Airworthiness Directives; Airbus Airplanes, 72401-72404 [2015-29444]

Download as PDF Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules not to exceed 200 flight cycles or 400 flight hours, whichever occurs first. (7) For Model A340–541 and –642 airplanes: Repeat the inspections at intervals not to exceed 100 flight cycles or 500 flight hours, whichever occurs first. rmajette on DSK2TPTVN1PROD with PROPOSALS (i) Corrective Action If any crack is found during any inspection required by paragraphs (g) or (h) of this AD: Before further flight, replace the cracked MLG support rib 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). Replacement of an MLG support rib does not terminate the repetitive inspections required by paragraph (h) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (j)(1) through (j)(15) of this AD. (1) Airbus Service Bulletin A330–57A3096, dated December 5, 2006, which was incorporated by reference in AD 2007–03–04, Amendment 39–14915 (74 FR 4416, January 31, 2007). (2) Airbus Service Bulletin A330–57A3096, Revision 01, dated April 18, 2007, which is not incorporated by reference by this AD. (3) Airbus Service Bulletin A330–57–3096, Revision 02, dated August 13, 2007, which was incorporated by reference in AD 2007– 22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)). (4) Airbus Service Bulletin A330–57–3096, Revision 03, dated October 24, 2012, which is not incorporated by reference by this AD. (5) Airbus Service Bulletin A330–57–3096, Revision 04, dated February 6, 2013, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A330–57–3096, Revision 05, dated October 17, 2013, which was incorporated by reference in AD 2015– 03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015). (7) Airbus Service Bulletin A340–57A4104, dated December 5, 2006, which was incorporated by reference in AD 2007–03–04, Amendment 39–14915 (72 FR 4416, January 31, 2007). (8) Airbus Service Bulletin A340–57–4104, Revision 01, dated August 13, 2007, which is not incorporated by reference in this AD. (9) Airbus Service Bulletin A340–57–4104, Revision 02, dated September 5, 2007, which was incorporated by reference in AD 2007– 22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)). (10) Airbus Service Bulletin A340–57– 4104, Revision 03, dated October 24, 2012, which is not incorporated by reference in this AD. (11) Airbus Service Bulletin A340– 57A5009, dated December 5, 2006, which was incorporated by reference in AD 2007– 03–04, Amendment 39–14915 (72 FR 4416, January 31, 2007). VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 72401 (12) Airbus Service Bulletin A340–57– 5009, Revision 01, dated August 13, 2007, which was incorporated by reference in AD 2007–22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)). (13) Airbus Service Bulletin A340–57– 5009, Revision 02, dated October 24, 2012, which is not incorporated by reference in this AD. (14) Airbus Alert Operators Transmission A57L005–14, dated July 15, 2014, which is not incorporated by reference in this AD. (15) Airbus Alert Operators Transmission A57L005–14, Revision 01, dated August 15, 2014, which is not incorporated by reference in this AD. June 26, 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– 2015–4815. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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 EASA; or Airbus’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 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. Issued in Renton, Washington, on November 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0120, dated PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 [FR Doc. 2015–29442 Filed 11–18–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4816; Directorate Identifier 2014–NM–238–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This proposed 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 proposed AD would require modifying the BDDV having certain part numbers; modifying the drain hose of the BDDV; checking for the presence of water, ice, and hydraulic fluid; and re-identifying the BDDV; and related investigative and corrective actions if necessary. We are proposing this AD to prevent damage to the BDDV, which could lead to water ingestion in the BDDV and freezing of the BDDV in flight, possibly resulting in loss of braking system function after landing. DATES: We must receive comments on this proposed AD by January 4, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\19NOP1.SGM 19NOP1 72402 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules • 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 proposed AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4816; 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: rmajette on DSK2TPTVN1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–4816; Directorate Identifier 2014–NM–238–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0251R1, dated December 17, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A319, A320, and A321 series airplanes. The MCAI states: In 1998, an operator experienced a dual loss of braking systems. Investigation results revealed that the cover seal of the Brake Dual Distribution Valve (BDDV) was damaged and did not ensure the sealing efficiency. This condition, if not corrected, could lead to water ingestion in the BDDV and freezing of the BDDV in flight, possibly resulting in loss of braking system function after landing. [The Directorate General for Civil Aviation] (DGAC) France issued AD 2000–258–146 [http://ad.easa.europa.eu/blob/20002580tb_ superseded.pdf/AD_F-2000-258-146_1] [which corresponds to certain actions in FAA AD 2001–15–10, Amendment 39–12344 (66 FR 39413, July 31, 2001)] to require modification of the BDDV with a new cover and installation of a draining tube with a cap. Since that French AD was issued, following a new event, Airbus developed a modification of the BDDV drain tube which will leave it open, ensuring continuous drainage of any ingested water, thereby preventing freezing of the brake system. For the reasons described above, EASA issued [another AD] * * *, to require modification of the BDDV drain tube. Since that [EASA] AD was issued, comments were received that indicated a need for correction and clarification. Consequently, this [EASA] AD is revised to add a Note to Table 1 and to amend paragraph (3). The modification includes a check for the presence of water, ice, and hydraulic fluid, and related investigative and corrective actions if necessary. Related investigative actions include an inspection for corrosion. Corrective actions include replacing the BDDV. 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–2015– 4816. PO 00000 Frm 00045 Fmt 4702 Sfmt 4702 Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–32–1415, dated September 2, 2014. The service information describes procedures for modifying the BDDV having certain part numbers; and modifying the drain hose of the BDDV; the modification includes a check for the presence of water, ice, and hydraulic fluid; and re-identifying the BDDV; and related investigative and corrective actions if necessary. 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 of this NPRM. 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 ‘‘RC’’ Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as RC (required for compliance) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and E:\FR\FM\19NOP1.SGM 19NOP1 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 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 alternative method of compliance (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 will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 953 airplanes of U.S. registry. We also estimate that it would take about 6 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $421 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $887,243, or $931 per product. 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. rmajette on DSK2TPTVN1PROD with PROPOSALS 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; VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–4816; Directorate Identifier 2014–NM–238–AD. (a) Comments Due Date We must receive comments by January 4, 2016. (b) Affected ADs None. (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. (1) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (3) Airbus 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 BDDV was damaged and did not ensure efficient sealing. We are issuing this AD to prevent damage to the BDDV, which could lead to water ingestion in the BDDV and freezing of the BDDV in flight, possibly resulting in loss of braking system function after landing. PO 00000 Frm 00046 Fmt 4702 Sfmt 4702 72403 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification and Re-Identification Within 24 months after the effective date of this AD, modify the BDDV having a part number listed in the column ‘‘Old Part Number’’ in table 1 to paragraph (g) of this AD; modify the drain hose of the affected BDDV; check for the presence of water, ice, and hydraulic fluid; and re-identify the BDDV to the corresponding part number, as applicable, as listed as ‘‘New Part Number’’ in table 1 to paragraph (g) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1415, dated September 2, 2014. Do all applicable related investigative and corrective actions before further flight. TABLE 1 TO PARAGRAPH (g) OF THIS AD—BDDV PART NUMBER REIDENTIFICATION Old part number New part number A25434006–3 ................. A25434005–101 ............. A25434005–201 ............. A25434005–301 ............. A25434005–401 ............. A25434006–101 ............. A25434006–3000. A25434005–1010. A25434005–2010. A25434005–3010. A25434005–4010. A25434006–1010. Note 2 to table 1 to paragraph (g) of this AD: The part number listed in table 1 to paragraph (g) of this AD can have an ‘‘A’’ or ‘‘B’’ suffix, which is an indication of the amendment level of the BDDV. This does not affect compliance with this AD. (h) Parts Installation Limitations 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 listed as ‘‘Old Part Number’’ in table 1 to paragraph (g) 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 listed as ‘‘Old Part Number’’ in table 1 to paragraph (g) of this AD: After modification of the airplane, as required by paragraph (g) of this AD. (2) For any airplane that, on the effective date of this AD, has a BDDV installed with a part number listed as ‘‘New Part Number’’ in table 1 to paragraph (g) of this AD, or has a BDDV installed with a part number not listed in table 1 to paragraph (g) of this AD: As of the effective date of this AD. (i) 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 E:\FR\FM\19NOP1.SGM 19NOP1 72404 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. rmajette on DSK2TPTVN1PROD with PROPOSALS (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0251R1, dated December 17, 2014, 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–2015–4816. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 10, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–29444 Filed 11–18–15; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 147 [Docket No.: FAA–2015–3901; Notice No. 15–10] RIN 2120–AK48 Aviation Maintenance Technician Schools Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM); extension of comment period. AGENCY: This action extends the comment period for an NPRM published on October 2, 2015. In that document, the FAA proposes to amend the regulations governing the curriculum and operations of FAA-certificated Aviation Maintenance Technician Schools. These amendments would modernize and reorganize the required curriculum subjects in the appendices of the current regulations. They would also remove the course content items currently located in the appendices and require that they be placed in each school’s operations specifications so they could more easily be amended when necessary. The amendments are needed because the existing curriculums are outdated, do not meet current industry needs, and can be changed only through notice and comment rulemaking. These amendments would ensure that aviation maintenance technician students receive up-to-date foundational training to meet the demanding and consistently changing needs of the aviation industry. This extension is a result of a joint request from Aviation Technical Education Council (ATEC), Aeronautical Repair Station Association (ARSA), Aircraft Owners and Pilots Association (AOPA), Airlines for America (A4A), Aviation Suppliers Association (ASA), Helicopter Association International (HAI), Modification And Replacement Parts Association (MARPA), National Air Carrier Association (NACA), National Air Transport Association (NATA), Regional Airline Association, STEM Education Coalition (STEM), and University Aviation Association (UAA) (collectively, the ‘‘Petitioners’’). DATES: The comment period for the notice of proposed rulemaking published on October 2, 2015 (80 FR 59674), is extended. Send comments on or before February 1, 2016. SUMMARY: PO 00000 Frm 00047 Fmt 4702 Sfmt 4702 Send comments identified by docket number FAA–2015–3901 using any of the following methods: • Federal Rulemaking Portal: Go to http://www.regulations.gov and follow the online instructions for sending your comments electronically. • Mail: Send comments to Docket Operations, M–30; U.S. Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room W12–140, West Building Ground Floor, Washington, DC 20590–0001. • Hand Delivery or Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: Fax comments to Docket Operations at 202–493–2251. Privacy: In accordance with 5 U.S.C. 553(c), DOT solicits comments from the public to better inform its rulemaking process. DOT posts these comments, without edit, including any personal information the commenter provides, to www.regulations.gov, as described in the system of records notice (DOT/ALL– 14 FDMS), which can be reviewed at www.dot.gov/privacy. Docket: Background documents or comments received may be read at http://www.regulations.gov at any time. Follow the online instructions for accessing the docket or go to the Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: For technical questions concerning this action, contact Robert Warren, Aircraft Maintenance Division, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone (202) 267–1711; email robert.w.warren@faa.gov. For legal questions concerning this action, contact Edmund Averman, Office of the Chief Counsel (AGC–210), Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone (202) 267–3147; email Ed.Averman@faa.gov. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited The FAA continues to invite interested persons to take part in this rulemaking by submitting written comments, data, or views about the NPRM we issued on October 2, 2015 (part 147, Aviation Maintenance Technician Schools (80 FR 59674)(October 2, 2015). The most E:\FR\FM\19NOP1.SGM 19NOP1

Agencies

[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72401-72404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29444]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4816; Directorate Identifier 2014-NM-238-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A319, A320, and A321 series airplanes. This 
proposed 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 proposed AD would require modifying 
the BDDV having certain part numbers; modifying the drain hose of the 
BDDV; checking for the presence of water, ice, and hydraulic fluid; and 
re-identifying the BDDV; and related investigative and corrective 
actions if necessary. We are proposing this AD to prevent damage to the 
BDDV, which could lead to water ingestion in the BDDV and freezing of 
the BDDV in flight, possibly resulting in loss of braking system 
function after landing.

DATES: We must receive comments on this proposed AD by January 4, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 72402]]

     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 proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4816; 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2015-4816; 
Directorate Identifier 2014-NM-238-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0251R1, dated December 17, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319, A320, and A321 series airplanes. The MCAI states:

    In 1998, an operator experienced a dual loss of braking systems. 
Investigation results revealed that the cover seal of the Brake Dual 
Distribution Valve (BDDV) was damaged and did not ensure the sealing 
efficiency.
    This condition, if not corrected, could lead to water ingestion 
in the BDDV and freezing of the BDDV in flight, possibly resulting 
in loss of braking system function after landing.
    [The Directorate General for Civil Aviation] (DGAC) France 
issued AD 2000-258-146 [http://ad.easa.europa.eu/blob/20002580tb_superseded.pdf/AD_F-2000-258-146_1] [which corresponds to 
certain actions in FAA AD 2001-15-10, Amendment 39-12344 (66 FR 
39413, July 31, 2001)] to require modification of the BDDV with a 
new cover and installation of a draining tube with a cap.
    Since that French AD was issued, following a new event, Airbus 
developed a modification of the BDDV drain tube which will leave it 
open, ensuring continuous drainage of any ingested water, thereby 
preventing freezing of the brake system.
    For the reasons described above, EASA issued [another AD] * * *, 
to require modification of the BDDV drain tube.
    Since that [EASA] AD was issued, comments were received that 
indicated a need for correction and clarification. Consequently, 
this [EASA] AD is revised to add a Note to Table 1 and to amend 
paragraph (3).

    The modification includes a check for the presence of water, ice, 
and hydraulic fluid, and related investigative and corrective actions 
if necessary. Related investigative actions include an inspection for 
corrosion. Corrective actions include replacing the BDDV. 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-2015-
4816.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-32-1415, dated September 2, 
2014. The service information describes procedures for modifying the 
BDDV having certain part numbers; and modifying the drain hose of the 
BDDV; the modification includes a check for the presence of water, ice, 
and hydraulic fluid; and re-identifying the BDDV; and related 
investigative and corrective actions if necessary. 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 of this NPRM.

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 ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as RC (required for compliance) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and

[[Page 72403]]

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 alternative method of 
compliance (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 
will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 953 airplanes of U.S. 
registry.
    We also estimate that it would take about 6 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $421 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $887,243, or $931 per product.

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-4816; Directorate Identifier 2014-NM-
238-AD.

(a) Comments Due Date

    We must receive comments by January 4, 2016.

(b) Affected ADs

    None.

(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.
    (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (2) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (3) Airbus 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 BDDV was damaged and did not ensure efficient 
sealing. We are issuing this AD to prevent damage to the BDDV, which 
could lead to water ingestion in the BDDV and freezing of the BDDV 
in flight, possibly resulting in loss of braking system function 
after landing.

(f) Compliance

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

(g) Modification and Re-Identification

    Within 24 months after the effective date of this AD, modify the 
BDDV having a part number listed in the column ``Old Part Number'' 
in table 1 to paragraph (g) of this AD; modify the drain hose of the 
affected BDDV; check for the presence of water, ice, and hydraulic 
fluid; and re-identify the BDDV to the corresponding part number, as 
applicable, as listed as ``New Part Number'' in table 1 to paragraph 
(g) of this AD; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1415, dated 
September 2, 2014. Do all applicable related investigative and 
corrective actions before further flight.

 Table 1 to Paragraph (g) of This AD--BDDV Part Number Re-Identification
------------------------------------------------------------------------
                   Old part number                      New part number
------------------------------------------------------------------------
A25434006-3..........................................    A25434006-3000.
A25434005-101........................................    A25434005-1010.
A25434005-201........................................    A25434005-2010.
A25434005-301........................................    A25434005-3010.
A25434005-401........................................    A25434005-4010.
A25434006-101........................................    A25434006-1010.
------------------------------------------------------------------------


    Note 2 to table 1 to paragraph (g) of this AD: The part number 
listed in table 1 to paragraph (g) of this AD can have an ``A'' or 
``B'' suffix, which is an indication of the amendment level of the 
BDDV. This does not affect compliance with this AD.

(h) Parts Installation Limitations

    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 
listed as ``Old Part Number'' in table 1 to paragraph (g) 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 listed as ``Old Part Number'' in 
table 1 to paragraph (g) of this AD: After modification of the 
airplane, as required by paragraph (g) of this AD.
    (2) For any airplane that, on the effective date of this AD, has 
a BDDV installed with a part number listed as ``New Part Number'' in 
table 1 to paragraph (g) of this AD, or has a BDDV installed with a 
part number not listed in table 1 to paragraph (g) of this AD: As of 
the effective date of this AD.

(i) 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

[[Page 72404]]

Flight Standards District Office, as appropriate. If sending 
information directly to the International Branch, send it to ATTN: 
Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0251R1, dated December 17, 
2014, 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-2015-4816.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on November 10, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-29444 Filed 11-18-15; 8:45 am]
BILLING CODE 4910-13-P