Airworthiness Directives; Airbus Airplanes, 14404-14408 [2016-05830]

Download as PDF 14404 Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules (c) Applicability This AD applies to The Boeing Company Model 777–200 and -300 series airplanes equipped with Rolls-Royce Model Trent 800 engines. (d) Subject Air Transport Association (ATA) of America Code 78, Engine Exhaust. (e) Unsafe Condition This AD was prompted by reports of damage to the upper bifurcation forward fire seal and seal deflector, and localized damage to the insulation blanket installed just aft of the fire seal. We are issuing this AD to prevent a breach in the engine firewall due to a failed upper bifurcation forward fire seal. A breach could delay or prevent the fire detection and suppression system from functioning properly, and could result in an increased risk of a fire, prolonged burning, and breach of the fire zone; and could allow fire to reach unprotected areas of the engine, the strut, and wing after engine shutdown. Also, fan air bypassing the seal could cause localized damage to the thrust reverser (T/R) insulation blanket installed just aft of the fire seal, which could allow limited thermal degradation of the thrust reverser inner wall. This could aggravate existing damage and cause the thrust reverser’s inner wall to fail. (f) Compliance Comply with this AD within the compliance times specified, unless already done. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (g) Installation of Serviceable T/R Halves on Each Engine Within 60 months after the effective date of this AD: Install serviceable left and right T/R halves on the left and right engines, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78–0101, Revision 1, dated October 30, 2015. A serviceable T/R half is defined in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78–0101, Revision 1, dated October 30, 2015. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (i) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing VerDate Sep<11>2014 16:06 Mar 16, 2016 Jkt 238001 Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (h)(4)(i) and (h)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (i) Related Information (1) For more information about this AD, contact Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.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. Issued in Renton, Washington, on March 9, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–05831 Filed 3–16–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–4226; Directorate Identifier 2015–NM–095–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 We propose to supersede Airworthiness Directive (AD) 2003–25– 07 for certain Airbus Model A319 and A320 series airplanes; and AD 2005–13– 39 for certain Airbus Model A321 series airplanes. AD 2003–25–07 currently requires a revision to the airplane flight manual (AFM) and replacement of both elevator aileron computers (ELACs) having L80 standards with new ELACs having L81 standards. AD 2005–13–39 currently requires a revision to the AFM, replacement of existing ELACs with ELACs having either L83 or L91 standards, as applicable; and a concurrent action. Since we issued AD 2003–25–07 and AD 2005–13–39, we have determined that new ELAC standards must be incorporated. The ELAC standards have been upgraded to version L97+, which implements enhanced angle-of-attack (AOA) monitoring to better detect AOA blockage, including multiple AOA blockages. This proposed AD would require replacing existing ELACs with new ELACs having L97+ standards or revising the software in an existing ELAC to the L97+ standards, as applicable, which would terminate the requirements of AD 2003–25–07 and AD 2005–13–39. This proposed AD would also add Airbus Model A318 series airplanes to the applicability. We are proposing this AD to prevent inadvertent activation of the AOA protections. Inadvertent activation of the AOA protections could result in a continuous nose down pitch rate that could result in reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by May 2, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, 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; SUMMARY: E:\FR\FM\17MRP1.SGM 17MRP1 Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules 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–2016– 4226; 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: asabaliauskas on DSK3SPTVN1PROD 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–2016–4226; Directorate Identifier 2015–NM–095–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On December 5, 2003, we issued AD 2003–25–07, Amendment 39–13390 (68 FR 70431, December 18, 2003). AD 2003–25–07 requires a revision of the AFM and replacement of both ELACs having L80 standards with new ELACs having L81 standards on Airbus Model A319 and A320 series airplanes equipped with L80 standards. The replacement of both ELACs terminates the requirement for the AFM revision. VerDate Sep<11>2014 16:06 Mar 16, 2016 Jkt 238001 14405 On June 17, 2005, we issued AD 2005–13–39, Amendment 39–14176 (70 FR 38580, July 5, 2005). AD 2005–13– 39 requires a revision of the AFM, a concurrent action, and replacement of existing ELACs with ELACs having L83 or L91 standards on certain Airbus Model A321 series airplanes. Since we issued AD 2003–25–07, Amendment 39–13390 (68 FR 70431, December 18, 2003); and AD 2005–13– 39, Amendment 39–14176 (70 FR 38580, July 5, 2005); we have determined that new ELAC standards must be incorporated. The ELAC standard software has been updated to version L97+ and the hardware is available in a data loadable version and a non-data-loadable version. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0088R1, dated June 2, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states: existing ELACs to L97+ standards. This proposed AD also adds Airbus Model A318 series airplanes to the applicability. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–4226. The latest elevator aileron computer (ELAC) standard, L97+, implements enhanced Angle of Attack (AOA) monitoring in order to better detect cases of AOA blockage, including multiple AOA blockage. Two ELAC L97+ versions are currently available, Part Number (P/N) 3945129109 with data loading capability, and P/N 3945128215 without the data loading capability. Three existing [EASA] ADs requiring installation of earlier ELAC (software) have been identified and taken into account for cancellation by this new [EASA] AD. For the reasons described above, EASA issued AD 2015–0088, cancelling DGAC ´ ´ [Direction Generale de l’Aviation Civile] France AD 95–203–072 (no requirements retained) [which corresponds to FAA AD 98– 09–18, Amendment 39–10499 (63 FR 23374, April 29, 1998)], and partially retaining the requirements of DGAC France AD 2001–508 [which corresponds to FAA AD 2003–25–07, Amendment 39–13390 (68 FR 70431, December 18, 2003), and [DGAC] AD F– 2004–147 (EASA approval ref. 2004–8601) [which corresponds to FAA AD 2005–13–39, Amendment 39–14176 (70 FR 38580, July 5, 2005)], which were superseded, and to require replacement of all ELAC with ELAC L97+ standard. Since that [EASA] AD was issued, some errors were detected in Appendix 1 of the [EASA] AD, and one P/N ELAC was inadvertently omitted. This [EASA] AD revises EASA AD 2015–0088 to correct these errors and to add clarification to paragraph (7) [of the EASA AD]. 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. The required actions include either replacing existing ELACs with new ELACs having L97+ standards uploaded, or revising the software in the PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–27–1243, dated March 17, 2015. The service information describes procedures for replacing the existing ELACs with new ELACs having L97+ standards, and modifying existing ELACs into units with L97+ standards. Airbus has also issued Service Bulletin A320–27–1244, dated March 5, 2015. The service information describes procedures for modification of an airplane by replacing any existing ELAC unit with an ELAC 97+ unit having P/N 3945128215. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this proposed AD affects 940 airplanes of U.S. registry. The actions required by AD 2003–25– 07, Amendment 39–13390 (68 FR 70431, December 18, 2003), and retained in this proposed AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2003–25–07 is $85 per product. The actions required by AD 2005–13– 39, Amendment 39–14176 (70 FR 38580, July 5, 2005), and retained in this proposed AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2005–13–39 is $85 per product. E:\FR\FM\17MRP1.SGM 17MRP1 14406 Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules We also estimate that it would take about 3 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 $7,230 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $7,035,900, or $7,485 per product. According to the parts manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS 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, VerDate Sep<11>2014 16:06 Mar 16, 2016 Jkt 238001 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: a. Removing Airworthiness Directive (AD) 2003–25–07, Amendment 39– 13390 (68 FR 70431, December 18, 2003); and AD 2005–13–39, Amendment 39–14176 (70 FR 38580, July 5, 2005); and ■ b. Adding the following new AD: ■ ■ Airbus: Docket No. FAA–2016–4226; Directorate Identifier 2015–NM–095–AD. (a) Comments Due Date We must receive comments by May 2, 2016. (b) Affected ADs This AD replaces AD 2003–25–07, Amendment 39–13390 (68 FR 70431, December 18, 2003); and AD 2005–13–39, Amendment 39–14176 (70 FR 38580, July 5, 2005). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (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 27, Flight Controls. (e) Reason This AD was prompted by a determination that new elevator aileron computers (ELAC) standards must be incorporated. The ELAC standards have been upgraded to version L97+, which implements enhanced angle-of- PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 attack (AOA) monitoring to better detect AOA blockage, including multiple AOA blockages. We are issuing this AD to prevent inadvertent activation of the AOA protections. Inadvertent activation of the AOA protections could result in a continuous nose down pitch rate that could result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Replacement of ELAC L80 Units With L81 Units, With No Changes For Model A319 and A320 series airplanes, equipped with ELAC L80 standards having part numbers listed in Airbus Service Bulletin A320–27–1135, dated June 29, 2001: This paragraph restates the requirements of paragraph (b) of AD 2003–25–07, Amendment 39–13390 (68 FR 70431, December 18, 2003), with no changes. Within 1 year after January 22, 2004 (the effective date of AD 2003–25–07): Replace both ELACs having L80 standards with new ELACs having L81 standards, by doing all the actions per paragraphs A., B., C., and D. of the Accomplishment Instructions of Airbus Service Bulletin A320–27–1135, dated June 29, 2001. (h) Retained Installation of ELAC L83 or L91 Software, With No Changes For Model A321–111, –112, –131, –211, and –231 airplanes, except those with Airbus Modification 34043 installed in production: This paragraph restates the requirements of paragraph (g) of AD 2005–13–39, Amendment 39–14176 (70 FR 38580, July 5, 2005), with no changes. Within 16 months after August 9, 2005 (the effective date of AD 2005–13–39): Replace existing ELACs with ELACs having L83 standards, by accomplishing all of the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320–27–1151, dated March 9, 2004, including Appendix 01, dated March 9, 2004; or with ELACs having L91 standards, by accomplishing all of the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320–27–1152, dated June 4, 2004, including Appendix 01, dated June 4, 2004; as applicable. (i) New Requirement of This AD: ELAC Replacement or Modification At the applicable times specified in table 1 to paragraph (i) of this AD: Replace each ELAC unit with an ELAC L97+ unit having part number (P/N) 3945129100 and software having P/N 3945129109, or modify existing ELAC units into ELAC L97+ units having P/ N 3945129100 with L97+ operational software P/N 3945129109 loaded, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1243, dated March 17, 2015. Accomplishing this replacement terminates the actions required by paragraphs (g) and (h) of this AD. E:\FR\FM\17MRP1.SGM 17MRP1 14407 Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules TABLE 1 TO PARAGRAPH (I) OF THIS AD—COMPLIANCE TIMES Compliance time (after the effective date of this AD) Airbus airplane models Model A318 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N tions (captain, first officer, and standby). Model A319 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N tions (captain, first officer, and standby). Model A320 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N tions (captain, first officer, and standby). Model A321 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N tions (captain, first officer, and standby). Model A318, A319, A320, and A321 series airplanes that do not have UTAS (formerly P/N 0861ED2 installed in all 3 positions (captain, first officer, and standby). (j) Optional Method of Compliance Modification of an airplane by replacing any existing ELAC unit with an ELAC 97+ unit having P/N 3945128215, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1244, dated March 5, 2015, is an acceptable method of compliance for the requirements of paragraph (i) of this AD, for only that modified airplane. Accomplishing this modification terminates the actions required by paragraphs (g) and (h) of this AD for that modified airplane. 0861ED2 installed in all 3 posi- Within 5 months. 0861ED2 installed in all 3 posi- Within 10 months. 0861ED2 installed in all 3 posi- Within 10 months. 0861ED2 installed in all 3 posi- Within 5 months. Goodrich) AOA P/N 0861ED or Within 25 months. Note 1 to paragraph (j) of this AD: ELAC unit P/N 3945128215 is not data-loadable, but it is fully interchangeable and mixable with data-loadable ELAC 97+ unit P/N 3945129100 with software P/N 3945129109 loaded. (k) Exclusion From Requirements of Paragraphs (g), (h), and (i), and the Actions in Paragraph (j), of This AD Airplanes on which Airbus Modification 156546 (installation of ELAC L97+ with software P/N 3945129109) was installed in production are excluded from the requirements of paragraphs (g), (h), and (i) of this AD and the actions specified in paragraph (j) of this AD, provided it can be determined that no ELAC having a part number identified in table 2 to paragraph (k) of this AD has been installed on that airplane since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness. TABLE 2 TO PARAGRAPH (k) OF THIS AD—PROHIBITED ELAC PART NUMBERS asabaliauskas on DSK3SPTVN1PROD with PROPOSALS Part number Designation 3945122202 ............................................ 3945122203 ............................................ 3945122303 ............................................ 3945122304 ............................................ 3945122305 ............................................ 3945122306 ............................................ 3945122307 ............................................ C12370AA01 ........................................... 3945122501 ............................................ 3945122502 ............................................ 3945122503 ............................................ 3945122504 ............................................ 3945122505 ............................................ 3945123505 ............................................ 3945128101 ............................................ 3945122506 ............................................ 3945123506 ............................................ 3945128102 ............................................ 3945122507 ............................................ 3945123507 ............................................ 3945128103 ............................................ 3945122608 ............................................ 3945123608 ............................................ 3945122609 ............................................ 3945123609 ............................................ 3945128204 ............................................ 3945128205 ............................................ 3945128206 ............................................ 3945129101 ............................................ 3945128207 ............................................ 3945128208 ............................................ 3945128209 ............................................ 3945129103 ............................................ 3945128210 ............................................ 3945129104 ............................................ 3945128212 ............................................ 3945129106 ............................................ 3945129107 ............................................ 3945128214 ............................................ 3945129108 ............................................ VerDate Sep<11>2014 16:06 Mar 16, 2016 ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC ELAC Jkt 238001 FIN A320–111 Type Def ..................................................................................... L50C ............................................................................................................. L50C ............................................................................................................. L60 ............................................................................................................... L61B ............................................................................................................. L61F ............................................................................................................. L62C ............................................................................................................. L68C ............................................................................................................. L69 ............................................................................................................... L69J .............................................................................................................. L77 ............................................................................................................... L78 ............................................................................................................... A L80 ............................................................................................................ A’ L80 ........................................................................................................... B L80 ............................................................................................................ A L81 ............................................................................................................ A’ L81 ........................................................................................................... B L81 ............................................................................................................ A L82 ............................................................................................................ A’ L82 ........................................................................................................... B L82 ............................................................................................................ A L83 ............................................................................................................ A’ L83 ........................................................................................................... A L84 ............................................................................................................ A’ L84 ........................................................................................................... B L90L .......................................................................................................... B L90N ......................................................................................................... B L91 ............................................................................................................ B L91 data loadable ..................................................................................... B L92 ............................................................................................................ B L92L .......................................................................................................... B L93 ............................................................................................................ B L93 data loadable ..................................................................................... B L94 ............................................................................................................ B L94 data loadable ..................................................................................... B L96 ............................................................................................................ B L96 data loadable ..................................................................................... B L96 H–A data loadable ............................................................................. B L97 ............................................................................................................ B L97 data loadable ..................................................................................... PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\17MRP1.SGM 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE CE 17MRP1 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2. 1/2 SW1. 1/2. 1/2. 1/2. 1/2 SW1. 1/2. 1/2 SW1. 1/2. 1/2 SW1. 1/2 SW1. 1/2. 1/2 SW1. 14408 Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules (l) Later-Approved Parts Installation of an ELAC version (part number) approved after the effective date of this AD is an approved method of compliance with the requirements of paragraphs (i) and (j) of this AD, provided the requirements specified in paragraphs (l)(1) and (l)(2) of this AD are met. (1) The version (part number) must be 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). (2) The installation must be done using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (m) Parts Installation Limitation As of the applicable time specified in paragraph (m)(1) or (m)(2) of this AD, do not install on any airplane an ELAC unit having a part number identified in table 2 to paragraph (k) of this AD, except as specified in paragraph (m)(3) of this AD. (1) For an airplane that, as of the effective date of this AD, has any ELAC unit installed having a part number identified in table 2 to paragraph (k) of this AD: After modification of that airplane as required by paragraph (i) of this AD, or as specified in paragraph (j) of this AD. (2) For an airplane that, as of the effective date of this AD, does not have any ELAC unit installed having a part number identified in table 2 to paragraph (k) of this AD: As of the effective date of this AD. (3) As of the effective date of this AD, a data-loadable ELAC B unit having a part number identified in table 2 to paragraph (k) of this AD can be installed on an airplane provided that L97+ software P/N 3945129109 is uploaded at the applicable time specified in paragraph (m)(3)(i) or (m)(3)(ii) of this AD. (i) For all airplanes except those identified in paragraph (m)(3)(ii) of this AD: Before further flight after the ELAC B unit installation. (ii) For airplanes that have not been modified as required by paragraph (i) of this AD: Within the applicable compliance time specified in table 1 to paragraph (i) of this AD. (n) 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. VerDate Sep<11>2014 16:06 Mar 16, 2016 Jkt 238001 (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2003–25–07, Amendment 39–13390 (68 FR 70431, December 18, 2003), are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (iii) AMOCs approved previously for AD 2005–13–39, Amendment 39–14176 (70 FR 38580, July 5, 2005), are approved as AMOCs for the corresponding provisions of paragraph (h) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0088R1, dated June 2, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2016–4226. (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 March 9, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–05830 Filed 3–16–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 DEPARTMENT OF THE TREASURY Financial Crimes Enforcement Network 31 CFR Part 1010 RIN 1506–AB19 Financial Crimes Enforcement Network; Withdrawal of Notice of Proposed Rulemaking Regarding JSC CredexBank Financial Crimes Enforcement Network (‘‘FinCEN’’), Treasury. ACTION: Proposed rule; withdrawal. AGENCY: This document withdraws FinCEN’s proposed rulemaking to impose the first and fifth special measure regarding JSC CredexBank (‘‘Credex’’), renamed JSC InterPayBank (‘‘InterPay’’), as a financial institution of primary money laundering concern, pursuant to Section 311 of the USA PATRIOT Act (‘‘Section 311’’). Because of material subsequent developments that have mitigated the money laundering risks associated with Credex, FinCEN has determined that Credex is no longer a primary money laundering concern that warrants the implementation of a special measure under Section 311. Elsewhere in this issue of the Federal Register, FinCEN is publishing a withdrawal of the related finding regarding Credex. DATES: As of March 17, 2016 the proposed rule published May 30, 2012, at 77 FR 31794, is withdrawn. FOR FURTHER INFORMATION CONTACT: The FinCEN Resource Center at (800) 767– 2825. SUPPLEMENTARY INFORMATION: SUMMARY: I. Background On October 26, 2001, the President signed into law the Uniting and Strengthening America by Providing Appropriate Tools Required to Intercept and Obstruct Terrorism Act of 2001, Public Law 107–56 (the ‘‘USA PATRIOT Act’’). Title III of the USA PATRIOT Act amends the anti-money laundering provisions of the Bank Secrecy Act (‘‘BSA’’), codified at 12 U.S.C. 1829b, 12 U.S.C. 1951–1959, and 31 U.S.C. 5311– 5314, 5316–5332, to promote the prevention, detection, and prosecution of money laundering, tax evasion, the financing of terrorism, and other financial crimes. Regulations implementing the BSA appear at 31 CFR Chapter X. The authority of the Secretary of the Treasury to administer the BSA and its implementing regulations has been delegated to the Director of FinCEN. Section 311 of the USA PATRIOT Act (‘‘Section 311’’), codified at 31 U.S.C. E:\FR\FM\17MRP1.SGM 17MRP1

Agencies

[Federal Register Volume 81, Number 52 (Thursday, March 17, 2016)]
[Proposed Rules]
[Pages 14404-14408]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05830]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4226; Directorate Identifier 2015-NM-095-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-25-
07 for certain Airbus Model A319 and A320 series airplanes; and AD 
2005-13-39 for certain Airbus Model A321 series airplanes. AD 2003-25-
07 currently requires a revision to the airplane flight manual (AFM) 
and replacement of both elevator aileron computers (ELACs) having L80 
standards with new ELACs having L81 standards. AD 2005-13-39 currently 
requires a revision to the AFM, replacement of existing ELACs with 
ELACs having either L83 or L91 standards, as applicable; and a 
concurrent action. Since we issued AD 2003-25-07 and AD 2005-13-39, we 
have determined that new ELAC standards must be incorporated. The ELAC 
standards have been upgraded to version L97+, which implements enhanced 
angle-of-attack (AOA) monitoring to better detect AOA blockage, 
including multiple AOA blockages. This proposed AD would require 
replacing existing ELACs with new ELACs having L97+ standards or 
revising the software in an existing ELAC to the L97+ standards, as 
applicable, which would terminate the requirements of AD 2003-25-07 and 
AD 2005-13-39. This proposed AD would also add Airbus Model A318 series 
airplanes to the applicability. We are proposing this AD to prevent 
inadvertent activation of the AOA protections. Inadvertent activation 
of the AOA protections could result in a continuous nose down pitch 
rate that could result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by May 2, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
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;

[[Page 14405]]

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-2016-
4226; 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-2016-4226; 
Directorate Identifier 2015-NM-095-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 5, 2003, we issued AD 2003-25-07, Amendment 39-13390 
(68 FR 70431, December 18, 2003). AD 2003-25-07 requires a revision of 
the AFM and replacement of both ELACs having L80 standards with new 
ELACs having L81 standards on Airbus Model A319 and A320 series 
airplanes equipped with L80 standards. The replacement of both ELACs 
terminates the requirement for the AFM revision.
    On June 17, 2005, we issued AD 2005-13-39, Amendment 39-14176 (70 
FR 38580, July 5, 2005). AD 2005-13-39 requires a revision of the AFM, 
a concurrent action, and replacement of existing ELACs with ELACs 
having L83 or L91 standards on certain Airbus Model A321 series 
airplanes.
    Since we issued AD 2003-25-07, Amendment 39-13390 (68 FR 70431, 
December 18, 2003); and AD 2005-13-39, Amendment 39-14176 (70 FR 38580, 
July 5, 2005); we have determined that new ELAC standards must be 
incorporated. The ELAC standard software has been updated to version 
L97+ and the hardware is available in a data loadable version and a 
non-data-loadable version.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0088R1, dated June 2, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320, and A321 series airplanes. The MCAI states:

    The latest elevator aileron computer (ELAC) standard, L97+, 
implements enhanced Angle of Attack (AOA) monitoring in order to 
better detect cases of AOA blockage, including multiple AOA 
blockage.
    Two ELAC L97+ versions are currently available, Part Number (P/
N) 3945129109 with data loading capability, and P/N 3945128215 
without the data loading capability. Three existing [EASA] ADs 
requiring installation of earlier ELAC (software) have been 
identified and taken into account for cancellation by this new 
[EASA] AD.
    For the reasons described above, EASA issued AD 2015-0088, 
cancelling DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France AD 95-203-072 (no requirements retained) [which 
corresponds to FAA AD 98-09-18, Amendment 39-10499 (63 FR 23374, 
April 29, 1998)], and partially retaining the requirements of DGAC 
France AD 2001-508 [which corresponds to FAA AD 2003-25-07, 
Amendment 39-13390 (68 FR 70431, December 18, 2003), and [DGAC] AD 
F-2004-147 (EASA approval ref. 2004-8601) [which corresponds to FAA 
AD 2005-13-39, Amendment 39-14176 (70 FR 38580, July 5, 2005)], 
which were superseded, and to require replacement of all ELAC with 
ELAC L97+ standard.
    Since that [EASA] AD was issued, some errors were detected in 
Appendix 1 of the [EASA] AD, and one P/N ELAC was inadvertently 
omitted. This [EASA] AD revises EASA AD 2015-0088 to correct these 
errors and to add clarification to paragraph (7) [of the EASA AD].

    The required actions include either replacing existing ELACs with 
new ELACs having L97+ standards uploaded, or revising the software in 
the existing ELACs to L97+ standards. This proposed AD also adds Airbus 
Model A318 series airplanes to the applicability. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-4226.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1243, dated March 17, 
2015. The service information describes procedures for replacing the 
existing ELACs with new ELACs having L97+ standards, and modifying 
existing ELACs into units with L97+ standards.
    Airbus has also issued Service Bulletin A320-27-1244, dated March 
5, 2015. The service information describes procedures for modification 
of an airplane by replacing any existing ELAC unit with an ELAC 97+ 
unit having P/N 3945128215.
    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.

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.

Costs of Compliance

    We estimate that this proposed AD affects 940 airplanes of U.S. 
registry.
    The actions required by AD 2003-25-07, Amendment 39-13390 (68 FR 
70431, December 18, 2003), and retained in this proposed AD take about 
1 work-hour per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2003-25-07 is $85 per product.
    The actions required by AD 2005-13-39, Amendment 39-14176 (70 FR 
38580, July 5, 2005), and retained in this proposed AD take about 1 
work-hour per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2005-13-39 is $85 per product.

[[Page 14406]]

    We also estimate that it would take about 3 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 $7,230 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $7,035,900, or $7,485 per product.
    According to the parts manufacturer, some of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. We do not control warranty coverage for 
affected individuals. As a result, we have included all costs in our 
cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2003-25-07, Amendment 39-13390 
(68 FR 70431, December 18, 2003); and AD 2005-13-39, Amendment 39-14176 
(70 FR 38580, July 5, 2005); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2016-4226; Directorate Identifier 2015-NM-
095-AD.

(a) Comments Due Date

    We must receive comments by May 2, 2016.

(b) Affected ADs

    This AD replaces AD 2003-25-07, Amendment 39-13390 (68 FR 70431, 
December 18, 2003); and AD 2005-13-39, Amendment 39-14176 (70 FR 
38580, July 5, 2005).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (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 27, Flight 
Controls.

(e) Reason

    This AD was prompted by a determination that new elevator 
aileron computers (ELAC) standards must be incorporated. The ELAC 
standards have been upgraded to version L97+, which implements 
enhanced angle-of-attack (AOA) monitoring to better detect AOA 
blockage, including multiple AOA blockages. We are issuing this AD 
to prevent inadvertent activation of the AOA protections. 
Inadvertent activation of the AOA protections could result in a 
continuous nose down pitch rate that could result in reduced 
controllability of the airplane.

(f) Compliance

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

(g) Retained Replacement of ELAC L80 Units With L81 Units, With No 
Changes

    For Model A319 and A320 series airplanes, equipped with ELAC L80 
standards having part numbers listed in Airbus Service Bulletin 
A320-27-1135, dated June 29, 2001: This paragraph restates the 
requirements of paragraph (b) of AD 2003-25-07, Amendment 39-13390 
(68 FR 70431, December 18, 2003), with no changes. Within 1 year 
after January 22, 2004 (the effective date of AD 2003-25-07): 
Replace both ELACs having L80 standards with new ELACs having L81 
standards, by doing all the actions per paragraphs A., B., C., and 
D. of the Accomplishment Instructions of Airbus Service Bulletin 
A320-27-1135, dated June 29, 2001.

(h) Retained Installation of ELAC L83 or L91 Software, With No Changes

    For Model A321-111, -112, -131, -211, and -231 airplanes, except 
those with Airbus Modification 34043 installed in production: This 
paragraph restates the requirements of paragraph (g) of AD 2005-13-
39, Amendment 39-14176 (70 FR 38580, July 5, 2005), with no changes. 
Within 16 months after August 9, 2005 (the effective date of AD 
2005-13-39): Replace existing ELACs with ELACs having L83 standards, 
by accomplishing all of the actions specified in the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1151, dated March 9, 
2004, including Appendix 01, dated March 9, 2004; or with ELACs 
having L91 standards, by accomplishing all of the actions specified 
in the Accomplishment Instructions of Airbus Service Bulletin A320-
27-1152, dated June 4, 2004, including Appendix 01, dated June 4, 
2004; as applicable.

(i) New Requirement of This AD: ELAC Replacement or Modification

    At the applicable times specified in table 1 to paragraph (i) of 
this AD: Replace each ELAC unit with an ELAC L97+ unit having part 
number (P/N) 3945129100 and software having P/N 3945129109, or 
modify existing ELAC units into ELAC L97+ units having P/N 
3945129100 with L97+ operational software P/N 3945129109 loaded, as 
applicable, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-27-1243, dated March 17, 2015. 
Accomplishing this replacement terminates the actions required by 
paragraphs (g) and (h) of this AD.

[[Page 14407]]



          Table 1 to Paragraph (i) of This AD--Compliance Times
------------------------------------------------------------------------
                                          Compliance time  (after the
        Airbus airplane models             effective date of this AD)
------------------------------------------------------------------------
Model A318 series airplanes with UTAS  Within 5 months.
 (formerly Goodrich) AOA P/N 0861ED
 or P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A319 series airplanes with UTAS  Within 10 months.
 (formerly Goodrich) AOA P/N 0861ED
 or P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A320 series airplanes with UTAS  Within 10 months.
 (formerly Goodrich) AOA P/N 0861ED
 or P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A321 series airplanes with UTAS  Within 5 months.
 (formerly Goodrich) AOA P/N 0861ED
 or P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A318, A319, A320, and A321       Within 25 months.
 series airplanes that do not have
 UTAS (formerly Goodrich) AOA P/N
 0861ED or P/N 0861ED2 installed in
 all 3 positions (captain, first
 officer, and standby).
------------------------------------------------------------------------

(j) Optional Method of Compliance

    Modification of an airplane by replacing any existing ELAC unit 
with an ELAC 97+ unit having P/N 3945128215, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1244, 
dated March 5, 2015, is an acceptable method of compliance for the 
requirements of paragraph (i) of this AD, for only that modified 
airplane. Accomplishing this modification terminates the actions 
required by paragraphs (g) and (h) of this AD for that modified 
airplane.

    Note 1 to paragraph (j) of this AD: ELAC unit P/N 3945128215 is 
not data-loadable, but it is fully interchangeable and mixable with 
data-loadable ELAC 97+ unit P/N 3945129100 with software P/N 
3945129109 loaded.

(k) Exclusion From Requirements of Paragraphs (g), (h), and (i), and 
the Actions in Paragraph (j), of This AD

    Airplanes on which Airbus Modification 156546 (installation of 
ELAC L97+ with software P/N 3945129109) was installed in production 
are excluded from the requirements of paragraphs (g), (h), and (i) 
of this AD and the actions specified in paragraph (j) of this AD, 
provided it can be determined that no ELAC having a part number 
identified in table 2 to paragraph (k) of this AD has been installed 
on that airplane since the date of issuance of the original 
airworthiness certificate or the date of issuance of the original 
export certificate of airworthiness.

    Table 2 to Paragraph (k) of This AD--Prohibited ELAC Part Numbers
------------------------------------------------------------------------
          Part number                 Designation              FIN
------------------------------------------------------------------------
3945122202....................  ELAC A320-111 Type Def  2 CE 1/2.
3945122203....................  ELAC L50C.............  2 CE 1/2.
3945122303....................  ELAC L50C.............  2 CE 1/2.
3945122304....................  ELAC L60..............  2 CE 1/2.
3945122305....................  ELAC L61B.............  2 CE 1/2.
3945122306....................  ELAC L61F.............  2 CE 1/2.
3945122307....................  ELAC L62C.............  2 CE 1/2.
C12370AA01....................  ELAC L68C.............  2 CE 1/2.
3945122501....................  ELAC L69..............  2 CE 1/2.
3945122502....................  ELAC L69J.............  2 CE 1/2.
3945122503....................  ELAC L77..............  2 CE 1/2.
3945122504....................  ELAC L78..............  2 CE 1/2.
3945122505....................  ELAC A L80............  2 CE 1/2.
3945123505....................  ELAC A' L80...........  2 CE 1/2.
3945128101....................  ELAC B L80............  2 CE 1/2.
3945122506....................  ELAC A L81............  2 CE 1/2.
3945123506....................  ELAC A' L81...........  2 CE 1/2.
3945128102....................  ELAC B L81............  2 CE 1/2.
3945122507....................  ELAC A L82............  2 CE 1/2.
3945123507....................  ELAC A' L82...........  2 CE 1/2.
3945128103....................  ELAC B L82............  2 CE 1/2.
3945122608....................  ELAC A L83............  2 CE 1/2.
3945123608....................  ELAC A' L83...........  2 CE 1/2.
3945122609....................  ELAC A L84............  2 CE 1/2.
3945123609....................  ELAC A' L84...........  2 CE 1/2.
3945128204....................  ELAC B L90L...........  2 CE 1/2.
3945128205....................  ELAC B L90N...........  2 CE 1/2.
3945128206....................  ELAC B L91............  2 CE 1/2.
3945129101....................  ELAC B L91 data         2 CE 1/2 SW1.
                                 loadable.
3945128207....................  ELAC B L92............  2 CE 1/2.
3945128208....................  ELAC B L92L...........  2 CE 1/2.
3945128209....................  ELAC B L93............  2 CE 1/2.
3945129103....................  ELAC B L93 data         2 CE 1/2 SW1.
                                 loadable.
3945128210....................  ELAC B L94............  2 CE 1/2.
3945129104....................  ELAC B L94 data         2 CE 1/2 SW1.
                                 loadable.
3945128212....................  ELAC B L96............  2 CE 1/2.
3945129106....................  ELAC B L96 data         2 CE 1/2 SW1.
                                 loadable.
3945129107....................  ELAC B L96 H-A data     2 CE 1/2 SW1.
                                 loadable.
3945128214....................  ELAC B L97............  2 CE 1/2.
3945129108....................  ELAC B L97 data         2 CE 1/2 SW1.
                                 loadable.
------------------------------------------------------------------------


[[Page 14408]]

(l) Later-Approved Parts

    Installation of an ELAC version (part number) approved after the 
effective date of this AD is an approved method of compliance with 
the requirements of paragraphs (i) and (j) of this AD, provided the 
requirements specified in paragraphs (l)(1) and (l)(2) of this AD 
are met.
    (1) The version (part number) must be 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).
    (2) The installation must be done using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the EASA; or Airbus's EASA DOA.

(m) Parts Installation Limitation

    As of the applicable time specified in paragraph (m)(1) or 
(m)(2) of this AD, do not install on any airplane an ELAC unit 
having a part number identified in table 2 to paragraph (k) of this 
AD, except as specified in paragraph (m)(3) of this AD.
    (1) For an airplane that, as of the effective date of this AD, 
has any ELAC unit installed having a part number identified in table 
2 to paragraph (k) of this AD: After modification of that airplane 
as required by paragraph (i) of this AD, or as specified in 
paragraph (j) of this AD.
    (2) For an airplane that, as of the effective date of this AD, 
does not have any ELAC unit installed having a part number 
identified in table 2 to paragraph (k) of this AD: As of the 
effective date of this AD.
    (3) As of the effective date of this AD, a data-loadable ELAC B 
unit having a part number identified in table 2 to paragraph (k) of 
this AD can be installed on an airplane provided that L97+ software 
P/N 3945129109 is uploaded at the applicable time specified in 
paragraph (m)(3)(i) or (m)(3)(ii) of this AD.
    (i) For all airplanes except those identified in paragraph 
(m)(3)(ii) of this AD: Before further flight after the ELAC B unit 
installation.
    (ii) For airplanes that have not been modified as required by 
paragraph (i) of this AD: Within the applicable compliance time 
specified in table 1 to paragraph (i) of this AD.

(n) 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.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously for AD 2003-25-07, Amendment 39-
13390 (68 FR 70431, December 18, 2003), are approved as AMOCs for 
the corresponding provisions of paragraph (g) of this AD.
    (iii) AMOCs approved previously for AD 2005-13-39, Amendment 39-
14176 (70 FR 38580, July 5, 2005), are approved as AMOCs for the 
corresponding provisions of paragraph (h) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0088R1, dated June 2, 2015, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-4226.
    (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 March 9, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2016-05830 Filed 3-16-16; 8:45 am]
 BILLING CODE 4910-13-P