Airworthiness Directives; Airbus Airplanes, 79750-79754 [2015-30821]

Download as PDF 79750 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules TABLE 1 TO PARAGRAPH (I) OF THIS AD—REPLACEMENT COMPLIANCE TIMES—Continued Year of manufacture Compliance time 2009 ............... Before exceeding 10 years since date of manufacture of the passenger chemical oxygen generator. (j) Definition of Serviceable For the purpose of this AD, a serviceable unit is a passenger chemical oxygen generator having P/N 117042–XX (XX represents any numerical value) with a manufacturing date not older than 10 years, or any other approved part number, provided that the generator has not exceeded the life limit established for that generator by the manufacturer. (k) Reporting At the applicable time specified in paragraph (k)(1) or (k)(2) of this AD, submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD, in accordance with paragraph 7, ‘‘Reporting,’’ of Airbus AOT A35W008–14, dated December 18, 2014. The report must include the information specified in Appendix 1 of Airbus AOT A35W008–14, dated December 18, 2014. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (l) Parts Installation Limitation As of the effective date of this AD, no person may install a passenger chemical oxygen generator, unless it is determined, prior to installation, that the oxygen generator is a serviceable unit (as defined in paragraph (j) of this AD). (m) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116 Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–2125; fax: 425–227– 1149. Information may be emailed to: 9ANM-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/ VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 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) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0118, dated June 24, 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– 2015–7528. (2) For Airbus service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 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.airwortheas@airbus.com; Internet http:// www.airbus.com. For B/E service identified in this AD, contact B/E Aerospace Inc., 10800 Pflumm Road, Lenexa, KS 66215; telephone: 913–338–9800; fax: 913–469–8419; Internet http://beaerospace.com/home/globalsupport. 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 December 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–32084 Filed 12–22–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00032 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0250; Directorate Identifier 2014–NM–216–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM proposed to require replacing certain pitot probes on the captain, first officer, and standby sides with certain new pitot probes. The NPRM was prompted by reports of airspeed indication discrepancies while flying at high altitudes in inclement weather. This action revises the NPRM by reducing the proposed compliance time for replacing certain pitot probes based on a risk assessment due to additional reports of airspeed indication discrepancies while flying at high altitudes in inclement weather. We are proposing this supplemental NPRM (SNPRM) to prevent airspeed indication discrepancies during inclement weather, which, depending on the prevailing altitude, could lead to unknown accumulation of ice crystals and consequent reduced controllability of the airplane. Since these actions impose an additional burden over those proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this SNPRM by January 22, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey SUMMARY: E:\FR\FM\23DEP1.SGM 23DEP1 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 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– 0250; 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 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: asabaliauskas on DSK5VPTVN1PROD 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–2015–0250; Directorate Identifier 2014–NM–216–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. VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 79751 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on March 6, 2015 (80 FR 12094) (‘‘the NPRM’’). The NPRM was prompted by reports of airspeed indication discrepancies while flying at high altitudes in inclement weather. The NPRM proposed to require replacing certain pitot probes on the captain, first officer, and standby sides with certain new pitot probes. Consequently, EASA issued AD 2014–0237 (later revised) [http://ad.easa.europa.eu/ blob/easa_ad_2014_0237.pdf/AD_20140237], retaining the requirements of DGAC France AD 2001–362, which was superseded, and cancelling two other DGAC ADs, to require replacement of Thales Avionics pitot probes P/N C16195AA and P/N C16195BA. Since EASA issued AD 2014–0237R1 [http://ad.easa.europa.eu/ad/2014-0237R1] was issued, results of further analyses have determined that the compliance time (48 months) of that AD has to be reduced in relation to the risk assessment. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014–0237R1, which is superseded, but reduces the compliance time. Actions Since Previous NPRM (80 FR 12094, March 6, 2015) Was Issued Since we issued the NPRM (80 FR 12094, March 6, 2015), we have determined it is necessary to reduce the compliance time for replacing certain pitot probes based on a risk assessment due to additional reports of airspeed indication discrepancies while flying at high altitudes in inclement weather. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, issued EASA Airworthiness Directive 2015–0205, dated October 9, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states: 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– 0250. Occurrences have been reported on A320 family aeroplanes of airspeed indication discrepancies while flying at high altitudes in inclement weather conditions. Investigation results indicated that A320 aeroplanes equipped with Thales Avionics Part Number (P/N) 50620–10 or P/N C16195AA pitot probes appear to have a greater susceptibility to adverse environmental conditions that aeroplanes equipped with certain other pitot probes. Prompted by earlier occurrences, DGAC ´ ´ [Direction Generale de l’Aviation Civile] France issued [DGAC] AD 2001-362 [http:// ad.easa.europa.eu/blob/easa_ad_2001_ 362.pdf/AD_2001-362] [which corresponds to paragraph (f) of FAA AD 2004-03-33, Amendment 39-13477 (69 FR 9936, March 3, 2004)] to require replacement of Thales (formerly known as Sextant) P/N 50620-10 pitot probes with Thales P/N C16195AA probes. Since that [DGAC] AD was issued, Thales pitot probe P/N C15195BA was designed, which improved airspeed indication behavior in heavy rain conditions, but did not demonstrate the same level of robustness to withstand high-altitude ice crystals. Based on these findings, EASA have decided to implement replacement of the affected Thales [pitot] probes as a precautionary measure to improve the safety level of the affected aeroplanes. PO 00000 Frm 00033 Fmt 4702 Sfmt 4702 Related Rulemaking On February 4, 2004, we issued AD 2004–03–33, Amendment 39–13477 (69 FR 9936, March 3, 2004), applicable to certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4–600, A300 B4–600R, and A300 F4–600R series airplanes; Model A310 series Airplanes; Model A319, A320, and A321 series airplanes; Model A330–301, –321, –322, –341, and –342 airplanes; and Model A340 series airplanes. That AD requires, among other actions, replacement of certain pitot probes with certain new pitot probes. That AD was issued to prevent loss or fluctuation of indicated airspeed, which could result in misleading information being provided to the flightcrew. Accomplishing the replacement specified in paragraph (g) of this SNPRM would terminate the requirements of paragraph (f) of AD 2004–03–33, for that airplane only. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Service Bulletin A320–34–1170, Revision 30, dated June 18, 2015. • Service Bulletin A320–34–1456, Revision 01, dated May 15, 2012. • Service Bulletin A320–34–1463, Revision 01, dated May 15, 2012. The service information describes procedures for replacing certain Thales Avionics pitot probes on the captain, first officer, and standby sides. 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 SNPRM. E:\FR\FM\23DEP1.SGM 23DEP1 79752 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules Comments We gave the public the opportunity to participate in developing this SNPRM. We considered the comments received. American Airlines supports the proposed compliance time of 48 months for retrofit. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Request To Refer To Revised Service Information United Airlines (UAL) and Virgin America asked that the NPRM be revised to refer to Airbus Service Bulletin A320–34–1170, Revision 29, dated February 16, 2015. (The NPRM (80 FR 12094, March 6, 2015) referred to Airbus Service Bulletin A320–34– 1170, Revision 28, dated September 1, 2014, as the appropriate source of service information for replacing the pitot probes.) UAL stated that Airbus Service Bulletin A320–34–1170, Revision 29, dated February 16, 2015, includes UAL effectivity, as well as all A320 family airplanes fitted with Thales Pitot Probes. Virgin America stated that Airbus Service Bulletin A320–34–1170, Revision 28, dated September 1, 2014, is available only to select operators who previously purchased the change; Airbus Service Bulletin A320–34–1170, Revision 29, dated February 16, 2015, is available to all operators with airplanes having Thales pitot probes installed. American Airlines (AAL) asked that we refer to Airbus Service Bulletin A320– 34–1170, Revision 30, which is scheduled for release in the near future. AAL added that the effectivity in Airbus Service Bulletin A320–34–1170, Revision 28, dated September 1, 2014, is incomplete. We agree to refer to Airbus Service Bulletin A320–34–1170, Revision 30, dated June 18, 2015, for the pitot probe replacement. Airbus Service Bulletin A320–34–1170, Revision 30, dated June 18, 2015, was issued to update the operator list and related information in the effectivity, and does not include additional work. We have changed paragraph (g) of this SNPRM to refer to Airbus Service Bulletin A320–34–1170, Revision 30, dated June 18, 2015. In addition, to give credit for using Airbus Service Bulletin A320–34–1170, Revision 28, dated September 1, 2014, and Airbus Service Bulletin A320–34– 1170, Revision 29, dated February 16, 2015, we added new paragraphs (i)(1)(xxv) and (i)(1)(xxvi) to this SNPRM. Request To Reduce the Compliance Time The Airline Pilots Association International (ALPA) asked that the compliance time for replacement of the VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 pitot probes, as specified in paragraph (g) of the proposed AD (80 FR 12094, March 6, 2015), be reduced to 24 months or less. ALPA stated that it recognizes the potential flight safety risk of operating an airplane with reduced controllability characteristics, which justifies reducing the compliance time. We agree with the request to reduce the compliance time for replacement of the pitot probes. As specified under ‘‘Actions Since Previous NPRM was Issued,’’ we have reduced the proposed compliance time for replacing certain pitot probes based on a risk assessment due to additional reports of airspeed indication discrepancies while flying at high altitudes in inclement weather. EASA has issued Airworthiness Directive 2015–0205, dated October 9, 2015, to reduce the compliance time for replacement of the pitot probes to 24 months. We have changed the compliance time in paragraph (g) of this SNPRM accordingly. Request for Clarification AAL stated the use of a pitot probe which meets the current icing specification, as specified in the NPRM (80 FR 12094, March 6, 2015), should note that a new icing specification is forthcoming. In addition, the UTAS (formerly Goodrich) pitot probe having part number 0851HL is built to the current specification. AAL noted that the data available today shows that pitot probes on which the new icing requirement is met should be available for retrofit in 2016. We acknowledge the commenter’s statement about the NPRM proposing the use of a pitot probe that meets the current icing airworthiness requirements and not the new icing airworthiness requirements of Amendment 25–140 (79 FR 65508, November 4, 2014) to 14 CFR part 25. Since we are currently not aware of any pitot probes certified to the new icing airworthiness requirements, this SNPRM would mandate Goodrich pitot probes having part number 0851HL, which meet the icing airworthiness requirements in effect at the time of establishing the certification basis for Airbus Model A318, A319, A320, and A321 series airplanes. AAL may request approval for an alternative method of compliance for the installation of pitot probes that meet the new certification standards once the pitot probes are available for installation, under the provisions of paragraph (k)(1) of this proposed AD. AAL also asked the following related questions and we have provided a response to each comment: PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 • What FAA activities are scheduled with suppliers to meet the expectations of the new icing requirement? FAA activities associated with the new icing requirements are related to new design modifications. At this time we are not mandating installation of pitot probes which meet the new icing certification standards. • Does the FAA anticipate issuing a new AD mandating a retrofit/forward fit to the new icing requirement? We do not plan to issue further rulemaking mandating a retrofit/forward fit to the new icing requirement at this time. • Would the FAA extend the compliance time if another pitot probe supplier demonstrates compliance to the new icing requirement? We would not extend the compliance time because this SNPRM does not require installing pitot probes that meet the new icing requirement; therefore, the compliance time for the installation is considered adequate to address the unsafe condition. FAA’s Determination and Requirements of This SNPRM 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. Certain changes described above expand the scope of the proposed AD (80 FR 12094, March 6, 2015). As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. 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 E:\FR\FM\23DEP1.SGM 23DEP1 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 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 Airbus Service Bulletin A320–34–1170, Revision 30, dated June 18, 2015, 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 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 4 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $21,930 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $21,223,310, or $22,270 per product. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Authority for This Rulemaking 17:28 Dec 22, 2015 Jkt 238001 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 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. VerDate Sep<11>2014 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. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–0250; Directorate Identifier 2014–NM–216–AD. (a) Comments Due Date We must receive comments by January 22, 2016. (b) Affected ADs This AD affects AD 2004–03–33, Amendment 39–13477 (69 FR 9936, March 3, 2004). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. PO 00000 Frm 00035 Fmt 4702 Sfmt 4702 79753 (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 34, Navigation. (e) Reason This AD was prompted by reports of airspeed indication discrepancies while flying at high altitudes in inclement weather. We are issuing this AD to prevent airspeed indication discrepancies during inclement weather, which, depending on the prevailing altitude, could lead to unknown accumulation of ice crystals and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of Certain Pitot Probes on the Captain, First Officer, and Standby Sides Within 24 months after the effective date of this AD: Replace any Thales pitot probe having part number (P/N) C16195AA or P/N C16195BA, with a Goodrich pitot probe having P/N 0851HL, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–34–1170, Revision 30, dated June 18, 2015. Accomplishing the replacement in this paragraph terminates the requirements of paragraph (f) of AD 2004– 03–33, Amendment 39–13477 (69 FR 9936, March 3, 2004), for that airplane only. (h) Optional Methods of Compliance for Replacement Required by Paragraph (g) of This AD (1) Replacement of the pitot probes in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 34–1456, Revision 01, dated May 15, 2012 (pitot probes on the captain and standby sides); and Airbus Service Bulletin A320–34– 1463, Revision 01, dated May 15, 2012 (pitot probes on the first officer side); is an acceptable method of compliance with the requirements of paragraph (g) of this AD. (2) Airplanes on which Airbus Modification 25578 was embodied in production, except for post-modification 25578 airplanes on which Airbus Modification 155737 (installation of Thales pitot probes) was also embodied in production, are compliant with the requirements of paragraph (g) of this AD, provided it can be conclusively determined that no Thales pitot probe having P/N C16195AA, P/N C16195BA, or P/N 50620–10 has been installed since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness. Post-modification 25578 airplanes on which Airbus Modification 155737 (installation of Thales pitot probes) was also embodied in production must be in compliance with the requirements of paragraph (g) of this AD. (i) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service E:\FR\FM\23DEP1.SGM 23DEP1 asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 79754 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules information identified in paragraph (i)(1)(i) through (i)(1)(xxvi) of this AD. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A320–34–1170, Revision 04, dated May 24, 2000. (ii) Airbus Service Bulletin A320–34–1170, Revision 05, dated September 11, 2000. (iii) Airbus Service Bulletin A320–34– 1170, Revision 06, dated October 18, 2001. (iv) Airbus Service Bulletin A320–34– 1170, Revision 07, dated December 4, 2001. (v) Airbus Service Bulletin A320–34–1170, Revision 08, dated January 15, 2003. (vi) Airbus Service Bulletin A320–34– 1170, Revision 09, dated February 17, 2003. (vii) Airbus Service Bulletin A320–34– 1170, Revision 10, dated November 21, 2003. (viii) Airbus Service Bulletin A320–34– 1170, Revision 11, dated August 18, 2004. (ix) Airbus Service Bulletin A320–34– 1170, Revision 12, dated December 2, 2004. (x) Airbus Service Bulletin A320–34–1170, Revision 13, dated January 18, 2005. (xi) Airbus Service Bulletin A320–34– 1170, Revision 14, dated April 21, 2005. (xii) Airbus Service Bulletin A320–34– 1170, Revision 15, dated July 19, 2005. (xiii) Airbus Service Bulletin A320–34– 1170, Revision 16, dated November 23, 2006. (xiv) Airbus Service Bulletin A320–34– 1170, Revision 17, dated February 14, 2007. (xv) Airbus Service Bulletin A320–34– 1170, Revision 18, dated October 9, 2009. (xvi) Airbus Service Bulletin A320–34– 1170, Revision 19, dated November 9, 2009. (xvii) Airbus Service Bulletin A320–34– 1170, Revision 20, dated December 1, 2010. (xviii) Airbus Service Bulletin A320–34– 1170, Revision 21, dated March 24, 2011. (xix) Airbus Service Bulletin A320–34– 1170, Revision 22, dated July 19, 2011. (xx) Airbus Service Bulletin A320–34– 1170, Revision 23, dated February 3, 2012. (xxi) Airbus Service Bulletin A320–34– 1170, Revision 24, dated April 12, 2012. (xxii) Airbus Service Bulletin A320–34– 1170, Revision 25, dated September 4, 2012. (xxiii) Airbus Service Bulletin A320–34– 1170, Revision 26, dated September 16, 2013. (xxiv) Airbus Service Bulletin A320–34– 1170, Revision 27, dated March 18, 2014. (xxv) Airbus Service Bulletin A320–34– 1170, Revision 28, dated September 1, 2014. (xxvi) Airbus Service Bulletin A320–34– 1170, Revision 29, dated February 16, 2015. (2) This paragraph provides credit for the replacement of pitot probes on the captain and standby sides specified in paragraph (h)(1) of this AD, if the replacement was performed before the effective date of this AD using Airbus Service Bulletin A320–34–1456, dated December 2, 2009, which is not incorporated by reference in this AD. (3) This paragraph provides credit for the replacement of pitot probes on the first officer side as specified in paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–34–1463, dated March 9, 2010, which is not incorporated by reference in this AD. (j) Parts Installation Limitations (1) At the applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD: No VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 person may install on any airplane a Thales pitot probe having P/N C16195AA or P/N C16195BA. (i) For airplanes with a Thales pitot probe having P/N C16195AA or P/N C16195BA installed: After accomplishing the replacement required by paragraph (g) of this AD. (ii) For airplanes without a Thales pitot probe having P/N C16195AA or P/N C16195BA installed: As of the effective date of this AD. (2) As of the effective date of this AD, no person may install on any airplane a Thales pitot probe having part number P/N 50620– 10. (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: 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. (l) Related Information (1) Refer to EASA Airworthiness Directive 2015–0205, dated October 9, 2015, for related information. This MCAI may be found in the PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–0250. (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 25, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–30821 Filed 12–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7527; Directorate Identifier 2015–NM–094–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. This proposed AD would require modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. This proposed AD would also require an inspection to identify the part number of the motor operated valve (MOV) actuators for the left and right engine fuel spar valves; replacement of specified MOV actuators with new MOV actuators; certain bonding resistance measurements; and applicable corrective actions. We are proposing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as SUMMARY: E:\FR\FM\23DEP1.SGM 23DEP1

Agencies

[Federal Register Volume 80, Number 246 (Wednesday, December 23, 2015)]
[Proposed Rules]
[Pages 79750-79754]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30821]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0250; Directorate Identifier 2014-NM-216-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. 
The NPRM proposed to require replacing certain pitot probes on the 
captain, first officer, and standby sides with certain new pitot 
probes. The NPRM was prompted by reports of airspeed indication 
discrepancies while flying at high altitudes in inclement weather. This 
action revises the NPRM by reducing the proposed compliance time for 
replacing certain pitot probes based on a risk assessment due to 
additional reports of airspeed indication discrepancies while flying at 
high altitudes in inclement weather. We are proposing this supplemental 
NPRM (SNPRM) to prevent airspeed indication discrepancies during 
inclement weather, which, depending on the prevailing altitude, could 
lead to unknown accumulation of ice crystals and consequent reduced 
controllability of the airplane. Since these actions impose an 
additional burden over those proposed in the NPRM, we are reopening the 
comment period to allow the public the chance to comment on these 
proposed changes.

DATES: We must receive comments on this SNPRM by January 22, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey

[[Page 79751]]

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-
0250; 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 
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-2015-0250; 
Directorate Identifier 2014-NM-216-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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on March 6, 2015 (80 FR 12094) (``the NPRM''). The 
NPRM was prompted by reports of airspeed indication discrepancies while 
flying at high altitudes in inclement weather. The NPRM proposed to 
require replacing certain pitot probes on the captain, first officer, 
and standby sides with certain new pitot probes.

Actions Since Previous NPRM (80 FR 12094, March 6, 2015) Was Issued

    Since we issued the NPRM (80 FR 12094, March 6, 2015), we have 
determined it is necessary to reduce the compliance time for replacing 
certain pitot probes based on a risk assessment due to additional 
reports of airspeed indication discrepancies while flying at high 
altitudes in inclement weather. The European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Union, issued EASA Airworthiness Directive 2015-0205, dated 
October 9, 2015 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition on all Airbus Model A318, A319, A320, and A321 series 
airplanes. The MCAI states:

    Occurrences have been reported on A320 family aeroplanes of 
airspeed indication discrepancies while flying at high altitudes in 
inclement weather conditions. Investigation results indicated that 
A320 aeroplanes equipped with Thales Avionics Part Number (P/N) 
50620-10 or P/N C16195AA pitot probes appear to have a greater 
susceptibility to adverse environmental conditions that aeroplanes 
equipped with certain other pitot probes.
    Prompted by earlier occurrences, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [DGAC] AD 
2001[dash]362 [http://ad.easa.europa.eu/blob/easa_ad_2001_362.pdf/AD_2001-362] [which corresponds to paragraph (f) of FAA AD 
2004[dash]03[dash]33, Amendment 39[dash]13477 (69 FR 9936, March 3, 
2004)] to require replacement of Thales (formerly known as Sextant) 
P/N 50620[dash]10 pitot probes with Thales P/N C16195AA probes.
    Since that [DGAC] AD was issued, Thales pitot probe P/N C15195BA 
was designed, which improved airspeed indication behavior in heavy 
rain conditions, but did not demonstrate the same level of 
robustness to withstand high[dash]altitude ice crystals. Based on 
these findings, EASA have decided to implement replacement of the 
affected Thales [pitot] probes as a precautionary measure to improve 
the safety level of the affected aeroplanes.
    Consequently, EASA issued AD 2014-0237 (later revised) [http://ad.easa.europa.eu/blob/easa_ad_2014_0237.pdf/AD_2014-0237], 
retaining the requirements of DGAC France AD 2001-362, which was 
superseded, and cancelling two other DGAC ADs, to require 
replacement of Thales Avionics pitot probes P/N C16195AA and P/N 
C16195BA.
    Since EASA issued AD 2014-0237R1 [http://ad.easa.europa.eu/ad/2014-0237R1] was issued, results of further analyses have determined 
that the compliance time (48 months) of that AD has to be reduced in 
relation to the risk assessment.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0237R1, which is superseded, but 
reduces the compliance time.

    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-
0250.

Related Rulemaking

    On February 4, 2004, we issued AD 2004-03-33, Amendment 39-13477 
(69 FR 9936, March 3, 2004), applicable to certain Airbus Model A300 B2 
and B4 series airplanes; Model A300 B4-600, A300 B4-600R, and A300 F4-
600R series airplanes; Model A310 series Airplanes; Model A319, A320, 
and A321 series airplanes; Model A330-301, -321, -322, -341, and -342 
airplanes; and Model A340 series airplanes. That AD requires, among 
other actions, replacement of certain pitot probes with certain new 
pitot probes. That AD was issued to prevent loss or fluctuation of 
indicated airspeed, which could result in misleading information being 
provided to the flightcrew. Accomplishing the replacement specified in 
paragraph (g) of this SNPRM would terminate the requirements of 
paragraph (f) of AD 2004-03-33, for that airplane only.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Service Bulletin A320-34-1170, Revision 30, dated June 18, 
2015.
     Service Bulletin A320-34-1456, Revision 01, dated May 15, 
2012.
     Service Bulletin A320-34-1463, Revision 01, dated May 15, 
2012.
    The service information describes procedures for replacing certain 
Thales Avionics pitot probes on the captain, first officer, and standby 
sides. 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 
SNPRM.

[[Page 79752]]

Comments

    We gave the public the opportunity to participate in developing 
this SNPRM. We considered the comments received.
    American Airlines supports the proposed compliance time of 48 
months for retrofit.

Request To Refer To Revised Service Information

    United Airlines (UAL) and Virgin America asked that the NPRM be 
revised to refer to Airbus Service Bulletin A320-34-1170, Revision 29, 
dated February 16, 2015. (The NPRM (80 FR 12094, March 6, 2015) 
referred to Airbus Service Bulletin A320-34-1170, Revision 28, dated 
September 1, 2014, as the appropriate source of service information for 
replacing the pitot probes.) UAL stated that Airbus Service Bulletin 
A320-34-1170, Revision 29, dated February 16, 2015, includes UAL 
effectivity, as well as all A320 family airplanes fitted with Thales 
Pitot Probes. Virgin America stated that Airbus Service Bulletin A320-
34-1170, Revision 28, dated September 1, 2014, is available only to 
select operators who previously purchased the change; Airbus Service 
Bulletin A320-34-1170, Revision 29, dated February 16, 2015, is 
available to all operators with airplanes having Thales pitot probes 
installed. American Airlines (AAL) asked that we refer to Airbus 
Service Bulletin A320-34-1170, Revision 30, which is scheduled for 
release in the near future. AAL added that the effectivity in Airbus 
Service Bulletin A320-34-1170, Revision 28, dated September 1, 2014, is 
incomplete.
    We agree to refer to Airbus Service Bulletin A320-34-1170, Revision 
30, dated June 18, 2015, for the pitot probe replacement. Airbus 
Service Bulletin A320-34-1170, Revision 30, dated June 18, 2015, was 
issued to update the operator list and related information in the 
effectivity, and does not include additional work. We have changed 
paragraph (g) of this SNPRM to refer to Airbus Service Bulletin A320-
34-1170, Revision 30, dated June 18, 2015. In addition, to give credit 
for using Airbus Service Bulletin A320-34-1170, Revision 28, dated 
September 1, 2014, and Airbus Service Bulletin A320-34-1170, Revision 
29, dated February 16, 2015, we added new paragraphs (i)(1)(xxv) and 
(i)(1)(xxvi) to this SNPRM.

Request To Reduce the Compliance Time

    The Airline Pilots Association International (ALPA) asked that the 
compliance time for replacement of the pitot probes, as specified in 
paragraph (g) of the proposed AD (80 FR 12094, March 6, 2015), be 
reduced to 24 months or less. ALPA stated that it recognizes the 
potential flight safety risk of operating an airplane with reduced 
controllability characteristics, which justifies reducing the 
compliance time.
    We agree with the request to reduce the compliance time for 
replacement of the pitot probes. As specified under ``Actions Since 
Previous NPRM was Issued,'' we have reduced the proposed compliance 
time for replacing certain pitot probes based on a risk assessment due 
to additional reports of airspeed indication discrepancies while flying 
at high altitudes in inclement weather. EASA has issued Airworthiness 
Directive 2015-0205, dated October 9, 2015, to reduce the compliance 
time for replacement of the pitot probes to 24 months. We have changed 
the compliance time in paragraph (g) of this SNPRM accordingly.

Request for Clarification

    AAL stated the use of a pitot probe which meets the current icing 
specification, as specified in the NPRM (80 FR 12094, March 6, 2015), 
should note that a new icing specification is forthcoming. In addition, 
the UTAS (formerly Goodrich) pitot probe having part number 0851HL is 
built to the current specification. AAL noted that the data available 
today shows that pitot probes on which the new icing requirement is met 
should be available for retrofit in 2016.
    We acknowledge the commenter's statement about the NPRM proposing 
the use of a pitot probe that meets the current icing airworthiness 
requirements and not the new icing airworthiness requirements of 
Amendment 25-140 (79 FR 65508, November 4, 2014) to 14 CFR part 25. 
Since we are currently not aware of any pitot probes certified to the 
new icing airworthiness requirements, this SNPRM would mandate Goodrich 
pitot probes having part number 0851HL, which meet the icing 
airworthiness requirements in effect at the time of establishing the 
certification basis for Airbus Model A318, A319, A320, and A321 series 
airplanes. AAL may request approval for an alternative method of 
compliance for the installation of pitot probes that meet the new 
certification standards once the pitot probes are available for 
installation, under the provisions of paragraph (k)(1) of this proposed 
AD.
    AAL also asked the following related questions and we have provided 
a response to each comment:
     What FAA activities are scheduled with suppliers to meet 
the expectations of the new icing requirement? FAA activities 
associated with the new icing requirements are related to new design 
modifications. At this time we are not mandating installation of pitot 
probes which meet the new icing certification standards.
     Does the FAA anticipate issuing a new AD mandating a 
retrofit/forward fit to the new icing requirement? We do not plan to 
issue further rulemaking mandating a retrofit/forward fit to the new 
icing requirement at this time.
     Would the FAA extend the compliance time if another pitot 
probe supplier demonstrates compliance to the new icing requirement? We 
would not extend the compliance time because this SNPRM does not 
require installing pitot probes that meet the new icing requirement; 
therefore, the compliance time for the installation is considered 
adequate to address the unsafe condition.

FAA's Determination and Requirements of This SNPRM

    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.
    Certain changes described above expand the scope of the proposed AD 
(80 FR 12094, March 6, 2015). As a result, we have determined that it 
is necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this SNPRM.

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

[[Page 79753]]

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 
Airbus Service Bulletin A320-34-1170, Revision 30, dated June 18, 2015, 
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 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 4 work-hours per product 
to comply with the new basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $21,930 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $21,223,310, or $22,270 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-2015-0250; Directorate Identifier 2014-NM-
216-AD.

(a) Comments Due Date

    We must receive comments by January 22, 2016.

(b) Affected ADs

    This AD affects AD 2004-03-33, Amendment 39-13477 (69 FR 9936, 
March 3, 2004).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any 
category, all manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 34, Navigation.

(e) Reason

    This AD was prompted by reports of airspeed indication 
discrepancies while flying at high altitudes in inclement weather. 
We are issuing this AD to prevent airspeed indication discrepancies 
during inclement weather, which, depending on the prevailing 
altitude, could lead to unknown accumulation of ice crystals and 
consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Replacement of Certain Pitot Probes on the Captain, First Officer, 
and Standby Sides

    Within 24 months after the effective date of this AD: Replace 
any Thales pitot probe having part number (P/N) C16195AA or P/N 
C16195BA, with a Goodrich pitot probe having P/N 0851HL, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-34-1170, Revision 30, dated June 18, 2015. 
Accomplishing the replacement in this paragraph terminates the 
requirements of paragraph (f) of AD 2004-03-33, Amendment 39-13477 
(69 FR 9936, March 3, 2004), for that airplane only.

(h) Optional Methods of Compliance for Replacement Required by 
Paragraph (g) of This AD

    (1) Replacement of the pitot probes in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-34-1456, 
Revision 01, dated May 15, 2012 (pitot probes on the captain and 
standby sides); and Airbus Service Bulletin A320-34-1463, Revision 
01, dated May 15, 2012 (pitot probes on the first officer side); is 
an acceptable method of compliance with the requirements of 
paragraph (g) of this AD.
    (2) Airplanes on which Airbus Modification 25578 was embodied in 
production, except for post-modification 25578 airplanes on which 
Airbus Modification 155737 (installation of Thales pitot probes) was 
also embodied in production, are compliant with the requirements of 
paragraph (g) of this AD, provided it can be conclusively determined 
that no Thales pitot probe having P/N C16195AA, P/N C16195BA, or P/N 
50620-10 has been installed since the date of issuance of the 
original certificate of airworthiness or the date of issuance of the 
original export certificate of airworthiness. Post-modification 
25578 airplanes on which Airbus Modification 155737 (installation of 
Thales pitot probes) was also embodied in production must be in 
compliance with the requirements of paragraph (g) of this AD.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service

[[Page 79754]]

information identified in paragraph (i)(1)(i) through (i)(1)(xxvi) 
of this AD. This service information is not incorporated by 
reference in this AD.
    (i) Airbus Service Bulletin A320-34-1170, Revision 04, dated May 
24, 2000.
    (ii) Airbus Service Bulletin A320-34-1170, Revision 05, dated 
September 11, 2000.
    (iii) Airbus Service Bulletin A320-34-1170, Revision 06, dated 
October 18, 2001.
    (iv) Airbus Service Bulletin A320-34-1170, Revision 07, dated 
December 4, 2001.
    (v) Airbus Service Bulletin A320-34-1170, Revision 08, dated 
January 15, 2003.
    (vi) Airbus Service Bulletin A320-34-1170, Revision 09, dated 
February 17, 2003.
    (vii) Airbus Service Bulletin A320-34-1170, Revision 10, dated 
November 21, 2003.
    (viii) Airbus Service Bulletin A320-34-1170, Revision 11, dated 
August 18, 2004.
    (ix) Airbus Service Bulletin A320-34-1170, Revision 12, dated 
December 2, 2004.
    (x) Airbus Service Bulletin A320-34-1170, Revision 13, dated 
January 18, 2005.
    (xi) Airbus Service Bulletin A320-34-1170, Revision 14, dated 
April 21, 2005.
    (xii) Airbus Service Bulletin A320-34-1170, Revision 15, dated 
July 19, 2005.
    (xiii) Airbus Service Bulletin A320-34-1170, Revision 16, dated 
November 23, 2006.
    (xiv) Airbus Service Bulletin A320-34-1170, Revision 17, dated 
February 14, 2007.
    (xv) Airbus Service Bulletin A320-34-1170, Revision 18, dated 
October 9, 2009.
    (xvi) Airbus Service Bulletin A320-34-1170, Revision 19, dated 
November 9, 2009.
    (xvii) Airbus Service Bulletin A320-34-1170, Revision 20, dated 
December 1, 2010.
    (xviii) Airbus Service Bulletin A320-34-1170, Revision 21, dated 
March 24, 2011.
    (xix) Airbus Service Bulletin A320-34-1170, Revision 22, dated 
July 19, 2011.
    (xx) Airbus Service Bulletin A320-34-1170, Revision 23, dated 
February 3, 2012.
    (xxi) Airbus Service Bulletin A320-34-1170, Revision 24, dated 
April 12, 2012.
    (xxii) Airbus Service Bulletin A320-34-1170, Revision 25, dated 
September 4, 2012.
    (xxiii) Airbus Service Bulletin A320-34-1170, Revision 26, dated 
September 16, 2013.
    (xxiv) Airbus Service Bulletin A320-34-1170, Revision 27, dated 
March 18, 2014.
    (xxv) Airbus Service Bulletin A320-34-1170, Revision 28, dated 
September 1, 2014.
    (xxvi) Airbus Service Bulletin A320-34-1170, Revision 29, dated 
February 16, 2015.
    (2) This paragraph provides credit for the replacement of pitot 
probes on the captain and standby sides specified in paragraph 
(h)(1) of this AD, if the replacement was performed before the 
effective date of this AD using Airbus Service Bulletin A320-34-
1456, dated December 2, 2009, which is not incorporated by reference 
in this AD.
    (3) This paragraph provides credit for the replacement of pitot 
probes on the first officer side as specified in paragraph (h)(1) of 
this AD, if those actions were performed before the effective date 
of this AD using Airbus Service Bulletin A320-34-1463, dated March 
9, 2010, which is not incorporated by reference in this AD.

(j) Parts Installation Limitations

    (1) At the applicable time specified in paragraph (j)(1)(i) or 
(j)(1)(ii) of this AD: No person may install on any airplane a 
Thales pitot probe having P/N C16195AA or P/N C16195BA.
    (i) For airplanes with a Thales pitot probe having P/N C16195AA 
or P/N C16195BA installed: After accomplishing the replacement 
required by paragraph (g) of this AD.
    (ii) For airplanes without a Thales pitot probe having P/N 
C16195AA or P/N C16195BA installed: As of the effective date of this 
AD.
    (2) As of the effective date of this AD, no person may install 
on any airplane a Thales pitot probe having part number P/N 50620-
10.

(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: 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.

(l) Related Information

    (1) Refer to EASA Airworthiness Directive 2015-0205, dated 
October 9, 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-2015-0250.
    (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 25, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30821 Filed 12-22-15; 8:45 am]
 BILLING CODE 4910-13-P