Airworthiness Directives; Airbus SAS Airplanes, 62690-62693 [2018-26362]

Download as PDF 62690 Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations certification requirements of 14 CFR part 36. The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.17(a)(2). Novel or Unusual Design Features The Textron Model 700 airplane will incorporate the following novel or unusual design feature: A fly-by-wire rudder-control system that requires a continuous source of electrical power to maintain an operable rudder flightcontrol system. The loss of this system may result in loss of flight control and may be catastrophic to the airplane. khammond on DSK30JT082PROD with RULES Discussion The Textron Model 700 airplane has a fly-by-wire rudder-control system that requires a continuous source of electrical power to maintain an operable flight-control system. Section 25.1351(d), operation without normal electrical power, requires safe operation in visual flight rule (VFR) conditions for at least 5 minutes after loss of normal electrical power, excluding the battery. This rule is structured around traditional designs that use mechanical control cables and linkages for flight control. These manual controls allow the crew to maintain aerodynamic control of the airplane for an indefinite time after loss of all electrical power. Under these conditions, a mechanical flight-control system provides the crew with the ability to fly the airplane while attempting to identify the cause of the electrical failure, restart engine(s) if necessary, and attempt to re-establish some of the electrical-power-generation capability. A critical assumption in § 25.1351(d) is that the airplane is in VFR conditions at the time of an electrical failure. This is not a valid assumption in today’s airline operating environment, where airplanes fly much of the time in instrument-meteorological conditions on air-traffic-control-defined flight paths. Another assumption in the existing rule is that the loss of all normal electrical power is the result of the loss of all engines. The 5-minute period in the rule is to allow at least one engine to be restarted, following an allengines power loss, to continue the flight to a safe landing. However, service experience on airplanes with similar electrical-power-system architecture as the Textron Model 700 airplane has shown that at least the temporary loss of all electrical power for causes other than all-engine failure is not extremely improbable. VerDate Sep<11>2014 16:05 Dec 04, 2018 Jkt 247001 To maintain the same level of safety envisioned by the existing rule with traditional mechanical flight controls, the Textron Model 700 airplane design must not be time-limited in its operation under all reasonably foreseeable conditions, including loss of all normal sources of engine or auxiliary power unit (APU)-generated electrical power. Textron must demonstrate that the airplane can maintain safe flight and landing (including rollout and brake control through full stop) with the use of its emergency/alternate electricalpower systems. These electrical-power systems, or the minimum restorable electrical-power sources, must be able to power loads that are essential for continued safe flight and landing, including those required for the maximum length of approved flight diversion. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by existing airworthiness standards. Applicability As discussed above, these special conditions are applicable to the Textron Model 700 airplane. Should Textron apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model of airplane. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Textron Model 700 airplanes. In lieu of 14 CFR 25.1351(d), the following special condition applies: Textron must show, by test or combination of test and analysis that the airplane is capable of continued safe flight and landing with all normal PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 sources of engine- and APU-generated electrical power inoperative (electrical power sources excluding the battery and any other standby electrical sources). The airplane operation should be considered at the critical phase of flight, and should include the ability to restart the engines and maintain flight for the maximum diversion-time capability being certified. Issued in Des Moines, Washington, on November 30, 2018. Paul Siegmund, Acting Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2018–26455 Filed 12–4–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0512; Product Identifier 2017–NM–170–AD; Amendment 39–19513; AD 2018–25–02] 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 certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the principal structural elements and certain life-limited parts are subject to widespread fatigue damage (WFD). This AD requires revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 10, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 10, 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:// SUMMARY: E:\FR\FM\06DER1.SGM 06DER1 Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations 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– 0512. 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– 0512; 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: khammond on DSK30JT082PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A318, A319, A320 and A321 series airplanes. The NPRM published in the Federal Register on June 14, 2018 (83 FR 27724). The NPRM was prompted by an evaluation by the DAH indicating that the principal structural elements and certain life-limited parts are subject to WFD. The NPRM proposed to require revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. We are issuing this AD to address prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity 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 Airworthiness Directive 2017–0231, dated November 21, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct VerDate Sep<11>2014 16:05 Dec 04, 2018 Jkt 247001 an unsafe condition for all Airbus SAS Model A318, A319, A320 and A321 series airplanes. The MCAI states: The airworthiness limitations for the A320 family aeroplanes are currently defined and published in the Airbus A318/A319/A320/ A321 Airworthiness Limitations Section (ALS) document(s). The Damage Tolerant Airworthiness Limitation Items are published in ALS Part 2, approved by EASA. The instructions contained in the ALS Part 2 have been identified as mandatory actions for continued airworthiness. Failure to comply with these instructions could result in an unsafe condition. Previously, EASA issued AD 2016–0239 [which corresponds to FAA AD 2017–22–03, Amendment 39–19083 (82 FR 49091, October 24, 2017) (‘‘AD 2017–22–03’’)] to require accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 05, and [EASA] AD 2015–0038 (later revised) [which corresponds to FAA AD 2016–09–06, Amendment 39–18504 (81 FR 26113, May 2, 2016) (‘‘AD 2016–09–06’’)] to require the implementation of reduced thresholds and intervals for the detailed inspection of the forward engine mount on both right hand and left hand sides of aeroplanes equipped with CFM56–5A/5B engines, as specified in the ALS task 712111–01. Since those [EASA] ADs were issued, Airbus published Revision 06 of the ALS Part 2, and variations up to 6.3, including new and/or more restrictive items, and new A320 family models were certified and added to the Applicability of the ALS. The ALS Part 2 Revision 06 also includes the reduced threshold and intervals required by EASA AD 2015–0038R1. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016–0239 and EASA AD 2015–0038R1, which are superseded, requires accomplishment of all maintenance tasks as described in the ALS Part 2 Revision 06, and ALS Part 2 variations 6.1, 6.2 and 6.3 (hereafter collectively referred to as ‘‘the ALS’’ in this [EASA] AD), and maintains specific compliance times for ALS task 572021–01–1 (Wide Spread Fatigue Damage related). 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– 0512. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA’s response to that comment. Request To Use the Latest Service Information Lufthansa Technik requested that we use the latest service information in the NPRM. Lufthansa Technik stated that Airbus issued A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 62691 Limitation Items (DT–ALI), Revision 07, dated June 13, 2018, which is the latest revision of the document. We disagree with the commenter’s request. We, along with the EASA, have not determined that Airbus A318/A319/ A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT– ALI), Revision 07, dated June 13, 2018, is required for airplanes that do not include Revision 07 as part of the type design. In the future, should we determine that Revision 07 is required, we would consider issuing additional rulemaking at that time. However, operators may request approval to incorporate Revision 07 as an alternative method of compliance (AMOC) under the provisions of paragraph (j) of this AD. We have not changed this AD in this regard. Change to Language for Previous Approved AMOCs We have revised paragraph (j)(1)(ii) of this AD to state that AMOCs previously approved for AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015) (‘‘AD 2015–05–02’’), as applicable to ALS Part 2, are approved as AMOCs for the corresponding provisions of this AD. In paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), and (j)(1)(ii)(D) of the proposed AD, we had identified specific ALS documents. However, any previously approved AMOC for AD 2015–05–02, as applicable to ALS Part 2, is acceptable for the corresponding requirements of this AD. Removal of Terminating Action for AD 2016–09–06 We have removed paragraph (i)(1) of the proposed AD, which specified that accomplishing the action required by paragraph (g) of this AD terminates the requirements of paragraphs (g) and (j) of AD 2016–09–06. However, we have determined that the actions required by this AD, do not terminate the requirements specified in AD 2016–09– 06. The actions specified in paragraph (g) of AD 2016–09–06 were not incorporated into Airbus A318/A319/ A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT– ALI), Revision 06, dated April 10, 2017, which is specified in paragraph (g) of this AD. We have coordinated this issue with EASA. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this E:\FR\FM\06DER1.SGM 06DER1 62692 Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations 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. khammond on DSK30JT082PROD with RULES Related Service Information Under 1 CFR Part 51 Airbus has issued A318/A319/A320/ A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 06, dated April 10, 2017. This service information describes damage tolerant airworthiness limitations. Airbus has also issued the following variations to A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 06, dated April 10, 2017. • A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.1, dated May 18, 2017. The service information describes ALI tasks applicable to certain Model A320–200 and A321–200 airplane configurations. • A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.2, dated May 24, 2017. This service information describes ALI tasks applicable to Model A321–271N and –272N airplanes. • A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.3, dated October 24, 2017. This service information describes ALI tasks associated with door stops for certain Model A318, A319, A320, and A321 series airplanes. 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 1,180 airplanes of U.S. registry. We estimate the following costs to comply with this AD: We have determined that revising the existing maintenance or inspection program takes an average of 90 work- VerDate Sep<11>2014 16:05 Dec 04, 2018 Jkt 247001 hours per operator, although we recognize that this number may vary from operator to operator. In the past, we have estimated that this action takes 1 work-hour per airplane. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), we have determined that a per-operator estimate is more accurate than a per-airplane estimate. Therefore, we estimate the total cost per operator to be $7,650 (90 work-hours × $85 per work-hour). 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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): ■ 2018–25–02 Airbus SAS: Amendment 39– 19513; Docket No. FAA–2018–0512; Product Identifier 2017–NM–170–AD. (a) Effective Date This AD is effective January 10, 2019. (b) Affected ADs This AD affects AD 2017–22–03, Amendment 39–19083 (82 FR 49091, October 24, 2017) (‘‘AD 2017–22–03’’). (c) Applicability This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any category; with an original certificate of airworthiness or original export certificate of airworthiness issued on or before October 24, 2017. (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, –232, –251N, –253N, –271N, and –272N airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Time Limits/Maintenance Checks. (e) Reason This AD was prompted by an evaluation by the design approval holder, which indicates that principal structural elements and certain life-limited parts are subject to widespread E:\FR\FM\06DER1.SGM 06DER1 Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. khammond on DSK30JT082PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) New Maintenance or Inspection Program Revision (1) Within 90 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the airworthiness limitations (ALIs) specified in Airbus A318/A319/A320/ A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 06, dated April 10, 2017; and Airbus A318/ A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.3, dated October 24, 2017. Except for ALIs identified in paragraphs (g)(2) and (g)(3) of this AD, the initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 06, dated April 10, 2017, and Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.3, dated October 24, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017–22–03. (2) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.1, dated May 18, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.1, dated May 18, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.1, dated May 18, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017–22–03. (3) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.2, dated May 24, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the existing maintenance or inspection program, VerDate Sep<11>2014 16:05 Dec 04, 2018 Jkt 247001 as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.2, dated May 24, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.2, dated May 24, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017–22–03. (h) No Alternative Actions or Intervals After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. (i) Terminating Action for AD 2017–22–03 Accomplishing the applicable actions required by paragraph (g) of this AD terminates the requirements of paragraphs (g)(2) and (i) of AD 2017–22–03. (j) 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 (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (ii) AMOCs previously approved for AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015), as applicable to Airworthiness Limitations Section (ALS) Part 2, are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 62693 (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0231, dated November 21, 2017, 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–2018–0512. (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. (l) 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 A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 06, dated April 10, 2017. (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.1, dated May 18, 2017. (iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.2, dated May 24, 2017. (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2— Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 6.3, dated October 24, 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/ibrlocations.html. Issued in Des Moines, Washington, on November 23, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–26362 Filed 12–4–18; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\06DER1.SGM 06DER1

Agencies

[Federal Register Volume 83, Number 234 (Thursday, December 6, 2018)]
[Rules and Regulations]
[Pages 62690-62693]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26362]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD; Amendment 
39-19513; AD 2018-25-02]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD 
was prompted by an evaluation by the design approval holder (DAH) 
indicating that the principal structural elements and certain life-
limited parts are subject to widespread fatigue damage (WFD). This AD 
requires revising the existing maintenance or inspection program to 
incorporate new or more restrictive airworthiness limitations. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 10, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 10, 
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 [email protected]; 
internet http://

[[Page 62691]]

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-
0512.

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-
0512; 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 certain Airbus SAS Model 
A318, A319, A320 and A321 series airplanes. The NPRM published in the 
Federal Register on June 14, 2018 (83 FR 27724). The NPRM was prompted 
by an evaluation by the DAH indicating that the principal structural 
elements and certain life-limited parts are subject to WFD. The NPRM 
proposed to require revising the existing maintenance or inspection 
program to incorporate new or more restrictive airworthiness 
limitations.
    We are issuing this AD to address prevent fatigue cracking, 
accidental damage, or corrosion in principal structural elements, and 
WFD, which could result in reduced structural integrity 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 
Airworthiness Directive 2017-0231, dated November 21, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus SAS Model 
A318, A319, A320 and A321 series airplanes. The MCAI states:

    The airworthiness limitations for the A320 family aeroplanes are 
currently defined and published in the Airbus A318/A319/A320/A321 
Airworthiness Limitations Section (ALS) document(s). The Damage 
Tolerant Airworthiness Limitation Items are published in ALS Part 2, 
approved by EASA. The instructions contained in the ALS Part 2 have 
been identified as mandatory actions for continued airworthiness.
    Failure to comply with these instructions could result in an 
unsafe condition.
    Previously, EASA issued AD 2016-0239 [which corresponds to FAA 
AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) 
(``AD 2017-22-03'')] to require accomplishment of all maintenance 
tasks as described in ALS Part 2 at Revision 05, and [EASA] AD 2015-
0038 (later revised) [which corresponds to FAA AD 2016-09-06, 
Amendment 39-18504 (81 FR 26113, May 2, 2016) (``AD 2016-09-06'')] 
to require the implementation of reduced thresholds and intervals 
for the detailed inspection of the forward engine mount on both 
right hand and left hand sides of aeroplanes equipped with CFM56-5A/
5B engines, as specified in the ALS task 712111-01.
    Since those [EASA] ADs were issued, Airbus published Revision 06 
of the ALS Part 2, and variations up to 6.3, including new and/or 
more restrictive items, and new A320 family models were certified 
and added to the Applicability of the ALS. The ALS Part 2 Revision 
06 also includes the reduced threshold and intervals required by 
EASA AD 2015-0038R1.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0239 and EASA AD 2015-0038R1, which are 
superseded, requires accomplishment of all maintenance tasks as 
described in the ALS Part 2 Revision 06, and ALS Part 2 variations 
6.1, 6.2 and 6.3 (hereafter collectively referred to as ``the ALS'' 
in this [EASA] AD), and maintains specific compliance times for ALS 
task 572021-01-1 (Wide Spread Fatigue Damage related).

    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-
0512.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comment received on the 
NPRM and the FAA's response to that comment.

Request To Use the Latest Service Information

    Lufthansa Technik requested that we use the latest service 
information in the NPRM. Lufthansa Technik stated that Airbus issued 
A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Revision 07, dated 
June 13, 2018, which is the latest revision of the document.
    We disagree with the commenter's request. We, along with the EASA, 
have not determined that Airbus A318/A319/A320/A321 Airworthiness 
Limitation Section Part 2--Damage Tolerant Airworthiness Limitation 
Items (DT-ALI), Revision 07, dated June 13, 2018, is required for 
airplanes that do not include Revision 07 as part of the type design. 
In the future, should we determine that Revision 07 is required, we 
would consider issuing additional rulemaking at that time. However, 
operators may request approval to incorporate Revision 07 as an 
alternative method of compliance (AMOC) under the provisions of 
paragraph (j) of this AD. We have not changed this AD in this regard.

Change to Language for Previous Approved AMOCs

    We have revised paragraph (j)(1)(ii) of this AD to state that AMOCs 
previously approved for AD 2015-05-02, Amendment 39-18112 (80 FR 15152, 
March 23, 2015) (``AD 2015-05-02''), as applicable to ALS Part 2, are 
approved as AMOCs for the corresponding provisions of this AD. In 
paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), and 
(j)(1)(ii)(D) of the proposed AD, we had identified specific ALS 
documents. However, any previously approved AMOC for AD 2015-05-02, as 
applicable to ALS Part 2, is acceptable for the corresponding 
requirements of this AD.

Removal of Terminating Action for AD 2016-09-06

    We have removed paragraph (i)(1) of the proposed AD, which 
specified that accomplishing the action required by paragraph (g) of 
this AD terminates the requirements of paragraphs (g) and (j) of AD 
2016-09-06. However, we have determined that the actions required by 
this AD, do not terminate the requirements specified in AD 2016-09-06. 
The actions specified in paragraph (g) of AD 2016-09-06 were not 
incorporated into Airbus A318/A319/A320/A321 Airworthiness Limitation 
Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-
ALI), Revision 06, dated April 10, 2017, which is specified in 
paragraph (g) of this AD. We have coordinated this issue with EASA.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this

[[Page 62692]]

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 A318/A319/A320/A321 Airworthiness Limitation 
Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-
ALI), Revision 06, dated April 10, 2017. This service information 
describes damage tolerant airworthiness limitations.
    Airbus has also issued the following variations to A318/A319/A320/
A321 Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 
2017.
     A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 
6.1, dated May 18, 2017. The service information describes ALI tasks 
applicable to certain Model A320-200 and A321-200 airplane 
configurations.
     A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 
6.2, dated May 24, 2017. This service information describes ALI tasks 
applicable to Model A321-271N and -272N airplanes.
     A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 
6.3, dated October 24, 2017. This service information describes ALI 
tasks associated with door stops for certain Model A318, A319, A320, 
and A321 series airplanes.
    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 1,180 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:
    We have determined that revising the existing maintenance or 
inspection program takes an average of 90 work-hours per operator, 
although we recognize that this number may vary from operator to 
operator. In the past, we have estimated that this action takes 1 work-
hour per airplane. Since operators incorporate maintenance or 
inspection program changes for their affected fleet(s), we have 
determined that a per-operator estimate is more accurate than a per-
airplane estimate. Therefore, we estimate the total cost per operator 
to be $7,650 (90 work-hours x $85 per work-hour).

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):

2018-25-02 Airbus SAS: Amendment 39-19513; Docket No. FAA-2018-0512; 
Product Identifier 2017-NM-170-AD.

(a) Effective Date

    This AD is effective January 10, 2019.

(b) Affected ADs

    This AD affects AD 2017-22-03, Amendment 39-19083 (82 FR 49091, 
October 24, 2017) (``AD 2017-22-03'').

(c) Applicability

    This AD applies to all Airbus SAS airplanes identified in 
paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; 
certificated in any category; with an original certificate of 
airworthiness or original export certificate of airworthiness issued 
on or before October 24, 2017.
    (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, -232, -
251N, -253N, -271N, and -272N airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Time Limits/
Maintenance Checks.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder, which indicates that principal structural elements and 
certain life-limited parts are subject to widespread

[[Page 62693]]

fatigue damage (WFD). We are issuing this AD to prevent fatigue 
cracking, accidental damage, or corrosion in principal structural 
elements, and WFD, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) New Maintenance or Inspection Program Revision

    (1) Within 90 days after the effective date of this AD, revise 
the existing maintenance or inspection program, as applicable, to 
incorporate the airworthiness limitations (ALIs) specified in Airbus 
A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated 
April 10, 2017; and Airbus A318/A319/A320/A321 Airworthiness 
Limitation Section Part 2--Damage Tolerant Airworthiness Limitation 
Items (DT-ALI), Variation 6.3, dated October 24, 2017. Except for 
ALIs identified in paragraphs (g)(2) and (g)(3) of this AD, the 
initial compliance time for accomplishing the actions is at the 
applicable time identified in the ALIs specified in Airbus A318/
A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated 
April 10, 2017, and Airbus A318/A319/A320/A321 Airworthiness 
Limitation Section Part 2--Damage Tolerant Airworthiness Limitation 
Items (DT-ALI), Variation 6.3, dated October 24, 2017; or within 90 
days after the effective date of this AD; whichever occurs later, 
without exceeding the inspection intervals in the ALIs required by 
paragraph (i) of AD 2017-22-03.
    (2) For airplanes identified in Airbus A318/A319/A320/A321 
Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 
18, 2017: Concurrently with the revision required by paragraph 
(g)(1) of this AD, revise the existing maintenance or inspection 
program, as applicable, to incorporate the ALIs specified in Airbus 
A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, 
dated May 18, 2017. The initial compliance time for accomplishing 
the actions is at the applicable time identified in the ALIs 
specified in Airbus A318/A319/A320/A321 Airworthiness Limitation 
Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-
ALI), Variation 6.1, dated May 18, 2017; or within 90 days after the 
effective date of this AD; whichever occurs later, without exceeding 
the inspection intervals in the ALIs required by paragraph (i) of AD 
2017-22-03.
    (3) For airplanes identified in Airbus A318/A319/A320/A321 
Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 
24, 2017: Concurrently with the revision required by paragraph 
(g)(1) of this AD, revise the existing maintenance or inspection 
program, as applicable, to incorporate the ALIs specified in Airbus 
A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, 
dated May 24, 2017. The initial compliance time for accomplishing 
the actions is at the applicable time identified in the ALIs 
specified in Airbus A318/A319/A320/A321 Airworthiness Limitation 
Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-
ALI), Variation 6.2, dated May 24, 2017; or within 90 days after the 
effective date of this AD; whichever occurs later, without exceeding 
the inspection intervals in the ALIs required by paragraph (i) of AD 
2017-22-03.

(h) No Alternative Actions or Intervals

    After the existing maintenance or inspection program has been 
revised as required by paragraph (g) of this AD, no alternative 
actions (e.g., inspections) or intervals may be used unless the 
actions or intervals are approved as an alternative method of 
compliance (AMOC) in accordance with the procedures specified in 
paragraph (j)(1) of this AD.

(i) Terminating Action for AD 2017-22-03

    Accomplishing the applicable actions required by paragraph (g) 
of this AD terminates the requirements of paragraphs (g)(2) and (i) 
of AD 2017-22-03.

(j) 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 (k)(2) of this AD. Information 
may be emailed to: [email protected].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs previously approved for AD 2015-05-02, Amendment 39-
18112 (80 FR 15152, March 23, 2015), as applicable to Airworthiness 
Limitations Section (ALS) Part 2, are approved as AMOCs for the 
corresponding provisions of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus SAS's EASA Design Organization 
Approval (DOA). If approved by the DOA, the approval must include 
the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0231, dated November 21, 2017, 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-2018-0512.
    (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.

(l) 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 A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Revision 06, dated April 10, 2017.
    (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Variation 6.1, dated May 18, 2017.
    (iii) Airbus A318/A319/A320/A321 Airworthiness Limitation 
Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-
ALI), Variation 6.2, dated May 24, 2017.
    (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Variation 6.3, dated October 24, 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 [email protected]; 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 November 23, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26362 Filed 12-4-18; 8:45 am]
 BILLING CODE 4910-13-P