24654 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations

Administrator, the following special operated at low speed and high engine FOR FURTHER INFORMATION CONTACT: conditions are issued as part of the type , an engine did not restart Sanjay Ralhan, Aerospace Engineer, certification basis for Bombardier Model following a fuel interruption shorter International Section, Transport BD–700–2A12 and Model BD–700– than five seconds. We are issuing this Standards Branch, FAA, 2200 South 2A13 airplanes. AD to address the unsafe condition on 216th St., Des Moines, WA 98198; these products. telephone and fax 206–231–3323. Autobraking System Structural Loads DATES: This AD becomes effective May SUPPLEMENTARY INFORMATION: A landing pitchover condition must 30, 2018. be addressed that takes into account the The Director of the Federal Register Discussion effect of the system. The approved the incorporation by reference The European Aviation Safety Agency airplane is assumed to be at the design of a certain publication listed in this AD (EASA), which is the Technical Agent maximum landing weight, or at the as of May 30, 2018. for the Member States of the European maximum weight allowed with the We must receive comments on this Union, has issued EASA AD 2018–0110, autobrake system on. The airplane is AD by July 16, 2018. dated May 18, 2018 (referred to after assumed to land in a tail-down attitude ADDRESSES: You may send comments, this as the Mandatory Continuing at the speeds defined by § 25.481. using the procedures found in 14 CFR Airworthiness Information, or ‘‘the Following main gear contact, the 11.43 and 11.45, by any of the following MCAI’’), to correct an unsafe condition airplane is assumed to rotate about the methods: for all Airbus Model A320–271N • main gear wheels at the highest pitch Federal eRulemaking Portal: Go to airplanes, and Model A321–271N, rate generated by the autobrake system. http://www.regulations.gov. Follow the –271NX, –272N, and –272NX airplanes. This is considered a limit load instructions for submitting comments. The MCAI states: condition from which ultimate loads • Fax: 202–493–2251. • Mail: U.S. Department of During certification test flights of an A320– must also be determined. Loads must be 271N aeroplane, it has been identified that, determined for a critical fuel and Transportation, Docket Operations, M– 30, West Building Ground Floor, Room when operated at low speed and high engine payload distribution and centers of thrust, the tested engine did not re-start in gravity. Nose gear loads, as well as W12–140, 1200 New Jersey Avenue SE, case of a fuel interruption shorter than 5 Washington, DC 20590. loads, must be determined. The • seconds. Investigation revealed that this was airplane must support these loads as Hand Delivery: U.S. Department of due to the software logic implemented in the described in § 25.305. Transportation, Docket Operations, M– FADEC EEC of affected A320 family models. 30, West Building Ground Floor, Room This condition, if not corrected, could Issued in Des Moines, Washington, on May W12–140, 1200 New Jersey Avenue SE, prevent restart of a shut down engine while 23, 2018. Washington, DC, between 9 a.m. and 5 operating in high power conditions [after a Victor Wicklund, p.m., Monday through Friday, except single or dual in-flight engine shutdown]. Manager, Transport Standards Branch, Policy Federal holidays. To address this potentially unsafe and Innovation Division, For service information identified in condition, software (SW) standard FCS4.4 for Certification Service. this final rule, contact Airbus, the FADEC EEC has been developed, and [FR Doc. 2018–11506 Filed 5–29–18; 8:45 am] Airbus published the SB [Airbus Service Airworthiness Office—EIAS, 1 Rond Bulletin A320–73–1128, Revision 01, dated BILLING CODE 4910–13–P Point Maurice Bellonte, 31707 Blagnac May 17, 2018] providing modification Cedex, France; telephone +33 5 61 93 36 instructions. 96; fax +33 5 61 93 44 51; email For the reasons described above, this DEPARTMENT OF TRANSPORTATION [email protected]; [EASA] AD requires modification of internet http://www.airbus.com. You aeroplanes by [replacing the affected FADEC Federal Aviation Administration may view this referenced service EECs or by] installation of this FADEC EEC information at the FAA, Transport SW [software] standard [and re-identification 14 CFR Part 39 Standards Branch, 2200 South 216th St., of the affected FADEC EECs]. [Docket No. FAA–2018–0492; Product Des Moines, WA. For information on the You may examine the MCAI on the Identifier 2018–NM–083–AD; Amendment availability of this material at the FAA, internet at http://www.regulations.gov 39–19303; AD 2018–11–15] call 206–231–3195. It is also available by searching for and locating Docket No. on the internet at http:// FAA–2018–0492. RIN 2120–AA64 www.regulations.gov by searching for Related Service Information Under 1 and locating Docket No. FAA–2018– Airworthiness Directives; Airbus CFR Part 51 Airplanes 0492. Airbus has issued Service Bulletin AGENCY: Federal Aviation Examining the AD Docket A320–73–1128, Revision 01, dated May Administration (FAA), DOT. You may examine the AD docket on 17, 2018. This service information ACTION: Final rule; request for the internet at http:// describes procedures for replacing comments. www.regulations.gov by searching for affected FADEC EECs and for installing and locating Docket No. FAA–2018– software standard FCS4.4 and re- SUMMARY: We are adopting a new 0492; or in person at the Docket identifying affected FADEC EECs. This airworthiness directive (AD) for all Operations office between 9 a.m. and 5 service information is reasonably Airbus Model A320–271N airplanes, p.m., Monday through Friday, except available because the interested parties and Model A321–271N, –271NX, –272N Federal holidays. The AD docket have access to it through their normal and –272NX airplanes. This AD requires contains this AD, the regulatory course of business or by the means replacing certain full authority digital evaluation, any comments received, and identified in the ADDRESSES section. engine control (FADEC) electronic other information. The street address for engine controllers (EECs); or installing the Docket Operations office (telephone FAA’s Determination and Requirements software standard FCS4.4 and re- 800–647–5527) is in the ADDRESSES of This AD identifying the FADEC EECs. This AD section. Comments will be available in This product has been approved by was prompted by a report that, when the AD docket shortly after receipt. the aviation authority of another

VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\30MYR1.SGM 30MYR1 sradovich on DSK3GMQ082PROD with RULES Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations 24655

country, and is approved for operation defect might prevent restart of an engine at the beginning of your comments. We in the United States. Pursuant to our after a single or dual in-flight engine specifically invite comments on the bilateral agreement with the State of shutdown under certain conditions. overall regulatory, economic, Design Authority, we have been notified Therefore, we determined that notice environmental, and energy aspects of of the unsafe condition described in the and opportunity for public comment this AD. We will consider all comments MCAI and service information before issuing this AD are impracticable received by the closing date and may referenced above. We are issuing this and that good cause exists for making amend this AD based on those AD because we evaluated all pertinent this amendment effective in fewer than comments. information and determined the unsafe 30 days. We will post all comments we condition exists and is likely to exist or receive, without change, to http:// Comments Invited develop on other products of these same www.regulations.gov, including any type designs. This AD is a final rule that involves personal information you provide. We requirements affecting flight safety, and will also post a report summarizing each FAA’s Determination of the Effective we did not precede it by notice and substantive verbal contact we receive Date opportunity for public comment. We about this AD. An unsafe condition exists that invite you to send any written relevant requires the immediate adoption of this data, views, or arguments about this AD. Costs of Compliance AD. The FAA has found that the risk to Send your comments to an address We estimate that this AD affects 16 the flying public justifies waiving notice listed under the ADDRESSES section. airplanes of U.S. registry. We estimate and comment prior to adoption of this Include ‘‘Docket No. FAA–2018–0492; the following costs to comply with this rule because a FADEC EEC software Product Identifier 2018–NM–083–AD’’ AD:

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per product Cost on U.S. operators

Up to 7 work-hours × $85 per hour = Up to $595 ...... (1) Up to $595 ...... Up to $9,520. 1 We have received no definitive data that would enable us to provide cost estimates for parts needed to comply with the actions specified in this AD.

Authority for This Rulemaking Regulatory Findings PART 39—AIRWORTHINESS DIRECTIVES Title 49 of the United States Code We determined that this AD will not specifies the FAA’s authority to issue have federalism implications under ■ 1. The authority citation for part 39 rules on aviation safety. Subtitle I, Executive Order 13132. This AD will continues to read as follows: section 106, describes the authority of not have a substantial direct effect on Authority: 49 U.S.C. 106(g), 40113, 44701. the FAA Administrator. Subtitle VII: the States, on the relationship between Aviation Programs, describes in more the national government and the States, § 39.13 [Amended] detail the scope of the Agency’s or on the distribution of power and ■ 2. The FAA amends § 39.13 by adding authority. responsibilities among the various the following new airworthiness We are issuing this rulemaking under levels of government. directive (AD): the authority described in Subtitle VII, For the reasons discussed above, I Part A, Subpart III, Section 44701: 2018–11–15 Airbus: Amendment 39–19303; certify that this AD: Docket No. FAA–2018–0492; Product ‘‘General requirements.’’ Under that Identifier 2018–NM–083–AD. section, Congress charges the FAA with 1. Is not a ‘‘significant regulatory promoting safe flight of civil aircraft in action’’ under Executive Order 12866; (a) Effective Date air commerce by prescribing regulations 2. Is not a ‘‘significant rule’’ under the This AD becomes effective May 30, 2018. for practices, methods, and procedures DOT Regulatory Policies and Procedures (b) Affected ADs the Administrator finds necessary for (44 FR 11034, February 26, 1979); None. safety in air commerce. This regulation 3. Will not affect intrastate aviation in is within the scope of that authority Alaska; and (c) Applicability because it addresses an unsafe condition 4. Will not have a significant This AD applies to the Airbus airplanes that is likely to exist or develop on identified in paragraphs (c)(1) and (c)(2) of products identified in this rulemaking economic impact, positive or negative, this AD, certificated in any category, all action. on a substantial number of small entities manufacturer serial numbers (MSN). under the criteria of the Regulatory This AD is issued in accordance with (1) Model A320–271N airplanes. Flexibility Act. (2) Model A321–271N, –271NX, –272N and authority delegated by the Executive –272NX airplanes. Director, Aircraft Certification Service, List of Subjects in 14 CFR Part 39 as authorized by FAA Order 8000.51C. (d) Subject In accordance with that order, issuance Air transportation, Aircraft, Aviation Air Transport Association (ATA) of of ADs is normally a function of the safety, Incorporation by reference, America Code 72, Turbine/ engine. Safety. Compliance and Airworthiness (e) Reason Division, but during this transition Adoption of the Amendment This AD was prompted by a report that, period, the Executive Director has when operated at low speed and high engine delegated the authority to issue ADs Accordingly, under the authority thrust, an engine did not restart following a applicable to transport category delegated to me by the Administrator, fuel interruption shorter than five seconds. airplanes to the Director of the System the FAA amends 14 CFR part 39 as We are issuing this AD to address engines Oversight Division. follows: that might not restart while operating in high

VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\30MYR1.SGM 30MYR1 sradovich on DSK3GMQ082PROD with RULES 24656 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations

power conditions after a single or dual in- (2) The installation of the FADEC EEC or may examine the MCAI on the internet at flight engine shutdown. software standard must be accomplished in http://www.regulations.gov by searching for accordance with a method approved by the and locating Docket No. FAA–2018–0492. (f) Compliance Manager, International Section, Transport (2) For more information about this AD, Comply with this AD within the Standards Branch, FAA; or EASA; or contact Sanjay Ralhan, Aerospace Engineer, compliance times specified, unless already Airbus’s EASA DOA. If approved by the International Section, Transport Standards done. DOA, the approval must include the DOA- Branch, FAA, 2200 South 216th St., Des authorized signature. Moines, WA 98198; telephone and fax 206– (g) Definitions 231–3323. (1) For the purposes of this AD, an affected (k) Clarification of Affected Airplanes (3) Service information identified in this full authority digital engine control (FADEC) An airplane on which Airbus modification AD that is not incorporated by reference is electronic engine controller (EEC) is one with 163473 has been embodied in production is available at the addresses specified in a part number listed in table 1 to paragraph not affected by the requirements of paragraph paragraphs (o)(3) and (o)(4) of this AD. (h) of this AD, provided it can be (g)(1) of this AD. (o) Material Incorporated by Reference conclusively determined that no affected FADEC EEC is installed on that airplane. (1) The Director of the Federal Register TABLE 1 TO PARAGRAPH (g)(1) OF approved the incorporation by reference THIS AD—AFFECTED FADEC EEC (l) Credit for Previous Actions (IBR) of the service information listed in this PART NUMBERS This paragraph provides credit for the paragraph under 5 U.S.C. 552(a) and 1 CFR actions required by paragraph (h) of this AD, part 51. Affected FADEC EEC part No. if those actions were performed before the (2) You must use this service information effective date of this AD using Airbus Service as applicable to do the actions required by 5315126 Bulletin A320–73–1128, dated May 15, 2018. this AD, unless this AD specifies otherwise. 5315126SK02 (i) Airbus Service Bulletin A320–73–1128, (m) Other FAA AD Provisions 5323434 Revision 01, dated May 17, 2018. 5323745 The following provisions also apply to this (ii) Reserved. 5323746 AD: (3) For service information identified in 5324836 (1) Alternative Methods of Compliance this AD, contact Airbus, Airworthiness 5324836–001 (AMOCs): The Manager, International Office—EIAS, 1 Rond Point Maurice 5324836–002 Section, Transport Standards Branch, FAA, Bellonte, 31707 Blagnac Cedex, France; 5324837 has the authority to approve AMOCs for this telephone +33 5 61 93 36 96; fax +33 5 61 5325185 AD, if requested using the procedures found 93 44 51; email account.airworth-eas@ airbus.com; internet http://www.airbus.com. 5325971 in 14 CFR 39.19. In accordance with 14 CFR (4) You may view this service information 5325975 39.19, send your request to your principal inspector or local Flight Standards District at the FAA, Transport Standards Branch, Office, as appropriate. If sending information 2200 South 216th St., Des Moines, WA. For (2) For the purposes of this AD, Group 1 directly to the International Section, send it information on the availability of this airplanes are defined as those that have an to the attention of the person identified in material at the FAA, call 206–231–3195. affected FADEC EEC installed. paragraph (n)(2) of this AD. Information may (5) You may view this service information (3) For the purposes of this AD, Group 2 be emailed to: 9-ANM-116-AMOC- that is incorporated by reference at the airplanes are defined as those that do not [email protected]. Before using any National Archives and Records have an affected FADEC EEC installed. approved AMOC, notify your appropriate Administration (NARA). For information on (h) Modification principal inspector, or lacking a principal the availability of this material at NARA, call inspector, the manager of the local flight 202–741–6030, or go to: http:// For Group 1 airplanes: Within 30 days after standards district office/certificate holding www.archives.gov/federal-register/cfr/ibr- the effective date of this AD, modify the district office. locations.html. airplane by replacing affected FADEC EECs (2) Contacting the Manufacturer: For any installed on both engines with FADEC EEC Issued in Des Moines, Washington, on May requirement in this AD to obtain corrective 23, 2018. part number 5327582 (software standard actions from a manufacturer, the action must FCS4.4), or by installing software standard be accomplished using a method approved James Cashdollar, FCS4.4 and re-identifying the affected by the Manager, International Section, Acting Director, System Oversight Division, FADEC EEC, in accordance with the Transport Standards Branch, FAA; or EASA; Aircraft Certification Service. Accomplishment Instructions of Airbus or Airbus’s EASA DOA. If approved by the [FR Doc. 2018–11659 Filed 5–29–18; 8:45 am] Service Bulletin A320–73–1128, Revision 01, DOA, the approval must include the DOA- BILLING CODE 4910–13–P dated May 17, 2018. authorized signature. (i) Parts Installation Limitation (3) Required for Compliance (RC): If any service information contains procedures or As of 30 days after the effective date of this tests that are identified as RC, those DEPARTMENT OF ENERGY AD, do not install an affected FADEC EEC on procedures and tests must be done to comply any airplane. with this AD; any procedures or tests that are Federal Energy Regulatory Commission (j) Later-Approved Parts not identified as RC are recommended. Those procedures and tests that are not identified Installation on an airplane of a FADEC EEC as RC may be deviated from using accepted 18 CFR Parts 375 and 388 or software standard having a part number methods in accordance with the operator’s approved after the effective date of this AD maintenance or inspection program without [Docket No. RM16–15–001; Order is acceptable for compliance with the obtaining approval of an AMOC, provided No. 833–A] requirements of paragraph (h) of this AD, the procedures and tests identified as RC can provided the conditions in paragraphs (j)(1) be done and the airplane can be put back in FAST Act Section 61003—Critical and (j)(2) of this AD are met. an airworthy condition. Any substitutions or Electric Infrastructure Security and (1) The FADEC EEC or software standard changes to procedures or tests identified as Critical Energy Infrastructure part number must be approved by the RC require approval of an AMOC. Information Manager, International Section, Transport Standards Branch, FAA; or the European (n) Related Information AGENCY: Federal Energy Regulatory Aviation Safety Agency (EASA); or Airbus’s (1) Refer to Mandatory Continuing Commission. EASA Design Organization Approval (DOA). Airworthiness Information (MCAI) EASA ACTION: Order on clarification and If approved by the DOA, the approval must Airworthiness Directive 2018–0110, dated rehearing. include the DOA-authorized signature. May 18, 2018, for related information. You

VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\30MYR1.SGM 30MYR1 sradovich on DSK3GMQ082PROD with RULES