Airworthiness Directives; Airbus Airplanes, 83648-83653 [2016-25745]

Download as PDF 83648 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations (h) Dispute resolution. A requester seeking to engage in dispute resolution may make a request to the FOIA Public Liaison and/or OGIS by following the procedures set forth online in the FDIC’s FOIA Service Center at http:// www.fdic.gov. (i) * * * (2) A person whose initial request for records under this section, or whose request for a waiver of fees under paragraph (f)(1)(x) of this section, has been denied, either in part or in whole, has the right to appeal the denial to the FDIC’s General Counsel (or designee) within 90 calendar days after receipt of notification of the denial. Appeals of denials of initial requests or for a waiver of fees must be in writing and include any additional information relevant to consideration of the appeal. * * * * * Dated at Washington, DC, this 15th day of November, 2016. By order of the Board of Directors. Federal Deposit Insurance Corporation. Valerie J. Best, Assistant Executive Secretary. [FR Doc. 2016–27961 Filed 11–21–16; 8:45 am] BILLING CODE 6714–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–3701; Directorate Identifier 2015–NM–015–AD; Amendment 39–18689; AD 2016–21–08] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Examining the AD Docket Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding 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 required 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. This new AD removes airplanes from the applicability, and requires modifying sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 the green, blue, and yellow high pressure hydraulic manifolds by replacing certain check valves with improved check valves, which terminates the repetitive inspections required by this AD. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 27, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 27, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 31, 2014 (78 FR 78694, December 27, 2013). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of December 14, 2009 (74 FR 62208, November 27, 2009). ADDRESSES: For 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.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 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–2016–3701. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013) (‘‘AD 2013–25– 08’’). AD 2013–25–08 applied to all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200 and –300 series airplanes. The NPRM published in the Federal Register on February 25, 2016 (81 FR 9374) (‘‘the NPRM’’). The NPRM was prompted by multiple reports of hydraulic line check valves loosening. The NPRM proposed to continue to require 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. The NPRM also proposed to 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 the proposed AD. We are issuing 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. 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 E:\FR\FM\22NOR1.SGM 22NOR1 sradovich on DSK3GMQ082PROD with RULES Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 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 [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, 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, 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, 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 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 was issued, Airbus developed an improved check valve P/N CAR402, which is embodied in production through Airbus modification VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 83649 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 removes airplanes on which Airbus modification 203972 has been embodied from the applicability]. Service Bulletin A330–29–3125, Revision 02, including Appendixes 01 and 02, dated January 21, 2016; or 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. Additionally, we have reformatted paragraph (s) of this AD to improve readability; this change does not affect the intent or requirements of that paragraph. 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. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA’s response to the comment. Support for the NPRM American Airlines (AAL) stated that it operates 24 airplanes that will be affected by the NPRM, and that it agrees with the need to accomplish Airbus Service Bulletin A330–29–3125 on these airplanes. Request To Reference Revised Service Information AAL requested that we revise the NPRM to reference Airbus Service Bulletin A330–29–3125, Revision 02, including Appendixes 01 and 02, dated January 21, 2016. AAL pointed out that this revision includes several corrections in the Accomplishment Instructions. We agree to reference the latest service information in this final rule. Since we issued the NPRM, Airbus has issued Airbus Service Bulletin A330– 29–3125, Revision 03, including Appendixes 01 and 02, dated April 8, 2016; and Service Bulletin A340–29– 4096, Revision 02, including Appendixes 01 and 02, dated April 8, 2016. This service information states that no additional work is required by these revisions for airplanes modified by any previous issue. We have revised paragraph (p) of this AD to reference this revised service information as appropriate sources of service information for accomplishing the actions required by that paragraph. We have also revised paragraph (s) of this AD by adding credit for actions required by paragraph (p) of this AD, if those actions were performed before the effective date of this AD using Airbus PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–29–3125, Revision 03, including Appendixes 01 and 02, dated April 8, 2016; and Service Bulletin A340–29– 4096, Revision 02, including Appendixes 01 and 02, dated April 8, 2016. This service information describes procedures for modifying 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. These documents are distinct since they apply to different airplane models. 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. Costs of Compliance We estimate that this AD affects 88 airplanes of U.S. registry. We estimate the following costs to comply with this AD: The actions required by AD 2013–25– 08, and retained in this 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 were 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 AD. The average labor rate is $85 E:\FR\FM\22NOR1.SGM 22NOR1 83650 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations per work-hour. Based on these figures, we estimate the cost of this 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 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 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 sradovich on DSK3GMQ082PROD with RULES 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. 16:34 Nov 21, 2016 Jkt 241001 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) 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013), and adding the following new AD: ■ 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. VerDate Sep<11>2014 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 2016–21–08 Airbus: Amendment 39–18689; Docket No. FAA–2016–3701; Directorate Identifier 2015–NM–015–AD. (a) Effective Date This AD is effective December 27, 2016. (b) Affected ADs This AD replaces AD 2013–25–08, Amendment 39–17704 (78 FR 78694, December 27, 2013) (‘‘AD 2013–25–08’’). (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; 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. (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, with no changes. Except for Model A330–223F and A330–243F airplanes: Do the actions PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 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) (‘‘AD 2009–24–09’’)), 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 Airbus AOT A340– 29A4086, Revision 1, dated October 8, 2009 (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 Airbus AOT A340–29A4086, Revision 1, dated October 8, E:\FR\FM\22NOR1.SGM 22NOR1 sradovich on DSK3GMQ082PROD with RULES Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 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), whichever occurs first. (B) For airplanes on which Airbus Service Bulletin A330–29–3101 or Airbus Service Bulletin 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 Airbus Service Bulletin A340–29–4078 but no earlier than 700 flight cycles after the embodiment of Airbus Service Bulletin A330–29–3101 or Airbus Service Bulletin A340–29–4078. (2) Within 100 flight cycles or 28 days after December 14, 2009 (the effective date of AD 2009–24–09), 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 Airbus 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 Airbus AOT A340– 29A4086, Revision 1, dated October 8, 2009 (for Model A340–200 and –300 series airplanes). Do all applicable corrective VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 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, 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), 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 Mandatory Service Bulletin A330–29– 3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Mandatory 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 Mandatory Service Bulletin A330–29– 3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Mandatory 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, with no PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 83651 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 Mandatory Service Bulletin A330–29– 3111, Revision 02, dated June 23, 2011 (for Model A330–200, –200F, and –300 series airplanes); or Airbus Mandatory 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, 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), 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, 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, 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. E:\FR\FM\22NOR1.SGM 22NOR1 83652 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations (m) Retained Replacement Check Valve Torque Value, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2013–25–08, with no changes. As of January 31, 2014 (the effective date of AD 2013–25–08), at each replacement of a check valve with a check valve having P/N CAR401, apply a torque of 141 to 143 newton meters (N.m) (103.98 to 105.45 pounds-foot (lbf.ft)) during installation. sradovich on DSK3GMQ082PROD with RULES (n) Retained Credit for Previous Actions, With No Changes This paragraph restates the provisions of paragraph (n) of AD 2013–25–08, 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), 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), 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), which is incorporated by reference in this AD. (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), which is incorporated by reference in this AD. (o) Retained Provisions for Reporting, With No Changes This paragraph restates the provisions of paragraph (o) of AD 2013–25–08, 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. VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 (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 03, including Appendixes 01 and 02, dated April 8, 2016; or Airbus Service Bulletin A340–29– 4096, Revision 02, including Appendixes 01 and 02, dated April 8, 2016; as applicable. (q) New Provision of This AD: Terminating Action for Repetitive Inspections 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 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 the applicable service information specified in paragraphs (s)(1) through (s)(5) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A330–29–3125, dated August 8, 2014. (2) Airbus Service Bulletin A330–29–3125, Revision 01, including Appendixes 01 and 02, dated July 30, 2015. (3) Airbus Service Bulletin A330–29–3125, Revision 02, including Appendixes 01 and 02, dated January 21, 2016. (4) Airbus Service Bulletin A340–29–4096, dated August 8, 2014. (5) Airbus Service Bulletin A340–29–4096, Revision 01, including Appendixes 01 and 02, dated July 30, 2015. (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; PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 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. (ii) AMOC ANM–116–14–180 R1, dated February 21, 2014, is approved as an AMOC for the corresponding provisions of this AD. (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 is available at the addresses specified in paragraphs (v)(6) and (v)(7) of this AD. (v) 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 December 27, 2016. (i) Airbus Service Bulletin A330–29–3125, Revision 03, including Appendixes 01 and 02, dated April 8, 2016. (ii) Airbus Service Bulletin A340–29–4096, Revision 02, including Appendixes 01 and 02, dated April 8, 2016. E:\FR\FM\22NOR1.SGM 22NOR1 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations (4) The following service information was approved for IBR on January 31, 2014 (78 FR 78694, December 27, 2013). (i) Airbus Alert Operators Transmission A29L001–12, dated October 11, 2012. (ii) Airbus Mandatory Service Bulletin A330–29–3111, Revision 02, dated June 23, 2011. (iii) Airbus Mandatory Service Bulletin A340–29–4086, Revision 02, dated June 23, 2011. (5) The following service information was approved for IBR on December 14, 2009 (74 FR 62208, November 27, 2009). (i) Airbus Alert Operators Telex A330– 29A3111, Revision 1, dated October 8, 2009. Only the first page of this document contains the document number, revision level, and date; no other pages of this document contain this information. (ii) Airbus Alert Operators Telex A340– 29A4086, Revision 1, dated October 8, 2009. Only the first page of this document contains the document number, revision level, and date; no other pages of this document contain this information. (6) 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. (7) 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. (8) 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 October 12, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–25745 Filed 11–21–16; 8:45 am] BILLING CODE 4910–13–P We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, and 702), CL–600–2D15 (Regional Jet Series 705), CL–600–2D24 (Regional Jet Series 900), and CL–600–2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that wear and possible leakage of the high-pressure seal in the cylinder of the No. 3 hydraulic system reservoir could occur and cause high hydraulic fluid temperature and/or prevent the system from reaching normal operating pressure. This AD requires repetitive operational checks for wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective December 27, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 27, 2016. DATES: For service information identified in this final rule, contact ˆ Bombardier, Inc., 400 Cote Vertu Road ´ West, Dorval, Quebec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1–514–855–2999; fax 514–855–7401; email ac.yul@aero.bombardier.com; Internet http://www.bombardier.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– 7421. ADDRESSES: DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7421; 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 street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 14 CFR Part 39 [Docket No. FAA–2016–7421; Directorate Identifier 2015–NM–145–AD; Amendment 39–18705; AD 2016–22–16] sradovich on DSK3GMQ082PROD with RULES RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Sep<11>2014 16:34 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 83653 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516–794–5531. 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 certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, and 702), CL–600–2D15 (Regional Jet Series 705), CL–600–2D24 (Regional Jet Series 900), and CL–600–2E25 (Regional Jet Series 1000) airplanes. The NPRM published in the Federal Register on July 1, 2016 (81 FR 43122) (‘‘the NPRM’’). The NPRM was prompted by a determination that wear and possible leakage of the highpressure seal in the cylinder of the No. 3 hydraulic system reservoir could occur and cause high hydraulic fluid temperature and/or prevent the system from reaching normal operating pressure. The NPRM proposed to require repetitive operational checks for wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, and corrective actions if necessary. We are issuing this AD to detect and correct wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, which can result in high hydraulic fluid temperature. High hydraulic fluid temperature combined with a temperature transducer malfunction could result in un-annunciated overheating of the hydraulic system and consequent ignition sources inside the fuel tank, which, combined with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2015–27, dated September 14, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model CL– 600–2C10 (Regional Jet Series 700, 701, and 702), CL–600–2D15 (Regional Jet Series 705), CL–600–2D24 (Regional Jet Series 900), and CL–600–2E25 (Regional Jet Series 1000) airplanes. The MCAI states: E:\FR\FM\22NOR1.SGM 22NOR1

Agencies

[Federal Register Volume 81, Number 225 (Tuesday, November 22, 2016)]
[Rules and Regulations]
[Pages 83648-83653]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25745]


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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; 
Amendment 39-18689; AD 2016-21-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding 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 required 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. This new AD removes 
airplanes from the applicability, and requires modifying the green, 
blue, and yellow high pressure hydraulic manifolds by replacing certain 
check valves with improved check valves, which terminates the 
repetitive inspections required by this AD. This AD was prompted by 
multiple reports of hydraulic line check valves loosening. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective December 27, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 27, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
31, 2014 (78 FR 78694, December 27, 2013).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
December 14, 2009 (74 FR 62208, November 27, 2009).

ADDRESSES: For 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.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 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-
3701.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 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: 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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2013-25-08, Amendment 39-17704 (78 FR 78694, 
December 27, 2013) (``AD 2013-25-08''). AD 2013-25-08 applied to all 
Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and 
Model A340-200 and -300 series airplanes. The NPRM published in the 
Federal Register on February 25, 2016 (81 FR 9374) (``the NPRM''). The 
NPRM was prompted by multiple reports of hydraulic line check valves 
loosening. The NPRM proposed to continue to require 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. The NPRM also proposed to 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 the proposed AD. We are issuing 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.
    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

[[Page 83649]]

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 [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, 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, 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, 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 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 removes airplanes on which 
Airbus modification 203972 has been embodied from 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response to the comment.

Support for the NPRM

    American Airlines (AAL) stated that it operates 24 airplanes that 
will be affected by the NPRM, and that it agrees with the need to 
accomplish Airbus Service Bulletin A330-29-3125 on these airplanes.

Request To Reference Revised Service Information

    AAL requested that we revise the NPRM to reference Airbus Service 
Bulletin A330-29-3125, Revision 02, including Appendixes 01 and 02, 
dated January 21, 2016. AAL pointed out that this revision includes 
several corrections in the Accomplishment Instructions.
    We agree to reference the latest service information in this final 
rule. Since we issued the NPRM, Airbus has issued Airbus Service 
Bulletin A330-29-3125, Revision 03, including Appendixes 01 and 02, 
dated April 8, 2016; and Service Bulletin A340-29-4096, Revision 02, 
including Appendixes 01 and 02, dated April 8, 2016. This service 
information states that no additional work is required by these 
revisions for airplanes modified by any previous issue. We have revised 
paragraph (p) of this AD to reference this revised service information 
as appropriate sources of service information for accomplishing the 
actions required by that paragraph. We have also revised paragraph (s) 
of this AD by adding 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, Revision 02, 
including Appendixes 01 and 02, dated January 21, 2016; or 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. Additionally, we have reformatted paragraph (s) of this AD 
to improve readability; this change does not affect the intent or 
requirements of that paragraph.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-29-3125, Revision 03, 
including Appendixes 01 and 02, dated April 8, 2016; and Service 
Bulletin A340-29-4096, Revision 02, including Appendixes 01 and 02, 
dated April 8, 2016. This service information describes procedures for 
modifying 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. These documents are distinct since they apply 
to different airplane models. 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.

Costs of Compliance

    We estimate that this AD affects 88 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:
    The actions required by AD 2013-25-08, and retained in this 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 were 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 AD. The average labor 
rate is $85

[[Page 83650]]

per work-hour. Based on these figures, we estimate the cost of this 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 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 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 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) 
2013-25-08, Amendment 39-17704 (78 FR 78694, December 27, 2013), and 
adding the following new AD:

2016-21-08 Airbus: Amendment 39-18689; Docket No. FAA-2016-3701; 
Directorate Identifier 2015-NM-015-AD.

(a) Effective Date

    This AD is effective December 27, 2016.

(b) Affected ADs

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

(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; 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.

(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, 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) (``AD 2009-24-09'')), 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 Airbus AOT A340-29A4086, Revision 1, dated 
October 8, 2009 (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 Airbus AOT A340-
29A4086, Revision 1, dated October 8,

[[Page 83651]]

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), whichever occurs first.
    (B) For airplanes on which Airbus Service Bulletin A330-29-3101 
or Airbus Service Bulletin 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 Airbus Service Bulletin A340-29-
4078 but no earlier than 700 flight cycles after the embodiment of 
Airbus Service Bulletin A330-29-3101 or Airbus Service Bulletin 
A340-29-4078.
    (2) Within 100 flight cycles or 28 days after December 14, 2009 
(the effective date of AD 2009-24-09), 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 Airbus 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 Airbus 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, 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), 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 Mandatory Service Bulletin A330-29-3111, Revision 02, dated 
June 23, 2011 (for Model A330-200, -200F, and -300 series 
airplanes); or Airbus Mandatory 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 Mandatory Service Bulletin A330-29-3111, 
Revision 02, dated June 23, 2011 (for Model A330-200, -200F, and -
300 series airplanes); or Airbus Mandatory 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, 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 Mandatory Service Bulletin 
A330-29-3111, Revision 02, dated June 23, 2011 (for Model A330-200, 
-200F, and -300 series airplanes); or Airbus Mandatory 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, 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), 
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, 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, 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.

[[Page 83652]]

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

    This paragraph restates the requirements of paragraph (m) of AD 
2013-25-08, with no changes. As of January 31, 2014 (the effective 
date of AD 2013-25-08), at each replacement of a check valve with a 
check valve having P/N CAR401, apply a torque of 141 to 143 newton 
meters (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, 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), 
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), 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), which is 
incorporated by reference in this AD.
    (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), which is 
incorporated by reference in this AD.

(o) Retained Provisions for Reporting, With No Changes

    This paragraph restates the provisions of paragraph (o) of AD 
2013-25-08, 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 03, 
including Appendixes 01 and 02, dated April 8, 2016; or Airbus 
Service Bulletin A340-29-4096, Revision 02, including Appendixes 01 
and 02, dated April 8, 2016; as applicable.

(q) New Provision of This AD: Terminating Action for Repetitive 
Inspections

    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 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 the applicable service information specified 
in paragraphs (s)(1) through (s)(5) of this AD, which are not 
incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-29-3125, dated August 8, 2014.
    (2) Airbus Service Bulletin A330-29-3125, Revision 01, including 
Appendixes 01 and 02, dated July 30, 2015.
    (3) Airbus Service Bulletin A330-29-3125, Revision 02, including 
Appendixes 01 and 02, dated January 21, 2016.
    (4) Airbus Service Bulletin A340-29-4096, dated August 8, 2014.
    (5) Airbus Service Bulletin A340-29-4096, Revision 01, including 
Appendixes 01 and 02, dated July 30, 2015.

(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.
    (ii) AMOC ANM-116-14-180 R1, dated February 21, 2014, is 
approved as an AMOC for the corresponding provisions of this AD.
    (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 is available at the addresses specified in 
paragraphs (v)(6) and (v)(7) of this AD.

(v) 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 
December 27, 2016.
    (i) Airbus Service Bulletin A330-29-3125, Revision 03, including 
Appendixes 01 and 02, dated April 8, 2016.
    (ii) Airbus Service Bulletin A340-29-4096, Revision 02, 
including Appendixes 01 and 02, dated April 8, 2016.

[[Page 83653]]

    (4) The following service information was approved for IBR on 
January 31, 2014 (78 FR 78694, December 27, 2013).
    (i) Airbus Alert Operators Transmission A29L001-12, dated 
October 11, 2012.
    (ii) Airbus Mandatory Service Bulletin A330-29-3111, Revision 
02, dated June 23, 2011.
    (iii) Airbus Mandatory Service Bulletin A340-29-4086, Revision 
02, dated June 23, 2011.
    (5) The following service information was approved for IBR on 
December 14, 2009 (74 FR 62208, November 27, 2009).
    (i) Airbus Alert Operators Telex A330-29A3111, Revision 1, dated 
October 8, 2009. Only the first page of this document contains the 
document number, revision level, and date; no other pages of this 
document contain this information.
    (ii) Airbus Alert Operators Telex A340-29A4086, Revision 1, 
dated October 8, 2009. Only the first page of this document contains 
the document number, revision level, and date; no other pages of 
this document contain this information.
    (6) 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.
    (7) 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.
    (8) 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 October 12, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25745 Filed 11-21-16; 8:45 am]
 BILLING CODE 4910-13-P