Airworthiness Directives; Airbus Airplanes, 9374-9379 [2016-03699]

Download as PDF 9374 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules (m) Terminating Action Accomplishment of the actions required by paragraphs (k) and (l) of this AD terminate the requirements of paragraphs (g) and (i) of this AD. (n) Parts Installation Prohibition As of the effective date of this AD, no person may install or reinstall any barrel nut P/N SL4081C14SP1 at the forward engine mount assembly on any airplane, and only P/ N SL4750NA may be installed. (o) New Exceptions to Service Information Specifications (1) Where Boeing Special Attention Service Bulletin 747–71–2332, Revision 1, dated May 28, 2015, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Special Attention Service Bulletin 747–71–2332, Revision 1, dated May 28, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (p) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (l) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (r) of this AD. rmajette on DSK2TPTVN1PROD with PROPOSALS (q) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 747–71–2332, dated May 30, 2014, which is not incorporated by reference in this AD. (r) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (s)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2013–24–12 are approved as AMOCs for the corresponding provisions of this AD. (5) Except as required by paragraph (o)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (r)(5)(i) and (r)(5)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (s) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6428; fax: 425–917–6590; email: Nathan.p.weigand@faa.gov. (2) For service information identified in this AD, 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. Issued in Renton, Washington, on February 15, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–03690 Filed 2–24–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–3701; Directorate Identifier 2015–NM–015–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Notice of proposed rulemaking (NPRM). ACTION: We propose to supersede Airworthiness Directive (AD) 2013–25– 08, for all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200 and –300 series airplanes. AD 2013–25–08 currently requires a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installation of new lock wire, and corrective actions if needed. Since we issued AD 2013–25–08, Airbus has developed an improved check valve. This proposed AD would add airplanes to the applicability, and require modifying the green, blue and yellow high pressure hydraulic manifolds by replacing certain check valves with improved check valves, which would terminate the repetitive inspections required by this proposed AD. We are proposing this AD to detect and correct hydraulic check valve loosening; loosened valves could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane. SUMMARY: We must receive comments on this proposed AD by April 11, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on DATES: E:\FR\FM\25FEP1.SGM 25FEP1 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 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–2016– 3701; 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: rmajette on DSK2TPTVN1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–3701; Directorate Identifier 2015–NM–015–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 On November 26, 2013, we issued AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013) (‘‘AD 2013–25–08’’). AD 2013–25–08 requires actions intended to address an unsafe condition on all Airbus Model A330– 200 and –300 series airplanes; and Model A340–200 and –300 series airplanes. Since we issued AD 2013–25–08, which superseded AD 2009–24–09 Amendment 39–16068 (74 FR 62208, November 27, 2009), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 issued EASA Airworthiness Directive 2015–0009, dated January 16, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states: An A330 operator experienced a Yellow hydraulic circuit low level due to a loose check valve, Part Number (P/N) CAR401. During the inspection on the other two hydraulic systems, the other three check valves P/N CAR401 were also found to be loose with their lock wire broken in two instances. Airbus A340 aeroplanes are also equipped with P/N CAR401 high pressure manifold check valves. Additional cases of P/N CAR401 check valve loosening have been reported on aeroplanes having accumulated more than 1,000 flight cycles (FC). The check valve fitted on the Yellow hydraulic system is more affected, due to additional system cycles induced by cargo door operation. This condition, if not detected and corrected, could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the aeroplane. To address this unsafe condition, EASA issued Emergency AD 2009–0223–E (http:// ad.easa.europa.eu/blob/easa_ad_2009_ 0223E_superseded.pdf/EAD_2009-0223-E_1) [which corresponds to FAA AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)] to require an inspection programme to detect any check valve loosening and, if necessary, to apply the applicable corrective actions. EASA AD 2010–0145 (http:// ad.easa.europa.eu/blob/easa_ad_ 2010_0145_Superseded.pdf/AD_2010-0145 _1), which superseded EASA EAD 2009– 0223–E retaining its requirements, was issued to expand the applicability to the newly certified models A330–223F and A330–243F. Prompted by further reported in-service events of check valve P/N CAR401 loosening before reaching the threshold of 700 FC, EASA AD 2011–0139 (http:// ad.easa.europa.eu/blob/easa_ad_ 2011_0139_superseded.pdf/AD_2011-0139 _1), which superseded EASA AD 2010–0145, retaining its requirements, was issued to: —extend the requirement to identify the P/ N CAR401 check valves to all aeroplanes, and —reduce the inspection threshold for aeroplanes fitted with check valve P/N CAR401, either installed in production through Airbus modification 54491, or installed in service through Airbus Service Bulletin (SB) A330–29–3101 or Airbus SB A340–29–4078. EASA AD 2012–0070 (http:// ad.easa.europa.eu/blob/easa_ad_2012_0070_ Correction_superseded.pdf/AD_2012-0070 _1), which superseded EASA AD 2011–0139, retaining its requirements, was issued to require an increased torque value of the check valve tightening and High Pressure (HP) manifold re-identification. Since EASA AD 2012–0070 was issued, additional in-service events have been reported on aeroplanes fitted with check PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 9375 valves on which the increased torque value had been applied. Based on those events, it has been concluded that the action to retorque the check valves with an increased value is not a satisfactory terminating action for addressing the issue of those check valves. To address that, EASA issued AD 2012–0244, which partially retained the requirements of EASA AD 2012–0070, which was superseded. Additionally, for aeroplanes equipped with P/N CAR401 on which the increased torque value had been applied, EASA AD 2012–0244 required repetitive inspections of the check valves and HP manifolds. Finally, EASA AD 2012–0244 also required application of a lower torque value when a check valve P/N CAR401 is installed on an aeroplane. Note: The reporting and the torque value increase requirements for check valves P/N CAR401 of EASA AD 2012–0070 were no longer part of EASA AD 2012–0244. EASA AD was revised to clarify which actions are required for P/N CAR401 check valves, depending on applied (or not) torque value. Since EASA AD 2012–0244R1 (http:// ad.easa.europa.eu/blob/easa_ad_ 2012_0244_R1_superseded.pdf/AD_20120244R1_1) was issued, Airbus developed an improved check valve P/N CAR402, which is embodied in production through Airbus modification 203972, and in service through associated Airbus SB A330–29–3125, or Airbus SB A340–29–4096, as applicable to aeroplane type. In addition, these SBs provide instructions about the torque value (between 230 and 250 Nm) and reidentification of HP manifolds after check valve P/N CAR402 installation. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2012–0244R1, which is superseded, and requires the installation of check valves P/N CAR402 as terminating action to the repetitive inspections [and adds airplanes to the applicability]. 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–2016– 3701. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–29–3125, Revision 01, including Appendixes 01 and 02, dated July 30, 2015; and Service Bulletin A340–29– 4096, Revision 01, including Appendixes 01 and 02, dated July 30, 2015. This service information describes procedures for modifying the green, blue, and yellow high pressure hydraulic manifolds by replacing each check valve having part number (P/N) CAR401 with an improved check valve having P/N CAR402. 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. E:\FR\FM\25FEP1.SGM 25FEP1 9376 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 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. rmajette on DSK2TPTVN1PROD with PROPOSALS Explanation of a Certain Alternative Method of Compliance (AMOC) Paragraph (t)(1)(iii) of this proposed AD states that AMOC ANM–116–14– 429 is not approved as an AMOC for the corresponding provisions of this AD. This AMOC defines a terminating action when Airbus Modification 203972 is introduced in production or when the Airbus Service Bulletin A330–29–3125, dated August 8, 2014, is embodied in service. This proposed AD will exclude from the applicability airplanes with Airbus Modification 203972 and will mandate actions in accordance with Airbus Service Bulletin A330–29–3125, Revision 01, including Appendixes 01 and 02, dated July 30, 2015. Costs of Compliance We estimate that this proposed AD affects 88 airplanes of U.S. registry. The actions required by AD 2013–25– 08, and retained in this proposed AD take about 10 work-hours per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that are required by AD 2013–25–08 is $850 per product. We also estimate that it would take about 32 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 $239,360, or $2,720 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. We have no way of determining the number of aircraft that might need these actions. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 Authority for This Rulemaking § 39.13 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. ■ Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), and adding the following new AD: Airbus: Docket No. FAA–2016–3701; Directorate Identifier 2015–NM–015–AD. (a) Comments Due Date We must receive comments by April 11, 2016. (b) Affected ADs This AD replaces AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013). (c) Applicability This AD applies to Airbus airplanes, certificated in any category, as identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; all manufacturer serial numbers except those on which Airbus modification 203972 has been embodied in production. (2) Model A340–211, –212, –213, –311, –312, and –313 airplanes; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic power. (e) Reason This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to detect and correct hydraulic check valve loosening, which could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. Except for Model A330–223F and A330–243F airplanes: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD. (1) For airplanes that do not have Airbus Modification 54491 embodied in production, or Airbus Service Bulletin A330–29–3101 or Airbus Service Bulletin A340–29–4078 embodied in service: Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), whichever occurs first, inspect the check valves on the blue, green, and yellow hydraulic systems to identify their part numbers (P/Ns), in accordance with the instructions of Airbus All Operators Telex (AOT) A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 E:\FR\FM\25FEP1.SGM 25FEP1 rmajette on DSK2TPTVN1PROD with PROPOSALS Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules (for Model A340–200 and –300 series airplanes). Accomplishment of the inspection required by paragraph (h) of this AD terminates the requirements of this paragraph. (i) If check valves having P/N CAR401 are installed on all three hydraulic systems, before further flight, do the actions specified in paragraph (g)(2)(i) of this AD. After accomplishing the actions required by paragraph (g)(2)(i) of this AD, do the actions specified in paragraphs (g)(2)(ii) and (g)(2)(iii) of this AD at the applicable compliance times specified in those paragraphs. Accomplishment of the inspection required by paragraph (i) of this AD terminates the requirements of this paragraph. (ii) If check valves having P/N CAR401 are not installed on all three hydraulic systems, no further action is required by this paragraph until any check valve having P/N CAR400 is replaced with a check valve having P/N CAR401. If any check valve having P/N CAR400 is replaced by a check valve having P/N CAR401, before further flight, do the inspection specified in paragraph (g)(1) of this AD to determine if all three hydraulic systems are equipped with check valves having P/N CAR401. Accomplishment of the inspection required by paragraph (h) of this AD terminates the requirements of this paragraph. (2) For airplanes on which Airbus Modification 54491 was embodied in production, or Airbus Service Bulletin A330– 29–3101; or Airbus Service Bulletin A340– 29–4078 was embodied in service, do the actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Except as required by paragraph (g)(1)(i) of this AD, at the applicable times specified in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of this AD, as applicable: Do the inspection program (detailed inspection of the lock wire for presence and integrity, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) on yellow and blue high pressure manifolds, install new lock wires, and do all applicable corrective actions, in accordance with the instructions of paragraph 4.1.1 of Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Airbus Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Accomplishment of the inspection required by paragraph (h)(1) of this AD terminates the requirements of this paragraph. (A) For airplanes on which Airbus Modification 54491 has been embodied in production: At the later of the times specified in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) of this AD. (1) Before the accumulation of 1,000 total flight cycles since first flight but no earlier than the accumulation of 700 total flight cycles since first flight. (2) Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), whichever occurs first. VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 (B) For airplanes on which Airbus Service Bulletin A330–29–3101 or A340–29–4078 was embodied in service: At the later of the times specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this AD. (1) Within 1,000 flight cycles since the embodiment of Airbus Service Bulletin A330–29–3101 or A340–29–4078 but no earlier than 700 flight cycles after the embodiment of Airbus Service Bulletin A330–29–3101 or A340–29–4078. (2) Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), whichever occurs first. (ii) Within 900 flight hours after accomplishment of paragraph (g)(2)(i) of this AD, do the inspection program (detailed inspection of the lock wire for presence and integrity, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) and install a new lock wire on the green high pressure manifold; and do an inspection (detailed inspection for traces of seepage or black deposits, and detailed inspection to determine alignment of the check valve and manifold) on the yellow and blue high pressure manifolds, and do all applicable corrective actions; in accordance with the instructions of paragraph 4.1.2 of Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Accomplishment of the inspection program required by paragraph (i) of this AD terminates the requirements of this paragraph. (iii) Within 900 flight hours after accomplishment of paragraph (g)(2)(ii) of this AD, and thereafter at intervals not to exceed 900 flight hours, do the inspection program (detailed inspection for traces of seepage or black deposits, and detailed inspection to determine alignment of the check valve and manifold) on the green, yellow, and blue high pressure manifolds, and do all applicable corrective actions, in accordance with the instructions of paragraph 4.1.3 of Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330–200 and –300 series airplanes); or AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Accomplishment of the inspection program required by paragraph (i) of this AD terminates the requirements of this paragraph. (h) Retained Inspection, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013, with no changes. For airplanes equipped with check valves having P/N CAR400; and for airplanes equipped with check valves having P/N CAR401, except for airplanes on which Airbus Modification 201384 has been embodied during production, or on which Airbus Service Bulletin A330–29–3119 (for Model A330–200, –200F, and –300 series airplanes) PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 9377 or Airbus Service Bulletin A340–29–4091 (for Model A340–200 and –300 series airplanes) has been embodied in service: Within 900 flight hours after January 31, 2014 (the effective date of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013)), inspect the check valves on the blue, green, and yellow hydraulic systems to identify their part numbers, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F and –300 series airplanes); or Airbus Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011 (for Model A340–200 and –300 series airplanes). Accomplishment of the actions required by this paragraph terminates the requirements specified in paragraphs (g)(1) and (g)(1)(ii) of this AD. (1) If check valves having P/N CAR401 are installed on all three hydraulic systems: Before further flight, do the inspection program (detailed inspection for red mark presence and alignment integrity of the check valve and manifold, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) on yellow and blue high pressure manifolds, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011 (for Model A340–200 and –300 series airplanes). Accomplishment of the actions required by this paragraph terminates the requirements specified in paragraph (g)(2)(i) of this AD. (2) If check valves having P/N CAR401 are not installed on all three hydraulic systems, no further action is required by this paragraph until any check valve having P/N CAR400 is replaced with a check valve having P/N CAR401. If any check valve having P/N CAR400 is replaced by a check valve having P/N CAR401: Before further flight after such replacement, do the actions specified in paragraph (h) of this AD, to determine if all three hydraulic systems are equipped with check valves having P/N CAR401. If check valves having P/N CAR401 are installed on all three hydraulic systems: Before further flight, do the actions specified in paragraphs (h)(1) and (i) of this AD. (i) Retained Repetitive Inspection Program and Corrective Actions, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. Within 900 flight hours after accomplishment of paragraph (h)(1) of this AD, do the inspection program (detailed inspection for red mark presence and alignment integrity of the check valve and manifold, a detailed inspection for traces of seepage or black deposits, and an inspection for proper torque) on the green, yellow, and blue system check valves, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); E:\FR\FM\25FEP1.SGM 25FEP1 9378 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules or Airbus Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011 (for Model A340–200 and –300 series airplanes). Do all applicable corrective actions before further flight. Repeat the inspection program thereafter at intervals not to exceed 900 flight hours. Accomplishment of the actions required by this paragraph terminates the requirements specified in paragraphs (g)(1)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (j) Retained Repetitive Inspection for Certain Airplanes, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. For airplanes equipped with check valves having P/N CAR401 and on which Airbus Modification 201384 has been embodied during production, or on which Airbus Service Bulletin A330–29– 3119 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Service Bulletin A340–29–4091 (for Model A340–200 and –300 series airplanes) has been embodied in service: Within 1,000 flight hours after January 31, 2014 (the effective date of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013)), do a general visual inspection of the green, yellow, and blue high pressure manifolds and check valves having P/N CAR401 for any sign of rotation of the check valve head, and for any signs of hydraulic fluid leakage or seepage (including black deposits), in accordance with the instructions of Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. Repeat the inspection thereafter at interval not to exceed 900 flight hours. (k) Retained Corrective Action for Certain Airplanes, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. If, during any inspection required by paragraph (j) of this AD, any sign of rotation of the check valve head is found, or any sign of hydraulic fluid leakage or seepage (including black deposits) is found: Before further flight, do all applicable corrective actions, in accordance with the instructions of Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. rmajette on DSK2TPTVN1PROD with PROPOSALS (l) Retained Provisions Regarding Terminating Action, With No Changes This paragraph restates the provisions of paragraph (l) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. Accomplishment of the corrective actions required by this AD does not constitute terminating action for the repetitive inspections required by this AD. (m) Retained Replacement Check Valve Torque Value, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. As of January 31, 2014 (the effective date of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013)), at each replacement of a check valve with a check VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 valve having P/N CAR401, apply a torque of 141 to 143 newton meter (N.m) (103.98 to 105.45 pounds-foot (lbf.ft)) during installation. (n) Retained Credit for Previous Actions, With No Changes This paragraph restates the provisions of paragraph (n) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. (1) This paragraph provides credit for actions required by paragraph (g)(2)(i) of this AD, if those actions were performed before December 14, 2009 (the effective date of AD 2009–24–09, Amendment 39–16068 (74 FR 62208, November 27, 2009)), using the applicable service information specified in paragraphs (n)(1)(i) and (n)(1)(ii) of this AD. (i) Airbus AOT A330–29A3111, dated September 2, 2009 (for Model A330–200 and -300 series airplanes), which is not incorporated by reference in this AD. (ii) Airbus AOT A340–29A4086, dated September 2, 2009 (for Model A340–200 and -300 series airplanes), which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before January 31, 2014 (the effective date of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013)) using the applicable service information specified in paragraphs (n)(2)(i) through (n)(2)(iv) of this AD. (i) Airbus AOT A330–29A3111, dated September 2, 2009 (for Model A330–200 and –300 series airplanes), which is not incorporated by reference in this AD. (ii) Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009 (for Model A330– 200 and –300 series airplanes). (iii) Airbus AOT A340–29A4086, dated September 2, 2009, (for Model A340–200 and –300 series airplanes), which is not incorporated by reference in this AD. (iv) Airbus AOT A340–29A4086, Revision 1, dated October 8, 2009 (for Model A340– 200 and –300 series airplanes). (o) Retained Provisions for Reporting, With No Changes This paragraph restates the provisions of paragraph (o) of AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), with no changes. Although the service information specified in paragraphs (o)(1) through (o)(5) of this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. (1) Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. (2) Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011. (3) Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011. (4) Airbus AOT A330–29A3111, Revision 1, dated October 8, 2009. (5) Airbus AOT A340–29A4086, Revision 1, dated October 8, 2009. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 (p) New Requirement of This AD: Modify Hydraulic Systems Within 36 months after the effective date of this AD, modify the green, blue, and yellow high pressure hydraulic manifolds by replacing each check valve having P/N CAR401 with an improved check valve having P/N CAR402, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–29–3125, Revision 01, including Appendixes 01 and 02, dated July 30, 2015; or Airbus Service Bulletin A340– 29–4096, Revision 01, including Appendixes 01 and 02, dated July 30, 2015; as applicable. (q) New Requirement of This AD: Repetitive Inspection Terminating Action Modification of an airplane, as required by paragraph (p) of this AD, constitutes terminating action for the repetitive inspections required by this AD. (r) New Requirement of This AD: Parts Installation Limitations (1) For an airplane that, as of the effective date of this AD, has a check valve having P/ N CAR401 installed, after modification of an airplane as required by paragraph (p) of this AD, no person may install a check valve having P/N CAR401, on that airplane. (2) For an airplane that does not have a check valve having P/N CAR401 installed, as of the effective date of this AD, no person may install a check valve having P/N CAR401, on that airplane. (s) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (p) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330–29–3125, dated August 8, 2014; or Airbus Service Bulletin A340–29–4096, dated August 8, 2014; as applicable; which are not incorporated by reference in this AD. (t) 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 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. (i) 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. (ii) AMOC ANM–116–14–180 R1, dated February 21, 2014, is approved as an AMOC for the corresponding provisions of this AD. E:\FR\FM\25FEP1.SGM 25FEP1 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules (iii) AMOC ANM–116–14–429, dated September 25, 2014, is not approved as an AMOC for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. rmajette on DSK2TPTVN1PROD with PROPOSALS (u) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0009, dated January 16, 2015, 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–2016–3701. (2) Service information identified in this AD that is not incorporated by reference may be obtained at 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. (3) 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 February 15, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–03699 Filed 2–24–16; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 DEPARTMENT OF THE TREASURY Internal Revenue Service [REG–150349–12] RIN 1545–BL39 Amendments to the Low-Income Housing Credit Compliance-Monitoring Regulations Internal Revenue Service (IRS), Treasury. ACTION: Notice of proposed rulemaking by cross-reference to temporary regulations. AGENCY: In the Rules and Regulations section of this issue of the Federal Register, the IRS is issuing final and temporary regulations concerning the compliance-monitoring duties of a State or local housing credit agency (Agency) for purposes of the low-income housing credit. The final and temporary regulations revise and clarify certain rules relating to the requirements to conduct physical inspections and review low-income certifications and other documentation. The text of the temporary regulations also serves as the text of these proposed regulations. DATES: Comments and requests for a public hearing must be received by May 25, 2016. ADDRESSES: Send submissions to: CC:PA:LPD:PR (REG–150349–12), room 5203, Internal Revenue Service, P.O. Box 7604, Ben Franklin Station, Washington, DC 20044. Submissions may be hand delivered Monday through Friday between the hours of 8 a.m. and 4 p.m. to: CC:PA:LPD:PR (REG–150349– 12), Courier’s Desk, Internal Revenue Service, 1111 Constitution Avenue NW., Washington, DC. Submissions may also be sent electronically via the Federal eRulemaking Portal at www.regulations.gov (IRS REG–150349– 12). FOR FURTHER INFORMATION CONTACT: Concerning the regulations, Jian H. Grant, (202) 317–4137, and Martha M. Garcia, (202) 317–6853 (not toll-free numbers); concerning submission of comments, the hearing, and/or to be placed on the building access list to attend the hearing, Oluwafunmilayo Taylor at (202) 317–6901 (not a toll-free number). SUPPLEMENTARY INFORMATION: SUMMARY: Background Final and temporary regulations in the Rules and Regulations section of this issue of the Federal Register amend the Income Tax Regulations (26 CFR part 1) Frm 00017 Fmt 4702 Sfmt 4702 relating to section 42 and serve as the text for these proposed regulations. Special Analyses 26 CFR Part 1 PO 00000 9379 Certain IRS regulations, including this one, are exempt from the requirements of Executive Order 12866, as supplemented and reaffirmed by Executive Order 13563. Therefore, a regulatory assessment is not required. It also has been determined that section 553(b) of the Administrative Procedure Act (5 U.S.C. chapter 5) does not apply to these regulations, and because the regulations do not impose a collection of information on small entities, the Regulatory Flexibility Act (5 U.S.C. chapter 6) does not apply. Pursuant to section 7805(f) of the Internal Revenue Code, this notice of proposed rulemaking will be submitted to the Chief Counsel for Advocacy of the Small Business Administration for comment on their impact on small business. Comments and Requests for Public Hearing Before these proposed regulations are adopted as final regulations, consideration will be given to any comments that are submitted timely to the IRS as prescribed in this preamble under the ‘‘ADDRESSES’’ heading. The Treasury Department and the IRS request comments on all aspects of the proposed rules. All comments will be available at www.regulations.gov or upon request. A public hearing will be scheduled if requested in writing by any person that timely submits written comments. If a public hearing is scheduled, notice of the date, time, and place for the public hearing will be published in the Federal Register. Drafting Information The principal authors of these regulations are Jian H. Grant and Martha M. Garcia, Office of the Associate Chief Counsel (Passthroughs and Special Industries). However, other personnel from the IRS and the Treasury Department participated in their development. List of Subjects in 26 CFR Part 1 Income taxes, Reporting and recordkeeping requirements. Proposed Amendments to the Regulations Accordingly, 26 CFR part 1 is proposed to be amended as follows: PART 1—INCOME TAXES Paragraph 1. The authority citation continues to read in part as follows: ■ Authority: 26 U.S.C. 7805 * * * E:\FR\FM\25FEP1.SGM 25FEP1

Agencies

[Federal Register Volume 81, Number 37 (Thursday, February 25, 2016)]
[Proposed Rules]
[Pages 9374-9379]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03699]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3701; Directorate Identifier 2015-NM-015-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 supersede Airworthiness Directive (AD) 2013-25-
08, for all Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes; and Model A340-200 and -300 series airplanes. AD 2013-25-08 
currently requires a repetitive inspection program on certain check 
valves in the hydraulic systems that includes, among other things, 
inspections for lock wire presence and integrity, traces of seepage or 
black deposits, proper torque, alignment of the check valve and 
manifold, installation of new lock wire, and corrective actions if 
needed. Since we issued AD 2013-25-08, Airbus has developed an improved 
check valve. This proposed AD would add airplanes to the applicability, 
and require modifying the green, blue and yellow high pressure 
hydraulic manifolds by replacing certain check valves with improved 
check valves, which would terminate the repetitive inspections required 
by this proposed AD. We are proposing this AD to detect and correct 
hydraulic check valve loosening; loosened valves could result in 
hydraulic leaks, possibly leading to the loss of all three hydraulic 
systems and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by April 11, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on

[[Page 9375]]

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-2016-
3701; 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-2016-3701; 
Directorate Identifier 2015-NM-015-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

    On November 26, 2013, we issued AD 2013-25-08, Amendment 39-17704 
(78 FR 78694, December 27, 2013) (``AD 2013-25-08''). AD 2013-25-08 
requires actions intended to address an unsafe condition on all Airbus 
Model A330-200 and -300 series airplanes; and Model A340-200 and -300 
series airplanes.
    Since we issued AD 2013-25-08, which superseded AD 2009-24-09 
Amendment 39-16068 (74 FR 62208, November 27, 2009), the European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Union, has issued EASA Airworthiness 
Directive 2015-0009, dated January 16, 2015 (referred to after this as 
the Mandatory Continuing Airworthiness Information, or ``the MCAI''), 
to correct an unsafe condition. The MCAI states:

An A330 operator experienced a Yellow hydraulic circuit low level 
due to a loose check valve, Part Number (P/N) CAR401. During the 
inspection on the other two hydraulic systems, the other three check 
valves P/N CAR401 were also found to be loose with their lock wire 
broken in two instances. Airbus A340 aeroplanes are also equipped 
with P/N CAR401 high pressure manifold check valves.
Additional cases of P/N CAR401 check valve loosening have been 
reported on aeroplanes having accumulated more than 1,000 flight 
cycles (FC). The check valve fitted on the Yellow hydraulic system 
is more affected, due to additional system cycles induced by cargo 
door operation.
This condition, if not detected and corrected, could result in 
hydraulic leaks, possibly leading to the loss of all three hydraulic 
systems and consequent loss of control of the aeroplane.
To address this unsafe condition, EASA issued Emergency AD 2009-
0223-E (http://ad.easa.europa.eu/blob/easa_ad_2009_0223E_superseded.pdf/EAD_2009-0223-E_1) [which 
corresponds to FAA AD 2009-24-09, Amendment 39-16068 (74 FR 62208, 
November 27, 2009)] to require an inspection programme to detect any 
check valve loosening and, if necessary, to apply the applicable 
corrective actions.
EASA AD 2010-0145 (http://ad.easa.europa.eu/blob/easa_ad_2010_0145_Superseded.pdf/AD_2010-0145_1), which superseded 
EASA EAD 2009-0223-E retaining its requirements, was issued to 
expand the applicability to the newly certified models A330-223F and 
A330-243F.
Prompted by further reported in-service events of check valve P/N 
CAR401 loosening before reaching the threshold of 700 FC, EASA AD 
2011-0139 (http://ad.easa.europa.eu/blob/easa_ad_2011_0139_superseded.pdf/AD_2011-0139_1), which superseded 
EASA AD 2010-0145, retaining its requirements, was issued to:

--extend the requirement to identify the P/N CAR401 check valves to 
all aeroplanes, and
--reduce the inspection threshold for aeroplanes fitted with check 
valve P/N CAR401, either installed in production through Airbus 
modification 54491, or installed in service through Airbus Service 
Bulletin (SB) A330-29-3101 or Airbus SB A340-29-4078.

EASA AD 2012-0070 (http://ad.easa.europa.eu/blob/easa_ad_2012_0070_Correction_superseded.pdf/AD_2012-0070_1), which 
superseded EASA AD 2011-0139, retaining its requirements, was issued 
to require an increased torque value of the check valve tightening 
and High Pressure (HP) manifold re-identification.
Since EASA AD 2012-0070 was issued, additional in-service events 
have been reported on aeroplanes fitted with check valves on which 
the increased torque value had been applied. Based on those events, 
it has been concluded that the action to re-torque the check valves 
with an increased value is not a satisfactory terminating action for 
addressing the issue of those check valves.
To address that, EASA issued AD 2012-0244, which partially retained 
the requirements of EASA AD 2012-0070, which was superseded. 
Additionally, for aeroplanes equipped with P/N CAR401 on which the 
increased torque value had been applied, EASA AD 2012-0244 required 
repetitive inspections of the check valves and HP manifolds. 
Finally, EASA AD 2012-0244 also required application of a lower 
torque value when a check valve P/N CAR401 is installed on an 
aeroplane.
Note: The reporting and the torque value increase requirements for 
check valves P/N CAR401 of EASA AD 2012-0070 were no longer part of 
EASA AD 2012-0244.
EASA AD was revised to clarify which actions are required for P/N 
CAR401 check valves, depending on applied (or not) torque value.
Since EASA AD 2012-0244R1 (http://ad.easa.europa.eu/blob/easa_ad_2012_0244_R1_superseded.pdf/AD_2012-0244R1_1) was issued, 
Airbus developed an improved check valve P/N CAR402, which is 
embodied in production through Airbus modification 203972, and in 
service through associated Airbus SB A330-29-3125, or Airbus SB 
A340-29-4096, as applicable to aeroplane type. In addition, these 
SBs provide instructions about the torque value (between 230 and 250 
Nm) and re-identification of HP manifolds after check valve P/N 
CAR402 installation.
For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0244R1, which is superseded, and 
requires the installation of check valves P/N CAR402 as terminating 
action to the repetitive inspections [and adds airplanes to the 
applicability].

    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-2016-
3701.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-29-3125, Revision 01, 
including Appendixes 01 and 02, dated July 30, 2015; and Service 
Bulletin A340-29-4096, Revision 01, including Appendixes 01 and 02, 
dated July 30, 2015. This service information describes procedures for 
modifying the green, blue, and yellow high pressure hydraulic manifolds 
by replacing each check valve having part number (P/N) CAR401 with an 
improved check valve having P/N CAR402. 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.

[[Page 9376]]

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.

Explanation of a Certain Alternative Method of Compliance (AMOC)

    Paragraph (t)(1)(iii) of this proposed AD states that AMOC ANM-116-
14-429 is not approved as an AMOC for the corresponding provisions of 
this AD. This AMOC defines a terminating action when Airbus 
Modification 203972 is introduced in production or when the Airbus 
Service Bulletin A330-29-3125, dated August 8, 2014, is embodied in 
service. This proposed AD will exclude from the applicability airplanes 
with Airbus Modification 203972 and will mandate actions in accordance 
with Airbus Service Bulletin A330-29-3125, Revision 01, including 
Appendixes 01 and 02, dated July 30, 2015.

Costs of Compliance

    We estimate that this proposed AD affects 88 airplanes of U.S. 
registry.
    The actions required by AD 2013-25-08, and retained in this 
proposed AD take about 10 work-hours per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2013-25-08 is $850 per product.
    We also estimate that it would take about 32 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 $239,360, or 
$2,720 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD. We have no way of determining the number of aircraft that might 
need these actions.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-3701; Directorate Identifier 2015-NM-
015-AD.

(a) Comments Due Date

    We must receive comments by April 11, 2016.

(b) Affected ADs

    This AD replaces AD 2013-25-08, Amendment 39-17704 (78 FR 78694, 
December 27, 2013).

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, as identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes; all 
manufacturer serial numbers except those on which Airbus 
modification 203972 has been embodied in production.
    (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes; 
all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by multiple reports of hydraulic line check 
valves loosening. We are issuing this AD to detect and correct 
hydraulic check valve loosening, which could result in hydraulic 
leaks, possibly leading to the loss of all three hydraulic systems 
and consequent loss of control of the airplane.

(f) Compliance

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

(g) Retained Inspections, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. Except for Model A330-223F and A330-243F airplanes: 
Do the actions required by paragraphs (g)(1) and (g)(2) of this AD.
    (1) For airplanes that do not have Airbus Modification 54491 
embodied in production, or Airbus Service Bulletin A330-29-3101 or 
Airbus Service Bulletin A340-29-4078 embodied in service: Within 100 
flight cycles or 28 days after December 14, 2009 (the effective date 
of AD 2009-24-09, Amendment 39-16068 (74 FR 62208, November 27, 
2009)), whichever occurs first, inspect the check valves on the 
blue, green, and yellow hydraulic systems to identify their part 
numbers (P/Ns), in accordance with the instructions of Airbus All 
Operators Telex (AOT) A330-29A3111, Revision 1, dated October 8, 
2009 (for Model A330-200 and -300 series airplanes); or AOT A340-
29A4086, Revision 1, dated October 8, 2009

[[Page 9377]]

(for Model A340-200 and -300 series airplanes). Accomplishment of 
the inspection required by paragraph (h) of this AD terminates the 
requirements of this paragraph.
    (i) If check valves having P/N CAR401 are installed on all three 
hydraulic systems, before further flight, do the actions specified 
in paragraph (g)(2)(i) of this AD. After accomplishing the actions 
required by paragraph (g)(2)(i) of this AD, do the actions specified 
in paragraphs (g)(2)(ii) and (g)(2)(iii) of this AD at the 
applicable compliance times specified in those paragraphs. 
Accomplishment of the inspection required by paragraph (i) of this 
AD terminates the requirements of this paragraph.
    (ii) If check valves having P/N CAR401 are not installed on all 
three hydraulic systems, no further action is required by this 
paragraph until any check valve having P/N CAR400 is replaced with a 
check valve having P/N CAR401. If any check valve having P/N CAR400 
is replaced by a check valve having P/N CAR401, before further 
flight, do the inspection specified in paragraph (g)(1) of this AD 
to determine if all three hydraulic systems are equipped with check 
valves having P/N CAR401. Accomplishment of the inspection required 
by paragraph (h) of this AD terminates the requirements of this 
paragraph.
    (2) For airplanes on which Airbus Modification 54491 was 
embodied in production, or Airbus Service Bulletin A330-29-3101; or 
Airbus Service Bulletin A340-29-4078 was embodied in service, do the 
actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and 
(g)(2)(iii) of this AD.
    (i) Except as required by paragraph (g)(1)(i) of this AD, at the 
applicable times specified in paragraphs (g)(2)(i)(A) and 
(g)(2)(i)(B) of this AD, as applicable: Do the inspection program 
(detailed inspection of the lock wire for presence and integrity, a 
detailed inspection for traces of seepage or black deposits, and an 
inspection for proper torque) on yellow and blue high pressure 
manifolds, install new lock wires, and do all applicable corrective 
actions, in accordance with the instructions of paragraph 4.1.1 of 
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for 
Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
Revision 1, dated October 8, 2009 (for Airbus Model A340-200 and -
300 series airplanes). Do all applicable corrective actions before 
further flight. Accomplishment of the inspection required by 
paragraph (h)(1) of this AD terminates the requirements of this 
paragraph.
    (A) For airplanes on which Airbus Modification 54491 has been 
embodied in production: At the later of the times specified in 
paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) of this AD.
    (1) Before the accumulation of 1,000 total flight cycles since 
first flight but no earlier than the accumulation of 700 total 
flight cycles since first flight.
    (2) Within 100 flight cycles or 28 days after December 14, 2009 
(the effective date of AD 2009-24-09, Amendment 39-16068 (74 FR 
62208, November 27, 2009)), whichever occurs first.
    (B) For airplanes on which Airbus Service Bulletin A330-29-3101 
or A340-29-4078 was embodied in service: At the later of the times 
specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this 
AD.
    (1) Within 1,000 flight cycles since the embodiment of Airbus 
Service Bulletin A330-29-3101 or A340-29-4078 but no earlier than 
700 flight cycles after the embodiment of Airbus Service Bulletin 
A330-29-3101 or A340-29-4078.
    (2) Within 100 flight cycles or 28 days after December 14, 2009 
(the effective date of AD 2009-24-09, Amendment 39-16068 (74 FR 
62208, November 27, 2009)), whichever occurs first.
    (ii) Within 900 flight hours after accomplishment of paragraph 
(g)(2)(i) of this AD, do the inspection program (detailed inspection 
of the lock wire for presence and integrity, a detailed inspection 
for traces of seepage or black deposits, and an inspection for 
proper torque) and install a new lock wire on the green high 
pressure manifold; and do an inspection (detailed inspection for 
traces of seepage or black deposits, and detailed inspection to 
determine alignment of the check valve and manifold) on the yellow 
and blue high pressure manifolds, and do all applicable corrective 
actions; in accordance with the instructions of paragraph 4.1.2 of 
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for 
Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
Revision 1, dated October 8, 2009 (for Model A340-200 and -300 
series airplanes). Do all applicable corrective actions before 
further flight. Accomplishment of the inspection program required by 
paragraph (i) of this AD terminates the requirements of this 
paragraph.
    (iii) Within 900 flight hours after accomplishment of paragraph 
(g)(2)(ii) of this AD, and thereafter at intervals not to exceed 900 
flight hours, do the inspection program (detailed inspection for 
traces of seepage or black deposits, and detailed inspection to 
determine alignment of the check valve and manifold) on the green, 
yellow, and blue high pressure manifolds, and do all applicable 
corrective actions, in accordance with the instructions of paragraph 
4.1.3 of Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 
(for Model A330-200 and -300 series airplanes); or AOT A340-29A4086, 
Revision 1, dated October 8, 2009 (for Model A340-200 and -300 
series airplanes). Do all applicable corrective actions before 
further flight. Accomplishment of the inspection program required by 
paragraph (i) of this AD terminates the requirements of this 
paragraph.

(h) Retained Inspection, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013, with 
no changes. For airplanes equipped with check valves having P/N 
CAR400; and for airplanes equipped with check valves having P/N 
CAR401, except for airplanes on which Airbus Modification 201384 has 
been embodied during production, or on which Airbus Service Bulletin 
A330-29-3119 (for Model A330-200, -200F, and -300 series airplanes) 
or Airbus Service Bulletin A340-29-4091 (for Model A340-200 and -300 
series airplanes) has been embodied in service: Within 900 flight 
hours after January 31, 2014 (the effective date of AD 2013-25-08, 
Amendment 39-17704 (78 FR 78694, December 27, 2013)), inspect the 
check valves on the blue, green, and yellow hydraulic systems to 
identify their part numbers, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-29-3111, Revision 02, 
dated June 23, 2011 (for Model A330-200, -200F and -300 series 
airplanes); or Airbus Service Bulletin A340-29-4086, Revision 02, 
dated June 23, 2011 (for Model A340-200 and -300 series airplanes). 
Accomplishment of the actions required by this paragraph terminates 
the requirements specified in paragraphs (g)(1) and (g)(1)(ii) of 
this AD.
    (1) If check valves having P/N CAR401 are installed on all three 
hydraulic systems: Before further flight, do the inspection program 
(detailed inspection for red mark presence and alignment integrity 
of the check valve and manifold, a detailed inspection for traces of 
seepage or black deposits, and an inspection for proper torque) on 
yellow and blue high pressure manifolds, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-29-3111, Revision 02, 
dated June 23, 2011 (for Model A330-200, -200F, and -300 series 
airplanes); or Airbus Service Bulletin A340-29-4086, Revision 02, 
dated June 23, 2011 (for Model A340-200 and -300 series airplanes). 
Accomplishment of the actions required by this paragraph terminates 
the requirements specified in paragraph (g)(2)(i) of this AD.
    (2) If check valves having P/N CAR401 are not installed on all 
three hydraulic systems, no further action is required by this 
paragraph until any check valve having P/N CAR400 is replaced with a 
check valve having P/N CAR401. If any check valve having P/N CAR400 
is replaced by a check valve having P/N CAR401: Before further 
flight after such replacement, do the actions specified in paragraph 
(h) of this AD, to determine if all three hydraulic systems are 
equipped with check valves having P/N CAR401. If check valves having 
P/N CAR401 are installed on all three hydraulic systems: Before 
further flight, do the actions specified in paragraphs (h)(1) and 
(i) of this AD.

(i) Retained Repetitive Inspection Program and Corrective Actions, With 
No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. Within 900 flight hours after accomplishment of 
paragraph (h)(1) of this AD, do the inspection program (detailed 
inspection for red mark presence and alignment integrity of the 
check valve and manifold, a detailed inspection for traces of 
seepage or black deposits, and an inspection for proper torque) on 
the green, yellow, and blue system check valves, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-29-3111, Revision 02, 
dated June 23, 2011 (for Model A330-200, -200F, and -300 series 
airplanes);

[[Page 9378]]

or Airbus Service Bulletin A340-29-4086, Revision 02, dated June 23, 
2011 (for Model A340-200 and -300 series airplanes). Do all 
applicable corrective actions before further flight. Repeat the 
inspection program thereafter at intervals not to exceed 900 flight 
hours. Accomplishment of the actions required by this paragraph 
terminates the requirements specified in paragraphs (g)(1)(i), 
(g)(2)(ii), and (g)(2)(iii) of this AD.

(j) Retained Repetitive Inspection for Certain Airplanes, With No 
Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. For airplanes equipped with check valves having P/N 
CAR401 and on which Airbus Modification 201384 has been embodied 
during production, or on which Airbus Service Bulletin A330-29-3119 
(for Model A330-200, -200F, and -300 series airplanes); or Airbus 
Service Bulletin A340-29-4091 (for Model A340-200 and -300 series 
airplanes) has been embodied in service: Within 1,000 flight hours 
after January 31, 2014 (the effective date of AD 2013-25-08, 
Amendment 39-17704 (78 FR 78694, December 27, 2013)), do a general 
visual inspection of the green, yellow, and blue high pressure 
manifolds and check valves having P/N CAR401 for any sign of 
rotation of the check valve head, and for any signs of hydraulic 
fluid leakage or seepage (including black deposits), in accordance 
with the instructions of Airbus Alert Operators Transmission 
A29L001-12, dated October 11, 2012. Repeat the inspection thereafter 
at interval not to exceed 900 flight hours.

(k) Retained Corrective Action for Certain Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. If, during any inspection required by paragraph (j) 
of this AD, any sign of rotation of the check valve head is found, 
or any sign of hydraulic fluid leakage or seepage (including black 
deposits) is found: Before further flight, do all applicable 
corrective actions, in accordance with the instructions of Airbus 
Alert Operators Transmission A29L001-12, dated October 11, 2012.

(l) Retained Provisions Regarding Terminating Action, With No Changes

    This paragraph restates the provisions of paragraph (l) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. Accomplishment of the corrective actions required 
by this AD does not constitute terminating action for the repetitive 
inspections required by this AD.

(m) Retained Replacement Check Valve Torque Value, With No Changes

    This paragraph restates the requirements of paragraph (m) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. As of January 31, 2014 (the effective date of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013)), at 
each replacement of a check valve with a check valve having P/N 
CAR401, apply a torque of 141 to 143 newton meter (N.m) (103.98 to 
105.45 pounds-foot (lbf.ft)) during installation.

(n) Retained Credit for Previous Actions, With No Changes

    This paragraph restates the provisions of paragraph (n) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes.
    (1) This paragraph provides credit for actions required by 
paragraph (g)(2)(i) of this AD, if those actions were performed 
before December 14, 2009 (the effective date of AD 2009-24-09, 
Amendment 39-16068 (74 FR 62208, November 27, 2009)), using the 
applicable service information specified in paragraphs (n)(1)(i) and 
(n)(1)(ii) of this AD.
    (i) Airbus AOT A330-29A3111, dated September 2, 2009 (for Model 
A330-200 and -300 series airplanes), which is not incorporated by 
reference in this AD.
    (ii) Airbus AOT A340-29A4086, dated September 2, 2009 (for Model 
A340-200 and -300 series airplanes), which is not incorporated by 
reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before 
January 31, 2014 (the effective date of AD 2013-25-08, Amendment 39-
17704 (78 FR 78694, December 27, 2013)) using the applicable service 
information specified in paragraphs (n)(2)(i) through (n)(2)(iv) of 
this AD.
    (i) Airbus AOT A330-29A3111, dated September 2, 2009 (for Model 
A330-200 and -300 series airplanes), which is not incorporated by 
reference in this AD.
    (ii) Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 
(for Model A330-200 and -300 series airplanes).
    (iii) Airbus AOT A340-29A4086, dated September 2, 2009, (for 
Model A340-200 and -300 series airplanes), which is not incorporated 
by reference in this AD.
    (iv) Airbus AOT A340-29A4086, Revision 1, dated October 8, 2009 
(for Model A340-200 and -300 series airplanes).

(o) Retained Provisions for Reporting, With No Changes

    This paragraph restates the provisions of paragraph (o) of AD 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), 
with no changes. Although the service information specified in 
paragraphs (o)(1) through (o)(5) of this AD specifies to submit 
certain information to the manufacturer, this AD does not include 
that requirement.
    (1) Airbus Alert Operators Transmission A29L001-12, dated 
October 11, 2012.
    (2) Airbus Mandatory Service Bulletin A330-29-3111, Revision 02, 
dated June 23, 2011.
    (3) Airbus Mandatory Service Bulletin A340-29-4086, Revision 02, 
dated June 23, 2011.
    (4) Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009.
    (5) Airbus AOT A340-29A4086, Revision 1, dated October 8, 2009.

(p) New Requirement of This AD: Modify Hydraulic Systems

    Within 36 months after the effective date of this AD, modify the 
green, blue, and yellow high pressure hydraulic manifolds by 
replacing each check valve having P/N CAR401 with an improved check 
valve having P/N CAR402, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-29-3125, Revision 01, 
including Appendixes 01 and 02, dated July 30, 2015; or Airbus 
Service Bulletin A340-29-4096, Revision 01, including Appendixes 01 
and 02, dated July 30, 2015; as applicable.

(q) New Requirement of This AD: Repetitive Inspection Terminating 
Action

    Modification of an airplane, as required by paragraph (p) of 
this AD, constitutes terminating action for the repetitive 
inspections required by this AD.

(r) New Requirement of This AD: Parts Installation Limitations

    (1) For an airplane that, as of the effective date of this AD, 
has a check valve having P/N CAR401 installed, after modification of 
an airplane as required by paragraph (p) of this AD, no person may 
install a check valve having P/N CAR401, on that airplane.
    (2) For an airplane that does not have a check valve having P/N 
CAR401 installed, as of the effective date of this AD, no person may 
install a check valve having P/N CAR401, on that airplane.

(s) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(p) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A330-29-3125, dated 
August 8, 2014; or Airbus Service Bulletin A340-29-4096, dated 
August 8, 2014; as applicable; which are not incorporated by 
reference in this AD.

(t) 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 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.
    (i) 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.
    (ii) AMOC ANM-116-14-180 R1, dated February 21, 2014, is 
approved as an AMOC for the corresponding provisions of this AD.

[[Page 9379]]

    (iii) AMOC ANM-116-14-429, dated September 25, 2014, is not 
approved as an AMOC for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(u) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0009, dated January 16, 
2015, 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-2016-3701.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at 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.
    (3) 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 February 15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03699 Filed 2-24-16; 8:45 am]
BILLING CODE 4910-13-P