after the effective date of this AD, replace (modify) the RAT module, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–29–5021, dated October 2, 2012. As an option, accomplishment of the RAT module replacement (modification), in accordance with the Accomplishment Instructions of PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 8137 Airbus Service Bulletin A340–29–5025, dated June 16, 2014, constitutes compliance with the requirement of this paragraph. (m) Exception to Paragraphs (g), (h), and (j) of This AD The actions required by paragraphs (g), (h), and (j) of this AD are not required for airplanes on which Airbus Modification 202537 was embodied in production, provided it can be determined that, since the airplane’s first flight, no RAT hydraulic pump or RAT module having a part number identified in paragraph (o) of this AD is installed on that airplane. (n) Terminating Action for Certain Requirements of Other ADs (1) For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes: Accomplishment of the actions required by paragraphs (g), (h), and (j) of this AD constitutes compliance with the requirements of paragraphs (g)(1) and (g)(2) of AD 2012–21–19, Amendment 39–17235 (77 FR 65812, October 31, 2012); and paragraphs (g)(1) and (g)(2) of AD 2012–21– 20, Amendment 39–17236 (77 FR 65799, October 31, 2012). (2) For Airbus Model A340–541 and –642 airplanes: Accomplishment of the actions required by paragraph (l) of this AD constitutes compliance with the requirements of paragraphs (h)(1) and (h)(2) of AD 2012–21–20, Amendment 39–17236 (77 FR 65799, October 31, 2012). (o) Parts Installation Prohibition (1) For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and A340–211, –212, –213, –311, –312, and –313 airplanes: After modification of the RAT module as required by paragraph (h) of this AD, no person may install any complete RAT module having a part number identified in paragraph (o)(1)(i) of this AD, or any RAT hydraulic pump having the part number identified in paragraph (o)(1)(ii) of this AD, on any airplane. (i) RAT module P/N 766351, 768084, 770379, 770952, 770952A, 770952B, 1702934, 1702934A, or 1702934B. (ii) RAT hydraulic pump P/N 5909522 (Parker P/N 4207902). (2) For Airbus Model A340–541 and –642 airplanes: After modification of the RAT module as required by paragraph (l) of this AD, no person may install any complete RAT module having P/N 772722D, 772722E, 772722F, or 772722G, on any airplane. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as E:\FR\FM\18FER1.SGM 18FER1 8138 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 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 the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. wgreen on DSK2VPTVN1PROD with RULES (q) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0274, dated November 15, 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–2016–0467. (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on February 2, 2016 (80 FR 81174, December 29, 2015). (i) Airbus Service Bulletin A330–29–3122, dated October 25, 2012. (ii) Airbus Service Bulletin A330–29–3126, dated June 12, 2014. (iii) Airbus Service Bulletin A340–29– 4093, dated October 25, 2012. (iv) Airbus Service Bulletin A340–29– 4097, dated June 12, 2014. (v) Airbus Service Bulletin A340–29–5021, dated October 2, 2012. (vi) Airbus Service Bulletin A340–29– 5025, dated June 16, 2014. (vii) Hamilton Sundstrand Service Bulletin ERPS06M–29–19, dated August 6, 2012. (4) For Airbus 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.A330A340@airbus.com; Internet http:// www.airbus.com. (5) For Hamilton Sundstrand service information identified in this AD, contact Hamilton Sundstrand, Technical Publications, Mail Stop 302–9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125– VerDate Sep<11>2014 14:29 Feb 17, 2016 Jkt 238001 7002; telephone 860–654–3575; fax 860–998– 4564; email tech.solutions@hs.utc.com; Internet http:// www.hamiltonsundstrand.com. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on February 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–03215 Filed 2–17–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3630; Directorate Identifier 2014–NM–253–AD; Amendment 39–18397; AD 2016–04–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747–400F series airplanes. This AD was prompted by an analysis of the production methods used to increase fatigue resistance of the upper closure fittings at the nose cargo door portal’s C–3 frame, which showed that cracking could start too early to be caught in a timely manner by the inspection or maintenance program. This AD requires inspections of the upper closure fitting and connected strap and doubler at the nose cargo door portal for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could result in sudden decompression and loss of the airplane’s structural integrity. DATES: This AD is effective March 24, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 24, 2016. SUMMARY: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3630. ADDRESSES: 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– 3630; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: bill.ashforth@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 747–400F series airplanes. The NPRM published in the Federal Register on September 15, 2015 (80 FR 55273) (‘‘the NPRM’’). The NPRM was prompted by a report indicating that an analysis of the production methods used to increase fatigue resistance of the upper closure fittings at the nose cargo door portal’s C–3 frame showed that cracking could start too early to be caught in a timely manner by the inspection or maintenance program. The upper closure fittings used in the nose cargo door portal C–3 frame were shot peened to increase fatigue resistance. However, an analysis showed that the increase in E:\FR\FM\18FER1.SGM 18FER1

Agencies

[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)]
[Rules and Regulations]
[Pages 8134-8138]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03215]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0467; Directorate Identifier 2016-NM-008-AD; 
Amendment 39-18395; AD 2016-04-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-26-02 for 
all Airbus Model A330-200, A330-200 Freighter, and A330-300 series 
airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600 
series airplanes. AD 2015-26-02 required, for certain airplanes, 
identification of the part number, serial number, and standard of the 
ram air turbine (RAT) pump, RAT module, RAT actuator, and RAT lower 
gearbox assembly; replacement of the balance

[[Page 8135]]

weight screw, modification of the actuator coil spring, modification of 
the actuator, an inspection of the anti-stall valve for correct 
installation in the RAT pump housing; and corrective actions if 
necessary. For certain other airplanes, AD 2015-26-02 required re-
identification or replacement of the RAT module. This new AD requires 
the same actions as AD 2015-26-02. This new AD was prompted by a report 
of a typographical error in the regulatory text of AD 2015-26-02. We 
are issuing this AD to prevent loss of the impeller function and RAT 
pump pressurization capability, which, if preceded by a total engine 
flame-out, could result in loss of control of the airplane.

DATES: This AD becomes effective March 4, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 2, 
2016 (80 FR 81174, December 29, 2015).
    We must receive comments on this AD by April 4, 2016.

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 final rule, 
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.A330A340@airbus.com; Internet 
http://www.airbus.com.
    For Hamilton Sundstrand service information identified in this 
final rule, contact Hamilton Sundstrand, Technical Publications, Mail 
Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125-
7002; telephone 860-654-3575; fax 860-998-4564; email 
tech.solutions@hs.utc.com; Internet http://www.hamiltonsundstrand.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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0467.

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-2016-
0467; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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:

Discussion

    On December 9, 2015, we issued AD 2015-26-02, Amendment 39-18350 
(80 FR 81174, December 29, 2015) (``AD 2015-26-02''). AD 2015-26-02 
applied to all Airbus Model A330-200, A330-200 Freighter, and A330-300 
series airplanes; and Airbus Model A340-200, A340-300, A340-500, and 
A340-600 series airplanes. AD 2015-26-02 was prompted by a report 
indicating that, during a production flight test, the RAT did not 
pressurize the green hydraulic system. AD 2015-26-02 required for 
certain airplanes, identification of the part number, serial number, 
and standard of the RAT pump, RAT module, RAT actuator, and RAT lower 
gearbox assembly; replacement of the balance weight screw, modification 
of the actuator coil spring, modification of the actuator, an 
inspection of the anti-stall valve for correct installation in the RAT 
pump housing; and corrective actions if necessary. For certain other 
airplanes, AD 2015-26-02 required re-identification or replacement of 
the RAT module. We issued AD 2015-26-02 to prevent loss of the impeller 
function and RAT pump pressurization capability, which, if preceded by 
a total engine flame-out, could result in loss of control of the 
airplane.
    Since we issued AD 2015-26-02, we received a report of a 
typographical error in the regulatory text of AD 2015-26-02. Paragraph 
(m) of AD 2015-26-02 inadvertently referred to paragraph (n) and should 
have referred to paragraph (o), ``Parts Installation Prohibition.''
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0274, dated November 15, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, A330-200 Freighter, and A330-300 series airplanes; and Airbus 
Model A340-200, A340-300, A340-500, and A340-600 series airplanes. The 
MCAI states:

    During a production flight test of an A330-300 aeroplane, the 
Ram Air Turbine (RAT) did not pressurize the green hydraulic system. 
Investigation revealed that the impeller drive (hex) shaft had a 
reduced length of engagement with the pump drive shaft. This caused 
the impeller drive shaft to disengage from the pump and disconnect 
the impeller. It was determined that the disconnection was the 
result of internal hex dimensions on the pump impeller shaft, which 
had been changed in a manufacturing drawing. From the investigation 
analysis, it was possible to identify a list of affected parts.
    This condition, if not detected and corrected, could lead to the 
loss of impeller function and RAT pump pressurization capability, 
possibly resulting, in case of total engine flame out, to the loss 
of control of the aeroplane.
    To address this unsafe condition, a new design RAT pump shaft 
has been developed with a decreased hexagonal shaft housing depth, 
which increases the hexagonal drive shaft engagement in the impeller 
shaft to carry the impeller torque. Airbus issued Service Bulletin 
(SB) A330-29-3122, SB A340-29-4093 and SB A340-29-5021 to provide 
instructions for in-service replacement of the affected RAT 
hydraulic pumps, or re-identification of the RAT pump and complete 
RAT module, as applicable.
    For the reasons described above, this [EASA] AD requires 
identification and replacement [modification] or re-identification 
of all affected RAT hydraulic pumps on A330 and A340-200/300 
aeroplanes, and replacement [modification] of all affected RAT 
modules on A340-500/ -600 aeroplanes.

    For affected pumps, the required actions also include concurrent 
actions, as applicable, including replacement of the balance weight 
screw, modification of the actuator coil spring, modification of the 
actuator, an inspection of the anti-stall valve for correct 
installation in the RAT pump housing and re-installation if necessary. 
For affected pumps, corrective actions include replacement of the RAT 
hydraulic pump, and re-identification of the part number of the

[[Page 8136]]

RAT module. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0467.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-29-3122, dated October 25, 
2012.
     Airbus Service Bulletin A340-29-4093, dated October 25, 
2012.
    This service information describes procedures for identifying the 
part number, serial number, and standard of the RAT pump, RAT module, 
RAT actuator, and RAT lower gearbox assembly; replacing the balance 
weight screw, modifying the actuator coil spring, modifying the 
actuator, and doing an inspection of the anti-stall valve for correct 
installation; and re-identifying the part numbers of the RAT hydraulic 
pump and RAT module.
    Airbus also issued Service Bulletin A330-29-3126, dated June 12, 
2014; and Service Bulletin A340-29-4097, dated June 12, 2014, which 
describe procedures for identifying the part number and serial number 
of the RAT actuator; modifying the RAT actuators; and re-identifying 
the part numbers of the RAT module.
    In addition, Airbus issued Service Bulletin A340-29-5021, dated 
October 2, 2012; and Service Bulletin A340-29-5025, dated June 16, 
2014, which describe procedures for replacing (modifying) the RAT 
module.
    Hamilton Sundstrand has issued Service Bulletin ERPS06M-29-19, 
dated August 6, 2012, which identifies the serial numbers of the 
suspect hydraulic pump.
    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.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Determination of the Effective Date

    We are superseding AD 2015-26-02 to correct a typographical error 
in the regulatory text. No other changes have been made to AD 2015-26-
02. Therefore, we determined that notice and opportunity for prior 
public comment are unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2016-0467; Directorate 
Identifier 2016-NM-008-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 66 airplanes of U.S. registry.
    We also estimate that it will take about 14 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $78,540, or $1,190 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 18 work-hours and require parts costing up to $427,301, for 
a cost of $428,831 per product. We have no way of determining the 
number of aircraft that might need this action.

Authority for This Rulemaking

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

Regulatory Findings

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2015-26-02, Amendment 39-18350 (80 FR 81174, December 29, 2015), and 
adding the following new AD:

2016-04-01 Airbus: Amendment 39-18395; Docket No. FAA-2016-0467; 
Directorate Identifier 2016-NM-008-AD.

(a) Effective Date

    This AD becomes effective March 4, 2016.

[[Page 8137]]

(b) Affected ADs

    (1) This AD replaces AD 2015-26-02, Amendment 39-18350 (80 FR 
81174, December 29, 2015).
    (2) This AD affects AD 2012-21-19, Amendment 39-17235 (77 FR 
65812, October 31, 2012); and AD 2012-21-20, Amendment 39-17236 (77 
FR 65799, October 31, 2012).

(c) Applicability

    This AD applies to all Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD, all 
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Model A340-211, -212, -213, -311, -312, -313, -541, and -642 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 29, Hydraulic 
Power.

(e) Reason

    This AD was prompted by a report indicating that, during a 
production flight test, the ram air turbine (RAT) did not pressurize 
the green hydraulic system. We are issuing this AD to prevent loss 
of the impeller function and RAT pump pressurization capability, 
which, if preceded by a total engine flame-out, could result in loss 
of control of the airplane.

(f) Compliance

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

(g) Identification of RAT Components

    For Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; 
and Model A340-211, -212, -213, -311, -312, and -313 airplanes: 
Except as provided by paragraph (i) of this AD, within 36 months 
after the effective date of this AD, identify the part number, 
serial number, and standard (through the mod-dots) of the RAT pump, 
RAT module, RAT actuator, and RAT lower gearbox assembly, in 
accordance with the Accomplishment Instructions of the applicable 
Airbus service information specified in paragraphs (g)(1) and (g)(2) 
of this AD. A review of airplane maintenance records is acceptable 
in lieu of this identification if the part number, serial number, 
and standard can be conclusively determined from that review.
    (1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes: Airbus Service Bulletin A330-29-3122, dated October 25, 
2012.
    (2) For Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes: Airbus Service Bulletin A340-29-4093, dated October 25, 
2012.

(h) Corrective and Concurrent Actions

    If the serial number of the RAT hydraulic pump is included in 
table 7, ``Suspect Hydraulic Pump Serial Numbers,'' of Hamilton 
Sundstrand Service Bulletin ERPS06M-29-19, dated August 6, 2012: 
Within 36 months after the effective date of this AD, do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of the applicable Airbus service information specified 
in paragraphs (g)(1) and (g)(2) of this AD. Prior to or concurrently 
with doing the corrective actions required by this paragraph, do the 
actions specified in paragraphs (h)(1) through (h)(4) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-29-3122, dated October 25, 2012 (for Model A330-200, -
200 Freighter, and -300 series airplanes); or Airbus Service 
Bulletin A340-29-4093, dated October 25, 2012 (for Airbus Model 
A340-211, -212, -213, -311, -312, and -313 airplanes).
    (1) Replace the balance weight screw.
    (2) Modify the actuator coil spring.
    (3) Modify the actuator.
    (4) Do a general visual inspection of the anti-stall valve for 
correct installation in the RAT pump housing, and if any incorrect 
installation is found, before further flight, correctly install the 
anti-stall valve.

(i) Exception to Service Information Specifications

    Airbus Service Bulletin A330-29-3122, dated October 25, 2012 
(for Model A330-200, -200 Freighter, and -300 series airplanes), 
refers to Hamilton Sundstrand Service Bulletin ``EPRPS06M-29-13'' as 
an additional source of guidance for doing certain actions required 
by paragraph (h) of this AD. The first ``P'' in the citation should 
have been omitted; the correct reference is to Hamilton Sundstrand 
Service Bulletin ``ERPS06M-29-13.''

(j) Re-Identification of Part Numbers

    If the serial number of the RAT hydraulic pump is not included 
in table 7, ``Suspect Hydraulic Pump Serial Numbers,'' of Hamilton 
Sundstrand Service Bulletin ERPS06M-29-19, dated August 6, 2012: 
Within 36 months after the effective date of this AD, re-identify 
the part numbers of the RAT hydraulic pump and RAT module, in 
accordance with the Accomplishment Instructions of the applicable 
Airbus service information specified in paragraphs (g)(1) and (g)(2) 
of this AD.

(k) Service Information for Optional Actions

    Accomplishment of the actions required by paragraphs (g), (h), 
and (j) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-29-3126, dated June 12, 
2014; or Airbus Service Bulletin A340-29-4097, dated June 12, 2014, 
as applicable, constitutes compliance with the requirements of 
paragraphs (g), (h), and (j) of this AD.

(l) RAT Module Replacement (Modification)

    For Airbus Model A340-541 and -642 airplanes having RAT module 
part number (P/N) 772722D, 772722E, 772722F, or 772722G: Within 36 
months after the effective date of this AD, replace (modify) the RAT 
module, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A340-29-5021, dated October 2, 2012. As an option, 
accomplishment of the RAT module replacement (modification), in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A340-29-5025, dated June 16, 2014, constitutes compliance 
with the requirement of this paragraph.

(m) Exception to Paragraphs (g), (h), and (j) of This AD

    The actions required by paragraphs (g), (h), and (j) of this AD 
are not required for airplanes on which Airbus Modification 202537 
was embodied in production, provided it can be determined that, 
since the airplane's first flight, no RAT hydraulic pump or RAT 
module having a part number identified in paragraph (o) of this AD 
is installed on that airplane.

(n) Terminating Action for Certain Requirements of Other ADs

    (1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and Model A340-211, -212, -213, -311, -312, and -313 
airplanes: Accomplishment of the actions required by paragraphs (g), 
(h), and (j) of this AD constitutes compliance with the requirements 
of paragraphs (g)(1) and (g)(2) of AD 2012-21-19, Amendment 39-17235 
(77 FR 65812, October 31, 2012); and paragraphs (g)(1) and (g)(2) of 
AD 2012-21-20, Amendment 39-17236 (77 FR 65799, October 31, 2012).
    (2) For Airbus Model A340-541 and -642 airplanes: Accomplishment 
of the actions required by paragraph (l) of this AD constitutes 
compliance with the requirements of paragraphs (h)(1) and (h)(2) of 
AD 2012-21-20, Amendment 39-17236 (77 FR 65799, October 31, 2012).

(o) Parts Installation Prohibition

    (1) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and A340-211, -212, -213, -311, -312, and -313 airplanes: 
After modification of the RAT module as required by paragraph (h) of 
this AD, no person may install any complete RAT module having a part 
number identified in paragraph (o)(1)(i) of this AD, or any RAT 
hydraulic pump having the part number identified in paragraph 
(o)(1)(ii) of this AD, on any airplane.
    (i) RAT module P/N 766351, 768084, 770379, 770952, 770952A, 
770952B, 1702934, 1702934A, or 1702934B.
    (ii) RAT hydraulic pump P/N 5909522 (Parker P/N 4207902).
    (2) For Airbus Model A340-541 and -642 airplanes: After 
modification of the RAT module as required by paragraph (l) of this 
AD, no person may install any complete RAT module having P/N 
772722D, 772722E, 772722F, or 772722G, on any airplane.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as

[[Page 8138]]

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 the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(q) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2013-0274, dated November 15, 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-2016-0467.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
February 2, 2016 (80 FR 81174, December 29, 2015).
    (i) Airbus Service Bulletin A330-29-3122, dated October 25, 
2012.
    (ii) Airbus Service Bulletin A330-29-3126, dated June 12, 2014.
    (iii) Airbus Service Bulletin A340-29-4093, dated October 25, 
2012.
    (iv) Airbus Service Bulletin A340-29-4097, dated June 12, 2014.
    (v) Airbus Service Bulletin A340-29-5021, dated October 2, 2012.
    (vi) Airbus Service Bulletin A340-29-5025, dated June 16, 2014.
    (vii) Hamilton Sundstrand Service Bulletin ERPS06M-29-19, dated 
August 6, 2012.
    (4) For Airbus 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.
    (5) For Hamilton Sundstrand service information identified in 
this AD, contact Hamilton Sundstrand, Technical Publications, Mail 
Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125-
7002; telephone 860-654-3575; fax 860-998-4564; email 
tech.solutions@hs.utc.com; Internet http://www.hamiltonsundstrand.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03215 Filed 2-17-16; 8:45 am]
BILLING CODE 4910-13-P