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certification requirements of 14 CFR To maintain the same level of safety sources of engine- and APU-generated part 36. envisioned by the existing rule with electrical power inoperative (electrical The FAA issues special conditions, as traditional mechanical flight controls, power sources excluding the battery and defined in 14 CFR 11.19, in accordance the Textron Model 700 airplane design any other standby electrical sources). with § 11.38, and they become part of must not be time-limited in its operation The airplane operation should be the type certification basis under under all reasonably foreseeable considered at the critical phase of flight, § 21.17(a)(2). conditions, including loss of all normal and should include the ability to restart sources of engine or auxiliary power the engines and maintain flight for the Novel or Unusual Design Features unit (APU)-generated electrical power. maximum diversion-time capability The Textron Model 700 airplane will Textron must demonstrate that the being certified. incorporate the following novel or airplane can maintain safe flight and Issued in Des Moines, Washington, on unusual design feature: A fly-by-wire landing (including rollout and brake November 30, 2018. rudder-control system that requires a control through full stop) with the use Paul Siegmund, continuous source of electrical power to of its emergency/alternate electrical- Acting Manager, Transport Standards maintain an operable rudder flight- power systems. These electrical-power Branch, Policy and Innovation Division, control system. The loss of this system systems, or the minimum restorable Aircraft Certification Service. may result in loss of flight control and electrical-power sources, must be able to [FR Doc. 2018–26455 Filed 12–4–18; 8:45 am] power loads that are essential for may be catastrophic to the airplane. BILLING CODE 4910–13–P continued safe flight and landing, Discussion including those required for the The Textron Model 700 airplane has maximum length of approved flight DEPARTMENT OF TRANSPORTATION a fly-by-wire rudder-control system that diversion. requires a continuous source of These special conditions contain the Federal Aviation Administration electrical power to maintain an operable additional safety standards that the flight-control system. Section Administrator considers necessary to 14 CFR Part 39 establish a level of safety equivalent to 25.1351(d), operation without normal [Docket No. FAA–2018–0512; Product electrical power, requires safe operation that established by existing Identifier 2017–NM–170–AD; Amendment in visual flight rule (VFR) conditions for airworthiness standards. 39–19513; AD 2018–25–02] at least 5 minutes after loss of normal Applicability electrical power, excluding the battery. RIN 2120–AA64 This rule is structured around As discussed above, these special conditions are applicable to the Textron Airworthiness Directives; Airbus SAS traditional designs that use mechanical Airplanes control cables and linkages for flight Model 700 airplane. Should Textron control. These manual controls allow apply at a later date for a change to the AGENCY: Federal Aviation the crew to maintain aerodynamic type certificate to include another Administration (FAA), Department of control of the airplane for an indefinite model incorporating the same novel or Transportation (DOT). time after loss of all electrical power. unusual design feature, the special ACTION: Final rule. Under these conditions, a mechanical conditions would apply to that model as flight-control system provides the crew well. SUMMARY: We are adopting a new with the ability to fly the airplane while Conclusion airworthiness directive (AD) for certain attempting to identify the cause of the Airbus SAS Model A318, A319, A320, This action affects only certain novel electrical failure, restart engine(s) if and A321 series airplanes. This AD was or unusual design features on one model necessary, and attempt to re-establish prompted by an evaluation by the of airplane. It is not a rule of general some of the electrical-power-generation design approval holder (DAH) applicability. capability. indicating that the principal structural A critical assumption in § 25.1351(d) List of Subjects in 14 CFR Part 25 elements and certain life-limited parts is that the airplane is in VFR conditions are subject to widespread fatigue Aircraft, Aviation safety, Reporting damage (WFD). This AD requires at the time of an electrical failure. This and recordkeeping requirements. is not a valid assumption in today’s revising the existing maintenance or airline operating environment, where Authority Citation inspection program to incorporate new or more restrictive airworthiness airplanes fly much of the time in The authority citation for these limitations. We are issuing this AD to instrument-meteorological conditions special conditions is as follows: on air-traffic-control-defined flight address the unsafe condition on these Authority: 49 U.S.C. 106(g), 40113, 44701, products. paths. Another assumption in the 44702, 44704. existing rule is that the loss of all DATES: This AD is effective January 10, normal electrical power is the result of The Special Conditions 2019. the loss of all engines. The 5-minute Accordingly, pursuant to the The Director of the Federal Register period in the rule is to allow at least one authority delegated to me by the approved the incorporation by reference engine to be restarted, following an all- Administrator, the following special of certain publications listed in this AD engines power loss, to continue the conditions are issued as part of the type as of January 10, 2019. flight to a safe landing. However, service certification basis for Textron Model ADDRESSES: For service information experience on airplanes with similar 700 airplanes. identified in this final rule, contact electrical-power-system architecture as In lieu of 14 CFR 25.1351(d), the Airbus SAS, Airworthiness Office— the Textron Model 700 airplane has following special condition applies: EIAS, Rond-Point Emile Dewoitine No: shown that at least the temporary loss Textron must show, by test or 2, 31700 Blagnac Cedex, France; of all electrical power for causes other combination of test and analysis that the telephone +33 5 61 93 36 96; fax +33 5 than all-engine failure is not extremely airplane is capable of continued safe 61 93 44 51; email account.airworth- improbable. flight and landing with all normal [email protected]; internet http://

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www.airbus.com. You may view this an unsafe condition for all Airbus SAS Limitation Items (DT–ALI), Revision 07, service information at the FAA, Model A318, A319, A320 and A321 dated June 13, 2018, which is the latest Transport Standards Branch, 2200 series airplanes. The MCAI states: revision of the document. South 216th St., Des Moines, WA. For The airworthiness limitations for the A320 We disagree with the commenter’s information on the availability of this family aeroplanes are currently defined and request. We, along with the EASA, have material at the FAA, call 206–231–3195. published in the Airbus A318/A319/A320/ not determined that Airbus A318/A319/ It is also available on the internet at A321 Airworthiness Limitations Section A320/A321 Airworthiness Limitation http://www.regulations.gov by searching (ALS) document(s). The Damage Tolerant Section Part 2—Damage Tolerant for and locating Docket No. FAA–2018– Airworthiness Limitation Items are published Airworthiness Limitation Items (DT– 0512. in ALS Part 2, approved by EASA. The ALI), Revision 07, dated June 13, 2018, instructions contained in the ALS Part 2 have is required for airplanes that do not Examining the AD Docket been identified as mandatory actions for include Revision 07 as part of the type continued airworthiness. You may examine the AD docket on Failure to comply with these instructions design. In the future, should we the internet at http:// could result in an unsafe condition. determine that Revision 07 is required, www.regulations.gov by searching for Previously, EASA issued AD 2016–0239 we would consider issuing additional and locating Docket No. FAA–2018– [which corresponds to FAA AD 2017–22–03, rulemaking at that time. However, 0512; or in person at Docket Operations Amendment 39–19083 (82 FR 49091, October operators may request approval to between 9 a.m. and 5 p.m., Monday 24, 2017) (‘‘AD 2017–22–03’’)] to require incorporate Revision 07 as an through Friday, except Federal holidays. accomplishment of all maintenance tasks as alternative method of compliance described in ALS Part 2 at Revision 05, and (AMOC) under the provisions of The AD docket contains this final rule, [EASA] AD 2015–0038 (later revised) [which the regulatory evaluation, any corresponds to FAA AD 2016–09–06, paragraph (j) of this AD. We have not comments received, and other Amendment 39–18504 (81 FR 26113, May 2, changed this AD in this regard. information. The address for Docket 2016) (‘‘AD 2016–09–06’’)] to require the Change to Language for Previous Operations (phone: 800–647–5527) is implementation of reduced thresholds and Approved AMOCs U.S. Department of Transportation, intervals for the detailed inspection of the Docket Operations, M–30, West forward engine mount on both right hand We have revised paragraph (j)(1)(ii) of Building Ground Floor, Room W12–140, and left hand sides of aeroplanes equipped this AD to state that AMOCs previously 1200 New Jersey Avenue SE, with CFM56–5A/5B engines, as specified in approved for AD 2015–05–02, the ALS task 712111–01. Washington, DC 20590. Amendment 39–18112 (80 FR 15152, Since those [EASA] ADs were issued, March 23, 2015) (‘‘AD 2015–05–02’’), as FOR FURTHER INFORMATION CONTACT: Airbus published Revision 06 of the ALS Part applicable to ALS Part 2, are approved Sanjay Ralhan, Aerospace Engineer, 2, and variations up to 6.3, including new as AMOCs for the corresponding International Section, Transport and/or more restrictive items, and new A320 provisions of this AD. In paragraphs Standards Branch, FAA, 2200 South family models were certified and added to (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), and 216th St., Des Moines, WA 98198; the Applicability of the ALS. The ALS Part (j)(1)(ii)(D) of the proposed AD, we had telephone and fax 206–231–3223. 2 Revision 06 also includes the reduced threshold and intervals required by EASA identified specific ALS documents. SUPPLEMENTARY INFORMATION: AD 2015–0038R1. However, any previously approved Discussion For the reason described above, this AMOC for AD 2015–05–02, as [EASA] AD retains the requirements of EASA applicable to ALS Part 2, is acceptable We issued a notice of proposed AD 2016–0239 and EASA AD 2015–0038R1, for the corresponding requirements of which are superseded, requires rulemaking (NPRM) to amend 14 CFR this AD. part 39 by adding an AD that would accomplishment of all maintenance tasks as apply to certain Airbus SAS Model described in the ALS Part 2 Revision 06, and Removal of Terminating Action for AD A318, A319, A320 and A321 series ALS Part 2 variations 6.1, 6.2 and 6.3 2016–09–06 (hereafter collectively referred to as ‘‘the airplanes. The NPRM published in the ALS’’ in this [EASA] AD), and maintains We have removed paragraph (i)(1) of Federal Register on June 14, 2018 (83 specific compliance times for ALS task the proposed AD, which specified that FR 27724). The NPRM was prompted by 572021–01–1 (Wide Spread Fatigue Damage accomplishing the action required by an evaluation by the DAH indicating related). paragraph (g) of this AD terminates the that the principal structural elements You may examine the MCAI in the requirements of paragraphs (g) and (j) of and certain life-limited parts are subject AD docket on the internet at http:// AD 2016–09–06. However, we have to WFD. The NPRM proposed to require www.regulations.gov by searching for determined that the actions required by revising the existing maintenance or and locating Docket No. FAA–2018– this AD, do not terminate the inspection program to incorporate new 0512. requirements specified in AD 2016–09– or more restrictive airworthiness 06. The actions specified in paragraph limitations. Comments (g) of AD 2016–09–06 were not We are issuing this AD to address We gave the public the opportunity to incorporated into Airbus A318/A319/ prevent fatigue cracking, accidental participate in developing this final rule. A320/A321 Airworthiness Limitation damage, or corrosion in principal The following presents the comment Section Part 2—Damage Tolerant structural elements, and WFD, which received on the NPRM and the FAA’s Airworthiness Limitation Items (DT– could result in reduced structural response to that comment. ALI), Revision 06, dated April 10, 2017, integrity of the airplane. which is specified in paragraph (g) of Request To Use the Latest Service The European Aviation Safety Agency this AD. We have coordinated this issue Information (EASA), which is the Technical Agent with EASA. for the Member States of the European Lufthansa Technik requested that we Union, has issued EASA Airworthiness use the latest service information in the Conclusion Directive 2017–0231, dated November NPRM. Lufthansa Technik stated that We reviewed the relevant data, 21, 2017 (referred to after this as the Airbus issued A318/A319/A320/A321 considered the comment received, and Mandatory Continuing Airworthiness Airworthiness Limitation Section Part determined that air safety and the Information, or ‘‘the MCAI’’), to correct 2—Damage Tolerant Airworthiness public interest require adopting this

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final rule with the changes described hours per operator, although we Procedures (44 FR 11034, February 26, previously and minor editorial changes. recognize that this number may vary 1979), We have determined that these minor from operator to operator. In the past, (3) Will not affect intrastate aviation changes: we have estimated that this action takes in Alaska, and • Are consistent with the intent that 1 work-hour per airplane. Since (4) Will not have a significant was proposed in the NPRM for operators incorporate maintenance or economic impact, positive or negative, addressing the unsafe condition; and inspection program changes for their on a substantial number of small entities • Do not add any additional burden affected fleet(s), we have determined under the criteria of the Regulatory upon the public than was already that a per-operator estimate is more Flexibility Act. proposed in the NPRM. accurate than a per-airplane estimate. List of Subjects in 14 CFR Part 39 We also determined that these Therefore, we estimate the total cost per changes will not increase the economic operator to be $7,650 (90 work-hours × Air transportation, Aircraft, Aviation burden on any operator or increase the $85 per work-hour). safety, Incorporation by reference, scope of this final rule. Safety. Authority for This Rulemaking Adoption of the Amendment Related Service Information Under 1 Title 49 of the United States Code CFR Part 51 specifies the FAA’s authority to issue Accordingly, under the authority Airbus has issued A318/A319/A320/ rules on aviation safety. Subtitle I, delegated to me by the Administrator, A321 Airworthiness Limitation Section section 106, describes the authority of the FAA amends 14 CFR part 39 as Part 2—Damage Tolerant Airworthiness the FAA Administrator. Subtitle VII: follows: Limitation Items (DT–ALI), Revision 06, Aviation Programs, describes in more dated April 10, 2017. This service detail the scope of the Agency’s PART 39—AIRWORTHINESS information describes damage tolerant authority. DIRECTIVES airworthiness limitations. We are issuing this rulemaking under ■ 1. The authority citation for part 39 Airbus has also issued the following the authority described in Subtitle VII, continues to read as follows: variations to A318/A319/A320/A321 Part A, Subpart III, Section 44701: Airworthiness Limitation Section Part ‘‘General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701. 2—Damage Tolerant Airworthiness section, Congress charges the FAA with § 39.13 [Amended] Limitation Items (DT–ALI), Revision 06, promoting safe flight of civil aircraft in dated April 10, 2017. air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding • A318/A319/A320/A321 for practices, methods, and procedures the following new airworthiness Airworthiness Limitation Section Part the Administrator finds necessary for directive (AD): 2—Damage Tolerant Airworthiness safety in air commerce. This regulation 2018–25–02 Airbus SAS: Amendment 39– Limitation Items (DT–ALI), Variation is within the scope of that authority 19513; Docket No. FAA–2018–0512; 6.1, dated May 18, 2017. The service because it addresses an unsafe condition Product Identifier 2017–NM–170–AD. information describes ALI tasks that is likely to exist or develop on (a) Effective Date applicable to certain Model A320–200 products identified in this rulemaking This AD is effective January 10, 2019. and A321–200 airplane configurations. action. • A318/A319/A320/A321 This AD is issued in accordance with (b) Affected ADs Airworthiness Limitation Section Part authority delegated by the Executive This AD affects AD 2017–22–03, 2—Damage Tolerant Airworthiness Director, Aircraft Certification Service, Amendment 39–19083 (82 FR 49091, October Limitation Items (DT–ALI), Variation as authorized by FAA Order 8000.51C. 24, 2017) (‘‘AD 2017–22–03’’). 6.2, dated May 24, 2017. This service In accordance with that order, issuance (c) Applicability information describes ALI tasks of ADs is normally a function of the applicable to Model A321–271N and This AD applies to all Airbus SAS Compliance and Airworthiness airplanes identified in paragraphs (c)(1), –272N airplanes. Division, but during this transition • (c)(2), (c)(3), and (c)(4) of this AD; certificated A318/A319/A320/A321 period, the Executive Director has in any category; with an original certificate Airworthiness Limitation Section Part delegated the authority to issue ADs of airworthiness or original export certificate 2—Damage Tolerant Airworthiness applicable to transport category of airworthiness issued on or before October Limitation Items (DT–ALI), Variation airplanes and associated appliances to 24, 2017. 6.3, dated October 24, 2017. This service the Director of the System Oversight (1) Model A318–111, –112, –121, and –122 information describes ALI tasks Division. airplanes. associated with door stops for certain (2) Model A319–111, –112, –113, –114, Model A318, A319, A320, and A321 Regulatory Findings –115, –131, –132, and –133 airplanes. This AD will not have federalism (3) Model A320–211, –212, –214, –216, series airplanes. –231, –232, –233, –251N, and –271N This service information is reasonably implications under Executive Order airplanes. available because the interested parties 13132. This AD will not have a (4) Model A321–111, –112, –131, –211, have access to it through their normal substantial direct effect on the States, on –212, –213, –231, –232, –251N, –253N, course of business or by the means the relationship between the national –271N, and –272N airplanes. identified in the ADDRESSES section. government and the States, or on the (d) Subject distribution of power and Costs of Compliance responsibilities among the various Air Transport Association (ATA) of We estimate that this AD affects 1,180 levels of government. America Code 05, Time Limits/Maintenance airplanes of U.S. registry. For the reasons discussed above, I Checks. We estimate the following costs to certify that this AD: (e) Reason comply with this AD: (1) Is not a ‘‘significant regulatory This AD was prompted by an evaluation by We have determined that revising the action’’ under Executive Order 12866, the design approval holder, which indicates existing maintenance or inspection (2) Is not a ‘‘significant rule’’ under that principal structural elements and certain program takes an average of 90 work- the DOT Regulatory Policies and life-limited parts are subject to widespread

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fatigue damage (WFD). We are issuing this as applicable, to incorporate the ALIs (k) Related Information AD to prevent fatigue cracking, accidental specified in Airbus A318/A319/A320/A321 (1) Refer to Mandatory Continuing damage, or corrosion in principal structural Airworthiness Limitation Section Part 2— Airworthiness Information (MCAI) EASA AD elements, and WFD, which could result in Damage Tolerant Airworthiness Limitation 2017–0231, dated November 21, 2017, for reduced structural integrity of the airplane. Items (DT–ALI), Variation 6.2, dated May 24, related information. This MCAI may be 2017. The initial compliance time for (f) Compliance found in the AD docket on the internet at accomplishing the actions is at the applicable http://www.regulations.gov by searching for Comply with this AD within the time identified in the ALIs specified in and locating Docket No. FAA–2018–0512. compliance times specified, unless already Airbus A318/A319/A320/A321 (2) For more information about this AD, done. Airworthiness Limitation Section Part 2— contact Sanjay Ralhan, Aerospace Engineer, (g) New Maintenance or Inspection Program Damage Tolerant Airworthiness Limitation International Section, Transport Standards Revision Items (DT–ALI), Variation 6.2, dated May 24, Branch, FAA, 2200 South 216th St., Des (1) Within 90 days after the effective date 2017; or within 90 days after the effective date of this AD; whichever occurs later, Moines, WA 98198; telephone and fax 206– of this AD, revise the existing maintenance 231–3223. or inspection program, as applicable, to without exceeding the inspection intervals in incorporate the airworthiness limitations the ALIs required by paragraph (i) of AD (l) Material Incorporated by Reference 2017–22–03. (ALIs) specified in Airbus A318/A319/A320/ (1) The Director of the Federal Register A321 Airworthiness Limitation Section Part (h) No Alternative Actions or Intervals approved the incorporation by reference 2—Damage Tolerant Airworthiness (IBR) of the service information listed in this Limitation Items (DT–ALI), Revision 06, After the existing maintenance or paragraph under 5 U.S.C. 552(a) and 1 CFR dated April 10, 2017; and Airbus A318/ inspection program has been revised as part 51. A319/A320/A321 Airworthiness Limitation required by paragraph (g) of this AD, no Section Part 2—Damage Tolerant alternative actions (e.g., inspections) or (2) You must use this service information Airworthiness Limitation Items (DT–ALI), intervals may be used unless the actions or as applicable to do the actions required by Variation 6.3, dated October 24, 2017. Except intervals are approved as an alternative this AD, unless this AD specifies otherwise. for ALIs identified in paragraphs (g)(2) and method of compliance (AMOC) in (i) Airbus A318/A319/A320/A321 (g)(3) of this AD, the initial compliance time accordance with the procedures specified in Airworthiness Limitation Section Part 2— for accomplishing the actions is at the paragraph (j)(1) of this AD. Damage Tolerant Airworthiness Limitation applicable time identified in the ALIs Items (DT–ALI), Revision 06, dated April 10, specified in Airbus A318/A319/A320/A321 (i) Terminating Action for AD 2017–22–03 2017. Airworthiness Limitation Section Part 2— Accomplishing the applicable actions (ii) Airbus A318/A319/A320/A321 Damage Tolerant Airworthiness Limitation required by paragraph (g) of this AD Airworthiness Limitation Section Part 2— Items (DT–ALI), Revision 06, dated April 10, terminates the requirements of paragraphs Damage Tolerant Airworthiness Limitation 2017, and Airbus A318/A319/A320/A321 (g)(2) and (i) of AD 2017–22–03. Items (DT–ALI), Variation 6.1, dated May 18, Airworthiness Limitation Section Part 2— 2017. (j) Other FAA AD Provisions Damage Tolerant Airworthiness Limitation (iii) Airbus A318/A319/A320/A321 Items (DT–ALI), Variation 6.3, dated October The following provisions also apply to this Airworthiness Limitation Section Part 2— 24, 2017; or within 90 days after the effective AD: Damage Tolerant Airworthiness Limitation date of this AD; whichever occurs later, (1) Alternative Methods of Compliance Items (DT–ALI), Variation 6.2, dated May 24, without exceeding the inspection intervals in (AMOCs): The Manager, International 2017. the ALIs required by paragraph (i) of AD Section, Transport Standards Branch, FAA, (iv) Airbus A318/A319/A320/A321 2017–22–03. has the authority to approve AMOCs for this Airworthiness Limitation Section Part 2— (2) For airplanes identified in Airbus AD, if requested using the procedures found Damage Tolerant Airworthiness Limitation A318/A319/A320/A321 Airworthiness in 14 CFR 39.19. In accordance with 14 CFR Items (DT–ALI), Variation 6.3, dated October Limitation Section Part 2—Damage Tolerant 39.19, send your request to your principal 24, 2017. Airworthiness Limitation Items (DT–ALI), inspector or local Flight Standards District Variation 6.1, dated May 18, 2017: (3) For service information identified in Office, as appropriate. If sending information this AD, contact Airbus SAS, Airworthiness Concurrently with the revision required by directly to the International Section, send it paragraph (g)(1) of this AD, revise the Office—EIAS, Rond-Point Emile Dewoitine to the attention of the person identified in No: 2, 31700 Blagnac Cedex, France; existing maintenance or inspection program, paragraph (k)(2) of this AD. Information may as applicable, to incorporate the ALIs telephone +33 5 61 93 36 96; fax +33 5 61 be emailed to: 9-ANM-116-AMOC- specified in Airbus A318/A319/A320/A321 93 44 51; email account.airworth-eas@airbus. [email protected]. Airworthiness Limitation Section Part 2— com; internet http://www.airbus.com. (i) Before using any approved AMOC, Damage Tolerant Airworthiness Limitation (4) You may view this service information Items (DT–ALI), Variation 6.1, dated May 18, notify your appropriate principal inspector, at the FAA, Transport Standards Branch, 2017. The initial compliance time for or lacking a principal inspector, the manager 2200 South 216th St., Des Moines, WA. For accomplishing the actions is at the applicable of the local flight standards district office/ information on the availability of this certificate holding district office. time identified in the ALIs specified in material at the FAA, call 206–231–3195. (ii) AMOCs previously approved for AD Airbus A318/A319/A320/A321 (5) You may view this service information 2015–05–02, Amendment 39–18112 (80 FR Airworthiness Limitation Section Part 2— that is incorporated by reference at the 15152, March 23, 2015), as applicable to Damage Tolerant Airworthiness Limitation National Archives and Records Airworthiness Limitations Section (ALS) Part Items (DT–ALI), Variation 6.1, dated May 18, Administration (NARA). For information on 2, are approved as AMOCs for the 2017; or within 90 days after the effective the availability of this material at NARA, call date of this AD; whichever occurs later, corresponding provisions of this AD. (2) Contacting the Manufacturer: For any 202–741–6030, or go to: http:// without exceeding the inspection intervals in www.archives.gov/federal-register/cfr/ibr- the ALIs required by paragraph (i) of AD requirement in this AD to obtain corrective locations.html. 2017–22–03. actions from a manufacturer, the action must (3) For airplanes identified in Airbus be accomplished using a method approved Issued in Des Moines, Washington, on A318/A319/A320/A321 Airworthiness by the Manager, International Section, November 23, 2018. Limitation Section Part 2—Damage Tolerant Transport Standards Branch, FAA; or the John P. Piccola, Airworthiness Limitation Items (DT–ALI), European Aviation Safety Agency (EASA); or Acting Director, System Oversight Division, Variation 6.2, dated May 24, 2017: Airbus SAS’s EASA Design Organization Aircraft Certification Service. Concurrently with the revision required by Approval (DOA). If approved by the DOA, paragraph (g)(1) of this AD, revise the the approval must include the DOA- [FR Doc. 2018–26362 Filed 12–4–18; 8:45 am] existing maintenance or inspection program, authorized signature. BILLING CODE 4910–13–P

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