Airworthiness Directives; Airbus SAS Airplanes, 56704-56709 [2018-24688]

Download as PDF 56704 Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations under the criteria of the Regulatory Flexibility Act. Instructions of Airbus Service Bulletin A350– 53–P024, dated April 3, 2018. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (i)(2) of this AD. Information may be emailed to: 9-ANM–116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized 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. 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 adding the following new airworthiness directive (AD): ■ 2018–23–07 Airbus SAS: Amendment 39– 19493; Docket No. FAA–2018–0758; Product Identifier 2018–NM–093–AD. (a) Effective Date This AD is effective December 19, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A350–941 airplanes, certificated in any category, except those on which Airbus modification 110319 or Airbus modification 110348 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a review of the Airbus A350 structure design principles database for type definition that revealed that the balancer fitting part, installed on the tail cone, lower section of frame (FR) 103, has several corrosion-resistant stainless steel nuts installed on elementary aluminum parts, and this configuration does not meet the requirements for protection against corrosion. We are issuing this AD to address this condition, which if not corrected, could reduce the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0123, dated June 4, 2018, for related information. This MCAI may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0758. (2) For more information about this AD, contact Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. (g) Required Action Within 72 months since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, apply additional overcoat sealant and elastic varnish to the fastener heads and the anchor nuts of the balancer fitting at FR 103, in accordance with the Accomplishment (j) 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. VerDate Sep<11>2014 18:08 Nov 13, 2018 Jkt 247001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (i) Airbus Service Bulletin A350–53–P024, dated April 3, 2018. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on November 2, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–24683 Filed 11–13–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0297; Product Identifier 2017–NM–181–AD; Amendment 39–19497; AD 2018–23–11] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This AD was prompted by investigations that revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. This AD requires identifying the BDDV part number installed on the airplane, and modifying or replacing BDDVs having certain part numbers. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 19, 2018. SUMMARY: E:\FR\FM\14NOR1.SGM 14NOR1 Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 19, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; internet https:// www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0297. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0297; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is 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: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. 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 Airbus SAS Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on April 17, 2018 (83 FR 16799). The NPRM was prompted by investigations that revealed that the cover seal of the BDDV was damaged and did not ensure efficient sealing. The NPRM proposed to require identifying the BDDV part number installed on the airplane, and modifying or replacing BDDVs having certain part numbers. VerDate Sep<11>2014 18:08 Nov 13, 2018 Jkt 247001 We are issuing this AD to address water ingestion in the BDDV, freezing of the BDDV in flight, and consequent loss of braking system function after landing. These conditions could possibly result in damage to the airplane and injury to occupants. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0119, dated July 11, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: In 1998, an operator experienced a dual loss of braking systems. Investigation results revealed that the cover seal of the BDDV was damaged and did not ensure the sealing efficiency. This condition, if not corrected, could lead to water ingestion in the BDDV, freezing of the BDDV in flight, and consequent loss of braking system function after landing, possibly resulting in damage to the aeroplane and injury to occupants. To address this potential unsafe condition, Airbus issued Alert Operator Telex (AOT) 32–19 and Service Bulletin (SB) A320–32– 1199, providing instructions for repetitive functional tests. In addition, Airbus developed mod 28301 and published SB A320–32–1203 to provide modification instructions. Consequently, DGAC [Directorate General for Civil Aviation] France issued AD 2000– 258–146 [which corresponds to FAA AD 2001–15–10, Amendment 39–12344 (66 FR 39413, July 31, 2001) (‘‘AD 2001–15–10’’)] to require repetitive functional tests as a temporary solution (valid for a period of 15 months) and modification of the BDDV with a new cover and installation of a draining tube with a cap, which was terminating action for the repetitive functional tests. For pre-mod 27833 and pre-SB A320–32–1200 aeroplanes, repetitive inspections per SB A320–32–1199 were required as interim action, prior to the terminating action modification per SB A320–32–1203. After that [DGAC] AD was issued, following a new event, Airbus developed a new modification of the BDDV drain tube which leaves it open, ensuring continuous drainage of any ingested water, thereby preventing freezing of the brake system. Consequently, EASA issued AD 2014–0251 (later revised), partially retaining the requirements of DGAC France AD 2000–258– 146, which was superseded, and requiring an additional modification of the BDDV drain tube and re-identification of the BDDV. Since EASA AD 2014–0251R1 [which corresponds to FAA AD 2016–06–13, Amendment 39–18444 (81 FR 17365, March 29, 2016) (‘‘AD 2016–06–13’’)] was issued, comments were received that indicated a PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 56705 need for correction and clarification. Consequently, this [EASA] AD retains the requirements of EASA AD 2014–0251R1, which is superseded, and expands the list of BDDV Part Numbers (P/N) which must be removed from service and are no longer eligible for installation on an aeroplane [and includes replacing affected part numbers as an option]. This [EASA] AD also clarifies the intended requirements of EASA AD 2014– 0251 and introduces editorial changes, not affecting the requirements. You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0297. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Supportive Comments Air Line Pilots Association, International stated its support for the NPRM. In addition, United Airlines (UAL) stated it concurs with the expansion of the affected BDDV part numbers as identified in Figure 1 to paragraphs (g) and (h) of the proposed AD. Request To Withdraw the NPRM Delta Air lines (DAL) requested that we withdraw the NPRM. DAL stated that the NPRM does not address an unsafe condition and, therefore, it is unnecessary. DAL commented that airplanes included in paragraph (c) of the proposed AD are already required to comply with the actions required by AD 2001–15–10, depending on modification status. DAL also commented that the NPRM does not add any airplanes to the applicability of AD 2001–15–10 and 2016–06–13. DAL stated that tracking compliance with the redundant requirements of the proposed AD would place an undue burden on airlines. DAL stated that paragraphs (j)(1)(i) and (j)(2)(i) of the proposed AD give credit for actions accomplished using previously issued service information. DAL commented that FAA Letter ANM– 116–16–491, dated September 27, 2016, gives operators the authority to accomplish paragraph (g) of AD 2016– 06–13 as an alternative method of compliance (AMOC), and it is also a terminating action for the actions required by paragraphs (e) and (f) of AD 2001–15–10. DAL stated that the compliance times for AD 2001–15–10 and AD 2016–06–13 have passed, therefore, all airplanes must be in compliance. E:\FR\FM\14NOR1.SGM 14NOR1 56706 Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations We partially agree with the commenter’s request. We agree that airplanes included in paragraph (c) of this AD are also required to comply with AD 2001–15–10 and AD 2016–06– 13, and that this AD does not add any new Model airplanes related to those listed in AD 2001–15–10 and AD 2016– 06–13. However, as stated in paragraph (i) of this AD, compliance with paragraph (g) of this AD terminates the requirements in paragraphs (e) and (f) of AD 2001–15–10 (which terminates all requirements of AD 2001–15–10 for Model A318, A319 and A320 series airplanes) and all requirements of AD 2016–06–13. For clarification, we have modified paragraph (i)(1) of this AD to state that compliance with paragraph (g) of this AD terminates all requirements of AD 2001–15–10 for Model A319, A320 and A321 series airplanes. We agree that operators will be required to track certain ADs with expired compliance times, but we are in process of rescinding some of those ADs through future rulemaking. We agree that AMOC letter ANM–116–16–491 dated September 27, 2016, will still be applicable to AD 2016–06–13. We disagree with the commenter’s request to withdraw this AD. We, along with EASA, have determined that water ingestion in the BDDV, freezing of the BDDV in flight, and consequent loss of braking system function after landing, could possibly result in damage to the airplane and injury to occupants, and therefore, does constitute an unsafe condition, and that additional mandatory actions in this AD are required to mitigate the risks associated with the unsafe condition. Further, even if the current U.S.-Registered fleet is in compliance with the requirements of this AD, the issuance of the rule is still necessary to ensure that any affected airplane imported and placed on the U.S. Register in the future would be required to be in compliance as well. This AD expands the list of BDDV part numbers, which must be removed from service and are no longer eligible for installation on an airplane. Therefore, all U.S.-Registered airplanes might not be in compliance with the actions of this AD even when in full compliance with AD 2001–15–10 and AD 2016–06– 13. However, if DAL concludes that it is in compliance with the requirements of this AD, then it may utilize the provision in paragraph (f) to demonstrate compliance. We have not changed this AD in this regard. Request To Correct Certain Wording DAL observed that the word ‘‘actions’’ was inadvertently omitted from the first sentence in paragraph (g)(2) of the VerDate Sep<11>2014 18:08 Nov 13, 2018 Jkt 247001 proposed AD after the word ‘‘corrective.’’ We agree and have added the missing word accordingly. Request To Revise Certain Wording for Clarification UAL requested that we revise the wording in certain paragraphs of the proposed AD for clarification. UAL suggested that paragraph (g)(3) of the proposed AD be reworded because the way it is currently written, it could be interpreted as ‘‘a part number specified as new P/N in figure 2 to paragraphs (g)(3) and (h)(2)’’ cannot be installed. UAL also suggested that paragraph (h) of the proposed AD be revised to eliminate paragraphs (h)(1) and (h)(2) and be reworded to simply prohibit the installation of affected BDDVs as specified in figure 1 to paragraphs (g) and (h) of the proposed AD. We partially agree to the commenter’s requests. We agree to clarify paragraph (g)(3) of this AD. We have revised paragraph (g)(3) of this AD to clarify that operators should replace the old part number with a new part number as specified in figure 2 to paragraphs (g)(3) and (h)(2) of this AD. However, we disagree to simply prohibit installation of discrepant parts that are specified in figure 1 to paragraphs (g) and (h) of this AD from the effective date of this AD. Paragraph (h) provides operators flexibility by providing the full compliance time as specified in paragraph (g) to modify or replace discrepant parts, unless the discrepant part is either currently installed as of the effective date of this AD and is subsequently modified or replaced (after the effective date of this AD) as stated in paragraph (h)(1) of this AD, or has already been modified or replaced as of the effective date of this AD as stated in paragraph (h)(2) of this AD. Operators have the discretion to prohibit operation with a discrepant part in figure 1 to paragraphs (g) and (h) of this AD from the effective date of this AD. We have not changed the AD in this regard. Request To Clarify the Compliance Requirements JetBlue requested that we clarify the compliance requirements in paragraphs (g)(2), (g)(3), and (h)(2) of the proposed AD because of contradictory requirements. The commenter did not clearly identify which requirements needed clarification. We do not agree to revise paragraph (g)(2) of this AD. This AD and the Accomplishment Instructions of Airbus Service Bulletin A320–32–1415, Revision 02, dated December 10, 2015, specify that, if corrosion is found in a PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 non-permitted area, replace the BDDV before further flight. We have not changed this AD in this regard. As we stated previously, we have revised paragraph (g)(3) of this AD to clarify that operators should replace the old part number with a new part number as specified in figure 2 to paragraphs (g)(3) and (h)(2) of this AD. We agree to clarify the compliance requirements of paragraph (h)(2) of this AD. As stated in the previous comment response, paragraph (h) is intended to provide operators flexibility by providing the full compliance time as specified in paragraph (g) to modify or replace discrepant parts. However, paragraph (h)(2) of this AD specifically prohibits installation of a discrepant part as of the effective date of this AD if the discrepant part has already been modified or replaced as of the effective date of this AD. Paragraph (h)(1) of this AD prohibits installation of a discrepant part as of the effective date of this AD, if a discrepant part is currently installed as of the effective of this AD, but is modified or replaced after the effective date of this AD. Operators have the discretion to prohibit operation with a discrepant part in figure 1 to paragraphs (g) and (h) of this AD from the effective date of this AD. We have not changed the AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 Airbus SAS has issued Service Bulletin A320–32–1203, Revision 02, dated February 9, 2001. This service information describes procedures for identifying the BDDV part number installed on the airplane, and modifying or replacing BDDVs having certain part numbers. Airbus SAS has also issued Service Bulletin A320–32–1415, Revision 02, dated December 10, 2015. This service information describes procedures for E:\FR\FM\14NOR1.SGM 14NOR1 Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations modifying and re-identifying the BDDV. The modification includes modifying the drain hose of the BDDV, and doing all related investigative and corrective actions if applicable. The related investigative actions include an inspection for corrosion. Corrective actions include replacing the BDDV. 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. 56707 Costs of Compliance We estimate that this AD affects 1,136 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Identification and modification or replacement. Up to 6 work-hours × $85 per hour = $510. Up to $395 ....... Up to $905 ....... We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings 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 VerDate Sep<11>2014 18:08 Nov 13, 2018 Jkt 247001 distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2018–23–11 Airbus SAS: Amendment 39– 19497; Docket No. FAA–2018–0297; Product Identifier 2017–NM–181–AD. (a) Effective Date This AD is effective December 19, 2018. (b) Affected ADs This AD affects AD 2001–15–10, Amendment 39–12344 (66 FR 39413, July 31, 2001) (‘‘AD 2001–15–10’’), and AD 2016–06– PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Cost on U.S. operators Up to $1,028,080. 13, Amendment 39–18444 (81 FR 17365, March 29, 2016) (‘‘AD 2016–06–13’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 26925 has been embodied in production, which introduces a modified alternate braking system that removes the brake dual distribution valve (BDDV). (1) Airbus SAS Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Airbus SAS Model A320–211, –212, –214, –231, –232, and –233 airplanes. (3) Airbus SAS Model A321–111, –112, –131,–211,–212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by investigations that revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. We are issuing this AD to prevent water ingestion in the BDDV, freezing of the BDDV in flight, and consequent loss of braking system function after landing. These conditions could possibly result in damage to the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Identification and Modification or Replacement Within 3 months after the effective date of this AD, identify the BDDV part number installed on the airplane. For each affected BDDV part number specified in figure 1 to paragraphs (g) and (h) of this AD, within 3 months after the effective date of this AD, do the actions in paragraph (g)(1), (g)(2), or (g)(3) of this AD. A review of airplane maintenance records is acceptable to identify the BDDV part number if the part number of the BDDV can be conclusively determined from that review. E:\FR\FM\14NOR1.SGM 14NOR1 (1) Modify and re-identify the affected BDDV, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1203, Revision 02, dated February 9, 2001. (2) Modify and re-identify the affected BDDV, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1415, Revision 02, dated December 10, 2015. Do all applicable related investigative and corrective actions before further flight. (3) Replace the affected BDDV with a BDDV having a part number not specified in figure 1 to paragraphs (g) and (h) of this AD, or replace the old part number with a new part number as specified in figure 2 to paragraphs (g)(3) and (h)(2) of this AD. Do the replacement using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (h) Parts Installation Prohibition (i) Terminating Action for Other ADs (j) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraphs (j)(1)(i) or (j)(1)(ii) of this AD. (i) Airbus Service Bulletin A320–32–1203, dated June 4, 1999, which was incorporated by reference in AD 2001–15–10. (ii) Airbus Service Bulletin A320–32–1203, Revision 01, dated October 12, 2000. (2) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraphs (j)(2)(i) or (j)(2)(ii) of this AD. (i) Airbus Service Bulletin A320–32–1415, dated September 2, 2014, which was incorporated by reference in AD 2016–06–13. (ii) Airbus Service Bulletin A320–32–1415, Revision 01, dated April 23, 2015. (1) Doing the actions in paragraph (g) of this AD terminates the requirements in paragraphs (e) and (f) of AD 2001–15–10 for Model A319, A320 and A321 series airplanes. (2) Doing the actions in paragraph (g) of this AD terminates all of the requirements of AD 2016–06–13. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus SAS’s EASA 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 As of the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, no person may install a BDDV having a part number specified in figure 1 to paragraphs (g) and (h) of this AD, on any airplane. (1) For any airplane that, on the effective date of this AD, has a BDDV installed with a part number specified in figure 1 to paragraphs (g) and (h) of this AD: After modification or replacement of the BDDV, as required by paragraph (g) of this AD. (2) For any airplane that, on the effective date of this AD, has a BDDV installed or replaced with a part number specified as ‘new P/N’ in figure 2 to paragraphs (g)(3) and (h)(2) of this AD, or has a BDDV installed or replaced with a part number not specified in figure 1 to paragraphs (g) and (h) of this AD: As of the effective date of this AD. VerDate Sep<11>2014 18:08 Nov 13, 2018 Jkt 247001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\14NOR1.SGM 14NOR1 ER14NO18.002</GPH> Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations ER14NO18.001</GPH> 56708 Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0119, dated July 11, 2017, for related information. This MCAI may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0297. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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. (i) Airbus Service Bulletin A320–32–1203, Revision 02, dated February 9, 2001. (ii) Airbus Service Bulletin A320–32–1415, Revision 02, dated December 10, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on November 5, 2018. Christopher Spangenberg, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–24688 Filed 11–13–18; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 18:08 Nov 13, 2018 Jkt 247001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0637; Product Identifier 2018–NM–091–AD; Amendment 39–19496; AD 2018–23–10] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350–941 airplanes. This AD was prompted by leakage of shrouded pipe T-boxes in the potable water system. This AD requires replacement of the affected potable water T-boxes and clamps with new parts. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 19, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 19, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0637. SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0637; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 56709 Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. 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 Airbus SAS Model A350–941 airplanes. The NPRM published in the Federal Register on August 2, 2018 (83 FR 37766). The NPRM was prompted by leakage of shrouded pipe T-boxes in the potable water system. The NPRM proposed to require replacement of the affected potable water T-boxes and clamps with new parts. We are issuing this AD to address the possible leakage of water into the avionics bay. This condition, if not corrected, could lead to the loss of systems/equipment located inside the avionics bay and possible 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 AD 2018– 0111R1, dated May 30, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A350–941 airplanes. The MCAI states: During a pressure test on the A350 Final Assembly Line (FAL), leakage was observed on the potable water system shrouded pipes, due to a crack failure on the T-Boxes. Leakage of a primary pipe may cause water ingress into the avionics bay. Additionally, during another pressure proof test on the A350 FAL, loss of torque was detected on the clamps used to attach the shrouded pipes on the T-Boxes. This condition, if not corrected, could lead to loss of systems/equipment located inside the avionics bay, possibly resulting in an unsafe condition. Prompted by these findings, Airbus developed improved potable water T-Boxes and clamps, which are embodied in production through Airbus mod 111435 or mod 111440, and introduced in service through the SB [Service Bulletin A350–38– P004]. For the reasons described above, this [EASA] AD requires replacement of the affected potable water shrouded pipe T-Boxes and clamps with new parts. This [EASA] AD was revised to exclude post-mod 111440 aeroplanes from the Applicability. E:\FR\FM\14NOR1.SGM 14NOR1

Agencies

[Federal Register Volume 83, Number 220 (Wednesday, November 14, 2018)]
[Rules and Regulations]
[Pages 56704-56709]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24688]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0297; Product Identifier 2017-NM-181-AD; Amendment 
39-19497; AD 2018-23-11]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214, -
231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. This AD was prompted by 
investigations that revealed that the cover seal of the brake dual 
distribution valve (BDDV) was damaged and did not ensure efficient 
sealing. This AD requires identifying the BDDV part number installed on 
the airplane, and modifying or replacing BDDVs having certain part 
numbers. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective December 19, 2018.

[[Page 56705]]

    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 19, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email [email protected]; 
internet https://www.airbus.com. You may view this service information 
at the FAA, Transport Standards Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0297.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0297; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is 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: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

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 Airbus SAS Model 
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. The NPRM published in the Federal Register on April 17, 
2018 (83 FR 16799). The NPRM was prompted by investigations that 
revealed that the cover seal of the BDDV was damaged and did not ensure 
efficient sealing. The NPRM proposed to require identifying the BDDV 
part number installed on the airplane, and modifying or replacing BDDVs 
having certain part numbers.
    We are issuing this AD to address water ingestion in the BDDV, 
freezing of the BDDV in flight, and consequent loss of braking system 
function after landing. These conditions could possibly result in 
damage to the airplane and injury to occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0119, dated July 11, 2017 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus SAS Model A319 series airplanes; 
Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model 
A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The 
MCAI states:

    In 1998, an operator experienced a dual loss of braking systems. 
Investigation results revealed that the cover seal of the BDDV was 
damaged and did not ensure the sealing efficiency.
    This condition, if not corrected, could lead to water ingestion 
in the BDDV, freezing of the BDDV in flight, and consequent loss of 
braking system function after landing, possibly resulting in damage 
to the aeroplane and injury to occupants.
    To address this potential unsafe condition, Airbus issued Alert 
Operator Telex (AOT) 32-19 and Service Bulletin (SB) A320-32-1199, 
providing instructions for repetitive functional tests. In addition, 
Airbus developed mod 28301 and published SB A320-32-1203 to provide 
modification instructions.
    Consequently, DGAC [Directorate General for Civil Aviation] 
France issued AD 2000-258-146 [which corresponds to FAA AD 2001-15-
10, Amendment 39-12344 (66 FR 39413, July 31, 2001) (``AD 2001-15-
10'')] to require repetitive functional tests as a temporary 
solution (valid for a period of 15 months) and modification of the 
BDDV with a new cover and installation of a draining tube with a 
cap, which was terminating action for the repetitive functional 
tests. For pre-mod 27833 and pre-SB A320-32-1200 aeroplanes, 
repetitive inspections per SB A320-32-1199 were required as interim 
action, prior to the terminating action modification per SB A320-32-
1203.
    After that [DGAC] AD was issued, following a new event, Airbus 
developed a new modification of the BDDV drain tube which leaves it 
open, ensuring continuous drainage of any ingested water, thereby 
preventing freezing of the brake system.
    Consequently, EASA issued AD 2014-0251 (later revised), 
partially retaining the requirements of DGAC France AD 2000-258-146, 
which was superseded, and requiring an additional modification of 
the BDDV drain tube and re-identification of the BDDV.
    Since EASA AD 2014-0251R1 [which corresponds to FAA AD 2016-06-
13, Amendment 39-18444 (81 FR 17365, March 29, 2016) (``AD 2016-06-
13'')] was issued, comments were received that indicated a need for 
correction and clarification. Consequently, this [EASA] AD retains 
the requirements of EASA AD 2014-0251R1, which is superseded, and 
expands the list of BDDV Part Numbers (P/N) which must be removed 
from service and are no longer eligible for installation on an 
aeroplane [and includes replacing affected part numbers as an 
option]. This [EASA] AD also clarifies the intended requirements of 
EASA AD 2014-0251 and introduces editorial changes, not affecting 
the requirements.

    You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0297.

Comments

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

Supportive Comments

    Air Line Pilots Association, International stated its support for 
the NPRM. In addition, United Airlines (UAL) stated it concurs with the 
expansion of the affected BDDV part numbers as identified in Figure 1 
to paragraphs (g) and (h) of the proposed AD.

Request To Withdraw the NPRM

    Delta Air lines (DAL) requested that we withdraw the NPRM. DAL 
stated that the NPRM does not address an unsafe condition and, 
therefore, it is unnecessary. DAL commented that airplanes included in 
paragraph (c) of the proposed AD are already required to comply with 
the actions required by AD 2001-15-10, depending on modification 
status. DAL also commented that the NPRM does not add any airplanes to 
the applicability of AD 2001-15-10 and 2016-06-13. DAL stated that 
tracking compliance with the redundant requirements of the proposed AD 
would place an undue burden on airlines.
    DAL stated that paragraphs (j)(1)(i) and (j)(2)(i) of the proposed 
AD give credit for actions accomplished using previously issued service 
information. DAL commented that FAA Letter ANM-116-16-491, dated 
September 27, 2016, gives operators the authority to accomplish 
paragraph (g) of AD 2016-06-13 as an alternative method of compliance 
(AMOC), and it is also a terminating action for the actions required by 
paragraphs (e) and (f) of AD 2001-15-10. DAL stated that the compliance 
times for AD 2001-15-10 and AD 2016-06-13 have passed, therefore, all 
airplanes must be in compliance.

[[Page 56706]]

    We partially agree with the commenter's request. We agree that 
airplanes included in paragraph (c) of this AD are also required to 
comply with AD 2001-15-10 and AD 2016-06-13, and that this AD does not 
add any new Model airplanes related to those listed in AD 2001-15-10 
and AD 2016-06-13. However, as stated in paragraph (i) of this AD, 
compliance with paragraph (g) of this AD terminates the requirements in 
paragraphs (e) and (f) of AD 2001-15-10 (which terminates all 
requirements of AD 2001-15-10 for Model A318, A319 and A320 series 
airplanes) and all requirements of AD 2016-06-13. For clarification, we 
have modified paragraph (i)(1) of this AD to state that compliance with 
paragraph (g) of this AD terminates all requirements of AD 2001-15-10 
for Model A319, A320 and A321 series airplanes. We agree that operators 
will be required to track certain ADs with expired compliance times, 
but we are in process of rescinding some of those ADs through future 
rulemaking. We agree that AMOC letter ANM-116-16-491 dated September 
27, 2016, will still be applicable to AD 2016-06-13.
    We disagree with the commenter's request to withdraw this AD. We, 
along with EASA, have determined that water ingestion in the BDDV, 
freezing of the BDDV in flight, and consequent loss of braking system 
function after landing, could possibly result in damage to the airplane 
and injury to occupants, and therefore, does constitute an unsafe 
condition, and that additional mandatory actions in this AD are 
required to mitigate the risks associated with the unsafe condition. 
Further, even if the current U.S.-Registered fleet is in compliance 
with the requirements of this AD, the issuance of the rule is still 
necessary to ensure that any affected airplane imported and placed on 
the U.S. Register in the future would be required to be in compliance 
as well. This AD expands the list of BDDV part numbers, which must be 
removed from service and are no longer eligible for installation on an 
airplane. Therefore, all U.S.-Registered airplanes might not be in 
compliance with the actions of this AD even when in full compliance 
with AD 2001-15-10 and AD 2016-06-13. However, if DAL concludes that it 
is in compliance with the requirements of this AD, then it may utilize 
the provision in paragraph (f) to demonstrate compliance. We have not 
changed this AD in this regard.

Request To Correct Certain Wording

    DAL observed that the word ``actions'' was inadvertently omitted 
from the first sentence in paragraph (g)(2) of the proposed AD after 
the word ``corrective.'' We agree and have added the missing word 
accordingly.

Request To Revise Certain Wording for Clarification

    UAL requested that we revise the wording in certain paragraphs of 
the proposed AD for clarification. UAL suggested that paragraph (g)(3) 
of the proposed AD be reworded because the way it is currently written, 
it could be interpreted as ``a part number specified as new P/N in 
figure 2 to paragraphs (g)(3) and (h)(2)'' cannot be installed.
    UAL also suggested that paragraph (h) of the proposed AD be revised 
to eliminate paragraphs (h)(1) and (h)(2) and be reworded to simply 
prohibit the installation of affected BDDVs as specified in figure 1 to 
paragraphs (g) and (h) of the proposed AD.
    We partially agree to the commenter's requests. We agree to clarify 
paragraph (g)(3) of this AD. We have revised paragraph (g)(3) of this 
AD to clarify that operators should replace the old part number with a 
new part number as specified in figure 2 to paragraphs (g)(3) and 
(h)(2) of this AD.
    However, we disagree to simply prohibit installation of discrepant 
parts that are specified in figure 1 to paragraphs (g) and (h) of this 
AD from the effective date of this AD. Paragraph (h) provides operators 
flexibility by providing the full compliance time as specified in 
paragraph (g) to modify or replace discrepant parts, unless the 
discrepant part is either currently installed as of the effective date 
of this AD and is subsequently modified or replaced (after the 
effective date of this AD) as stated in paragraph (h)(1) of this AD, or 
has already been modified or replaced as of the effective date of this 
AD as stated in paragraph (h)(2) of this AD. Operators have the 
discretion to prohibit operation with a discrepant part in figure 1 to 
paragraphs (g) and (h) of this AD from the effective date of this AD. 
We have not changed the AD in this regard.

Request To Clarify the Compliance Requirements

    JetBlue requested that we clarify the compliance requirements in 
paragraphs (g)(2), (g)(3), and (h)(2) of the proposed AD because of 
contradictory requirements. The commenter did not clearly identify 
which requirements needed clarification.
    We do not agree to revise paragraph (g)(2) of this AD. This AD and 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1415, Revision 02, dated December 10, 2015, specify that, if corrosion 
is found in a non-permitted area, replace the BDDV before further 
flight. We have not changed this AD in this regard.
    As we stated previously, we have revised paragraph (g)(3) of this 
AD to clarify that operators should replace the old part number with a 
new part number as specified in figure 2 to paragraphs (g)(3) and 
(h)(2) of this AD.
    We agree to clarify the compliance requirements of paragraph (h)(2) 
of this AD. As stated in the previous comment response, paragraph (h) 
is intended to provide operators flexibility by providing the full 
compliance time as specified in paragraph (g) to modify or replace 
discrepant parts. However, paragraph (h)(2) of this AD specifically 
prohibits installation of a discrepant part as of the effective date of 
this AD if the discrepant part has already been modified or replaced as 
of the effective date of this AD. Paragraph (h)(1) of this AD prohibits 
installation of a discrepant part as of the effective date of this AD, 
if a discrepant part is currently installed as of the effective of this 
AD, but is modified or replaced after the effective date of this AD. 
Operators have the discretion to prohibit operation with a discrepant 
part in figure 1 to paragraphs (g) and (h) of this AD from the 
effective date of this AD. We have not changed the AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A320-32-1203, Revision 02, 
dated February 9, 2001. This service information describes procedures 
for identifying the BDDV part number installed on the airplane, and 
modifying or replacing BDDVs having certain part numbers.
    Airbus SAS has also issued Service Bulletin A320-32-1415, Revision 
02, dated December 10, 2015. This service information describes 
procedures for

[[Page 56707]]

modifying and re-identifying the BDDV. The modification includes 
modifying the drain hose of the BDDV, and doing all related 
investigative and corrective actions if applicable. The related 
investigative actions include an inspection for corrosion. Corrective 
actions include replacing the BDDV.
    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 1,136 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                      Labor cost                 Parts cost               Cost per  product             Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Identification and modification or   Up to 6 work-hours x    Up to $395.................  Up to $905.................  Up to $1,028,080.
 replacement.                         $85 per hour = $510.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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 adding the following new airworthiness 
directive (AD):

2018-23-11 Airbus SAS: Amendment 39-19497; Docket No. FAA-2018-0297; 
Product Identifier 2017-NM-181-AD.

(a) Effective Date

    This AD is effective December 19, 2018.

(b) Affected ADs

    This AD affects AD 2001-15-10, Amendment 39-12344 (66 FR 39413, 
July 31, 2001) (``AD 2001-15-10''), and AD 2016-06-13, Amendment 39-
18444 (81 FR 17365, March 29, 2016) (``AD 2016-06-13'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(3) of this AD, certificated in any category, all 
manufacturer serial numbers, except those on which Airbus 
Modification 26925 has been embodied in production, which introduces 
a modified alternate braking system that removes the brake dual 
distribution valve (BDDV).
    (1) Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes.
    (2) Airbus SAS Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (3) Airbus SAS Model A321-111, -112, -131,-211,-212, -213, -231, 
and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by investigations that revealed that the 
cover seal of the brake dual distribution valve (BDDV) was damaged 
and did not ensure efficient sealing. We are issuing this AD to 
prevent water ingestion in the BDDV, freezing of the BDDV in flight, 
and consequent loss of braking system function after landing. These 
conditions could possibly result in damage to the airplane and 
injury to occupants.

(f) Compliance

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

(g) Identification and Modification or Replacement

    Within 3 months after the effective date of this AD, identify 
the BDDV part number installed on the airplane. For each affected 
BDDV part number specified in figure 1 to paragraphs (g) and (h) of 
this AD, within 3 months after the effective date of this AD, do the 
actions in paragraph (g)(1), (g)(2), or (g)(3) of this AD. A review 
of airplane maintenance records is acceptable to identify the BDDV 
part number if the part number of the BDDV can be conclusively 
determined from that review.

[[Page 56708]]

[GRAPHIC] [TIFF OMITTED] TR14NO18.001

    (1) Modify and re-identify the affected BDDV, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1203, Revision 02, dated February 9, 2001.
    (2) Modify and re-identify the affected BDDV, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1415, Revision 02, dated December 10, 2015. Do all 
applicable related investigative and corrective actions before 
further flight.
    (3) Replace the affected BDDV with a BDDV having a part number 
not specified in figure 1 to paragraphs (g) and (h) of this AD, or 
replace the old part number with a new part number as specified in 
figure 2 to paragraphs (g)(3) and (h)(2) of this AD. Do the 
replacement using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus SAS's EASA Design Organization 
Approval (DOA). If approved by the DOA, the approval must include 
the DOA-authorized signature.
[GRAPHIC] [TIFF OMITTED] TR14NO18.002

 (h) Parts Installation Prohibition

    As of the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD, no person may install a BDDV having a part number 
specified in figure 1 to paragraphs (g) and (h) of this AD, on any 
airplane.
    (1) For any airplane that, on the effective date of this AD, has 
a BDDV installed with a part number specified in figure 1 to 
paragraphs (g) and (h) of this AD: After modification or replacement 
of the BDDV, as required by paragraph (g) of this AD.
    (2) For any airplane that, on the effective date of this AD, has 
a BDDV installed or replaced with a part number specified as `new P/
N' in figure 2 to paragraphs (g)(3) and (h)(2) of this AD, or has a 
BDDV installed or replaced with a part number not specified in 
figure 1 to paragraphs (g) and (h) of this AD: As of the effective 
date of this AD.

(i) Terminating Action for Other ADs

    (1) Doing the actions in paragraph (g) of this AD terminates the 
requirements in paragraphs (e) and (f) of AD 2001-15-10 for Model 
A319, A320 and A321 series airplanes.
    (2) Doing the actions in paragraph (g) of this AD terminates all 
of the requirements of AD 2016-06-13.

(j) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using the service information in 
paragraphs (j)(1)(i) or (j)(1)(ii) of this AD.
    (i) Airbus Service Bulletin A320-32-1203, dated June 4, 1999, 
which was incorporated by reference in AD 2001-15-10.
    (ii) Airbus Service Bulletin A320-32-1203, Revision 01, dated 
October 12, 2000.
    (2) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using the service information in 
paragraphs (j)(2)(i) or (j)(2)(ii) of this AD.
    (i) Airbus Service Bulletin A320-32-1415, dated September 2, 
2014, which was incorporated by reference in AD 2016-06-13.
    (ii) Airbus Service Bulletin A320-32-1415, Revision 01, dated 
April 23, 2015.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to: [email protected]. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the EASA; or Airbus 
SAS's EASA 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

[[Page 56709]]

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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0119, dated July 11, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0297.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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.
    (i) Airbus Service Bulletin A320-32-1203, Revision 02, dated 
February 9, 2001.
    (ii) Airbus Service Bulletin A320-32-1415, Revision 02, dated 
December 10, 2015.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; internet 
https://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on November 5, 2018.
Christopher Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-24688 Filed 11-13-18; 8:45 am]
 BILLING CODE 4910-13-P