Airworthiness Directives; Airbus SAS Airplanes, 4686-4692 [2019-02558]

Download as PDF 4686 Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations Costs of Compliance List of Subjects in 14 CFR Part 39 We estimate that this AD affects less than 75 helicopters of U.S. Registry (as this AD does not apply to Bell Model 429 helicopters with skid landing gear). At an average labor rate of $85 per hour, replacing a NLG assembly requires 10 work-hours, and required parts cost $104,648, for a cost of $105,498 per helicopter and up to $7,912,350 for the U.S. fleet. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 helicopters identified in this rulemaking action. tkelley on DSKBCP9HB2PROD with RULES Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–03–05 Bell Helicopter Textron Canada Limited: Amendment 39–19557; Docket No. FAA–2018–0647; Product Identifier 2017–SW–083–AD. (a) Applicability This AD applies to Bell Helicopter Textron Canada Limited Model 429 helicopters with a nose landing gear (NLG) assembly part number (P/N) 429–336–100–101 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue failure of an NLG assembly, which could result in subsequent damage to and loss of control of the helicopter. (c) Effective Date This AD becomes effective March 26, 2019. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Before further flight, remove from service any NLG assembly P/N 429–336–100–101 that has reached or exceeded 4,500 hours time-in-service (TIS) or 50,000 retirement index number (RIN). Thereafter, remove from service each NLG assembly P/N 429–336– 100–101 before accumulating 4,500 hours TIS or 50,000 RIN, whichever occurs first. For purposes of this AD, for every normal retraction or extension of the wheeled landing gear system, add one RIN. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information (1) Bell Helicopter Alert Service Bulletin No. 429–15–24, Revision A, dated September 23, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http:// www.bellcustomer.com/files/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in Transport Canada AD No. CF–2016–07, dated March 4, 2016. You may view the Transport Canada AD on the internet at http:// www.regulations.gov in Docket No. FAA– 2018–0647. (h) Subject Joint Aircraft Service Component (JASC) Code: 3200, Landing Gear System. Issued in Fort Worth, Texas, on February 8, 2019. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2019–02626 Filed 2–15–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0556; Product Identifier 2018–NM–015–AD; Amendment 39- 19555; AD 2019–03–03] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series; Model A319 series; Model A320 series; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This AD was prompted by reports of multiple angle of attack (AoA) probe blockages. This AD requires all elevator SUMMARY: E:\FR\FM\19FER1.SGM 19FER1 Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations aileron computer (ELAC) units to be upgraded with new software, or replaced with upgraded units. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 26, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 26, 2019. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; internet http:// www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0556. tkelley on DSKBCP9HB2PROD with RULES 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–2018– 0556; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus SAS Model A318 series; Model A319 series; Model A320 series; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on June 20, 2018 (83 FR 28555). The NPRM was prompted by reports of multiple AoA probe VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 blockages. The NPRM proposed to require all ELAC units to be upgraded with new software, or replaced with upgraded units. We are issuing this AD to address the blockage of AoA probes. This condition, if not corrected, could lead to undue activation of the AoA protection, reverting to manual control of the airplane, which, under specific circumstances, could result in reduced control of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018– 0007R1, dated January 19, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A318 series; Model A319 series; Model A320 series; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: Occurrences were reported on multiple Angle of Attack (AoA) probes blockages. Investigation results indicated the need for improved AoA monitoring in order to detect cases of AoA probe blockage. This condition, if not corrected, could lead to undue activation of the AoA protection, reverting to manual control of the aeroplane, which, under specific circumstances, could result in reduced control of the aeroplane. To address this potential unsafe condition, Airbus developed several Elevator Aileron Computer (ELAC) standards, i.e. ELAC units loaded with a specific software Part Number (P/N), and EASA issued AD 2017–0008, retaining part of the requirements of EASA AD 2015–0088R1 [which corresponds to FAA AD 2016–17–03, Amendment 39–18616 (81 FR 55358, August 19, 2016) (‘‘AD 2016–17– 03’’)], which was superseded, and requiring an upgrade of all ELAC units with ELAC L99 standard, which introduces improvements in the AoA probe monitoring for Current Engine Option (CEO) aeroplanes, and also incorporates flight control aspects for New Engine Option (NEO) aeroplanes. Since that [EASA] AD was issued, it was determined that clarification is necessary for the Parts Installation requirements, and some typographical (P/N) errors were detected. This [EASA] AD is revised accordingly. 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–2018– 0556. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. United Airlines had no objection to the NPRM. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 4687 Request To Reduce the Compliance Time for Model A320 Airplanes Air Line Pilots Association, International (ALPA), requested that the compliance time for the Model A320 series airplanes be reduced from 36 to 24 months, the same as for the other models. ALPA contended that 36 months is not an appropriate compliance time for the A320 because the severity of risk for the A320 is not less than for the other models. We disagree with the request to reduce the compliance time for Model A320 series airplanes. We concur with the compliance time established by EASA, the state of design authority, which is based on the overall risk to the fleet, including the severity of the failure and the likelihood of the failure’s occurrence. In conjunction with the manufacturer, we have determined that the compliance time for each airplane model will accommodate the time necessary to ensure the availability of required parts and maintain an adequate level of safety. However, if additional data are presented that would justify a shorter compliance time, we may consider further rulemaking on this issue. We have not changed this AD regarding this request. Request To Modify Paragraphs (h)(3) and (j)(2)(iii) of the Proposed AD Airbus SAS requested that we modify paragraphs (h)(3) and (j)(2)(iii) of the proposed AD to read: ‘‘The dataloadable ELAC unit is checked by two different means: by the line replaceable unit (LRU) identification and either the label call up or the Alpha Call Up ELA 1 and ELA 2 (if available).’’ We infer that this change was requested to clarify the meaning of those paragraphs. We agree to clarify the specified paragraphs. We have changed paragraphs (h)(3) and (j)(2)(iii) of this AD accordingly. Request To Clarify Paragraph (h)(3) of the Proposed AD Delta Air Lines (DAL) asked whether paragraph (h)(3) of the proposed AD, as written, actually requires two separate methods of identification for the same unit. DAL explained that not all ELAC units are labeled with the software load, that the labels were added later by Thales, and that there is no guarantee they will be present on the LRU. We agree to clarify that there are two methods of checking the data-loadable ELAC unit. As stated previously, we have revised paragraph (h)(3) of this AD and paragraph (j)(2)(iii) of this AD to make this more clear. E:\FR\FM\19FER1.SGM 19FER1 4688 Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations Request To Clarify Paragraphs (h) and (j)(2) of the Proposed AD Alaska Airlines asked whether the four conditions given in paragraphs (h)(1) through (h)(4) and (j)(2)(i) through (j)(2)(iv) of the proposed AD apply only to the ‘‘modification instructions approved by an EASA Design Organization Approval (DOA) (other than Airbus SAS’s EASA DOA),’’ or also to the modification instructions approved by other authorities, as mentioned earlier in the paragraph. We agree to clarify this aspect of the specified paragraphs. We have revised the language regarding the applicability of the four conditions given in paragraphs (h)(1) through (h)(4) and (j)(2)(i) through (j)(2)(iv) of this AD to clarify that these paragraphs are applicable only to the modification instructions that are part of an FAAaccepted maintenance or inspection program, as applicable. We have revised the language in paragraphs (h) and (j)(2) of this AD accordingly. Request To Address Onboard Data Loading of ELAC Units Alaska Airlines requested that we modify paragraph (j) of the proposed AD to address onboard loading of ELAC units with later software. Alaska Airlines also requested that we revise paragraphs (j)(2) and (j)(4) of the proposed AD to specify that those paragraphs are not applicable to onboard data loading, since they refer to removing and re-installing the dataloadable ELAC units. We infer that Alaska Airlines wants us to revise paragraphs (j)(2)(ii) and (j)(2)(iv) of the proposed AD because those paragraphs refer to the removal and re-installation of the data-loadable ELAC units. We agree. We have modified paragraph (j) of this AD to include onboard loading of ELAC software and revised paragraphs (j)(2)(ii) and (j)(2)(iv) of this AD as requested. tkelley on DSKBCP9HB2PROD with RULES Request To Remove DOA Signature Requirement DAL requested that the DOA signature requirement be removed from the proposed AD and that the previously established statement ‘‘The technical content of this document is approved under the authority of Design Organization Approval No. EASA 21J.031’’ used by the DOA in Airbus SAS service bulletins be deemed sufficient. DAL observed that if this document requires a signature, it is deviating from the previously established standard and will generate unnecessary alternative method of compliance (AMOC) requests from the VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 administrator and/or unnecessary revisions of service bulletins by the manufacturer. DAL also stated that requiring a signature does not enhance or affect the safety of the aircraft. We disagree with DAL’s request to remove the DOA signature requirement. The FAA specifies the DOA signature requirement in the ‘‘contacting the manufacturer’’ paragraph (such as paragraph (m)(2) of this AD) because in the past some U.S. operators misinterpreted that any document, including an email message, received from a manufacturer or the manufacturer’s customer support organization was considered DOA approved. Under the EASA DOA system, the only documents officially recognized as EASA-approved are those accompanied by the DOA-authorized signature. For the purpose of compliance with the ‘‘contacting the manufacturer’’ paragraph in FAA ADs, the FAA can only recognize the documents approved by the FAA, or EASA, or those authorized to make an EASA approval under the DOA system. We also disagree with the request to use the statement ‘‘The technical content of this document is approved under the authority of Design Organization Approval No. EASA 21J.031.’’ This statement only recognizes that the service bulletin was originally approved under the authority of the DOA system as approved by EASA, and does not provide any process for an operator to receive other approved instructions from either EASA or the authorized DOA as a means of compliance to the FAA AD. The current ‘‘contacting the manufacturer’’ paragraph and the requirement for the DOA-authorized signature actually results in fewer AMOCs because of the FAA’s recognition of both EASA and specific EASA DOA approvals under the ‘‘contacting the manufacturer’’ paragraph in this and other FAA ADs. We have not changed this AD in this regard. Request To Clarify Paragraph (h)(1) of the Proposed AD DAL questioned the purpose of the condition stated in paragraph (h)(1) of the proposed AD, i.e., that there should be no warning or maintenance message before the ELAC unit is removed. DAL stated that if an electronic centralized aircraft monitor (ECAM) has a maintenance message or ECAM warning that is not airworthy, as a standard procedure the aircraft will be repaired and put back in an airworthy condition prior to return to service. We agree that clarification is necessary. The intent of the condition PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 stated in paragraph (h)(1) of this AD is to ensure that all pre-existing conditions have been fixed before uploading new software to an ELAC unit or installing a unit with updated software. We have not changed this AD regarding this question. Request To Clarify Whether Certain Steps Are Required for Compliance DAL questioned whether all of the steps in Airbus SAS Aircraft Maintenance Manual (AMM) Tasks 27– 93–34–000–001–A and 27–93–34–400– 001–A, such as accessing the access doors using an adjustable platform, are required for compliance. We agree to clarify. The conditions in paragraphs (h)(2), (h)(4), (j)(2)(ii), and (j)(2)(iv) of this AD specified that actions must be done as specified in the AMM tasks. We did not intend the accessing and closing instructions of the AMM tasks to be required for compliance. We have revised paragraphs (h)(2), (h)(4), (j)(2)(ii), and (j)(2)(iv) of this AD accordingly. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–27–1263, dated April 28, 2017; and Service Bulletin A320–27–1264, dated April 28, 2017. The service information describes the software upgrade or replacement of ELAC units. These documents are distinct because they apply to different airplane configurations. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 1,250 airplanes of U.S. registry. E:\FR\FM\19FER1.SGM 19FER1 Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations 4689 We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Modification ................ Up to 3 work-hours × $85 per hour = $255 .... Up to $7,970 ............. Up to $8,225 ............. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. tkelley on DSKBCP9HB2PROD with RULES Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–03–03 Airbus SAS: Amendment 39– 19555; Docket No. FAA–2018–0556; Product Identifier 2018–NM–015–AD. (a) Effective Date This AD is effective March 26, 2019. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Cost on U.S. operators Up to $10,281,250. (b) Affected ADs This AD affects AD 2016–17–03, Amendment 39–18616 (81 FR 55358, August 19, 2016) (‘‘AD 2016–17–03’’). (c) Applicability This AD applies to the Airbus SAS airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –216, –231, –232, –233, –251N, and –271N airplanes. (4) 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 reports of multiple angle of attack (AoA) probe blockages. We are issuing this AD to address the blockage of AoA probes. This condition, if not corrected, could lead to undue activation of the AoA protection, reverting to manual control of the airplane, which, under specific circumstances, could result in reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Elevator Aileron Computer (ELAC) Units For the purposes of this AD, ELAC units having a part number (P/N) listed in table 1 to paragraphs (g), (h), and (i) of this AD are hereafter referred to as ‘‘affected ELAC units’’ in this AD. BILLING CODE 4910–13–P E:\FR\FM\19FER1.SGM 19FER1 4690 Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations ELAC Unit PIN 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 VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 PO 00000 Designation ELAC A320-111 Type Def. ELACL50C ELACL50C ELACL60 ELACL61B ELAC L61F ELACL62C ELACL68C ELACL69 ELAC L69J ELACL77 ELACL78 ELACAL80 ELACA' L80 ELACBL80 ELACAL81 ELACA' L81 ELAC B L81 ELACAL82 ELACA' L82 ELACBL82 ELACAL83 ELACA' L83 ELACAL84 ELACA' L84 ELACBL90L ELACBL90N ELACBL91 ELAC B L91 data loadable ELACBL92 ELACBL92L ELACBL93 ELAC B L93 data loadable ELACBL94 ELAC B L94 data loadable Frm 00014 Fmt 4700 Sfmt 4725 FIN 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 SW1 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 2 CE 1 I 2 SW1 2 CE 1 I 2 2 CE 1 I 2 SW1 E:\FR\FM\19FER1.SGM 19FER1 ER19FE19.014</GPH> tkelley on DSKBCP9HB2PROD with RULES Table 1 to paragraphs (g), (h), and (i) of this AD- Affected ELAC Unit Part Numbers (h) Required Actions For airplanes with ELAC unit part numbers listed in table 1 to paragraphs (g), (h), and (i) of this AD: Within the applicable compliance times defined in figure 1 to paragraph (h) of this AD, upgrade each ELAC unit by uploading L99 software part number (P/N) 3945129111 or by replacing the existing ELAC unit with an ELAC L99 P/N 3945128217 unit in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1263, dated April 28, 2017, or Airbus Service Bulletin A320– 27–1264, dated April 28, 2017, as applicable; or in accordance with modification instructions approved by the Manager, International Section, Transport Standards Branch, FAA, or by the European Aviation Safety Agency (EASA), or by Airbus SAS’s EASA Design Organization Approval (DOA); or in accordance with modification tkelley on DSKBCP9HB2PROD with RULES BILLING CODE 4910–13–C (i) Parts Installation Prohibition (1) For airplanes with ELAC units listed in table 1 to paragraphs (g), (h), and (i) of this AD: After modification of an airplane as required by paragraph (h) of this AD, do not install any affected ELAC unit on that airplane. (2) For airplanes with ELAC units not listed in table 1 to paragraphs (g), (h), and (i) of this AD: From the effective date of this AD, do not install any affected ELAC unit on that airplane. (j) Installation or Onboard Loading of Later Software Versions Installation or onboard loading of an ELAC unit with a software standard above L99 is equal to compliance with the requirements of paragraph (h) of this AD, provided the VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 4691 instructions that are part of an FAA-accepted maintenance or inspection program, as applicable, provided the conditions specified in paragraphs (h)(1) through (h)(4) of this AD are met. If approved by the DOA, the approval must include the DOA-authorized signature. (1) Absence of electronic centralized aircraft monitor (ECAM) warning or maintenance message related to ELAC, before the data-loadable ELAC unit is removed and software is loaded. (2) The data-loadable ELAC unit is removed as specified in Airbus SAS Aircraft Maintenance Manual (AMM) Task 27–93– 34–000–001–A. The access and closing instructions identified in AMM Task 27–93– 34–000–001–A are not required by this AD. Operators may perform those actions in accordance with instructions that are part of an FAA-accepted maintenance or inspection program, as applicable. (3) The data-loadable ELAC unit is checked by two different means: by the line replaceable unit (LRU) identification and either the label call-up or the Alpha Call-up ELA 1 and ELA 2 (if available). (4) After the software is loaded, the dataloadable ELAC unit is re-installed as specified in Airbus SAS AMM Task 27–93– 34–400–001–A. The access and closing instructions identified in AMM Task 27–93– 34–400–001–A are not required by this AD. Operators may perform those actions in accordance with instructions that are part of an FAA-accepted maintenance or inspection program, as applicable. Note 1 to paragraph (h) of this AD: Nondata-loadable ELAC L99 P/N 3945128217 units are fully interchangeable and mixable with data-loadable ELAC L99 P/N 3945129100 units with L99 software P/N 3945129111 loaded. conditions specified in paragraphs (j)(1) and (j)(2) of this AD are met. (1) The ELAC unit part number is approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. (2) The installation is accomplished in accordance with modification instructions approved by the Manager, International Section, Transport Standards Branch, FAA, or by EASA, or by Airbus SAS’s EASA DOA; or in accordance with modification instructions that are part of an FAA-accepted maintenance or inspection program, as applicable, provided the conditions in paragraphs (j)(2)(i) through (j)(2)(iv) of this AD are met. (i) Absence of ECAM warning or maintenance message related to ELAC, before the data-loadable ELAC unit is removed and software is loaded. (ii) The data-loadable ELAC unit is removed as specified in Airbus SAS AMM Task 27–93–34–000–001–A. This does not apply to the onboard loading of ELAC units. The access and closing instructions identified in AMM Task 27–93–34–000–001– A are not required by this AD. Operators may perform those actions in accordance with instructions that are part of an FAA-accepted maintenance or inspection program, as applicable. (iii) The data-loadable ELAC unit is checked by two different means: by the LRU identification and either the label call-up or the Alpha Call-up ELA 1 and ELA 2 (if available). (iv) After the software is loaded, the dataloadable ELAC unit is re-installed as PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\19FER1.SGM 19FER1 ER19FE19.015</GPH> ER19FE19.016</GPH> Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations 4692 Federal Register / Vol. 84, No. 33 / Tuesday, February 19, 2019 / Rules and Regulations specified in Airbus SAS AMM Task 27–93– 34–400–001–A. This does not apply to the onboard loading of ELAC units. The access and closing instructions identified in AMM Task 27–93–34–400–001–A are not required by this AD. Operators may perform those actions in accordance with instructions that are part of an FAA-accepted maintenance or inspection program, as applicable. (k) Airplanes Not Affected by the Requirements of Paragraph (h) of This AD (1) An airplane on which any modification (mod) specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD was embodied in production is not affected by the requirements of paragraph (h) of this AD, provided it is determined that no affected ELAC unit is installed as of the effective date of this AD. (i) Airbus SAS mod 161843 (installation of data-loadable ELAC P/N 3945129100 unit with L99 software P/N 3945129111) or mod 159979 (installation of non-data-loadable ELAC L99 P/N 3945128217 unit). (ii) Airbus SAS mod 160577 (installation of data-loadable ELAC P/N 3945129100 unit with L101 software P/N 3945129112) or mod 162042 (installation of non-data-loadable ELAC L101 P/N 3945128218 unit). (2) An airplane that has been modified as specified in the service information identified in paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD is not affected by the requirements of paragraph (h) of this AD, provided it is determined that no affected ELAC unit is installed as of the effective date of this AD. (i) Airbus Service Bulletin A320–27–1267, dated September 27, 2017 (installation of non-data-loadable ELAC L101 P/N 3945128218 unit). (ii) Airbus Service Bulletin A320–27–1268, dated September 27, 2017 (installation of data-loadable ELAC P/N 3945129100 unit with L101 software P/N 3945129112 for A320 NEO). (iii) Airbus Service Bulletin A320–27– 1269, dated September 27, 2017 (installation of data-loadable ELAC P/N 3945129100 unit with L101 software P/N 3945129112). tkelley on DSKBCP9HB2PROD with RULES (l) Terminating Action for AD 2016–17–03 Accomplishing the actions required by paragraph (h) of this AD or complying with the provisions specified in paragraph (k) of this AD terminates all requirements of AD 2016–17–03. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate VerDate Sep<11>2014 17:01 Feb 15, 2019 Jkt 247001 principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s 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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0007R1, dated January 19, 2018, 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–2018–0556. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–27–1263, dated April 28, 2017. (ii) Airbus Service Bulletin A320–27–1264, dated April 28, 2017. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this service information that is incorporated by reference at the PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on February 1, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–02558 Filed 2–15–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0555; Product Identifier 2010–SW–047–AD; Amendment 39–19537; 2014–05–06 R2] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Type Certificate Previously Held by Eurocopter Deutschland GmbH) Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments; removal. AGENCY: We are removing Airworthiness Directive (AD) 2014–05– 06 R1, which applied to Airbus Helicopters Deutschland GmbH (type certificate previously held by Eurocopter Deutschland GmbH) Model EC135 and MBB–BK 117 C–2 helicopters. AD 2014–05–06 R1 required installing bushings and washers on the flight controls. This action is prompted by an error in the issuance of 2014–05– 06 R1. Accordingly, AD 2014–05–06 R1 is removed. DATES: This AD becomes effective February 19, 2019. We must receive comments on this AD by April 22, 2019. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 SUMMARY: E:\FR\FM\19FER1.SGM 19FER1

Agencies

[Federal Register Volume 84, Number 33 (Tuesday, February 19, 2019)]
[Rules and Regulations]
[Pages 4686-4692]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02558]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0556; Product Identifier 2018-NM-015-AD; Amendment 
39- 19555; AD 2019-03-03]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A318 series; Model A319 series; Model A320 series; and 
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. 
This AD was prompted by reports of multiple angle of attack (AoA) probe 
blockages. This AD requires all elevator

[[Page 4687]]

aileron computer (ELAC) units to be upgraded with new software, or 
replaced with upgraded units. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective March 26, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 26, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
internet http://www.airbus.com. You may view this service information 
at the FAA, Transport Standards Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0556.

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-2018-
0556; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus SAS Model A318 
series; Model A319 series; Model A320 series; and Model A321-111, -112, 
-131, -211, -212, -213, -231, and -232 airplanes. The NPRM published in 
the Federal Register on June 20, 2018 (83 FR 28555). The NPRM was 
prompted by reports of multiple AoA probe blockages. The NPRM proposed 
to require all ELAC units to be upgraded with new software, or replaced 
with upgraded units.
    We are issuing this AD to address the blockage of AoA probes. This 
condition, if not corrected, could lead to undue activation of the AoA 
protection, reverting to manual control of the airplane, which, under 
specific circumstances, could result in reduced control of the 
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0007R1, dated January 19, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A318 series; Model 
A319 series; Model A320 series; and Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. The MCAI states:

    Occurrences were reported on multiple Angle of Attack (AoA) 
probes blockages. Investigation results indicated the need for 
improved AoA monitoring in order to detect cases of AoA probe 
blockage.
    This condition, if not corrected, could lead to undue activation 
of the AoA protection, reverting to manual control of the aeroplane, 
which, under specific circumstances, could result in reduced control 
of the aeroplane.
    To address this potential unsafe condition, Airbus developed 
several Elevator Aileron Computer (ELAC) standards, i.e. ELAC units 
loaded with a specific software Part Number (P/N), and EASA issued 
AD 2017-0008, retaining part of the requirements of EASA AD 2015-
0088R1 [which corresponds to FAA AD 2016-17-03, Amendment 39-18616 
(81 FR 55358, August 19, 2016) (``AD 2016-17-03'')], which was 
superseded, and requiring an upgrade of all ELAC units with ELAC L99 
standard, which introduces improvements in the AoA probe monitoring 
for Current Engine Option (CEO) aeroplanes, and also incorporates 
flight control aspects for New Engine Option (NEO) aeroplanes.
    Since that [EASA] AD was issued, it was determined that 
clarification is necessary for the Parts Installation requirements, 
and some typographical (P/N) errors were detected. This [EASA] AD is 
revised accordingly.

    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-2018-
0556.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment. United Airlines had no 
objection to the NPRM.

Request To Reduce the Compliance Time for Model A320 Airplanes

    Air Line Pilots Association, International (ALPA), requested that 
the compliance time for the Model A320 series airplanes be reduced from 
36 to 24 months, the same as for the other models. ALPA contended that 
36 months is not an appropriate compliance time for the A320 because 
the severity of risk for the A320 is not less than for the other 
models.
    We disagree with the request to reduce the compliance time for 
Model A320 series airplanes. We concur with the compliance time 
established by EASA, the state of design authority, which is based on 
the overall risk to the fleet, including the severity of the failure 
and the likelihood of the failure's occurrence. In conjunction with the 
manufacturer, we have determined that the compliance time for each 
airplane model will accommodate the time necessary to ensure the 
availability of required parts and maintain an adequate level of 
safety. However, if additional data are presented that would justify a 
shorter compliance time, we may consider further rulemaking on this 
issue. We have not changed this AD regarding this request.

Request To Modify Paragraphs (h)(3) and (j)(2)(iii) of the Proposed AD

    Airbus SAS requested that we modify paragraphs (h)(3) and 
(j)(2)(iii) of the proposed AD to read: ``The data-loadable ELAC unit 
is checked by two different means: by the line replaceable unit (LRU) 
identification and either the label call up or the Alpha Call Up ELA 1 
and ELA 2 (if available).'' We infer that this change was requested to 
clarify the meaning of those paragraphs.
    We agree to clarify the specified paragraphs. We have changed 
paragraphs (h)(3) and (j)(2)(iii) of this AD accordingly.

Request To Clarify Paragraph (h)(3) of the Proposed AD

    Delta Air Lines (DAL) asked whether paragraph (h)(3) of the 
proposed AD, as written, actually requires two separate methods of 
identification for the same unit. DAL explained that not all ELAC units 
are labeled with the software load, that the labels were added later by 
Thales, and that there is no guarantee they will be present on the LRU.
    We agree to clarify that there are two methods of checking the 
data-loadable ELAC unit. As stated previously, we have revised 
paragraph (h)(3) of this AD and paragraph (j)(2)(iii) of this AD to 
make this more clear.

[[Page 4688]]

Request To Clarify Paragraphs (h) and (j)(2) of the Proposed AD

    Alaska Airlines asked whether the four conditions given in 
paragraphs (h)(1) through (h)(4) and (j)(2)(i) through (j)(2)(iv) of 
the proposed AD apply only to the ``modification instructions approved 
by an EASA Design Organization Approval (DOA) (other than Airbus SAS's 
EASA DOA),'' or also to the modification instructions approved by other 
authorities, as mentioned earlier in the paragraph.
    We agree to clarify this aspect of the specified paragraphs. We 
have revised the language regarding the applicability of the four 
conditions given in paragraphs (h)(1) through (h)(4) and (j)(2)(i) 
through (j)(2)(iv) of this AD to clarify that these paragraphs are 
applicable only to the modification instructions that are part of an 
FAA-accepted maintenance or inspection program, as applicable. We have 
revised the language in paragraphs (h) and (j)(2) of this AD 
accordingly.

Request To Address Onboard Data Loading of ELAC Units

    Alaska Airlines requested that we modify paragraph (j) of the 
proposed AD to address onboard loading of ELAC units with later 
software. Alaska Airlines also requested that we revise paragraphs 
(j)(2) and (j)(4) of the proposed AD to specify that those paragraphs 
are not applicable to onboard data loading, since they refer to 
removing and re-installing the data-loadable ELAC units. We infer that 
Alaska Airlines wants us to revise paragraphs (j)(2)(ii) and (j)(2)(iv) 
of the proposed AD because those paragraphs refer to the removal and 
re-installation of the data-loadable ELAC units.
    We agree. We have modified paragraph (j) of this AD to include 
onboard loading of ELAC software and revised paragraphs (j)(2)(ii) and 
(j)(2)(iv) of this AD as requested.

Request To Remove DOA Signature Requirement

    DAL requested that the DOA signature requirement be removed from 
the proposed AD and that the previously established statement ``The 
technical content of this document is approved under the authority of 
Design Organization Approval No. EASA 21J.031'' used by the DOA in 
Airbus SAS service bulletins be deemed sufficient. DAL observed that if 
this document requires a signature, it is deviating from the previously 
established standard and will generate unnecessary alternative method 
of compliance (AMOC) requests from the administrator and/or unnecessary 
revisions of service bulletins by the manufacturer. DAL also stated 
that requiring a signature does not enhance or affect the safety of the 
aircraft.
    We disagree with DAL's request to remove the DOA signature 
requirement. The FAA specifies the DOA signature requirement in the 
``contacting the manufacturer'' paragraph (such as paragraph (m)(2) of 
this AD) because in the past some U.S. operators misinterpreted that 
any document, including an email message, received from a manufacturer 
or the manufacturer's customer support organization was considered DOA 
approved. Under the EASA DOA system, the only documents officially 
recognized as EASA-approved are those accompanied by the DOA-authorized 
signature. For the purpose of compliance with the ``contacting the 
manufacturer'' paragraph in FAA ADs, the FAA can only recognize the 
documents approved by the FAA, or EASA, or those authorized to make an 
EASA approval under the DOA system.
    We also disagree with the request to use the statement ``The 
technical content of this document is approved under the authority of 
Design Organization Approval No. EASA 21J.031.'' This statement only 
recognizes that the service bulletin was originally approved under the 
authority of the DOA system as approved by EASA, and does not provide 
any process for an operator to receive other approved instructions from 
either EASA or the authorized DOA as a means of compliance to the FAA 
AD. The current ``contacting the manufacturer'' paragraph and the 
requirement for the DOA-authorized signature actually results in fewer 
AMOCs because of the FAA's recognition of both EASA and specific EASA 
DOA approvals under the ``contacting the manufacturer'' paragraph in 
this and other FAA ADs. We have not changed this AD in this regard.

Request To Clarify Paragraph (h)(1) of the Proposed AD

    DAL questioned the purpose of the condition stated in paragraph 
(h)(1) of the proposed AD, i.e., that there should be no warning or 
maintenance message before the ELAC unit is removed. DAL stated that if 
an electronic centralized aircraft monitor (ECAM) has a maintenance 
message or ECAM warning that is not airworthy, as a standard procedure 
the aircraft will be repaired and put back in an airworthy condition 
prior to return to service.
    We agree that clarification is necessary. The intent of the 
condition stated in paragraph (h)(1) of this AD is to ensure that all 
pre-existing conditions have been fixed before uploading new software 
to an ELAC unit or installing a unit with updated software. We have not 
changed this AD regarding this question.

Request To Clarify Whether Certain Steps Are Required for Compliance

    DAL questioned whether all of the steps in Airbus SAS Aircraft 
Maintenance Manual (AMM) Tasks 27-93-34-000-001-A and 27-93-34-400-001-
A, such as accessing the access doors using an adjustable platform, are 
required for compliance.
    We agree to clarify. The conditions in paragraphs (h)(2), (h)(4), 
(j)(2)(ii), and (j)(2)(iv) of this AD specified that actions must be 
done as specified in the AMM tasks. We did not intend the accessing and 
closing instructions of the AMM tasks to be required for compliance. We 
have revised paragraphs (h)(2), (h)(4), (j)(2)(ii), and (j)(2)(iv) of 
this AD accordingly.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1263, dated April 28, 
2017; and Service Bulletin A320-27-1264, dated April 28, 2017. The 
service information describes the software upgrade or replacement of 
ELAC units. These documents are distinct because they apply to 
different airplane configurations.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 1,250 airplanes of U.S. registry.

[[Page 4689]]

    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
             Action                      Labor cost                   Parts cost                   Cost per product            Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification....................  Up to 3 work-hours x $85  Up to $7,970..................  Up to $8,225.................  Up to $10,281,250.
                                   per hour = $255.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2019-03-03 Airbus SAS: Amendment 39-19555; Docket No. FAA-2018-0556; 
Product Identifier 2018-NM-015-AD.

(a) Effective Date

    This AD is effective March 26, 2019.

(b) Affected ADs

    This AD affects AD 2016-17-03, Amendment 39-18616 (81 FR 55358, 
August 19, 2016) (``AD 2016-17-03'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (c)(4) of this AD, certificated in any 
category, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, 
and -271N airplanes.
    (4) 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 reports of multiple angle of attack 
(AoA) probe blockages. We are issuing this AD to address the 
blockage of AoA probes. This condition, if not corrected, could lead 
to undue activation of the AoA protection, reverting to manual 
control of the airplane, which, under specific circumstances, could 
result in reduced control of the airplane.

(f) Compliance

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

(g) Definition of Affected Elevator Aileron Computer (ELAC) Units

    For the purposes of this AD, ELAC units having a part number (P/
N) listed in table 1 to paragraphs (g), (h), and (i) of this AD are 
hereafter referred to as ``affected ELAC units'' in this AD.
BILLING CODE 4910-13-P

[[Page 4690]]

[GRAPHIC] [TIFF OMITTED] TR19FE19.014


[[Page 4691]]


[GRAPHIC] [TIFF OMITTED] TR19FE19.015

(h) Required Actions

    For airplanes with ELAC unit part numbers listed in table 1 to 
paragraphs (g), (h), and (i) of this AD: Within the applicable 
compliance times defined in figure 1 to paragraph (h) of this AD, 
upgrade each ELAC unit by uploading L99 software part number (P/N) 
3945129111 or by replacing the existing ELAC unit with an ELAC L99 
P/N 3945128217 unit in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1263, dated April 
28, 2017, or Airbus Service Bulletin A320-27-1264, dated April 28, 
2017, as applicable; or in accordance with modification instructions 
approved by the Manager, International Section, Transport Standards 
Branch, FAA, or by the European Aviation Safety Agency (EASA), or by 
Airbus SAS's EASA Design Organization Approval (DOA); or in 
accordance with modification instructions that are part of an FAA-
accepted maintenance or inspection program, as applicable, provided 
the conditions specified in paragraphs (h)(1) through (h)(4) of this 
AD are met. If approved by the DOA, the approval must include the 
DOA-authorized signature.
    (1) Absence of electronic centralized aircraft monitor (ECAM) 
warning or maintenance message related to ELAC, before the data-
loadable ELAC unit is removed and software is loaded.
    (2) The data-loadable ELAC unit is removed as specified in 
Airbus SAS Aircraft Maintenance Manual (AMM) Task 27-93-34-000-001-
A. The access and closing instructions identified in AMM Task 27-93-
34-000-001-A are not required by this AD. Operators may perform 
those actions in accordance with instructions that are part of an 
FAA-accepted maintenance or inspection program, as applicable.
    (3) The data-loadable ELAC unit is checked by two different 
means: by the line replaceable unit (LRU) identification and either 
the label call-up or the Alpha Call-up ELA 1 and ELA 2 (if 
available).
    (4) After the software is loaded, the data-loadable ELAC unit is 
re-installed as specified in Airbus SAS AMM Task 27-93-34-400-001-A. 
The access and closing instructions identified in AMM Task 27-93-34-
400-001-A are not required by this AD. Operators may perform those 
actions in accordance with instructions that are part of an FAA-
accepted maintenance or inspection program, as applicable.
    Note 1 to paragraph (h) of this AD: Non-data-loadable ELAC L99 
P/N 3945128217 units are fully interchangeable and mixable with 
data-loadable ELAC L99 P/N 3945129100 units with L99 software P/N 
3945129111 loaded.
[GRAPHIC] [TIFF OMITTED] TR19FE19.016

BILLING CODE 4910-13-C

(i) Parts Installation Prohibition

    (1) For airplanes with ELAC units listed in table 1 to 
paragraphs (g), (h), and (i) of this AD: After modification of an 
airplane as required by paragraph (h) of this AD, do not install any 
affected ELAC unit on that airplane.
    (2) For airplanes with ELAC units not listed in table 1 to 
paragraphs (g), (h), and (i) of this AD: From the effective date of 
this AD, do not install any affected ELAC unit on that airplane.

(j) Installation or Onboard Loading of Later Software Versions

    Installation or onboard loading of an ELAC unit with a software 
standard above L99 is equal to compliance with the requirements of 
paragraph (h) of this AD, provided the conditions specified in 
paragraphs (j)(1) and (j)(2) of this AD are met.
    (1) The ELAC unit part number is approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus SAS's EASA DOA.
    (2) The installation is accomplished in accordance with 
modification instructions approved by the Manager, International 
Section, Transport Standards Branch, FAA, or by EASA, or by Airbus 
SAS's EASA DOA; or in accordance with modification instructions that 
are part of an FAA-accepted maintenance or inspection program, as 
applicable, provided the conditions in paragraphs (j)(2)(i) through 
(j)(2)(iv) of this AD are met.
    (i) Absence of ECAM warning or maintenance message related to 
ELAC, before the data-loadable ELAC unit is removed and software is 
loaded.
    (ii) The data-loadable ELAC unit is removed as specified in 
Airbus SAS AMM Task 27-93-34-000-001-A. This does not apply to the 
onboard loading of ELAC units. The access and closing instructions 
identified in AMM Task 27-93-34-000-001-A are not required by this 
AD. Operators may perform those actions in accordance with 
instructions that are part of an FAA-accepted maintenance or 
inspection program, as applicable.
    (iii) The data-loadable ELAC unit is checked by two different 
means: by the LRU identification and either the label call-up or the 
Alpha Call-up ELA 1 and ELA 2 (if available).
    (iv) After the software is loaded, the data-loadable ELAC unit 
is re-installed as

[[Page 4692]]

specified in Airbus SAS AMM Task 27-93-34-400-001-A. This does not 
apply to the onboard loading of ELAC units. The access and closing 
instructions identified in AMM Task 27-93-34-400-001-A are not 
required by this AD. Operators may perform those actions in 
accordance with instructions that are part of an FAA-accepted 
maintenance or inspection program, as applicable.

(k) Airplanes Not Affected by the Requirements of Paragraph (h) of This 
AD

    (1) An airplane on which any modification (mod) specified in 
paragraphs (k)(1)(i) and (k)(1)(ii) of this AD was embodied in 
production is not affected by the requirements of paragraph (h) of 
this AD, provided it is determined that no affected ELAC unit is 
installed as of the effective date of this AD.
    (i) Airbus SAS mod 161843 (installation of data-loadable ELAC P/
N 3945129100 unit with L99 software P/N 3945129111) or mod 159979 
(installation of non-data-loadable ELAC L99 P/N 3945128217 unit).
    (ii) Airbus SAS mod 160577 (installation of data-loadable ELAC 
P/N 3945129100 unit with L101 software P/N 3945129112) or mod 162042 
(installation of non-data-loadable ELAC L101 P/N 3945128218 unit).
    (2) An airplane that has been modified as specified in the 
service information identified in paragraph (k)(2)(i), (k)(2)(ii), 
or (k)(2)(iii) of this AD is not affected by the requirements of 
paragraph (h) of this AD, provided it is determined that no affected 
ELAC unit is installed as of the effective date of this AD.
    (i) Airbus Service Bulletin A320-27-1267, dated September 27, 
2017 (installation of non-data-loadable ELAC L101 P/N 3945128218 
unit).
    (ii) Airbus Service Bulletin A320-27-1268, dated September 27, 
2017 (installation of data-loadable ELAC P/N 3945129100 unit with 
L101 software P/N 3945129112 for A320 NEO).
    (iii) Airbus Service Bulletin A320-27-1269, dated September 27, 
2017 (installation of data-loadable ELAC P/N 3945129100 unit with 
L101 software P/N 3945129112).

(l) Terminating Action for AD 2016-17-03

    Accomplishing the actions required by paragraph (h) of this AD 
or complying with the provisions specified in paragraph (k) of this 
AD terminates all requirements of AD 2016-17-03.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (n)(2) of this AD. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0007R1, dated January 19, 2018, 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-2018-0556.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-27-1263, dated April 28, 2017.
    (ii) Airbus Service Bulletin A320-27-1264, dated April 28, 2017.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet 
http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Des Moines, Washington, on February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-02558 Filed 2-15-19; 8:45 am]
 BILLING CODE 4910-13-P