81 FR 9374 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 37 (February 25, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 37 (February 25, 2016)
| Page Range | 9374-9379 | |
| FR Document | 2016-03699 |
[Federal Register Volume 81, Number 37 (Thursday, February 25, 2016)] [Proposed Rules] [Pages 9374-9379] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-03699] ----------------------------------------------------------------------- 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). ----------------------------------------------------------------------- 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 [email protected]; 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: [email protected]. (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 [email protected]; 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 [email protected]; 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
![9374 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules
(m) Terminating Action been authorized by the Manager, Seattle Notice of proposed rulemaking
ACTION:
Accomplishment of the actions required by ACO, to make those findings. To be (NPRM).
paragraphs (k) and (l) of this AD terminate approved, the repair method, modification
the requirements of paragraphs (g) and (i) of deviation, or alteration deviation must meet SUMMARY: We propose to supersede
this AD. the certification basis of the airplane, and the Airworthiness Directive (AD) 2013–25–
approval must specifically refer to this AD. 08, for all Airbus Model A330–200,
(n) Parts Installation Prohibition (4) AMOCs approved for AD 2013–24–12
–200 Freighter, and –300 series
As of the effective date of this AD, no are approved as AMOCs for the
corresponding provisions of this AD. airplanes; and Model A340–200 and
person may install or reinstall any barrel nut
(5) Except as required by paragraph (o)(2) –300 series airplanes. AD 2013–25–08
P/N SL4081C14SP1 at the forward engine
mount assembly on any airplane, and only P/ of this AD: For service information that currently requires a repetitive
N SL4750NA may be installed. contains steps that are labeled as Required inspection program on certain check
for Compliance (RC), the provisions of valves in the hydraulic systems that
(o) New Exceptions to Service Information paragraphs (r)(5)(i) and (r)(5)(ii) of this AD includes, among other things,
Specifications apply. inspections for lock wire presence and
(1) Where Boeing Special Attention Service (i) The steps labeled as RC, including integrity, traces of seepage or black
Bulletin 747–71–2332, Revision 1, dated May substeps under an RC step and any figures
deposits, proper torque, alignment of
28, 2015, specifies a compliance time ‘‘after identified in an RC step, must be done to
comply with the AD. An AMOC is required the check valve and manifold,
the original issue date of this service
bulletin,’’ this AD requires compliance for any deviations to RC steps, including installation of new lock wire, and
within the specified compliance time after substeps and identified figures. corrective actions if needed. Since we
the effective date of this AD. (ii) Steps not labeled as RC may be issued AD 2013–25–08, Airbus has
(2) Where Boeing Special Attention Service deviated from using accepted methods in developed an improved check valve.
Bulletin 747–71–2332, Revision 1, dated May accordance with the operator’s maintenance This proposed AD would add airplanes
28, 2015, specifies to contact Boeing for or inspection program without obtaining to the applicability, and require
appropriate action: Before further flight, approval of an AMOC, provided the RC steps, modifying the green, blue and yellow
repair using a method approved in including substeps and identified figures, can
high pressure hydraulic manifolds by
accordance with the procedures specified in still be done as specified, and the airplane
can be put back in an airworthy condition. replacing certain check valves with
paragraph (r) of this AD.
improved check valves, which would
(p) No Alternative Actions or Intervals (s) Related Information terminate the repetitive inspections
After the maintenance or inspection (1) For more information about this AD, required by this proposed AD. We are
program has been revised as required by contact Nathan Weigand, Aerospace proposing this AD to detect and correct
paragraph (l) of this AD, no alternative Engineer, Airframe Branch, ANM–120S, hydraulic check valve loosening;
actions (e.g., inspections) or intervals may be FAA, Seattle ACO, 1601 Lind Avenue SW., loosened valves could result in
used unless the actions or intervals are Renton, WA 98057–3356; phone: 425–917–
hydraulic leaks, possibly leading to the
approved as an alternative method of 6428; fax: 425–917–6590; email:
Nathan.p.weigand@faa.gov. loss of all three hydraulic systems and
compliance (AMOC) in accordance with the
procedures specified in paragraph (r) of this (2) For service information identified in consequent loss of control of the
AD. this AD, contact Boeing Commercial airplane.
Airplanes, Attention: Data & Services DATES: We must receive comments on
(q) Credit for Previous Actions Management, P.O. Box 3707, MC 2H–65, this proposed AD by April 11, 2016.
This paragraph provides credit for the Seattle, WA 98124–2207; telephone: 206–
actions specified in paragraph (k) of this AD, 544–5000, extension 1; fax: 206–766–5680; ADDRESSES: You may send comments by
if those actions were performed before the Internet https://www.myboeingfleet.com. You any of the following methods:
effective date of this AD using Boeing Special may view this referenced service information • Federal eRulemaking Portal: Go to
Attention Service Bulletin 747–71–2332, at the FAA, Transport Airplane Directorate, http://www.regulations.gov. Follow the
dated May 30, 2014, which is not 1601 Lind Avenue SW., Renton, WA. For instructions for submitting comments.
incorporated by reference in this AD. information on the availability of this • Fax: 202–493–2251.
material at the FAA, call 425–227–1221. • Mail: U.S. Department of
(r) Alternative Methods of Compliance
(AMOCs) Issued in Renton, Washington, on February Transportation, Docket Operations, M–
(1) The Manager, Seattle Aircraft 15, 2016. 30, West Building Ground Floor, Room
Certification Office (ACO), FAA, has the Michael Kaszycki, W12–140, 1200 New Jersey Avenue SE.,
authority to approve AMOCs for this AD, if Acting Manager, Transport Airplane Washington, DC 20590.
requested using the procedures found in 14 Directorate, Aircraft Certification Service. • Hand Delivery: U.S. Department of
CFR 39.19. In accordance with 14 CFR 39.19, [FR Doc. 2016–03690 Filed 2–24–16; 8:45 am] Transportation, Docket Operations, M–
send your request to your principal inspector BILLING CODE 4910–13–P 30, West Building Ground Floor, Room
or local Flight Standards District Office, as W12–140, 1200 New Jersey Avenue SE.,
appropriate. If sending information directly
Washington, DC, between 9 a.m. and 5
to the manager of the ACO, send it to the
attention of the person identified in DEPARTMENT OF TRANSPORTATION p.m., Monday through Friday, except
paragraph (s)(1) of this AD. Information may Federal holidays.
be emailed to: 9-ANM-Seattle-ACO-AMOC- Federal Aviation Administration For service information identified in
Requests@faa.gov. this NPRM, contact Airbus SAS—
(2) Before using any approved AMOC, 14 CFR Part 39 Airworthiness Office—EAL, 1 Rond
notify your appropriate principal inspector, [Docket No. FAA–2016–3701; Directorate Point Maurice Bellonte, 31707 Blagnac
rmajette on DSK2TPTVN1PROD with PROPOSALS
or lacking a principal inspector, the manager Identifier 2015–NM–015–AD] Cedex, France; telephone +33 5 61 93 36
of the local flight standards district office/ 96; fax +33 5 61 93 45 80; email
certificate holding district office. RIN 2120–AA64 airworthiness.A330–A340@airbus.com;
(3) An AMOC that provides an acceptable
level of safety may be used for any repair, Airworthiness Directives; Airbus Internet http://www.airbus.com. You
modification, or alteration required by this Airplanes may view this referenced service
AD if it is approved by the Boeing information at the FAA, Transport
Commercial Airplanes Organization AGENCY:Federal Aviation Airplane Directorate, 1601 Lind Avenue
Designation Authorization (ODA) that has Administration (FAA), DOT. SW., Renton, WA. For information on
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![Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 9375
the availability of this material at the issued EASA Airworthiness Directive valves on which the increased torque value
FAA, call 425–227–1221. 2015–0009, dated January 16, 2015 had been applied. Based on those events, it
(referred to after this as the Mandatory has been concluded that the action to re-
Examining the AD Docket torque the check valves with an increased
Continuing Airworthiness Information, value is not a satisfactory terminating action
You may examine the AD docket on or ‘‘the MCAI’’), to correct an unsafe for addressing the issue of those check
the Internet at http:// condition. The MCAI states: valves.
www.regulations.gov by searching for To address that, EASA issued AD 2012–0244,
An A330 operator experienced a Yellow
and locating Docket No. FAA–2016– hydraulic circuit low level due to a loose which partially retained the requirements of
3701; or in person at the Docket check valve, Part Number (P/N) CAR401. EASA AD 2012–0070, which was
Management Facility between 9 a.m. During the inspection on the other two superseded. Additionally, for aeroplanes
and 5 p.m., Monday through Friday, hydraulic systems, the other three check equipped with P/N CAR401 on which the
except Federal holidays. The AD docket valves P/N CAR401 were also found to be increased torque value had been applied,
contains this proposed AD, the loose with their lock wire broken in two EASA AD 2012–0244 required repetitive
instances. Airbus A340 aeroplanes are also inspections of the check valves and HP
regulatory evaluation, any comments manifolds. Finally, EASA AD 2012–0244 also
received, and other information. The equipped with P/N CAR401 high pressure
manifold check valves. required application of a lower torque value
street address for the Docket Operations when a check valve P/N CAR401 is installed
Additional cases of P/N CAR401 check valve
office (telephone 800–647–5527) is in loosening have been reported on aeroplanes on an aeroplane.
the ADDRESSES section. Comments will having accumulated more than 1,000 flight Note: The reporting and the torque value
be available in the AD docket shortly cycles (FC). The check valve fitted on the increase requirements for check valves P/N
after receipt. Yellow hydraulic system is more affected, CAR401 of EASA AD 2012–0070 were no
due to additional system cycles induced by longer part of EASA AD 2012–0244.
FOR FURTHER INFORMATION CONTACT: EASA AD was revised to clarify which
Vladimir Ulyanov, Aerospace Engineer, cargo door operation.
actions are required for P/N CAR401 check
International Branch, ANM–116, This condition, if not detected and corrected,
valves, depending on applied (or not) torque
could result in hydraulic leaks, possibly
Transport Airplane Directorate, FAA, value.
leading to the loss of all three hydraulic
1601 Lind Avenue SW., Renton, WA Since EASA AD 2012–0244R1 (http://
systems and consequent loss of control of the
98057–3356; telephone 425–227–1138; ad.easa.europa.eu/blob/easa_ad_
aeroplane.
fax 425–227–1149. 2012_0244_R1_superseded.pdf/AD_2012-
To address this unsafe condition, EASA
0244R1_1) was issued, Airbus developed an
SUPPLEMENTARY INFORMATION: issued Emergency AD 2009–0223–E (http://
improved check valve P/N CAR402, which is
ad.easa.europa.eu/blob/easa_ad_2009_
Comments Invited embodied in production through Airbus
0223E_superseded.pdf/EAD_2009-0223-E_1) modification 203972, and in service through
We invite you to send any written [which corresponds to FAA AD 2009–24–09, associated Airbus SB A330–29–3125, or
relevant data, views, or arguments about Amendment 39–16068 (74 FR 62208, Airbus SB A340–29–4096, as applicable to
November 27, 2009)] to require an inspection
this proposed AD. Send your comments aeroplane type. In addition, these SBs
programme to detect any check valve provide instructions about the torque value
to an address listed under the loosening and, if necessary, to apply the
ADDRESSES section. Include ‘‘Docket No. (between 230 and 250 Nm) and re-
applicable corrective actions. identification of HP manifolds after check
FAA–2016–3701; Directorate Identifier EASA AD 2010–0145 (http:// valve P/N CAR402 installation.
2015–NM–015–AD’’ at the beginning of ad.easa.europa.eu/blob/easa_ad_ For the reasons described above, this [EASA]
your comments. We specifically invite 2010_0145_Superseded.pdf/AD_2010-0145 AD retains the requirements of EASA AD
comments on the overall regulatory, _1), which superseded EASA EAD 2009– 2012–0244R1, which is superseded, and
economic, environmental, and energy 0223–E retaining its requirements, was requires the installation of check valves P/N
aspects of this proposed AD. We will issued to expand the applicability to the CAR402 as terminating action to the
newly certified models A330–223F and repetitive inspections [and adds airplanes to
consider all comments received by the A330–243F.
closing date and may amend this the applicability].
Prompted by further reported in-service
proposed AD based on those comments. events of check valve P/N CAR401 loosening You may examine the MCAI in the
We will post all comments we before reaching the threshold of 700 FC, AD docket on the Internet at http://
receive, without change, to http:// EASA AD 2011–0139 (http:// www.regulations.gov by searching for
www.regulations.gov, including any ad.easa.europa.eu/blob/easa_ad_ and locating Docket No. FAA–2016–
personal information you provide. We 2011_0139_superseded.pdf/AD_2011-0139 3701.
will also post a report summarizing each _1), which superseded EASA AD 2010–0145,
retaining its requirements, was issued to: Related Service Information Under 1
substantive verbal contact we receive
—extend the requirement to identify the P/ CFR Part 51
about this proposed AD.
N CAR401 check valves to all aeroplanes, Airbus has issued Service Bulletin
Discussion and A330–29–3125, Revision 01, including
—reduce the inspection threshold for
On November 26, 2013, we issued AD Appendixes 01 and 02, dated July 30,
aeroplanes fitted with check valve P/N
2013–25–08, Amendment 39–17704 (78 CAR401, either installed in production 2015; and Service Bulletin A340–29–
FR 78694, December 27, 2013) (‘‘AD through Airbus modification 54491, or 4096, Revision 01, including
2013–25–08’’). AD 2013–25–08 requires installed in service through Airbus Service Appendixes 01 and 02, dated July 30,
actions intended to address an unsafe Bulletin (SB) A330–29–3101 or Airbus SB 2015. This service information describes
condition on all Airbus Model A330– A340–29–4078. procedures for modifying the green,
200 and –300 series airplanes; and EASA AD 2012–0070 (http:// blue, and yellow high pressure
Model A340–200 and –300 series ad.easa.europa.eu/blob/easa_ad_2012_0070_ hydraulic manifolds by replacing each
rmajette on DSK2TPTVN1PROD with PROPOSALS
airplanes. Correction_superseded.pdf/AD_2012-0070 check valve having part number (P/N)
Since we issued AD 2013–25–08, _1), which superseded EASA AD 2011–0139, CAR401 with an improved check valve
which superseded AD 2009–24–09 retaining its requirements, was issued to having P/N CAR402. This service
require an increased torque value of the
Amendment 39–16068 (74 FR 62208, check valve tightening and High Pressure
information is reasonably available
November 27, 2009), the European (HP) manifold re-identification. because the interested parties have
Aviation Safety Agency (EASA), which Since EASA AD 2012–0070 was issued, access to it through their normal course
is the Technical Agent for the Member additional in-service events have been of business or by the means identified
States of the European Union, has reported on aeroplanes fitted with check in the ADDRESSES section.
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FAA’s Determination and Requirements Authority for This Rulemaking § 39.13 [Amended]
of This Proposed AD Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
This product has been approved by specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
the aviation authority of another rules on aviation safety. Subtitle I, 2013–25–08, Amendment 39–17704 (78
country, and is approved for operation section 106, describes the authority of FR 78694, December 27, 2013), and
in the United States. Pursuant to our the FAA Administrator. ‘‘Subtitle VII: adding the following new AD:
bilateral agreement with the State of Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2016–3701;
Design Authority, we have been notified detail the scope of the Agency’s Directorate Identifier 2015–NM–015–AD.
of the unsafe condition described in the authority. (a) Comments Due Date
MCAI and service information We are issuing this rulemaking under We must receive comments by April 11,
referenced above. We are proposing this the authority described in ‘‘Subtitle VII, 2016.
AD because we evaluated all pertinent Part A, Subpart III, Section 44701:
information and determined an unsafe General requirements.’’ Under that (b) Affected ADs
condition exists and is likely to exist or section, Congress charges the FAA with This AD replaces AD 2013–25–08,
develop on other products of these same promoting safe flight of civil aircraft in Amendment 39–17704 (78 FR 78694,
type designs. December 27, 2013).
air commerce by prescribing regulations
Explanation of a Certain Alternative for practices, methods, and procedures (c) Applicability
Method of Compliance (AMOC) the Administrator finds necessary for This AD applies to Airbus airplanes,
safety in air commerce. This regulation certificated in any category, as identified in
Paragraph (t)(1)(iii) of this proposed
is within the scope of that authority paragraphs (c)(1) and (c)(2) of this AD.
AD states that AMOC ANM–116–14– (1) Model A330–201, –202, –203, –223,
because it addresses an unsafe condition
429 is not approved as an AMOC for the –223F, –243, –243F, –301, –302, –303, –321,
that is likely to exist or develop on
corresponding provisions of this AD. –322, –323, –341, –342, and –343 airplanes;
products identified in this rulemaking
This AMOC defines a terminating action all manufacturer serial numbers except those
action. on which Airbus modification 203972 has
when Airbus Modification 203972 is
introduced in production or when the Regulatory Findings been embodied in production.
Airbus Service Bulletin A330–29–3125, (2) Model A340–211, –212, –213, –311,
We determined that this proposed AD –312, and –313 airplanes; all manufacturer
dated August 8, 2014, is embodied in
would not have federalism implications serial numbers.
service. This proposed AD will exclude
under Executive Order 13132. This (d) Subject
from the applicability airplanes with
proposed AD would not have a
Airbus Modification 203972 and will Air Transport Association (ATA) of
substantial direct effect on the States, on
mandate actions in accordance with America Code 29, Hydraulic power.
the relationship between the national
Airbus Service Bulletin A330–29–3125, (e) Reason
Government and the States, or on the
Revision 01, including Appendixes 01
distribution of power and This AD was prompted by multiple reports
and 02, dated July 30, 2015.
responsibilities among the various of hydraulic line check valves loosening. We
Costs of Compliance levels of government. are issuing this AD to detect and correct
For the reasons discussed above, I hydraulic check valve loosening, which
We estimate that this proposed AD could result in hydraulic leaks, possibly
affects 88 airplanes of U.S. registry. certify this proposed regulation:
leading to the loss of all three hydraulic
The actions required by AD 2013–25– 1. Is not a ‘‘significant regulatory systems and consequent loss of control of the
08, and retained in this proposed AD action’’ under Executive Order 12866; airplane.
take about 10 work-hours per product, 2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures (f) Compliance
at an average labor rate of $85 per work-
hour. Based on these figures, the (44 FR 11034, February 26, 1979); Comply with this AD within the
estimated cost of the actions that are 3. Will not affect intrastate aviation in compliance times specified, unless already
done.
required by AD 2013–25–08 is $850 per Alaska; and
product. 4. Will not have a significant (g) Retained Inspections, With No Changes
We also estimate that it would take economic impact, positive or negative, This paragraph restates the requirements of
about 32 work-hours per product to on a substantial number of small entities paragraph (g) of AD 2013–25–08,
comply with the basic requirements of under the criteria of the Regulatory Amendment 39–17704 (78 FR 78694,
this proposed AD. The average labor Flexibility Act. December 27, 2013), with no changes. Except
rate is $85 per work-hour. Based on for Model A330–223F and A330–243F
these figures, we estimate the cost of List of Subjects in 14 CFR Part 39 airplanes: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD.
this proposed AD on U.S. operators to Air transportation, Aircraft, Aviation
(1) For airplanes that do not have Airbus
be $239,360, or $2,720 per product. safety, Incorporation by reference, Modification 54491 embodied in production,
We have received no definitive data Safety. or Airbus Service Bulletin A330–29–3101 or
that would enable us to provide cost Airbus Service Bulletin A340–29–4078
estimates for the on-condition actions The Proposed Amendment
embodied in service: Within 100 flight cycles
specified in this proposed AD. We have Accordingly, under the authority or 28 days after December 14, 2009 (the
no way of determining the number of delegated to me by the Administrator, effective date of AD 2009–24–09,
aircraft that might need these actions. the FAA proposes to amend 14 CFR part Amendment 39–16068 (74 FR 62208,
rmajette on DSK2TPTVN1PROD with PROPOSALS
According to the manufacturer, some 39 as follows: November 27, 2009)), whichever occurs first,
of the costs of this proposed AD may be inspect the check valves on the blue, green,
PART 39—AIRWORTHINESS and yellow hydraulic systems to identify
covered under warranty, thereby
their part numbers (P/Ns), in accordance
reducing the cost impact on affected DIRECTIVES
with the instructions of Airbus All Operators
individuals. We do not control warranty Telex (AOT) A330–29A3111, Revision 1,
coverage for affected individuals. As a ■ 1. The authority citation for part 39
dated October 8, 2009 (for Model A330–200
result, we have included all available continues to read as follows: and –300 series airplanes); or AOT A340–
costs in our cost estimate. Authority: 49 U.S.C. 106(g), 40113, 44701. 29A4086, Revision 1, dated October 8, 2009
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![Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 9379
(iii) AMOC ANM–116–14–429, dated DEPARTMENT OF THE TREASURY relating to section 42 and serve as the
September 25, 2014, is not approved as an text for these proposed regulations.
AMOC for the corresponding provisions of Internal Revenue Service
this AD. Special Analyses
(2) Contacting the Manufacturer: As of the 26 CFR Part 1 Certain IRS regulations, including this
effective date of this AD, for any requirement one, are exempt from the requirements
[REG–150349–12]
in this AD to obtain corrective actions from of Executive Order 12866, as
a manufacturer, the action must be RIN 1545–BL39 supplemented and reaffirmed by
accomplished using a method approved by Executive Order 13563. Therefore, a
the Manager, International Branch, ANM– Amendments to the Low-Income regulatory assessment is not required. It
116, Transport Airplane Directorate, FAA; or Housing Credit Compliance-Monitoring also has been determined that section
the European Aviation Safety Agency Regulations 553(b) of the Administrative Procedure
(EASA); or Airbus’s EASA Design Act (5 U.S.C. chapter 5) does not apply
AGENCY: Internal Revenue Service (IRS),
Organization Approval (DOA). If approved by to these regulations, and because the
Treasury.
the DOA, the approval must include the regulations do not impose a collection
ACTION: Notice of proposed rulemaking
DOA-authorized signature. of information on small entities, the
(3) Required for Compliance (RC): If any by cross-reference to temporary
regulations. Regulatory Flexibility Act (5 U.S.C.
service information contains procedures or chapter 6) does not apply. Pursuant to
tests that are identified as RC, those SUMMARY: In the Rules and Regulations section 7805(f) of the Internal Revenue
procedures and tests must be done to comply section of this issue of the Federal Code, this notice of proposed
with this AD; any procedures or tests that are Register, the IRS is issuing final and rulemaking will be submitted to the
not identified as RC are recommended. Those temporary regulations concerning the Chief Counsel for Advocacy of the Small
procedures and tests that are not identified Business Administration for comment
compliance-monitoring duties of a State
as RC may be deviated from using accepted
or local housing credit agency (Agency) on their impact on small business.
methods in accordance with the operator’s
for purposes of the low-income housing
maintenance or inspection program without Comments and Requests for Public
credit. The final and temporary
obtaining approval of an AMOC, provided Hearing
regulations revise and clarify certain
the procedures and tests identified as RC can Before these proposed regulations are
rules relating to the requirements to
be done and the airplane can be put back in adopted as final regulations,
conduct physical inspections and
an airworthy condition. Any substitutions or consideration will be given to any
changes to procedures or tests identified as
review low-income certifications and
other documentation. The text of the comments that are submitted timely to
RC require approval of an AMOC.
temporary regulations also serves as the the IRS as prescribed in this preamble
(u) Related Information text of these proposed regulations. under the ‘‘ADDRESSES’’ heading. The
(1) Refer to Mandatory Continuing DATES: Comments and requests for a Treasury Department and the IRS
Airworthiness Information (MCAI) EASA public hearing must be received by May request comments on all aspects of the
Airworthiness Directive 2015–0009, dated 25, 2016. proposed rules. All comments will be
January 16, 2015, for related information. ADDRESSES: Send submissions to:
available at www.regulations.gov or
This MCAI may be found in the AD docket CC:PA:LPD:PR (REG–150349–12), room upon request. A public hearing will be
on the Internet at http://www.regulations.gov 5203, Internal Revenue Service, P.O. scheduled if requested in writing by any
by searching for and locating Docket No. Box 7604, Ben Franklin Station, person that timely submits written
FAA–2016–3701. Washington, DC 20044. Submissions comments. If a public hearing is
(2) Service information identified in this may be hand delivered Monday through scheduled, notice of the date, time, and
AD that is not incorporated by reference may Friday between the hours of 8 a.m. and place for the public hearing will be
be obtained at Airbus SAS—Airworthiness 4 p.m. to: CC:PA:LPD:PR (REG–150349– published in the Federal Register.
Office—EAL, 1 Rond Point Maurice Bellonte, 12), Courier’s Desk, Internal Revenue Drafting Information
31707 Blagnac Cedex, France; telephone +33 Service, 1111 Constitution Avenue NW.,
5 61 93 36 96; fax +33 5 61 93 45 80; email The principal authors of these
Washington, DC. Submissions may also
airworthiness.A330–A340@airbus.com; regulations are Jian H. Grant and Martha
be sent electronically via the Federal
Internet http://www.airbus.com. M. Garcia, Office of the Associate Chief
eRulemaking Portal at
(3) For service information identified in Counsel (Passthroughs and Special
www.regulations.gov (IRS REG–150349–
this AD, contact Airbus SAS—Airworthiness Industries). However, other personnel
12).
Office—EAL, 1 Rond Point Maurice Bellonte, from the IRS and the Treasury
31707 Blagnac Cedex, France; telephone +33 FOR FURTHER INFORMATION CONTACT: Department participated in their
5 61 93 36 96; fax +33 5 61 93 45 80; email Concerning the regulations, Jian H. development.
airworthiness.A330–A340@airbus.com; Grant, (202) 317–4137, and Martha M.
Internet http://www.airbus.com. You may Garcia, (202) 317–6853 (not toll-free List of Subjects in 26 CFR Part 1
view this service information at the FAA, numbers); concerning submission of Income taxes, Reporting and
Transport Airplane Directorate, 1601 Lind comments, the hearing, and/or to be recordkeeping requirements.
Avenue SW., Renton, WA. For information placed on the building access list to
on the availability of this material at the attend the hearing, Oluwafunmilayo Proposed Amendments to the
FAA, call 425–227–1221. Taylor at (202) 317–6901 (not a toll-free Regulations
rmajette on DSK2TPTVN1PROD with PROPOSALS
number). Accordingly, 26 CFR part 1 is
Issued in Renton, Washington, on February
15, 2016. SUPPLEMENTARY INFORMATION: proposed to be amended as follows:
Michael Kaszycki, Background PART 1—INCOME TAXES
Acting Manager, Transport Airplane Final and temporary regulations in
Directorate, Aircraft Certification Service. the Rules and Regulations section of this ■ Paragraph 1. The authority citation
[FR Doc. 2016–03699 Filed 2–24–16; 8:45 am] issue of the Federal Register amend the continues to read in part as follows:
BILLING CODE 4910–13–P Income Tax Regulations (26 CFR part 1) Authority: 26 U.S.C. 7805 * * *
VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\25FEP1.SGM 25FEP1](https://thefederalregister.org/doc/81_FR_9411/page/6.svg)
Document Created: 2018-02-02 14:35:36
Document Modified: 2018-02-02 14:35:36
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by April 11, 2016. | |
| 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. | |
| FR Citation | 81 FR 9374 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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